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WO2019018832A2 - Production de poussée de profil aérodynamique de trajet d'extrémité dans un aéronef à voilure tournante - Google Patents

Production de poussée de profil aérodynamique de trajet d'extrémité dans un aéronef à voilure tournante Download PDF

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Publication number
WO2019018832A2
WO2019018832A2 PCT/US2018/043196 US2018043196W WO2019018832A2 WO 2019018832 A2 WO2019018832 A2 WO 2019018832A2 US 2018043196 W US2018043196 W US 2018043196W WO 2019018832 A2 WO2019018832 A2 WO 2019018832A2
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WO
WIPO (PCT)
Prior art keywords
chain
tip
sprocket
stator
aircraft
Prior art date
Application number
PCT/US2018/043196
Other languages
English (en)
Other versions
WO2019018832A3 (fr
Inventor
David Allen ZORNES
Original Assignee
Zornes David Allen
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from PCT/US2018/036982 external-priority patent/WO2019005467A2/fr
Application filed by Zornes David Allen filed Critical Zornes David Allen
Publication of WO2019018832A2 publication Critical patent/WO2019018832A2/fr
Publication of WO2019018832A3 publication Critical patent/WO2019018832A3/fr
Priority to PCT/US2019/033009 priority Critical patent/WO2019222718A2/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16G—BELTS, CABLES, OR ROPES, PREDOMINANTLY USED FOR DRIVING PURPOSES; CHAINS; FITTINGS PREDOMINANTLY USED THEREFOR
    • F16G13/00—Chains
    • F16G13/02—Driving-chains
    • F16G13/06—Driving-chains with links connected by parallel driving-pins with or without rollers so called open links
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U40/00—On-board mechanical arrangements for adjusting control surfaces or rotors; On-board mechanical arrangements for in-flight adjustment of the base configuration
    • B64U40/10—On-board mechanical arrangements for adjusting control surfaces or rotors; On-board mechanical arrangements for in-flight adjustment of the base configuration for adjusting control surfaces or rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16G—BELTS, CABLES, OR ROPES, PREDOMINANTLY USED FOR DRIVING PURPOSES; CHAINS; FITTINGS PREDOMINANTLY USED THEREFOR
    • F16G13/00—Chains
    • F16G13/18—Chains having special overall characteristics
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/13—Propulsion using external fans or propellers

Definitions

  • the present invention is generally directed to moving thrust to the tip-path of a rotary-wing bladed system of a helicopter (or any propeller) assembly where energy required to rotate the blade is reduced by the force multiplied by the rotor blade moment arm (length of blade span). Morphing airfoil surfaces electrically with piezoelectric wafers improves the production of rotational relative wind.
  • This invention teaches that the magnitude of torque depends on three quantities: the force applied, the length of the lever arm connecting the axis to the point of force application, and the angle between the force vector and the lever arm.
  • torque is multiplied, because it equals the distance to the center of rotation from the wing tip multiplied by the force applied to the wing tip-path. Torque transfer through a central axis hub is eliminated.
  • a rotary airfoil blade of a propeller typically is mounted to a plane where air is crossing the bottom and top of a shaped airfoil wing to decrease the air density on top and increase the air density below the wing.
  • This invention teaches that in milliseconds, piezoelectric wafers mounted onto propeller airfoil blades morph from a symmetrical airfoil into a nonsymmetrical airfoil (chambered), to increase air density for more lift below the airfoil during high speed propeller rotation.
  • an aircraft must apply available sources of energy in the most efficient way.
  • aircraft do not have common flexible of morphing designs that provide the ability to fly aircraft together into one single aircraft that combines the resources of all or some of the individual aircrafts functions into one single aircraft.
  • An example is FIG 22 where a rotating tube ring aircraft is provided with helix air controls that enable it to fly up to the ends of another similar aircraft's frontend to backend making a longer more efficient tube to fly together.
  • several smaller diameter aircraft are provided with smaller of larger diameters, so individual aircraft unit assembles concentrically, fitting within each other, some are larger in diameter, and others are smaller in diameter to fit together concentrically at approximately the same length, which can vary in length depending on configurations.
  • Piezoelectric wafer morphing airfoil surfaces, FIG 19 helices air lift optimization to control a rotating tube flying, and increased efficiency from tip-path increased torque technologies is taught to physically connect many aircraft together into one aircraft to travel more efficiently as one aircraft using all the capabilities of each individual aircraft, integrating electric power, fuel sources, morphing aerodynamically on surfaces, and spinning rotating blades together or individually.
  • Laser light and other sensors can be combined to fly aircraft into each other.
  • Helix airduct control is one of the key features of tip-path propulsion, reaching the greatest distance from the center axis for aircraft control.
  • Pentazolate rings are applied as fuel in this inventions airborne aircraft:
  • a carbon-free inorganic-metal complex [ ⁇ ( ⁇ 2 ⁇ )4( ⁇ 5 )2] 4H2O can be synthesized by the ion metathesis of [Na(H20)(N5)] 2H2O solution with Zn(N0 3 )2 6H2O from any energy source on earth or airborne solar energy, because it is primarily produced from air and water requiring just electric input (wind power, solar, hydroelectric, or any other power source).
  • Nitrogen fuel sources are taught in this invention that do not emit any pollution but increase lift and propulsion most effectively along the helices air pathways. Just enough water can be added to an aircraft helix in FIG 19 to increase lift during takeoff minimizing the use of conventional fuels for propulsion.
  • the thrust is placed on the tips of rotors to optimize force by multiplying force by the moment arm. Torque transfer through a central hub axis will not occur, and any power sources for thrust will be easier to manage, since the thrust physically moves from the body of an aircraft location out to the most optimized location onto the tip-path.
  • piezoelectric wafers mounted onto propeller airfoil blades morph the airfoils to optimize force and minimize drag by ultrasonically vibrating leading edges of the morphing airfoil shape, so wind never contacts some surfaces, wind just contacts ultrasonically compressed smooth air, keeping surfaces clean, reducing drag.
  • a roller chain in prior art is a way of transmitting mechanical power from one place to another through linear links arranged in or extending along a straight or nearly straight line "linear movement" that are assembled around on sprockets providing a chain drive.
  • This invention teaches that a "triangular-chain link” replaces the past linear links assembled around on sprockets by providing a chain drive that extends a mechanical structure, an additional moment arm, at a greater radial distance from the center of sprocket's conventional linear chain drive links outer surface.
  • rotational refers to the method of producing relative wind.
  • Rotational relative wind flows opposite the physical flightpath of the airfoil, striking the blade at
  • Rotational relative wind velocity is highest at blade tips, decreasing uniformly to zero at the axis of rotation (center of the mast). This invention teaches how to improve rotational relative wind in the tip-path plane.
  • one of the objects of the present invention is to provide an improved structure and system to optimize airborne aircraft acted upon by four aerodynamic forces; thrust, drag, lift, and weight. Understanding how these forces work and knowing how to control them with the movement of thrust to the tip-path plane and adding to flight controls by adding piezoelectric wafers mounted onto airfoils to morph shapes are essential to future flight.
  • This invention teaches that thrust of the aircraft can be moved to the tips of rotary- wings and in milliseconds, piezoelectric wafers mounted onto propeller and wing airfoil blades morph from a symmetrical airfoil into a nonsymmetrical airfoil (chambered), to increase air density for more lift below the airfoil during high speed propeller rotation, improving efficiency and lowering the cost of fuel.
  • Hollow rotary wings can fill with air and then release air where optimization of flight is desired.
  • Balls shaped into airfoils can be propelled around a channel to move air to the desired location.
  • the aircraft when thrust is stopped, the aircraft turns into a glider to safely land without power.
  • a quiet decent to a terrestrial location provides less interference of human living environments: noise, hovering aircraft, lights in night sky from aircraft, and dust from propulsion of aircraft.
  • aircraft fuselages tubes within tubes concentrically provide a high-speed aircraft that is a natural glider.
  • tubes unroll into a flat stack of material for shipping relative to transporting aircraft after use.
  • wings unfold, wings slide apart, wings swing around an axis, and fuselage surface separates to become gliding structures to land without or less power in vertical takeoff and landing aircraft.
  • many aircraft are conFIGd to connect to each other in flight to become one more efficient combined aircraft, sharing power, recharging, refueling, and diagnosing each other for central shipping, or other combined functions.
  • Safety is increased, because airborne refueling, recharging, recalibrating, can minimize the requirement for terrestrial landing.
  • An electric motor is an electrical machine that converts electrical energy into mechanical energy. The reverse of this is the conversion of mechanical energy into electrical energy and is done by an electric generator, which has much in common with a motor.
  • Electric motors operate through the interaction between an electric motor's magnetic field and winding currents to generate force.
  • electric motors can also be used in reverse as generators to convert mechanical energy into electric power.
  • Electric motors can be powered by direct current (DC) sources, such as from batteries, motor vehicles or rectifiers, or by alternating current (AC) sources, such as from the power grid, inverters or generators.
  • DC direct current
  • AC alternating current
  • Small motors may be found in electric watches.
  • General -purpose motors with highly standardized dimensions and characteristics provide convenient mechanical power for industrial use. The largest of electric motors are used for ship propulsion, pipeline compression and pumped-storage applications with ratings reaching 100 megawatts. Electric motors may be classified by electric power source type, internal construction, application, type of motion output, and so on.
  • Electric motors are used to produce linear or rotary force (torque) and should be distinguished from devices such as magnetic solenoids and loudspeakers that convert electricity into motion but do not generate usable mechanical powers, which are respectively referred to as actuators and transducers.
  • Electric motors operate on three different physical principles: magnetic, electrostatic and piezoelectric. By far the most common is magnetic.
  • magnetic motors magnetic fields are formed in both the rotor and the stator. The product between these two fields gives rise to a force, and thus a torque on the motor shaft. One, or both, of these fields must be made to change with the rotation of the motor. This is done by switching the poles on and off at the right time or varying the strength of the pole.
  • the main types are DC motors and AC motors, the former increasingly being displaced by the latter.
  • AC electric motors are either asynchronous or synchronous.
  • a synchronous motor requires synchronism with the moving magnetic field's synchronous speed for all normal torque conditions.
  • the magnetic field In synchronous machines, the magnetic field must be provided by means other than induction such as from separately excited windings or permanent magnets.
  • a fractional horsepower (FHP) motor either has a rating below about 1 horsepower (0.746 kW) or is manufactured with a standard frame size smaller than a standard 1 HP motor. Many household and industrial motors are in the fractional horsepower class.
  • the moving part is the rotor, which turns the shaft to deliver the mechanical power.
  • the rotor usually has conductors laid into it that carry currents, which interact with the magnetic field of the stator to generate the forces that turn the shaft.
  • some rotors carry permanent magnets, and the stator holds the conductors.
  • the rotor is supported by bearings, which allow the rotor to turn on its axis.
  • the bearings are in turn supported by the motor housing.
  • the motor shaft extends through the bearings to the outside of the motor, where the load is applied. Because the forces of the load are exerted beyond the outermost bearing, the load is said to be overhung.
  • the stator is the stationary part of the motor's electromagnetic circuit and usually consists of either windings or permanent magnets.
  • the stator core is made up of many thin metal sheets, called laminations. Laminations are used to reduce energy losses that would result if a solid core were used.
  • the distance between the rotor and stator is called the air gap.
  • the air gap has important effects, and is generally as small as possible, as a large gap has a strong negative effect on the performance of an electric motor. It is the main source of the low power factor at which motors operate.
  • the air gap increases the magnetizing current needed. For this reason, the air gap should be minimal. Very small gaps may pose mechanical problems in addition to noise and losses.
  • Windings are wires that are laid in coils, usually wrapped around a laminated soft iron magnetic core providing magnetic poles when energized with current.
  • Electric machines come in two basic magnet field pole configurations: salient-pole machine and non-salient-pole machine.
  • salient-pole machine the pole's magnetic field is produced by a winding wound around the pole below the pole face.
  • non-salient-pole, or distributed field, or round-rotor, machine the winding is distributed in pole face slots.
  • a shaded- pole motor has a winding around part of the pole that delays the phase of the magnetic field for that pole.
  • Some motors have conductors that consist of thicker metal, such as bars or sheets of metal, usually copper, although sometimes aluminum is used. These are usually powered by electromagnetic induction.
  • a commutator is a mechanism used to switch the input of most DC machines and certain AC machines consisting of slip ring segments insulated from each other and from the electric motor's shaft.
  • the motor's armature current is supplied through the stationary brushes in contact with the revolving commutator, which causes required current reversal and applies power to the machine in an optimal manner as the rotor rotates from pole to pole. In absence of such current reversal, the motor would brake to a stop.
  • Significant advances have been made in the past few decades due to improved technologies in electronic controller, sensorless control, induction motor, and permanent magnet motor fields, electromechanically commutated motors are increasingly being displaced by externally commutated induction and permanent-magnet motors.
  • FIGURE (FIG) 1 is an isometric view of a three-rotor blade system assembly
  • FIG 2 is a side view of FIGURES (FIGS) 1 and 3;
  • FIG 3 is an elevated top view of FIGS 1 and 2;
  • FIG 4 is an elevated top view of a four-rotor blade system assembly with a 90-degree power strip providing power to all four blades during 360-degree of rotation;
  • FIG 5 illustrates a PL112.10 - PL140.10. L, LF, W, TH, see data table;
  • FIG 6A PICMA® Bender bending actuators have differential control, displacement of the PICMA® bending actuators: Clamped on one side (top) and on both sides (bottom);
  • FIG 6B is a data table of PL112 - PL140 PICMA® Bender All -Ceramic Bending Actuators with High Displacement;
  • FIG 7 is a data table of PL112 - PL140 PICMA® Bender
  • FIG 8 illustrates a symmetrical airfoil and nonsymmetrical airfoil (cambered) airfoil
  • FIG 9 illustrates a side view of a wing aerodynamic profile with a hinge at the front of the wing to pivot the two halves of the wings around the hinge;
  • FIG 10 illustrates a perspective view of the aircraft wing in FIG 9 pivoted around hinge 180-degree angle from a 90-degree angle from the original wing positions, which provides a maximum gliding function for aircraft in FIGS 12 through 15;
  • FIG 11 illustrates a perspective view of the aircraft wing in FIG 9 providing wings that slide open rather than hinge;
  • FIG 12 illustrates a perspective view of the fuselage in FIG 30 with rotating wings attached to the nose of the fuselage
  • FIG 13 illustrates a perspective view of the aircraft in FIG 34 with wings rotated into a rotary wing helicopter type lift or forward thrust configuration, which provides a tip-path thrust system with forces and aerodynamics around the same circular path;
  • FIG 14 illustrates a perspective view of the aircraft in FIGS 34 and 35 with additional rotary wings to add to the capacity of the aircraft, including a fuselage that rotates with each independent rotary wing assemble, providing additional X wing four rotary wings on back to stand the aircraft on the backs of the wings during lading or takeoff;
  • FIG 15 illustrates a perspective view of the aircraft in FIG 36 with the front two sets of rotary wings position to rotate in opposite directions;
  • FIG 16B illustrates a perspective view of the fuselage in FIG 21 provided a separated shell of the fuselage shape partially elevated into a fixed location to convert fuselage into a glider eliminating the need for power to land safely;
  • FIG 16B illustrates a perspective view of the fuselage in FIG 28 provided a hinge to pivot the split fuselage, converting it into a glider with more surface a perspective view of the aircraft in FIG 24 and resistance to falling;
  • FIG 17A illustrates a perspective view of the fuselage in FIG 30 with the bottom fuselage ends rotated to the top providing a glider function to land with minimum or no power;
  • FIG 17B illustrates a perspective view of the fuselage in FIG 29, before the fuselage to opened around the hinge;
  • FIG 18 illustrates a perspective view of the fuselage in FIG 30 with diagonal air pathways between the fuselage two halves, which are separated enough to direct top of fuselage air to the bottom for more lift, like the helix in FIG 21;
  • FIG 21 illustrates a fuselage of an aircraft with airduct helix pathways to optimize lift of any aircraft, which could include any shape;
  • FIG 22 illustrates a fuselage of an aircraft in FIG 21 with airduct helix pathways that have been isolated into airfoils around the fuselage, each scaled concentrically from the central axis of FIG 21 to optimize lift of any aircraft, which could include any shape;
  • FIG 23 illustrates a side perspective view of FIG 22 helix fuselage scaled around one-point origin, which forms a more aerodynamic fuselage than concentric scaling radially rather than radially and along the axis of the fuselage;
  • FIG 24 illustrates a top view of FIG 23 helix fuselage unrolled around helix intersecting mirrored sides
  • FIG 25 illustrates an end view of FIG 24 helix fuselage unrolled around helix intersecting mirrored sides of FIG 23;
  • FIG 26 illustrates a perspective view of FIGS 23, 24, 25, and 26 providing a view of helices and data centerline at rear of fuselage;
  • FIG 27 illustrates a perspective view of FIGS 23, 24, 25, 26, and 27 providing a view of rear wings and tail of aircraft unrolled from top helices airfoil and data centerline at rear of fuselage;
  • FIG 28 illustrates a side view, and end view, and an elevated view of two of the aircraft in FIGS 27 (or 22), without wings or a tail, traveling suspended on air within a tube where air is blown in one end and vacuumed out the opposite end;
  • FIG 29A illustrates an end view of FIG 29B which is a propulsion ball in the airduct on the surface of an aircraft or migrating to the surface of an engineering mobility system;
  • FIG 29B illustrates a perspective view of FIG 28 A for viewing the propulsion ball entering the firing tube and a second propulsion ball is exiting the firing tube into the open-air propulsion chamber to move air aerodynamically on the surface of an aircraft;
  • FIG 30 illustrates an aircraft wing aerodynamic, provided with a chain roller and sprocket to wing surface around the aircraft wing, which may be used to position the aircraft on a terrestrial surface too;
  • FIG 31 illustrates an isometric view of a circle-arc stator roller chain type assembly chain links stator;
  • FIG 32 illustrates an isometric view of a circle-arc stator roller chain type assembly chain links stator in FIG 31 stacked on ends to circle around a circular helix stator within a tube shape in FIGS 19 and 20;
  • FIG 33 illustrates roller chain motor stator fastened along the circumference of circle in a circle-arc of about 90-degrees of rotation requiring four motor poles arrayed as radius lengths from center at 90-degrees, a circle-arc of about 120-degrees of rotation requiring three motor poles arrayed as radius lengths from center at 120-degrees, and a circle-arc of about 180-degrees of rotation requiring two motor poles arrayed as radius lengths from center at 180-degrees;
  • FIG 34A illustrates a side view prior art of a roller chain and sprocket chain drive in
  • FIG 35
  • FIG 34B illustrates a side view of a roller chain and sprocket chain drive in FIG 35;
  • FIG 35 illustrates a perspective view of a roller chain and sprocket chain drive as a way of transmitting mechanical power from one place to another, which a triangular modification provides an additional motion translational geometry to reciprocate rods, a motion translational function, to compress and expand piston cylinder assembly, stretch and compress piezoelectric material to drive the chain assembly or energy that moves the chain assembly can generate electricity;
  • FIG 36 illustrates an expanded assembly to configure piston and cylinders, piezoelectric material insertion, and other energy conversion systems, like Stirling engines expanded to a 1.41 -centimeter distance between the two rocker arms in FIG 35;
  • FIG 37 illustrates a perspective view of FIG 36 expanded to a maximum 1.41- centimeter distance between the two rocker arms;
  • FIG 38 illustrates a perspective view of FIG 36 closed to a 0.00-centimeter distance between the two rocker arms
  • FIG 39 illustrates a perspective view of FIG 36 reduced to a 0.39-centimeter distance between the two rocker arms
  • FIG 40 illustrates a perspective view of FIG 36 reduced to a 1.06-centimeter distance between the two rocker arms
  • FIG 41 illustrates a roller chain triangular-link and prior art two pin link
  • FIG 42 illustrates a roller chain triangular-link 370 with an axle inserted at a triangular distance from pairs of elements 80 and 79 that contact the sprockets 301 at a distance that will fit the double sprocket in FIG 35.
  • FIG 43 illustrates a side view of a roller chain and sprocket chain drive in FIGS 34 through 40.
  • FIG 44 illustrates a roller chain triangular-link 370 with an axle inserted at a distance that will fit the double sprocket in FIG 49, with greater detail in FIG 53 illustration of perspective view.
  • FIG 45 illustrates a roller chain triangular-link with an axle inserted at a distance that will fit the double sprocket in FIG 49;
  • FIG 46 illustrates a roller chain triangular-link with an axle inserted at a distance that will fit the double sprocket in FIG 49;
  • FIG 47 illustrates a perspective view of FIG 46 to observe the double sprocket assembly and triangular-link connection, which provides a double sided triangular-link for bending the chain in reverse to increase the compression and expansion angles for a given geometry and sizes;
  • FIG 48 illustrates a perspective view of a roller chain and sprocket chain drive as a way of transmitting mechanical power from one place to another, which a triangular modification provides an additional motion translational geometry to reciprocate rods, a motion translational function, and a modification of the second link in a chain drive provides a rotation function when transitioning from straight chains to curving around the sprockets and back to straight pathways;
  • FIG 55 illustrates a perspective top view of FIGS 54 and 56 to observe the angle of 26.1 -degrees that a design provides;
  • FIG 50 illustrates a side view of FIG 49 to view the chain drive pathway relative to the sprocket that rotates the links configured around second link;
  • FIG 51 illustrates a perspective view of a roller chain and sprocket chain drive in FIG 35 stacked three wide in the axial direction of rotation;
  • FIG 52 illustrates a perspective close up view of a roller chain and sprocket chain drive in FIG 51 stacked three wide in the axial direction of rotation;
  • FIG 53 illustrates a hinge 450 for compressing and stretching piezoelectric or reciprocating components at and radial distance that material strength will tolerate.
  • FIG 54 illustrates an end and side view of an all-ceramic bending circular actuator with high displacement
  • FIG 55 illustrates an end and side view of an all-ceramic bending circular actuator with high displacement.
  • FIG 56 illustrates a ball joint that has the freedom to rotate around its axis 360- degrees, which differentiates it from a chain link, and a 25-degree angle is possible in this view providing the ability to curve around a chain roller sprocket designed to receive the ball shape;
  • FIG 57 illustrates a cycloid curve shape to describe how distance objects start out at on the curve arrive at the same time when starting out at the same time;
  • FIG 58 illustrates a cycloid curve shaped sprocket rotated 90-degrees, 42.19-degrees, and 0-degrees to provide the area of the cycloid sprocket, which is equal when divided along the line going through the center point of rotation;
  • FIG 59 illustrates the cycloid sprocket of FIG 58 coordinate points generated when rotating a circle along a straight line the length of the circle's circumference
  • FIG 60 illustrates the cycloid sprocket in FIG 59 rotated 90-degrees
  • FIG 61 illustrates a hexagonal fuselage with all the elements of this inventions Tip- Path elements
  • FIG 62 illustrates two options to fasten the edges of surface curved snap fastener edges together around different shapes.
  • FIG 63 illustrates a perpendicular view of letter "t" 136 optical center C (also known as camera projection center) 130 of the image 134 on plane
  • FIGURE 13 illustrates
  • FIG 64 illustrates flexible helix video display camera dimensional observation for software programming an image from the math.
  • FIG 65 illustrates a hexagonal fuselage with all the elements of this inventions Tip- Path elements
  • FIG 66 illustrates rotating wings to provide gliding for all drones or other aircraft with or without wings.
  • FIG 1 is an elevated isometric view of a three-rotor blade system assembly 1 comprised of helicopter rotor airfoil blades 2, 3, and 4 fastened to rotor blade spoked mast hub 5 and cap 6 to provide a central mast for a 360-degree rotational direction 11 for assembly 1 to rotate around axis 16 on a gimbal that is a pivoted support that allows the rotation of an object about a single axis.
  • rotational refers to the method of producing relative wind.
  • Rotational relative wind flows opposite the physical flightpath of the airfoil, striking the blade at 90° to the leading edge and parallel to the plane of rotation illustrated in the side view of FIG 2 and elevated top view in FIG 3; and it is constantly changing in direction during rotation. Rotational relative wind velocity is highest at blade tips 20, decreasing uniformly to zero at the axis of rotation (center of the hub mast) 16.
  • This invention teaches that in prior art torque from an engine (or electric motors, magnetic drive, jets, or turbines) transferring forces through the hub mast 5 is eliminated by moving the thrust production to the airfoil blade tips 20 of three rotor bladed (two-bladed, or any number of blades can be added) system assembly 1 by spinning propellers rotor system assemblies 12, 13, and 14, comprised of helicopter three rotor (propeller) blades 7, 8, and 9 connected to electric motor hub systems 17, that rotates blades 360-degrees in rotational direction 10 on a gimbal 17 that is a pivoted support that allows the rotation of an object about a single axis.
  • Thrust is moved to the tip 20 of rotor bladed system assembly 1 where energy required to rotate the blade is reduced by the force times the rotor blade moment arm, length of blade span 18.
  • Hub 5 provides electrical connections to electric motor hub 17, from the body of the aircraft with the power source.
  • Propeller assemblies 12, 13, and 14, could be dimensionally the same as assembly 1 blades 7, 8, and 9, scaled down to size. Any number of thrust sources can be placed along the length of blade span 18 and then can be rotated in any direction to control airflow, even to stop the rotation of assembly 1 to just hover in the air.
  • Angle of attack on the leading edge of the airfoil blades 2, 3, and 4 can be increased or decreased by rotating blades around rotating coupling joint 19 in FIG 1.
  • the rotational velocity of the rotor blade 1 is lowest closer to the hub 5 and increases outward towards the tip 20 of the blade during rotation, providing an aircraft that is more efficient than a central axis driven system: engines, electric motors, jets, or turbines forcing rotation through a central mast, like assembly 1, which transferred torque through hub 5 in the plane of rotational direction 11.
  • Torque, moment, or moment of force is rotational force 11.
  • a torque can be thought of as a twist 11 to an object 1.
  • torque is defined as the cross product of the vector by which the force's application point 20 is offset relative to the fixed suspension point 16 (distance vector 18) and the force vector 15, which tends to produce rotational motion 11.
  • torque is a measure of the turning force 11, 15 on an object such as a rotary-wing assembly 1.
  • Pushing or pulling the rotary -wing 1 produces a torque (turning force 11) that rotates the rotary-wing assembly 1.
  • the magnitude of torque depends on three quantities: the force applied 15, the length of the lever arm 18 connecting the axis 16 to the point of force application 20, 15, and the angle between the force vector and the lever arm.
  • the force applied 15 the force applied 15
  • the length of the lever arm 18 connecting the axis 16 to the point of force application 20, 15 the angle between the force vector and the lever arm.
  • ⁇ is the torque vector and ⁇ is the magnitude of the torque
  • r is the position vector (a vector from the origin of the coordinate
  • x denotes the cross product
  • ⁇ is the angle between the force vector and the lever arm vector.
  • the SI unit for torque is the newton meter (N-m).
  • torque is used for the closely related "resultant moment of a couple".
  • Torque is defined mathematically as the rate of change of angular momentum of an object.
  • the definition of torque states that one or both; of the angular velocity or the moment of inertia of an object are changing.
  • Moment is the general term used for the tendency of one or more applied forces to rotate an object about an axis, but not necessarily to change the angular momentum of the object (the concept which is called torque in physics).
  • the direction of the torque can be determined by using the right-hand grip rule: if the fingers of the right hand are curled from the direction of the lever arm to the direction of the force, then the thumb points in the direction of the torque.
  • the torque on a particle (which has the position r in some reference frame) can be defined as the cross product:
  • the construction of the "moment arm” is illustrated in the FIGs 1, 2, and 3, along with the vectors r 18 and F 15 mentioned above.
  • the problem with this definition is that it does not give the direction of the torque but only the magnitude, and hence it is difficult to use in three- dimensional cases. If the force is perpendicular to the displacement vector r, the moment arm will be equal to the distance to the center 18, and torque will be a maximum for the given force 15.
  • the torque will be 5 N-m - assuming that the person moves the wrench by applying force in the plane of movement and perpendicular to the wrench.
  • Torque is part of the basic specification of an engine: the power output of an engine is expressed as its torque multiplied by its rotational speed of the axis.
  • Internal- combustion engines produce useful torque only over a limited range of rotational speeds (typically from around 1,000-6,000 rpm for a small car). The varying torque output over that range can be measured with a dynamometer and shown as a torque curve.
  • Capstone power generation solutions help to improve operations by putting the end-user in control of their energy costs and fuel selection.
  • Capstone microturbines provide distributed energy to this invention's aircraft.
  • Capstone aero-based turbine with high speed air bearings provides reliability and a thrust force source for the tip of a rotary wing to drive a propeller, electric motor, wired to an electric motor from the center 16 of the aircraft to just provide the electricity, or be distributed into the wing tip with the intake and exhaust thrusting the aircraft wing.
  • a Capstone turbine is installed in the wing tip, a fuel supply can be provided through the central hub 5 (or in a large wing), as it rotates, it can capture fuel for transport through the rotor blades 2, 3, and 4.
  • Propellers 12, 13, and 14 would be replaced by Capstone turbines on the tips 20 of the rotor blades 2, 3, and 4.
  • a round airfoil structure can be provided with an inside diameter of ring 27 where rotor bladed airfoils are attached to the ring 27, adding a structure to house Capstone turbines, connect a helium or hot air balloon, house batteries, and connect to larger aircraft airfoil wings as a subsystem.
  • rotary- wings could be stacked onto www.LevX.com magnetic levitating bearing rings.
  • the ring 27 could also provide a magnetic drive to force the tip 20 with a magnetic coupling provided to couple around the ring 27, providing force 15.
  • a two-rotor bladed airfoil in a rotary -wing aircraft could change the function of the rotor blades into conventional airplane wings, then return back into rotary-wings.
  • Capstone Microturbines operate on a variety of fuels, including natural gas, associated gas, biogas, LPG/propane, and liquid fuels (diesel, kerosene, and aviation fuel). In resource recovery applications, microturbines burn waste gases that would otherwise be flared or released directly into the atmosphere. Capstone microturbines: Capstone Turbine Corporation (CPST), 21211 Nordhoff Street, Chatsworth, CA 91311, www.capstoneturbine.com .
  • Capstone microturbines feature low maintenance air bearing technology, the lowest emissions of any non-catalyzed gas combustion engine, and digital power conversion to stand as the optimal power generation solution.
  • Capstone microturbines stand out as a robust source of clean power.
  • Capstone microturbines can be installed individually or in a "multi-pack" configuration and function as thrust on rotary-wings. Capstone microturbines are compact, quiet and lightweight for integration into the tips of rotary wings to provide reliable energy.
  • an aircraft like a conventional helicopter system can be attached to hub 5.
  • a cycloid curve 26 is illustrated on the leading edge, providing a wind air particle path that would traverse a segment of an inverted cycloidal arch in the same amount of time, regardless of its starting point on curve 26.
  • this invention teaches a cycloid curved rotor bladed airfoil inner leading-edge curve 26 (whole airfoil surface wind entry and exit could be a cycloid curve), first capturing air, wind air particle would traverse a segment of an inverted cycloidal arch 26 illustrated, in the same amount of time, regardless of its starting point on curve 26.
  • Controlling air dynamics by providing a synchronized wind departure cycloid curve increases control, reducing drag and turbulence of wind at the compressed air particle level. Every wind path on the aircraft would be a design optimization by applying cycloid shapes, which could be optimized by adding piezoelectric wafers to reshape the aircraft.
  • Micro propellers of drones or human air taxis could be comprised of piezoelectric wafers shaped into turbines, fans, and propellers.
  • FIG 8 illustrates a symmetrical airfoil and nonsymmetrical airfoil (cambered) airfoil.
  • the symmetrical airfoil 31 is distinguished by having identical upper and lower surfaces.
  • the mean camber line and chord line are the same on a symmetrical airfoil, and it produces no lift at zero angle of attack (AO A).
  • Most light helicopters incorporate symmetrical airfoils in the main rotor blades.
  • the upper and lower curvatures are the same on a symmetrical airfoil and vary on a nonsymmetrical airfoil.
  • the nonsymmetrical airfoil 30 has different upper and lower surfaces, with a greater curvature of the airfoil above the chord line than below.
  • the mean camber line and chord line are different.
  • the nonsymmetrical airfoil design can produce useful lift at zero AOA.
  • nonsymmetrical design has advantages and disadvantages.
  • the advantages are more lift production at a given AOA than a symmetrical design, an improved lift-to-drag ratio, and better stall characteristics.
  • the disadvantages are center of pressure travel of up to 20 percent of the chord line (creating undesirable torque on the airfoil structure) and greater production costs.
  • Blade twist provides higher pitch angles at the root where velocity is low and lower pitch angles nearer the tip where velocity is higher. This increases the induced air velocity and blade loading near the inboard section of the blade in FIG 1.
  • Rotary wing blades 2, 3, and 4 in this invention can be spinning around the blades individual axis relative to the blade not the blade assembly 1.
  • a central rotary blade hub axis 16 can have a stationary gear fixed relative to the fuselage, so when all the blades rotate around the central hub 5 axis 16, each blade is rotating around its own axis to provide more lift with near the same power source, air frame, and blade assembly.
  • Each blade could be mounted to independent electric motors to spin the blades independent of each other.
  • blades can morph
  • Blade assembly 1 can also rotate all the blades together at the same time blades 2, 3, and 4 are rotating independently.
  • FIG 6 PICMA® illustrates Bender bending actuators have differential control to reshape the aero dynamics of airfoil surfaces.
  • a rotary airfoil blade 1 of a propeller typically is mounted to a plane where air is crossing a shaped airfoil wing to decrease the air density on top of area 23 and increase the air density below bottom area 22, where the wing is dependent upon the wing airfoil shape.
  • this invention teaches that in milliseconds, piezoelectric wafers mounted onto propeller airfoil blades 2, 3, and 4 of FIG 3 are morphed from a symmetrical airfoil 31 into a nonsymmetrical airfoil (chambered) 30, to increase air density for more lift during high speed propeller rotation.
  • FIG 3 illustrates an upper half of a circle 27 area 23 divided by dashed line 21 where airfoil shape 31 (FIG. 8) is provided to capture or decrease wind by morphing piezoelectric wafers.
  • FIG 3 illustrates a lower half of a circle 27 area 22, divided by dashed line 21, where airfoil shape 30 (FIG. 8) is provided by morphing piezoelectric wafers to produce more rotational relative wind (tip-path plane) for more lift and travel speed.
  • airfoil shape 31 (FIG. 8) is applied to capture wind, it is released where higher density air is desired to lift or travel.
  • FIGS 5 to 7 provide the data for selecting all-ceramic bending actuators with high displacement.
  • FIG 7 is a data table of PL112 - PL140 PICMA® Bender
  • FIG 5A illustrates a PL112.10 - PL140.10. L, LF, W, TH, see data table;
  • FIG 5B PICMA® illustrates Bender bending actuators have differential control to reshape the aero dynamics of airfoil surfaces;
  • FIG 6 Displacement of the PICMA® bending actuators: Clamped on one side (top) and on both sides (bottom).
  • Displacement to 2 mm Fast response in the ms range, nanometer resolution, low operating voltage, and operating temperature up to 150 °C.
  • Operating voltage 0 to 60 V.
  • Bidirectional displacement, bimorph design Ceramic insulation, polymer free.
  • UHV compatible to 10-9 hPa no outgassing, high bake out temperature. Reliable even under extreme conditions.
  • Resonant frequency Measured at 1 Vpp, clamped on one side with remaining length LF, unloaded.
  • Standard connections Solderable contacts (PLlxx.10) or PTFE-insulated stranded wires, 100 mm, AWG 32, 0 0.49 mm (PLlxx. l l).
  • PICMA® multilayer piezo bending actuator 200 ⁇ travel range, 18 mm x 9.60 mm x 0.67 mm.
  • PICMA® multilayer piezo bending actuator 620 ⁇ travel range, 25 mm x 9.60 mm x 0.67 mm.
  • PICMA® multilayer piezo bending actuator 900 ⁇ travel range, 31 mm x 9.60 mm x 0.67 mm.
  • PICMA® multilayer piezo bending actuator 900 ⁇ travel range, 36 mm x 6.15 mm x 0.67 mm.
  • PL140.10 PICMA® multilayer piezo bending actuator 2000 ⁇ travel range, 45 mm x 11.00 mm x 0.55 mm.
  • PICMA® multilayer piezo bending actuator 620 ⁇ travel range, 25 mm x 9.60 mm x 0.67 mm, stranded wires.
  • PICMA® multilayer piezo bending actuator 900 ⁇ travel range, 31 mm x 9.60 mm x 0.67 mm, stranded wires.
  • PICMA® multilayer piezo bending actuator 900 ⁇ travel range, 36 mm x 6.15 mm x 0.67 mm, stranded wires.
  • PICMA® multilayer piezo bending actuator 2000 ⁇ travel range, 45 mm x 11.00 mm x 0.55 mm, stranded wires.
  • Hollow propellers can be opened by opening piezoelectric wafers to fill a propeller blade with air on top of a wing, then piezoelectric wafers can be shut on one side, opened on the other to release captured air under a wing or structures configured to lift an aircraft.
  • Wafers can be wired with optional nano wires made of graphene that are very dense and flexible, so vibrating wafer at ultrasonic speeds do not damage the wire windings.
  • VTO is supporting research and development (R&D) to improve motors in hybrid and plug-in electric vehicles, with a particular focus on reducing the use of rare earth materials currently used for permanent magnet-based motors.
  • an electric motor converts the stored electrical energy in a battery to mechanical energy.
  • Electric motors consist of a rotor (the moving part of the motor) and a stator (the stationary part of the motor).
  • a permanent magnet motor includes a rotor containing a series of magnets and a current-carrying stator (typically taking the form of an iron ring), separated by an air gap.
  • This invention teaches that the current-carrying stator is reduced in size to match the number of "poles" on the rotor (Example Given: four blades of a helicopter would have a 90-degree Circle-arc (arc-power strip stator)), which would provide 360-degrees of force as each of the tip-path ends of four electrically wired blade poles pass within the 90-degree arc-power strip stator.
  • Permanent magnets can be reduced in size, weight and power capacity by mounting the magnet on the end of piezoelectric wafer that move the magnet back and forth up to an ultrasonic speed, providing more eddy currents increasing the electromagnetic currents across an airgap between a stator and rotor.
  • IPM motors Internal Permanent Magnet (IPM) motors have high power density and maintain high efficiency over a high percentage of their operating range. Almost all hybrid and plug -in electric vehicles use rare earth permanent magnets in their traction motors. Because of the high costs of magnets and rotor fabrication, these motors are relatively expensive. Other challenges to using IPM motors include the limited availability and high cost of rare earth magnetic materials. Despite the challenges, the automotive industry anticipates continuing to use IPM motors in the majority of electric drive vehicles over the next decade.
  • Induction motors have high starting torque and offer high reliability. However, their power density and overall efficiency are lower than that of IPM motors. They are widely available and common in various industries today, including some production vehicles. Because this motor technology is mature, it is unlikely research could achieve additional improvements in efficiency, cost, weight, and volume for competitive future electric vehicles.
  • Switched reluctance motors offer a lower cost option that can be easy to manufacture. They also have a rugged structure that can tolerate high temperatures and speeds. However, they produce more noise and vibration than comparable motor designs, which is a major challenge for use in vehicles. Also, switched reluctance motors are less efficient than other motor types, and require additional sensors and complex motor controllers that increase the overall cost of the electric drive system.
  • VTO's primary goal is to decrease electric motors' cost, volume, and weight while maintaining or increasing performance, efficiency, and reliability.
  • the National Renewable Energy Laboratory is focusing research on improving electric motor thermal management, performance and reliability.
  • FIG 4 is an elevated top view of a four-rotor blade 42 system assembly with a 90- degree arc-power strip stator 41 providing electric power to all four blades 42 during full 360- degrees of rotation by electromagnetically forcing the magnetic tip 40 along the arc-power strip stator 41 aligned close enough to rotor tip-path tip 40 to transfer electromagnetic force across air gap between assembly stator 41 and tip 40 of blade 42.
  • This invention teaches that a full 360- degrees of force can be applied to each rotor blade 42 pole tip 40 by providing an electric arc-power strip 40 shaped to match the path of the rotor pole blade 42 tip 40 and each blade rotating next through the path of arc-power strip stator 41.
  • FIG 3 illustrates a three-blade assembly, so a 120-degree arc-power strip stator would be mounted in the arc between any two of the triangles illustrated next to the blades 2, 3, and 4 tips.
  • Two-blade rotors would have a 180-degree arc power strip, so any design and number of blades can be provided the corresponding arc-power strip stator length.
  • a six-bladed rotary wing would have 60-degree of arc-power strip stator.
  • Electromagnetic arc-power strips can be designed with any rotating electric motor technology, including any controls and sensors to keep the power transfer from arc-power strip 41 to blade 42 electric motor element tip 40.
  • Tip 40 can be a permanent magnet, electric coil, or any other element that will electromagnetically transfer rotational motion to the rotor assembly.
  • tip 40 could be shaped into a "jet" energy receptacle to capture high speed air or exhaust fumes jetting out to blow or vacuum the rotor blade tip 40 to rotate all four of the blades 42 arrayed around a center point of rotation.
  • High speed rotating elements at the tip (or anywhere along the radial distance to the tip) of the blades can be electromagnetic elements that add to the energy for forcing rotation or generating electricity.
  • Arc-power strip divisions and positioning In yet a further embodiment of this invention, teaches that in a three-blade assembly in FIG 3, an 120-degree power strip is taught to be mounted in the arc between any two of the three triangles illustrated next to the blade tips, which 120-degree arc could further be divided up into three 40-degree arc-power strip stators arrayed into separate positions to provide one of three tips of the blades to each engage the tip of a corresponding 40-degree arc-power strip stator.
  • FIG 3 A full 360-degrees of force is provided by FIG 3 as blade 2 arc-power strip stator forces the blade the first 40-degrees, blade 3, now rotated 40-degrees from its original position is the "continuous" force for the second 40-degree arc-power strip stator, then blade 4 now rotated 80-degrees from its original position would provide the last (third) 40- degrees of force from the last 40-degree arc-power strip stator totaling 120-degrees of forced motion, first phase of three. In second phase, blade 4 rotated 120-degrees into the original position of blade 2 starting point, which provides the same sequences as blade 2, 3, and 4 were forced through in the first phase.
  • blade 3 rotated 120-degrees into the original position of blade 2 starting point, which provides the same sequences as blade 2, 3, and 4 were forced through in the first phase.
  • 360-degrees of continuous force from three 40-degree arc-power strip stators teach that further breakdown of any rotor with any number of blades can be positioned to provide 360-degrees of rotation forces.
  • Arc-power strip stators can be placed anywhere along the axis in a perpendicular position relative to the axis, and in addition can be moved too, if they add force to the rotation at the correct time to force rotation around that axis.
  • a belt or chain arc-power strip, full of permanent magnets or electric coils (any power source) can be rotated into the form of an arc-power strip, where the motion of the arc-power strip is driven into motion with another power source of any shape or size.
  • Engineered hybrid devices could have arc-power strips provide half the power of rotation, while some other force, like water, wind, or steam provides the balance of 360-degree force. Capacitors could be charged remotely, then moved into the cycle.
  • This invention teaches that piezoelectric All-Ceramic Bending Actuators with High Displacement in FIGS 5 through 7, and 54 and 55 are provided with permanent magnets or a wired electromagnetic coil to drive a motion translation device, like arc-power strip stators taught in this invention or adding force to any other motion translational device: tip-path of turbine, turboprop, turbo fans, jets, and morphing objects, like robots. Diving rotational devices with piezoelectric wafers at the tip-path of the structures increases the efficiency and the devices can reach ultrasonic speed staying clean during operation in addition to higher electromagnetic force, because of the ultrasonic speed capability magnetic field density increases.
  • Wind power blades can be equipped with electromagnetic (permanent magnets or wired coils) tips to generate electricity from wind energy with a full 360-degrees, or arc-power strips corresponding to the number of blades (blades are poles, like a pole motor wired or containing permanent magnets).
  • Automotive, bicycle, or other motion translational devices can provide equally spaces electric components inside or outside a tire, wheel rim, or axil to adapt this arc-power strip to an application.
  • An innertube could be a wired arc-power component to upgrade a car and bike tire, or the tire can be made into an arc-power strip with corresponding components on the frame of the engineered motion machine.
  • FIG 1 through 4 rotary blades can be hollow, providing a rotating air vessel to capture, compress, then release air to optimize control through airducts shaped for capturing air, all controlled by valving with optional morphing piezoelectric wafers controlled at fractions of a second, controlled by the revolutions per minute.
  • Hollow bladed rotary wings are provided optional small high-speed air fans (turbofan, propeller, or other air capture devices) near the blades tip-path that can capture more air than just the outside surface of a rotary blade airfoil and then release air adding to propulsion and noise reduction at the Tip-Path of propulsion.
  • a cylindrical ring can be part of the rotary blades structure, but another turbine or propeller can be ported from inside the ring to outside the ring to manage the air wasted exiting the tip-path of a rotary wing, again capture and direct the air inside the tip-path ring, but port the air to an air path optimized shape, or through another outer propulsion device that can redirect inner air inside the inner ring diameter or from the hollow rotary blade to the outside of the ring diameter, or work independently to control Gyroscopic Precession the spinning main rotor of a helicopter acts like a gyroscope moving the blades in and out of the tip-path.
  • FIG 9 illustrates a side view of a wing aerodynamic profile with a hinge at the front of the wing to pivot the two halves of the wings around the hinge.
  • FIG 10 illustrates a perspective view of the aircraft wing in FIG 9 pivoted around hinge 180-degree angle from a 90-degree angle from the original wing positions, which provides a maximum gliding function for aircraft in FIGS 12 through 15.
  • FIG 11 illustrates a perspective view of the aircraft wing in FIG 9 providing wings that slide open rather than hinge.
  • FIG 12 illustrates a perspective view of the fuselage in FIG 17B with rotating wings attached to the nose of the fuselage.
  • FIG 13 illustrates a perspective view of the aircraft in FIG 12 with wings rotated into a rotary wing helicopter type lift or forward thrust configuration, which provides a tip-path thrust system with forces and aerodynamics around the same circular path.
  • FIG 14 illustrates a perspective view of the aircraft in FIGS 12 and 13 with additional rotary wings to add to the capacity of the aircraft, including a fuselage that rotates with each independent rotary wing assemble, providing additional X wing four rotary wings on back to stand the aircraft on the backs of the wings during lading or takeoff.
  • FIG 15 illustrates a perspective view of the aircraft in FIG 14 with the front two sets of rotary wings position to rotate in opposite directions.
  • FIG 12 illustrates perspective view of an aircraft fuselage and wing assembly 200, providing wings 218 and 219 on a fuselage 201 with tip-path propulsion rotary wing propellers on the ends of the wings 218 and 219.
  • Wings 218 and 219 rotate in FIG 13 around rotating cylinder 201 to provide a helicopter type rotary wing assembly 200 to convert from horizontal flight by rotating the wings near 180-degrees apart from FIG 12 to rotary wings in FIG 13.
  • FIG 14 and 15 illustrates an aircraft fuselage and wing assembly 200, provided three rotating sections 201a, 201b, and 201c of the fuselage 200.
  • Wings 218 and 219 including rotating wing propellers to provide rotating wing propeller in FGURE 13.
  • rotating wings 218 and 219 including rotating wing propellers provided rotating wing propeller around rotating fuselage hub 201c.
  • Wings 216 and 211 including rotating wing propellers provided rotating wing propeller around rotating fuselage hub 201b.
  • Wings 211. 212, 213 and 214 including rotating wing propellers provided rotating wing propeller around rotating fuselage hub 201a, which also can be stable cross to stand the aircraft up, pointing the fuselage vertical into a liftoff or landing position.
  • FIG 14 is a stable flight positions to fly horizontal to the ground.
  • These wings in FIGS 12, 13, 14, and 15 can unfold into a parafoil or parachute, which may have optional controls to phase the aircraft into a glider without power or minimized power to direct the aircraft to a destination.
  • Fuel or electric energy will be saved for applications, like product delivery or drone application. Future air taxi travel services would be much safer, if the aircraft phased from high speed into a glider when energy input was withdrawn, just like parachuting down to destination on every flight.
  • Fuselage in FIG 16A has a top 160c with nose 151c and tail 159c that separates from at a fixed distance from the fuselage 160b, nose 151a and 151b, including tail 159a and 159b into a parachute or paragliding type structure.
  • FIG 17A fuselage 160b has a hinge 170, also illustrated in FIG 17B that the fuselage rotates around with opening facing the ground expanding the aerodynamics toward a parachute or glider function.
  • FIG 16B fuselage is illustrated in FIG 17B with nose half 151b and tail half 159b rotated around fuselage center-point 161 providing a glider or parachute function relative to landing without power, or minimum power input on the decent to a destination.
  • FIG 18 fuselage 160 has airducts 171 moving air from the top of fuselage 160 to the bottom through the center of the fuselage. These ducts could be exhaust from energy supplies or added to the fuselage in FIG 21 to optimize the control and redirecting of airflow that is left over from helix 147 and 148. FUGRE 18 diagonal ducts could also be functioning alone as a method to redirect air below a fuselage with other structures, like wings, engines, electric fans or propellers.
  • Any flexible material can be applied over frames or inflated to be applied as aircraft components under any design engineering.
  • FIG 19 illustrates a helix 100.
  • FIG 20 applies the helix in FIG 19.
  • the pitch of a helix is the height of one complete helix turn, measured parallel to the axis 101 of the helix 100.
  • a curve 111 is called a general helix or cylindrical helix 111, if its tangent makes a constant angle with a fixed line 101 in space.
  • a curve is a general helix, if the ratio of curvature to torsion is constant.
  • FIG 20 illustrates a helix 100.
  • FIG 19 illustrates a round cylindrical fuselage, but the concept of redirecting air from the top of an aircraft around to down under the aircraft into compression zones, could be applied to any shape and aerodynamic element in air, water, or space.
  • the helix can be spread over the length of the fuselage into just an 180-degree of each helix around a fuselage length, up to many complete 360-degree turns around a fuselage as illustrated in fuselage 150 of FIG 19.
  • optimizing the airducts around wings attached to the fuselage can modify a perfect helix, including shaping the curves illustrated in FIG 21 into a cycloidal curve that moves all air down to the compression exhaust port during the same period of time during travel, because duplicated specifications applied to several cycloid curves can move objects to the same point starting at different distances along the curves.
  • airduct intake, exhaust, and air pathways can have turbines, fans, and any propulsion installed to add to control of the aircraft.
  • the pitch of a helix is the height of one complete helix turn, measured parallel to the axis 101 of the helix 100.
  • a double helix consists of two (typically congruent) helices with the same axis, differing by a translation along the axis.
  • a conic helix may be defined as a spiral on a conic surface, with the distance to the apex an exponential function of the angle indicating direction from the axis.
  • An example is the Corkscrew roller coaster at Cedar Point amusement park.
  • a circular helix, (i.e. one with constant radius) has constant band curvature and constant torsion.
  • a curve 1 1 1 is called a general helix or cylindrical helix 1 1 1 if its tangent makes a constant angle with a fixed line 101 in space.
  • a curve is a general helix if and only if the ratio of curvature to torsion is constant.
  • a curve is called a slant helix if its principal normal makes a constant angle with a fixed line in space. It can be constructed by applying a transformation to the moving frame of a general helix.
  • curves found in nature consist of multiple helices of different handedness joined together by transitions known as tendril perversions.
  • a helix composed of sinusoidal x a dy components
  • a helix is a curve in 3 -dimensional space.
  • the point (x(t),y(t),z(t)) traces a right-handed helix of pitch 2 ⁇ (or slope 1) and radius 1 about the z-axis, in a right-handed coordinate system.
  • a circular helix of radius a and slope bla (or pitch 2 b) is described by the following parametrization:
  • a charged particle in a uniform magnetic field following a helical path A charged particle in a uniform magnetic field following a helical path.
  • FIG 21 illustrates how to increase the climb gradient of a fuselage assembly 150 travelling in direction of centerline arrow 161 through atmospheric airstream relative resistant path 149, which provides double helix aerodynamic air paths consisting of two (typically congruent) helices 147 and 148 with the same axis 161, differing by translation pathways 147 and 148 along the centerline axis 161.
  • Helix 147 has the same mirrored dimension as helix 148, which this invention teaches is a mirrored helix around intersection points 152 and 158 on an aircraft fuselage 160 with center-axis 161 providing more lift 163 for an increase climb gradient (during long term flight altitude too), after exhausting through each bottom intersecting compression points 153, 155, and 157.
  • An airduct can be constructed around the fuselage 160 surface in the path of each helix; helix 147 is in a clockwise rotation relative to moving in the direction of centerline arrow 161 from back-tail end 159 to front-nose 151, and helix 148 is in a counterclockwise rotation around center- axis 161 moving from the back-tail end 159 on fuselage 160 up to the front nose end 151.
  • a mirrored double helix of equal helices intersects at 180-degree intervals starting at point 152, followed by 153, 154, 155, 156, 157, 158, and ending up at 159, which this invention teaches is an optimized pathway for air currents during flight of an aircraft providing more climb gradient lift forces 163 by directing air on top of the aircraft from helices intersections 152, 154, 156, and 158 to the corresponding compression zones underneath the aircraft, where the helices intersect 153, 155, and 157.
  • Helices are designed into air ducts to capture air to be directed under the aircraft for lift 163 arrows following each bottom intersecting air compression points 153, 155, and 157.
  • Valving or reshaping of the ducts can be provided to modify the location force vectors 162 and 164 of the air flow around the whole fuselage 160.
  • Directing air from the top of the aircraft to the bottom of the aircraft with helices of the least air turbulence shape (length, duct diameter, coating surfaces, and other standard best practices) reduces the density of air above the aircraft by accelerating air from above to below the aircraft sooner than prior art, increases density during compression of air under the center of the fuselage within the intersecting points of the helices geometry 153, 155, and 157.
  • the outer surface can increase in diameter segmented into a stepped fuselage surface along each helix line between helix intersecting points to multiply the amount of air the surfaces of the fuselage captures by stepping the fuselage surface to greater diameters while moving from front nose 151 to the tail-end 159.
  • This invention teaches several concentric spaced fuselage's surfaces relative to centerline 161 capture more air for increased lift 163.
  • FIG 22 illustrates a fuselage 160 of an aircraft in FIG 21 with airduct helix pathways that have been isolated into airfoils, 162, 164, and 166 around the fuselage centerline 161, each airfoil is scaled concentrically from the central axis of FIG 21 to optimize lift of any aircraft, which could include any layered-out shape, like the tubes.
  • FIG 23 illustrates a side perspective view of FIG 22 helix fuselage scaled around one-point of origin 158, which forms a more aerodynamic fuselage than concentric scaling radially rather than radially and along the axis 166 of the fuselage 160.
  • Helix lines from point 156 to point 157 along helix 147 and 148 are copied back to the scaling origin point 158, providing tube 166, after scaling concentrically, not including scaling along the center line 161.
  • FIG 24 illustrates a top view of FIG 23 helix fuselage unrolled around helix intersecting mirrored sides around points 152 and 158 in FIG 21. Wings 166 on top, then 166b, 166c, and 166d are unrolled from the fuselage illustrated in FIG 23.
  • FIG 25 illustrates an end view of FIG 24 helix fuselage unrolled around helix intersecting mirrored sides of FIGS 23 and 27.
  • FIG 26 illustrates a perspective view of the fuselage in FIGS 23, 24, 25, and 27 unrolled flat, providing a view of helices 150 and data centerline at rear of fuselage when rolled up into a tube in FIG 23 and 27.
  • FIG 27 illustrates a perspective view of FIGS 23, 44, 25, and 26 providing a view of rear wings 166a and tail 166b of aircraft unrolled from top helices airfoil 166 three dimensionally along data centerline from points 158 to points 156 at the rear on top of fuselage.
  • Three to four extra layers of tube 166 is provided to form tail 166c and 166d, and then a second set of three layers of tube 166 form wing 166a and 166b.
  • these unrolled wings have geometry that stops the unrolling to the aerodynamic destination tail or wing, including wing modifying infrastructure.
  • Ribs can unfold with flexible material under the wings that tightens when the wing aerodynamic location is reached.
  • Tail 166c and 166d can connect by the same method as the wings, but a fastening structure is recommended.
  • the wing and tail can have many configurations relative to speed, propulsion source, and stacking aircraft for transportation when being transported.
  • FIG 28 illustrates transport tube 1000 with aircraft fuselage 160 in FIG 23 traveling within the tube 1000.
  • First view is an end view of the aircraft within the tube, which is concentric tubes within tubes from FIG 23 fuselage 160 helix tube 166d is the most inner tube of aircraft 160 tube 166d is closest to the inner dimension of tube 1000.
  • a cross-sectional view VI is in the third side view of two aircraft 160 of FIG 23.
  • a Hyperlooop project
  • a tube within a tube aircraft can replace a train in a hyperloop tube by sizing the aircraft to fit within the transport tube in FIGS 21 through 27.
  • Each type of tube within a tube can drive on the grounds with tires that can be automatically extended out for roads and then withdrawn when entering a hyperloop tube 1000. Tires can be slightly extended, until the aircraft becomes completely airborne with tube 1000.
  • tires can be extended, including a customized tube designed just for entering and leaving hyperloop tube 1000 in FIG 28.
  • Teaching a design that inherently fits within a tube 1000 for high speed travel is key to integrate road travel on street with wheels, flying in any sky, landing on any road, and then traveling within hyperloop type tube 1000.
  • Hot air balloons, helium balloons, water skies, and other desired adaptations can be engineered into the tubes providing unrolled tubes. These can replace any location a conventional propulsion system is on a wing now.
  • Tubes within tubes can also slide out longer along the axis 161 in FIG 21, lengthening the cargo capability matching the tube 1000 capability, normal relative air travel, and driving on the road or floating on water.
  • This invention teaches that all connections between the ends of the aircraft, two in FIG 28, can be cycloid curved fastener systems, so as movement occurs between the aircrafts the moving elements are focused around midpoint of a full or fractional cycloid keeping motion synchronized to the midpoint under one period of motion.
  • airborne fueling systems tethered to provide new batteries, recharge batteries, refuel tanks with any fuel in airborne aircraft are easier to connect under the math of a cycloid curve, sustaining the period of time required to fuel.
  • This invention teaches drones or manned aircraft can centrally fly out from a hub in moving traffic and refuel automobiles, boats, aircraft, and other systems by focusing on the cycloid midpoint is where the application function is located for predictability over time periods of connection: plugin, fuel links, and other tether functions like combining and integrating a lot of aircraft into one.
  • Water vapor is a lighter gas than other gaseous components of air at the same temperature, so humid air will tend to rise by natural convection. This is a mechanism behind thunderstorms and other weather phenomena. Relative humidity is often mentioned in weather forecasts and reports, as it is an indicator of the likelihood of precipitation, dew, or fog. In hot summer weather, it also increases the apparent temperature to humans (and other animals) by hindering the evaporation of perspiration from the skin as the relative humidity rises. This effect is calculated as the heat index or humidex.
  • This invention teaches that regulating the redirected cycling air between the top and bottom of the fuselage can add to the propulsion and fueling economy by managing moisture, temperature, and heat source in air flowing within the helices air ducts constructed to compress air below the aircraft.
  • Air with higher humidity is less dense, providing lower lift and lower propeller or turbine efficiency (this is somewhat offset by decreased drag), so this invention teaches how to regulate the less dense air to the top of the aircraft and the dryer air with greater density to the bottom of the aircraft.
  • Pilots must take humidity into account when calculating takeoff distances, because high humidity will require longer runways and will decrease the climb gradient.
  • Density altitude is the altitude relative to the standard atmosphere conditions (International Standard Atmosphere) at which the air density would be equal to the indicated air density at the place of observation, or, in other words, the height when measured in terms of the density of the air rather than the distance from the ground.
  • Density Altitude is the pressure altitude adjusted for non-standard temperature.
  • a useful rule of thumb is that the maximum absolute humidity doubles for every 20 °F or 10 °C increase in temperature.
  • the relative humidity will drop by a factor of 2 for each 20 °F or 10 °C increase in temperature, assuming conservation of absolute moisture.
  • air at 68 °F or 20 °C and 50% relative humidity will become saturated if cooled to 50 °F or 10 °C, its dew point, and 41 °F or 5 °C air at 80% relative humidity warmed to 68 °F or 20 °C will have a relative humidity of only 29% and feel dry.
  • thermal comfort standard ASHRAE 55 requires systems designed to control humidity to maintain a dew point of 16.8 °C (62.2 °F) though no lower humidity limit is established.
  • a device used to measure humidity is called a hygrometer; one used to regulate it is called a humidistat, or sometimes hygrostat. (These are analogous to a thermometer and thermostat for temperature, respectively.)
  • Relative humidity is the ratio of the partial pressure of water vapor to the equilibrium vapor pressure of water at a given temperature. Relative humidity depends on temperature and the pressure of the system of interest. It requires less water vapor to attain high relative humidity at low temperatures; more water vapor is required to attain high relative humidity in warm or hot air.
  • the relative humidity of an air-water mixture is defined as the ratio of the partial pressure of water vapor in the mixture to the equilibrium vapor pressure of water over a flat surface of pure water at a given temperature:
  • Relative humidity is normally expressed as a percentage; a higher percentage means that the air-water mixture is more humid.
  • Airliners operate with low internal relative humidity, often under 10%, especially on long flights. The low humidity is a consequence of drawing in the very cold air with a low absolute humidity, which is found at airliner cruising altitudes. Subsequent warming of this air lowers its relative humidity, increasing air density. Humidifiers are not employed to raise it to comfortable mid-range levels because the volume of water required to be carried on board can be a significant weight penalty. As airliners descend from colder altitudes into warmer air (perhaps even flying through clouds a few thousand feet above the ground), the ambient relative humidity can increase dramatically.
  • Pentazolate rings for fuel A carbon-free inorganic-metal complex
  • [Zn(H 2 0) 4 (N 5 )2] ⁇ 4H 2 0 can be synthesized by the ion metathesis of [Na(H 2 0)(N 5 )] ⁇ 2H 2 0 solution with ⁇ ( ⁇ 3 ) 2 6H 2 0.
  • the axial position is formed by two nitrogen atoms (Nl) from two pentazolate rings (cyclo-Ns ⁇ ) and the equatorial plane is formed by four oxygen atoms (01) from four coordinated water molecules.
  • Thermal control of [Zn(H 2 0) 4 (N5) 2 ] 4H 2 0 water stabilizes cyclo- N 5 ⁇ , dehydration does not cause immediate decomposition of the anion.
  • This invention teaches regulating the dehydration by thermal control of [Zn(H 2 0) 4 (N5) 2 ] 4H 2 0; water stabilizes cyclo-Ns ⁇ , so dehydration causes immediate decomposition of the anion, providing cyclo- N 5 ⁇ decomposed into N 3 ⁇ and N 2 gas at 107.9 °C (onset), which is an energetic material denser than air with moisture and a force to propel the aircraft in any direction crafted by design.
  • Above- mentioned piezoelectric wafer can morph the airducts aerodynamic properties and can open and close airducts.
  • Piezoelectric wafer can also ultrasonically decompose [Zn(H 2 0) 4 (N5) 2 ] 4H 2 0 into energy within any airduct, in any direction of airflow for optimizing the forces of lift and propulsion to move the aircraft through air up or down through the atmosphere.
  • This invention teaches piezoelectric wafers conFIGd with some magnetic fields pulsing provide an electric energy to spark [Zn(H 2 0)4(N5) 2 ] 4H 2 0 into decomposition, releasing energy.
  • Other standard fuels can be included as heat sources, which also can be managed by piezoelectric wafers.
  • FIG 65 illustrates a hexagonal fuselage provided with helix ducting provided in FIG 21.
  • Hexagonal fuselage components can update existing aircraft that are round cylindrical shapes.
  • Hexagonal fuselage can also be a flying tube in the helix direct illustrated without a standard fuselage but propelled and controlled by the FIG 21 helix airducts molded (or 3D printed) into the curved Hexagons that are offset from the CenterPoint to one of the six hexagon points, piezoelectric wafers morphing airfoils, and the application of rotor blade elements on the inside diameter of the tube for Tip-Path propulsion, if desired.
  • This invention teaches that aircraft surfaces can be coated with superhydrophobic surfaces that provide the Cassie-Baxter state when water droplets become very mobile and quickly slides off the aircraft surface by repelling water.
  • the mobility of the water droplets on the aircraft surfaces has another effect by water zooming around the surface of the aircraft rather than sticking, the droplets of water collect small particles of dust, hoovering them up.
  • This cleaning mechanism of these superhydrophobic surfaces is called the lotus effect, which is an option to control the humidity of high speed air more accurately through the helices pathway to direct higher or lower density air through the proper airducts.
  • Superhydrophobic surfaces have been synthesized and studied in labs for decades, but it is only recently that commercial versions have been produced. Now there are quite a few coming on to the market (e.g. neverwet.com), and they are impressive - when water is poured on to these surfaces it behaves like mercury and bounces off providing the ability to control humidity for lift or the direction of travel desired.
  • a simple helix paint pattern of stripes from top to bottom of an aerodynamic surface improves lift, including adhesive shaped materials applied to a surface for more efficient aerodynamic control.
  • Hot air balloons, dirigibles, and other drones can be improved by managing elements described in this invention.
  • Reverse rotation of airflow can remove water, increasing the density of air, which can be added to manage water, removing water for increasing density of air below the aircraft, while increasing density of air by adding the water to the airstream up on top of the aircraft to reduce air density.
  • Managing water is taught in this invention by reverse rotating the water for its separation from air as it flows around the aircraft.
  • Rotational relative wind flows opposite the physical flightpath of the airfoil, striking the blade at 90° to the leading edge and parallel to the plane of rotation; and it is constantly changing in direction during rotation. Rotational relative wind velocity is highest at blade tips, decreasing uniformly to zero at the axis of rotation (center of the mast).
  • Hub— on the mast is the center point and attaching point for the root of the blade.
  • Tip the farthest outboard section of the rotor blade.
  • Root the inner end of the blade and is the point that attaches to the hub.
  • Twist the change in blade incidence from the root to the outer blade
  • the angular position of the main rotor blades is measured from the helicopter's longitudinal axis, which is usually the nose position and the blade.
  • the radial position of a segment of the blade is the distance from the hub as a fraction of the total distance
  • Coriolis Effect (Law of Conservation of Angular Momentum)
  • the Coriolis Effect is also referred to as the law of conservation of angular momentum. It states that the value of angular momentum of a rotating body does not change unless an external force is applied. In other words, a rotating body continues to rotate with the same rotational velocity until some external force is applied to change the speed of rotation.
  • Angular momentum is the moment of inertia (mass times distance from the center of rotation squared) multiplied by the speed of rotation.
  • angular acceleration and deceleration Changes in angular velocity, known as angular acceleration and deceleration, take place as the mass of a rotating body is moved closer to or farther away from the axis of rotation.
  • the speed of the rotating mass varies proportionately with the square of the radius.
  • the rotor blade rotating about the rotor hub possesses angular momentum. As the rotor begins to cone due to G-loading maneuvers, the diameter or the rotor disk shrinks. Due to conservation of angular momentum, the blades continue to travel the same speed even though the blade tips have a shorter distance to travel due to reduced disk diameter. The action results in an increase in rotor rpm which causes a slight increase in lift. Most pilots arrest this increase of rpm with an increase in collective pitch. This increase in blade rpm lift is somewhat negated by the slightly smaller disk area as the blades cone upward.
  • Gyroscopic Precession The spinning main rotor of a helicopter acts like a gyroscope.
  • Water propulsion can apply this invention's airfoil technologies underwater in the marine industry, because air and water are fluid.
  • This invention teaches how to improve propulsion in fluid; water or air.
  • FIG 29A illustrates an end view of FIG 29B which is a propulsion ball 431 in the airduct 432 on the surface of an aircraft or migrating to the surface of an engineering mobility system.
  • FIG 29B illustrates a perspective view of FIG 29A for viewing the propulsion ball
  • Propulsion balls can be made of a soft material with aerodynamic bladed shapes, including electric circuits that can move the propulsion ball back to the firing propulsion tube 434 to fire down the axis 435 into open air duct 432 again.
  • Propulsion balls can be electric capacitors, act like motors, contain chemicals to clean and air flow, and travel in FIG 21 through 27 helix pathways 147 and 148.
  • FIG 59 illustrates how two balls starting out on the top of the cycloid curves illustrated, reach the bottom center of the curve at the same time, even though the balls started at different distances from the midpoint of the cycloid curve, which this invention applies in FIG 28 and 29 airducts when it provides optimization on wings fuselages or internally to return the propulsion ball to the firing tube.
  • Firing tube can be electrically wired to propel the ball or explosive fuels, steam, and any force projecting source, like a just compressed air pulse.
  • Roller chain and sprocket Chain drive is a way of transmitting mechanical power from one place to another. It is often used to convey power to the wheels of a vehicle, particularly bicycles and motorcycles. It is also used in a wide variety of machines besides vehicles.
  • Roller chain and sprocket Chain drive is a way of transmitting mechanical power from one place to another, which a triangular addition provides a reciprocating motion translational function to compress and expand piston cylinder assembly, stretch and compress piezoelectric material to drive the chain assembly, or energy that moves the chain assembly, can generate electricity.
  • the power is conveyed by a roller chain, known as the drive chain or transmission chain, passing over a sprocket gear, with the teeth of the gear meshing with the holes in the links of the chain.
  • the gear is turned, and this pulls the chain putting mechanical force into the system.
  • Another type of drive chain is the Morse chain, invented by the Morse Chain Company of Ithaca, New York, United States. This has inverted teeth.
  • gear ratio can be altered. For example, when the bicycle pedals' gear rotates once, it causes the gear that drives the wheels to rotate more than one revolution.
  • Roller chain and sprockets is a very efficient method of power transmission compared to (friction-drive) belts, with far less frictional loss.
  • Drive chains are most often made of metal, while belts are often rubber, plastic, urethane, or other substances.
  • this invention teaches chain link belts with composite system integration into belt material or with fasteners embedder in the belt can serve the same function as this chain roller triangular system.
  • Sprocket links and sprockets can be made into any size or width.
  • sprocket 301 could have structures on the surface along the lines illustrated (including full 360-degrees) on the sprocket to project mechanical contact with sprocket systems: electrical probe connections, a mechanical leverage against a chain-link system, like engines of piezoelectric wafers, motors, generators, and the sprocket could be a turbo fan, or turbo blade, fan or water propeller.
  • a second function can be placed on the sprocket, like helicopter blades within the sprocket. Systems would be extending perpendicular to the sprocket's surfaces, and possibly adding the mechanical motion of devices on the chain links.
  • This invention teaches mounting functions in the direction of the rotation axis on the face of the sprocket, extending into the chain- links, and there is no limit to the radial distance from the center point that a system can be added, only limited by stress and durability.
  • Drive belts can slip unless they have teeth, which means that the output side may not rotate at a precise speed, and some work gets lost to the friction of the belt as it bends around the pulleys. Wear on rubber or plastic belts and their teeth is often easier to observe, and chains wear out faster than belts if not properly lubricated.
  • roller chains One problem with roller chains is the variation in speed, or surging, caused by the acceleration and deceleration of the chain as it goes around the sprocket link by link. It starts as soon as the pitch line of the chain contacts the first tooth of the sprocket. This contact occurs at a point below the pitch circle of the sprocket. As the sprocket rotates, the chain is raised up to the pitch circle and is then dropped down again as sprocket rotation continues. Because of the fixed pitch length, the pitch line of the link cuts across the chord between two pitch points on the sprocket, remaining in this position relative to the sprocket until the link exits the sprocket. This rising and falling of the pitch line is what causes chordal effect or speed variation.
  • Chains are often narrower than belts, and this can make it easier to shift them to larger or smaller gears in order to vary the gear ratio. Multi-speed bicycles with derailleurs make use of this. Also, the more positive meshing of a chain can make it easier to build gears that can increase or shrink in diameter, again altering the gear ratio. However, some newer synchronous belts claim to have "equivalent capacity to roller chain drives in the same width".
  • Drive shafts are another common method used to move mechanical power around that is sometimes evaluated in comparison to chain drive; in particular belt drive vs chain drive vs shaft drive is a key design decision for most motorcycles.
  • Drive shafts tend to be tougher and more reliable than chain drive, but the bevel gears have far more friction than a chain. For this reason, virtually, all high-performance motorcycles use chain drive, with shaft-driven arrangements generally used for non-sporting machines. Toothed-belt drives are used for some (non-sporting) models.
  • Timing chain In engines: Internal combustion engines often use a timing chain to drive the camshaft(s). This is an area in which chain drives frequently compete directly with timing belt drive systems, particularly when the engine has one or more overhead camshafts, and provides an excellent example of some of the differences and similarities between the two approaches. For this application, chains last longer, but are often harder to replace, as they must be enclosed in a space into which lubricating oil can be introduced. Being heavier, the chain robs more power, [dubious - discuss] but is also less likely to fail.
  • the camshaft of a four-stroke engine rotates at half crankshaft speed, so the camshaft sprocket has twice as many teeth as the crankshaft sprocket. Less common alternatives to timing chain drives include spur gears or bevel gears combined with a shaft.
  • FIG 30 illustrates an aircraft wing aerodynamic, provided with a chain roller 410 and sprocket (not shown) to move the wing surface 411 around the aircraft wing, which may be used to position the aircraft on a terrestrial surface too.
  • the surface material has a cable (metal, polymer, composite, or nanosized graphene cables) threaded through the surface of 410 sandwiched between the chain roller links 410.
  • FIG 57 illustrates a ball joint 420 that has the freedom to rotate around its axis 360- degrees in ball joint socket 421, which differentiates it from a prior art chain link, and a 25-degree angle is possible in this view providing the ability to curve around a chain roller sprocket designed to receive the ball shape.
  • Surface 425 between two ball joint links 420 limit the angle in this view however other joint can replace this example to twist sprockets at any angle to optimize an application.
  • This link can also be made triangular, but without limits of rotation in socket 421, again 360-degrees.
  • FIG 31 illustrates an isometric view of a circle-arc stator roller chain type assembly 70 (chain links stator 70), comprised of bolt fastener 71 inserted through the pin (tube) 80, which provides the assembly of outer plate 75, roller bearing bushing tube 78, roller bearing tube 79, inner plate fastener 76, and outer plate fastener 75 to complete roller chain 70 assembly.
  • View 70b is provided to illustrate stacking chain link 70 on top of one another to provide a helix when rotating around line 77 to align with the circumference of a circle specified. These helix 70b can be left or right-handed helix.
  • Pin tube 80 is pressure fit into hole 81 of outer plate fastener 75. Ends of bushing tube 78 outside diameter fits within the pressure fit hole 82 of inner plate fastener 76. Outside diameter of pressure fit fastener pin 80 fits inside diameter 83 of roller bearing bushing tube 78. Roller bearing tube 79 inside diameter 84 assembles over roller bearing bushing tube 78 to provide a roller bearing clamped between plates 75 and 76. 3D Printing surfaces can be specified on any or all the components: plate 75 and 76, bearing bushing 78, and roller bearing 79. Any additional components can be added to the roller chain link stator 70 to adapt any electronic components designed as a motor or generator. A high-speed motor can be substituted for roller bearing 79.
  • FIG 33 illustrates roller chain motor stator 70 fastened along the circumference of circle 84 in a circle-arc of about 90-degrees of rotation requiring four motor poles arrayed as radius lengths from center at 90-degrees.
  • Rotation of the circle-arc stator roller chain type assembly 70 in FIG 33 links around the centerline 77 of bolt 71 (screw, bolt, or dowel can be applied), which provides any length and curve of a circle-arc by adding or subtracting the number of circle-arc stator roller chain links 70 to optimize and adapt manufacturing the stator into structures, like automotive, aerospace, and generators.
  • FIG 31 Exploded view in FIG 31 of all components assembled along axis centerline 77 illustrates all components fastened around center axis of bolt 71 comprised of plain unthreaded shank (called the grip length) to make a strong dowel 73 to fasten a circle-arc stator to any structure designed to match the specifications.
  • Bolt 71 is a form of threaded fastener, external male thread 74.
  • Hexagonal head 72 (any other type head) of bolt 71 is turned with a spanner or wrench to fasten roller chain circle-arc motor stators any curves and length can be provided.
  • FIG 14 also illustrates a linear straight assembly that can be the wired rotating pole of the motor.
  • the wire windings of the motor can be assembled on any of the components of chain link stator 70, including winding around the roller bearing tube 70, or replacing the roller bearing with a winding, permanent magnet, or other elements.
  • a motor circle- Arc stator can be slightly longer than the circle-arc in order to phase in the electromagnetic field between the independent poles.
  • This chain link stator can be rotated around more than one pole rotating rotor, like a bicycle spoke chain in sprockets.
  • the chain link electric motor stator can also phase from straight linear motors to any curve of a motor (generator) or drive, providing mechanical links, but also providing the electric motor function in motion in almost any configuration (e.g. a bicycle chain that also is an electric motor relative to the sprocket acting as motor poles, stator and poles of the electric chain sprocket motor would be in motion).
  • Chain roller drive materials in pins 80, bushings 78, and rollers 79 are electrically insulated materials, sandwiched between the electrically conductive plates 75 and 76 (FIG 36 and FIG 42 plate 375, and FIG 48 plate 376) to provide plate- circuits in stationary stators or rotating sprockets.
  • All the small chain link plates 75 and 76 can be assembled into roller chains with all the electrically insulating pins 80, bushings 78, and rollers 79, sandwiched between the plates 75 and 76, providing two Plate-Circuits in electrically independent contact with two sprockets faces illustrated in FIGS 34 through 53.
  • FIGS 34 through 53 two optional Plate- Circuits electrically contact sprockets 301 and 302 that have one side of sprocket face electrically conductive and the opposite surface electrically insulating to provide electrical connections for all the electrically conductive chain-link plate-circuits traveling on one side of each sprocket, so one sprocket would be the positive electric charge and the other sprocket the negative charge (electric source or ground).
  • each face of one sprocket could be electrically conductive with a layer of insulating material between to complete an electric circuit along independent plate circuits traveling in contact with each sprocket face.
  • Sprockets could five layers: conductive, insulating, conductive, insulating and conductive, so that the two outer surfaces are circuits with an independent circuit in the middle that only connects to pins, bushings, and rollers sandwiched between the conductive plates.
  • Each individual sprocket can be a circuit, so each chain link is an independently connected circuit component.
  • FIGS 34 and 35 illustrates a perspective view of a roller chain triangular-chain links
  • a triangular modification to link 303 in FIG 36 provides an additional motion translational geometry to reciprocate rods 321 and 322 of a piston 323 and cylinder 324 in FIGS 37 through 40, a motion translational function, to compress and expand piston cylinder assembly, stretch and compress piezoelectric material in FIGS 54 and 55 to drive the chain assembly or the forces from energy, like wind or water that moves the chain assembly can generate electricity by stretching and compressing materials like piezoelectric material.
  • FIG 36 illustrates a perspective view of an expanded triangular-chain link assembly 303 to configure pistons and cylinders 321, 322, 323, and 324 provided in assembly 320 (replacing a roller bearing tube 79, piezoelectric material insertion, and other energy conversion systems, like Stirling engines, expanded to a 1.41 -centimeter distance between the two rocker arms in FIG 37.
  • Triangular chain link assembly 303 is and expanded view along three axis lines 377 comprised of the pin (tube) 80, which provides the assembly of outer plate 375 (replacing plate 75 in FIG 31), roller bearing bushing tube 78, roller bearing tube 79, inner plate fastener 76 (in FIG 37), and outer plate fastener 375 to complete roller chain 303 assembled around in FIGS 34 and 43 spaced and linked by 311, 312, 313, and 314 in corresponding FIGS 37, 38, 39, and 40.
  • a piston is a component of reciprocating engines, reciprocating pumps, gas compressors and pneumatic cylinders, among other similar mechanisms. It is the moving component that is contained by a cylinder and is made gas-tight by piston rings.
  • the piston In an engine, its purpose is to transfer force from expanding gas in the cylinder to the crankshaft via a piston rod and/or connecting rod. In a pump, the function is reversed, and force is transferred from the crankshaft to the piston for compressing or ejecting the fluid in the cylinder. In some engines, the piston also acts as a valve by covering and uncovering ports in the cylinder. Large slow-speed Diesel engines may require additional support for the side forces on the piston. These engines typically use crosshead pistons.
  • the main piston has a large piston rod extending downwards from the piston to what is effectively a second smaller- diameter piston.
  • the main piston is responsible for gas sealing and carries the piston rings.
  • the smaller piston is purely a mechanical guide.
  • a connecting rod is a shaft which connects a piston to a crank or crankshaft in a reciprocating engine. Together with the crank, it forms a simple mechanism that converts reciprocating motion into rotating motion.
  • a connecting rod may also convert rotating motion into reciprocating motion, its original use. Earlier mechanisms, such as the chain, could only impart pulling motion. Being rigid, a connecting rod may transmit either push or pull, allowing the rod to rotate the crank through both halves of a revolution. In a few two-stroke engines the connecting rod is only required to push.
  • the connecting rod is best known through its use in internal combustion piston engines, such as automobile engines. These are of a distinctly different design from earlier forms of connecting rod used in steam engines and steam locomotives.
  • Radial engines typically have a master rod for one cylinder and multiple slave rods for all the other cylinders in the same bank.
  • Fork and blade rods The usual solution for high-performance aero-engines is a "forked" connecting rod. One rod is split in two at the big end and the other is thinned to fit into this fork.
  • a Stirling engine is a heat engine that operates by cyclic compression and expansion of air or other gas (the working fluid) at different temperatures, such that there is a net conversion of heat energy to mechanical work. More specifically, the Stirling engine is a closed-cycle regenerative heat engine with a permanently gaseous working fluid. Closed-cycle, in this context, means a thermodynamic system in which the working fluid is permanently contained within the system, and regenerative describes the use of a specific type of internal heat exchanger and thermal store, known as the regenerator. Strictly speaking, the inclusion of the regenerator is what differentiates a Stirling engine from other closed cycle hot air engines. Stirling engines have a high efficiency compared to internal combustion engines, being able to reach 50% efficiency.
  • the heat energy source is generated external to the Stirling engine rather than by internal combustion as with the Otto cycle or Diesel cycle engines. Because the Stirling engine is compatible with alternative and renewable energy sources it could become increasingly significant as the price of conventional fuels rises, and also in light of concerns such as depletion of oil supplies and climate change.
  • This type of engine is currently generating interest as the core component of micro combined heat and power (CHP) units, in which it is more efficient and safer than a comparable steam engine. However, it has a low power-to-weight ratio, rendering it more suitable for use in static installations where space and weight are not at a premium.
  • CHP micro combined heat and power
  • the Stirling engine is traditionally classified as an external combustion engine, as all heat transfers to and from the working fluid take place through a solid boundary (heat exchanger) thus isolating the combustion process and any contaminants it may produce from the working parts of the engine.
  • heat exchanger heat exchanger
  • heat input is by combustion of a fuel within the body of the working fluid.
  • Most of the many possible implementations of the Stirling engine fall into the category of reciprocating piston engine.
  • the heat driving a Stirling engine must be transmitted from a heat source to the working fluid by heat exchangers and finally to a heat sink.
  • a Stirling engine system has at least one heat source, one heat sink and heat exchangers. Some types may combine or dispense with some of these.
  • the heat source may be provided by the combustion of a fuel and, since the combustion products do not mix with the working fluid and hence do not come into contact with the internal parts of the engine, a Stirling engine can run on fuels that would damage other engines types' internals, such as landfill gas, which may contain siloxane that could deposit abrasive silicon dioxide in conventional engines.
  • the heat sink is typically the environment the engine operates in, at ambient temperature.
  • a radiator is required to transfer the heat from the engine to the ambient air.
  • Marine engines have the advantage of using cool ambient sea, lake, or river water, which is typically cooler than ambient air.
  • the engine's cooling water is used directly or indirectly for heating purposes, raising efficiency.
  • heat may be supplied at ambient temperature and the heat sink maintained at a lower temperature by such means as cryogenic fluid (see Liquid nitrogen economy) or iced water.
  • the displacer is a special-purpose piston, used in Beta and Gamma type Stirling engines, to move the working gas back and forth between the hot and cold heat exchangers.
  • the displacer may or may not be sealed to the cylinder, i.e. it may be a loose fit within the cylinder, allowing the working gas to pass around it as it moves to occupy the part of the cylinder beyond.
  • the alpha configuration has two power pistons, one in a hot cylinder, one in a cold cylinder, and the gas is driven between the two by the pistons; it is typically in a V-formation with the pistons joined at the same point on a crankshaft.
  • the beta configuration has a single cylinder with a hot end and a cold end, containing a power piston and a 'displacer' that drives the gas between the hot and cold ends. It is typically used with a rhombic drive to achieve the phase difference between the displacer and power pistons, but they can be joined 90 degrees out of phase on a crankshaft.
  • the gamma configuration has two cylinders: one containing a displacer, with a hot and a cold end, and one for the power piston; they are joined to form a single space with the same pressure in both cylinders; the pistons are typically in parallel and joined 90 degrees out of phase on a crankshaft.
  • FIG 37 illustrates a perspective view of rod assembly 320 in FIG 36 connected to triangular-chain link 303 with rods expanded to a maximum 1.41 -centimeter distance between the two rods 321 and 322 (rocker arms), which is position 311 in FIGS 34 and 35.
  • FIG 38 illustrates a perspective view of rod assembly 320 in FIG 36 connected to triangular-chain link 303 with rods expanded to a maximum 0.00-centimeter distance between the two rods 321 and 322 (rocker arms), which is position 312 in FIGS 34 and 35.
  • FIG 39 illustrates a perspective view of rod assembly 320 in FIG 36 connected to triangular-chain link 303 with rods expanded to a 0.39-centimeter distance between the two rods 321 and 322 (rocker arms), which is position 313 in FIGS 34 and 35.
  • FIG 40 illustrates a perspective view of rod assembly 320 in FIG 36 connected to triangular-chain link 303 with rods reduced to a 1.06-centimeter distance between the two rods 321 and 322 (rocker arms), which is position 314 in FIGS 34 and 35.
  • FIG 34 illustrates a side view of a roller chain and sprocket chain drive in FIG 35, providing a more precise view of the 180-degree angles around the sprockets 301 and 302, which moves the spacing between triangular tip of 303 with rods 321 and 322 attached.
  • the triangular-chain link 303 in FIGS 34 and 35 is observed in position 313, a spacing of 0.39- centimeters is measured, because as link 303 transitions around circular sprocket 301, aligning one pin on the start of 180-degree line, the angle starts to widen between any two of links 303.
  • position of 314 provides a reduced distance of 1.06-centimeters as the triangular-chain link passed the 180-degree of travel around sprocket 301.
  • position 312 is minimum distant spacing is measured on 312 in FIG 34 and 35 after passing by 180-degrees, then position of 312 provides a reduced distance of 0.00-centimeters as the triangular-chain link passed the 180-degree of travel around sprocket 301.
  • the measurement of 25 -centimeters and the radial distance and thickness of the sprockets 301 and 302 are all related to the triangular-chain link 303 and 304 configuration: angles of separation, size of the rods or pistons, length of the chain for cooling or heating energy elements, matching the size of an application (railroad engine versus micro-robot), and integration into engineering mobility (automotive, aerospace, oceanography, mining,..).
  • FIG 51 illustrates a perspective view of a roller chain 444 and sprocket 301 and 302 chain drive in FIG 35 with triangular-chain link assembly 303 in FIG 36 stacked three high (wide) with four plates 375 stacked too in the axial direction of rotation.
  • FIG 52 illustrates a perspective close-up view of a roller chain 444 and sprocket 302 chain drive in FIG 51 stacked three high (wide) in the axial direction of rotation.
  • Three separate reciprocating elements 321 and 322 can be removed or added from the multi-wide chain, including providing any function: one could compress air, one could be a closed Stirling piston cylinder, one could be a piezoelectric material, or other mechanical or electric function like reciprocating a permanent magnet within a coil to generate electricity. Pumping fluids or any valving system can be provided.
  • FIG 53 illustrates a hinged motion for compressing and stretching piezoelectric or reciprocating components at and radial distance that material strength will tolerate.
  • FIG 41 illustrates an actual piston within a cutaway view of the cylinder filled with air or other fluids, including the piezoelectric materials in FIGS 54 and 55, which require fixturing that stretches and compresses the piezoelectric material.
  • This inventing teaches nanocarbon fibers, sheeting, and/or woven materials can be inserted within the piston and cylinder to transfer heat to gas or fluid, and the materials performing function: heating and cooling Stirling Engine (heat engines) working gas (fluids) and any other fluid cycling desired relative to temperature controls and fluid phasing.
  • Nanomaterials can be floating freely, fixed to an object for heat exchange, but loose within the chamber at the other ends.
  • FIG 42 illustrates a roller chain triangular-link with an axle inserted at a distance that will fit the double sprocket in FIG 43.
  • FIG 42 illustrates a side view of a roller chain and sprocket chain drive in FIG 34, 35, 50, 51, 52, and 53.
  • FIG 42 illustrates a roller chain triangular-link 370 with an axle inserted at a distance that will fit the double sprocket 301 and 301 spaced along their axis of rotation in FIG 43.
  • FIG 52 illustrates a roller chain triangular-link 370 with an axle inserted at a distance that will fit the double sprocket in FIG 43, which provides more expansion and compression cycles on a chain length with less time expanded and more time compressed.
  • FIG 43 illustrates a roller chain triangular-link 370 with an axle 331 inserted at a distance that will fit the double sprocket 301 and 302 in FIGS 43, 46 and 47.
  • FIG 47 illustrates a perspective view of FIG 46 to observe the double sprocket assembly 301 and 302 and triangular-link connection 370, which provides a double sided triangular-link for bending the chain in reverse to increase the compression and expansion angles for a given geometry and sizes.
  • the expansion of rods in FIG 37 are limited to 1.41 -centimeters with current triangle distance, but by curving the chain roller pathway 330 around the pair of sprockets 301 and 302 the expansion distance is increased to 2.82-centimeters.
  • FIG 54 illustrates a perspective view of a roller chain and sprocket chain drive LF K 370 and 376 as a way of transmitting mechanical power from one place to another, which a triangular modification triangular-chain link 370 provides an additional motion translational geometry to reciprocate rods, a motion translational function, and a modification of the second link 376, 335, and 336 in a triangular-chain link 376 from the "side" of the roller chain along the X axis, which provides a rotation function viewed in FIGS 55 and 56 when transitioning from straight chain pathways on 330 to 330 curving around the sprockets and back to straight pathways on 330.
  • a triangular modification triangular-chain link 370 provides an additional motion translational geometry to reciprocate rods, a motion translational function, and a modification of the second link 376, 335, and 336 in a triangular-chain link 376 from the "side" of the roller chain along the X axis, which provides
  • FIGS 57 illustrates a piezoelectric high displacement cylinder actuator and 58 illustrates an end and side view of an all-ceramic bending circular disk actuator 250 with high displacement too by fastener central hole 251, location viewed from top and side.
  • This high displacement cylinder or disk can be installed between connecting rods 321 and 322 in FIGS 43, 44, 45, and 46 to generate power when forces bend and then expand the piezoelectric materials, or electricity applied to the piezoelectric material can expand and contract rods 321 and 322 as they curve around sprocket 301 or 302 as illustrated in position 313, 311, 314, and then 312 providing forces for torque in the tip-path of sprockets 301 and 302 in the most efficient manner possible, at the greatest distance from the center of rotation.
  • Each period of expansion and contraction of piezoelectric elements has almost 180-degrees of open position then -almost the same time period in the closed compressed position along the straight length of 25-centimeters.
  • the 180-degrees of sprocket contact with the chain links and the straight chain drive links are each 25-centimeters, equal number of chain-links at equal distances, which in these FIGS is five sets of triangular-chain links 370.
  • One link 370 expands about 180-degrees around sprockets 301 and 302 for 25-centimeters, and then compresses twice along the 25-centimeters of straight chain drive illustrated.
  • No other prior art provides such a long-time period to heat, cool, clean, or stabilize components after a moment of energy exchange during relative motion of a reciprocating pair of connecting rods in motion.
  • Automotive, bicycle, or other motion translational devices can provide equally spaces electric components inside or outside a tire, wheel rim, or axil to adapt this arc-power strip to an application.
  • An innertube could be a wired arc-power component to upgrade a car and bike tire, or the tire can be made into an arc-power strip with corresponding components on the frame of the engineered motion machine.
  • FIG 57 illustrates a cycloid curve that is a specific form of trochoid, with the cusps 86 and 87 pointing upward relative to gravity.
  • Cycloid is the curve of fastest descent under constant gravity Time-period Tl to T2 of an object A and B, placed at different locations, in descent on the cycloid curve, does not depend on the object's starting position A or B, because they both arrive at location C at the same Time T2 starting at the same Time Tl .
  • Cycloid curves physically or electrodynamically is the most optimized way to superposition elements of spacetime, or this invention teaches in FIGS 58, 59, and 60, because mechanical force at any angle or location minimized the gravitational force providing the benefit of cycloid gravitational function between moving force vectors in any direction, including electrodynamic cycloid "field" almost independent of gravity, and can be orientated irrelevant to spacetime so quantum mass acquisition forms at the midpoint 88 of the cycloid curve under physical forces and electrical forces of any kind, specifically ultrasonic piezoelectric forces can provide the midpoint for motion control between a series of electrodynamic cycloid fields positioned to move objects toward or AWAY from the cycloid curve's midpoint.
  • FIGS 58 through 60 illustrate a cycloid sprocket.
  • the chain length must match the distance between crank sprocket 40 and rear hub 60 and the sizes of the front chain ring 46 and rear sprocket 63.
  • These bikes usually have some mechanism for small adjustments such as horizontal dropouts, track ends, or an eccentric mechanism in the rear hub or the bottom bracket. In extreme cases, a chain half-link may be necessary.
  • FIGS 59 and 60 illustrate a cycloid sprocket.
  • Sprocket 40 is a 26 tooth sprocket along cycloid curve 46.
  • Sprocket 60 is a 12 tooth sprocket along circle circumference 63.
  • Sprockets can be designed in any diameter, chain length, and number of sprockets.
  • Belts can have teeth, functioning like sprockets, and belts made with spaced permanent magnets along the belt would equal a sprocket when the sprocket is driven by the magnets.
  • Spiral around cylinders can be divided up and on curved surfaces, like circles parallel arc-power strips can be configured along the axis length, yet the arc-power strip would change in radial distance and still be aligned and in length to continue a 360-degree force.
  • Cycloid curve circumference line 46 is related to the pitch diameter in a circle, but this invention teaches a cycloid curve mirrored around line 58 into a sprocket 40 has more leverage, providing force multiplied by the moment arm half of line 58 leveraging around center point 45.
  • FIG 59 illustrates cycloid assembly 50, cycloid sprocket 40, and circular sprocket 60 are chained together, like a bicycle roller sprocket.
  • a cycloid curve is provided by rotating a circle 59 illustrated in five positions, 51,
  • Point 57 on the circumference of circle 59 is marked on 51, 52, 53, 54, and 55 to illustrate the cycloid path-line drawn, cycloid curve 46, which is mirrored around line 58 to provide the sprocket 40 cycloid geometric dimensions.
  • a center hole 48 and two holes 49 are cut out to mount the sprocket 40 onto a bike or machine, like a piston engine or compressor.
  • the cycloid sprocket can be mounted to keep the piston compressed for a longer period of time during combustion, providing more efficient combustion and less pollution by completely burning the fuel air mixture under high pressure for longer time. Air intake piston positions, at bottom of their cycle, will also have a longer period of time for air intake, increasing air, increases efficiency of an engine. Cycloid sprocket 40 can be positioned on machines, like piston engines, to obtain the desired efficiency.
  • circular sprocket 60 can be mounted inside cycloid sprocket 40 rotating within sprockets 40 surrounded by an outer housing structure, so the inner circle 53 can rotate all the way around cycloid curve 46 and 64.
  • Center line 58 can provide the reference points to separate the two halves 46 and 64 enough to fit circle 53 around each end if line 58.
  • Circle 50 with sprockets or just smooth roller bearing outer diameter can be attached to any mechanical motion device, like floats under a boat or floating docks to provide a synchronized motion between several identical cycloid assembles with inner roller 50 whenever the circle 50 is rolled against the inner surfaces of cycloid curve 46 or 64 when the reference line 58 is floating horizontally on water fluids.
  • Cycloid curve 46 coordinate point positioning is illustrated in FIG 59 as circle 59 is rotated along line 58, which is equal to the circles circumference length:
  • point 57 on the circle 59, in position 52 provides the second cycloid curve 46 coordinate point.
  • point 57 on the circle 59, in position 54 provides the forth cycloid curve coordinate point.
  • point 57 on the circle 59, in position 55 provides the fifth, last cycloid curve 46 coordinate point.
  • cycloid curve 46 is drawn from one point 57 on the circle 59.
  • a turbofan, turboprop, and propellers can be cycled on both sides of line 58 to power an air or water craft.
  • the motion on one side of line 58 can be covered protecting the motion from power generation resistant forces, while the opposite side of line 58 provides the energy capture phase of the cycle, where forces of wind or water move the objects for power generation.
  • Circle 59 would cycle around both ends of line 58 to continuously cycle over time.
  • Circle 59 would be linked to line 58, providing the full surface of the circle as a wind capture device with the torque generation from the tip-path of circle 59 power motion translational device.
  • a floating ball with a frictional extended surface (water paddles) that is captured under the near-water surface can be blown across the water, rotating at twice the torque, over the full diameter of the ball, generating electricity at more capacity than just a wind power blade above the water, on the ocean for example.
  • a ball with water capture paddles could travel inside a floating tube, covering the ball from the wind forces and water interference (or the ball could be rotated onto a non-paddle friction side of the ball, floating like a boat or completely lifted off the water), on one side of line 58, providing the opposite side of line 58 with maximum wind water capture forces to generate power when floating with surface paddle resistance.
  • One of the endpoints of line 58 could be “fixed” (anchored relative to forces), providing rotation in alignment with the maximum wind or water currents.
  • Electric energy capture can be provided by arc-power strips composed of permanent magnets, electric winding, coils, or any electric power capture technology, even conventional full circle generators.
  • FIG 60 illustrates cycloid sprocket 40, a description NOT related to rotating sprocket
  • FIG 58 illustrates that the cycloid curve 46 area is divided along the center point 45 by dividing line 44, providing the same symmetrical equal area above and below the line 44 no matter what the rotation angle.
  • the belt or chain length mounted around the cycloid sprocket 40 and circular sprocket 60 will not change, because the cycloid area does not change in FIG 58 as the cycloid is rotated around a center point 45.
  • FIGURE 20 illustrates a helix assembly 200 with a helical circuit fastener line 112 to electrically connect the two edges 112 and 113 of surface 99 wrapped around a three-dimensional cylinder 110 with top end 115 and bottom end 114.
  • Surface 99 has a clearance distance 116
  • a flexible video display 99 in the configuration of surface 99 provides complete flexible-display 99 covering cylinder 110, which provides the helix 100, central axis 101, helix 111, arrows 103, and starting point 102 in FIG 19 specification and geometry, where helix 111 and its arrows are also illustrated in FIG 20 as a centerline in flexible-display 99 with outer edges 112 and bottom edge 113.
  • Helix 111, in FIG 20, is wrapped three full turns around axis 101 :
  • Circuit line 112 is a circuit that senses the location of flexible-display 99, providing data to control what is displayed: one image of a "t" in FIGURE 20 can be displayed across the top edges 112 and bottom edges of flexible display 99, or can provided separated display data of any image.
  • Human anatomy is not uniform like the cylinder 110 and human muscle compression and contraction movement will compress and stretch the flexible display requiring motion joints (fasteners that provide flexible- display movement relative to edges 112 and 113 and measure flexible-display 99 motion) that provide data to the flexible-display circuit, so measurements of the display location relative to edges 112 and 113 is required to provide one image across line 112 over the full length of the helix flexible-display 99.
  • motion joints fasteners that provide flexible- display movement relative to edges 112 and 113 and measure flexible-display 99 motion
  • FIGURES in FIG 61 illustrates two options to fasten the edges 93 of surface curved snap fastener 92 edges 93 together around different shapes, like cylinders, cones, circles, and flat surfaces. Further, this invention teaches that the fasteners of edges 93 and 94 of surface 92 can be any shape that will securely fasten the edges together. In addition, this invention teaches that the fastener elements provide an electric circuit when fastened together. Examples given: A cylinder 91 can be pressed into a flexible fastener 92.
  • This invention teaches bendable, reliable, and curving video display screens
  • Flexible-displays have been disclosed by companies like Sony, Samsung, Sharp, and LG, but adapting flexible-displays to wrap around humans, robots, and aerospace drone machinery in motion is not provided.
  • Helix 99 in FIG 61 is a flexible-display 99.
  • potentiometers are illustrated, which is just a resistor with a sliding contact that can act as a voltage divider or a variable resistor.
  • a resistor's 90a resistance usually depends directly on its length 96 in FIG 61 or diameter of 120 in FIG 62. Longer the length 96 intercepted within the potentiometer 90a, larger the resistance.
  • a sliding contact called Wiper 92 slides over the resistor rod 91 and varies its resistance in a circuit according to the positioning distance 96 at which it touches the resistor 91. Any sensor can be applied to collect location data for software programs and circuits.
  • FIG 62 two identical flexible-displays 124 and 125 (sections of helix flexible- display 99 in FIG 20) are assembled around a rotating circular potentiometer with a common center 120 and two points 121 and 122 to vary the resistance of the potentiometer relative to the motion around point 120.
  • Both flexible-displays 124 and 125 in view 120a are at 90-degrees relative to points 121 and 122 and the full display is rotated 90-degrees relative to each other with the letters AZ displayed only on flexible-display 125.
  • Flexible-display 124 is on top of flexible display 125.
  • Both flexible-displays 124 and 125 in view 120b are at 45-degrees angle relative to points 121 and 122 and the full display is rotated 45-degrees relative to each other with the letter A of AZ partially displayed on 124 completing the letter AZ partially covered on flexible display 125.
  • Flexible- display 124 is on top of flexible display 125.
  • Both flexible-displays 124 and 125 in view 120c are at 0-degrees angle relative to points 121 and 122 (could be lightbulbs, micro LED, or any relative location sensors) meeting at the same point and the full display is rotated 0-degrees relative to each other with the letter A of AZ fully displayed on flexible-display 124and 125 positioning
  • Flexible- display 124 is on top of flexible display 125 with the full A of AZ displayed on 124, 125 and their overlapped area 126.
  • a volume knob works on the principle of a potentiometer only, but this invention teaches a potentiometer is only one method of aligning an image in the same location as the flexible-display moves relative to a helix or segments display 124 and 125 of a helix flexible- display 99.
  • rod 91 can be attached to the top edge 112 of flexible-display helix 99 or sleeve 92 can be attached to the bottom edge 112 of flexible-display helix 99, to provide the same complete video image by converting all relative motion of edges 112 and 113 into a single image across dividing lines, overlapped flexible-display material, and other motion sensors.
  • FIG 61 is a sliding potentiometer and FIG 62 is a rotating potentiometer, both providing the location of a flexible-display, so images can remain complete relative to motion of the flexible displays or adjoining edges. Any sensors configure under the full magnetic spectrum or GPS satellite systems can be applied or linked to smartphones.
  • Pinpoints of light can document location between related materials, like a potentiometer, and a touch sensitive flexible display can provide the data of "bumps" around the display that it can display.
  • a programmed set of bumps (protrusion points) can be laid out under the display to locate it, or recordable 3d elements can be added to the flexible- display providing data about where the display is relative the overlapping, jointing, motion, and any other changes that keep the flexible-display image defined by the programmer/user.
  • Nano graphene circuits and other nano-circuits can measure motion at a nano-scale, so motion of flexible-displays can be measured with extreme accuracy. Management of the energy required to display a flexible-display, like helix 99, can be managed with sensors in the observer's possession.
  • a snap fastener also called press stud, popper, snap or tich
  • press stud popper, snap or tich
  • a circular lip under one-disc fits into a groove on the top of the other, holding them fast until a certain amount of force is applied.
  • Different types of snaps can be attached to fabric or leather by riveting with a punch and die set specific to the type of rivet snaps used (striking the punch with a hammer to splay the tail), sewing, or plying with special snap pliers.
  • a retaining ring is a fastener that holds components or assemblies onto a shaft or in a housing/bore when installed in a groove. Once installed, the exposed portion acts as a shoulder which retains the specific component or assembly. Circlips are a type of retaining ring.
  • Self-locking retaining rings may be installed in applications where there is no groove.
  • Retaining rings are typically made from carbon steel, stainless steel or beryllium copper and may feature a variety of finishes for corrosion protection depending on the type of environment in which they are used
  • a Terry clip (or Terry's clip) is a spring metal clip used to hold a cylindrical object. Snap fasteners (also named poppers and press studs) and the hook and loop fastener are a few less common zipper alternatives.
  • a zipper, zip, fly, or zip fastener formerly known as a clasp locker, is a commonly used device for binding the edges of an opening of fabric or other flexible material, like on a garment or a bag. It is used in clothing (e.g., jackets and jeans), luggage and other bags, sporting goods, camping gear (e.g. tents and sleeping bags), and other items. Zippers come in all different sizes, shapes, and colors. Whitcomb L. Judson was an American inventor from Chicago who invented and constructed a workable zipper. The method, still in use today, is based on interlocking teeth. Initially, it was called the "hookless fastener" and was later redesigned to become more reliable.
  • the bulk of a zipper/zip consists of two rows of protruding teeth, which may be made to interdigitate, linking the rows, carrying from tens to hundreds of specially shaped metal or plastic teeth. These teeth can be either individual or shaped from a continuous coil and are also referred to as elements.
  • the slider operated by hand, moves along the rows of teeth. Inside the slider is a Y-shaped channel that meshes together or separates the opposing rows of teeth, depending on the direction of the slider's movement.
  • the word Zipper is onomatopoetic, because it was named for the sound the device makes when used, a high-pitched zip.
  • FIGURE 63 illustrates length of the circumference of flexible-display dl rolled open flat.
  • Length d2 is equal to one half of the circumference 115. cl .
  • Width i3 and i4 (can vary relative to the observation distance from the center axis 101) is the width of vertical il and horizontal i2 length of a "t" on flexible display 200 in FIGURE 20.
  • overlapped flexible video displays can be measure by optical scanning for a 3d image, measure by sensors, or fasteners locations can be measured to determine the programed image the display pixels illuminated for an observer.
  • Bluetooth, WiFi, wired, or other communication inks can provide any shape with a programmed image and observers can visualize in any configuration.
  • a touch sensitive flexible video display can have the sensors of the touch display defined to coordinates and three- dimensional geometry for the programmed display of the modified image to display the real-life image to an observer.
  • touch sensitive displays a known protrusion that a touch sensitive display can record, provides the programable data of where the element is located relative to the rest of the display that defines the software programed image.
  • Flexible displays can be loose when worn by people or motion translational devices, so motion sensors, triangulation measurements, and any measuring device that measures the required points of the three-dimensional geometry of the application the flexible display covers, and then senses the location of the observer or camera to display the image desired. Several images can be displayed and divided into observation windows for several observers.
  • FIGURE 63 illustrates a perpendicular view of letter "t" 136 optical center C (also known as camera projection center) 130 of the image 134 on plane 110, which is the cylinder 110 in FIG 20 with length dl equal to the circumference of cl on cylinder edge 115 in FIG 20 unrolled providing one half-length d2 of the circumference cl, of edge 115 marked by arrows on the plane of 112 on 110.
  • the distance of the image plane 112 on 110 from C, 130 is the focal length f from the arrow on top of 130 to the intersection of the "t" center lines 132 and 134 on the plane 110's surface.
  • the line from the camera center C, 130 perpendicular to the image of plane 110 is called the principal axis 138 or optical axis 138 of the camera C, 130.
  • the plane 140 parallel to the image plane 110 containing the optical center C, 130 is called the principal plane 140 or focal plane 140 of the camera C, 130.
  • the relationship between the 3-D coordinates of scene points 136 and 137, and the coordinates 134 and 133 of its projection onto the image plane 112 on plane 110 is described by the central or perspective projection of C, 130.
  • FIGURE 63 illustrates Pin-hole camera geometry of C, 130.
  • the left figure illustrates the projection of the point M on the image plane 110 by drawing the line 138 through the camera center C and the point 130 to be projected.
  • the right figure illustrates the same situation in the XZ plane, showing the similar triangles used to compute the position of the projected point m in the image plane 140 from image plane 112 with length d2 on fully rolled out plane 110 with length dl .
  • the pin-hole camera C is described by the following:
  • perspective projection can be expressed in terms of matrix multiplication as
  • the matrix describing the mapping is called the camera projection matrix P.
  • Equation (3) can be written simply as:
  • the projection matrix P in Eq. (3) represents the simplest possible case, as it only contains information about the focal distance f.
  • G is composed by a rotation matrix R and a translation vector t. It describes the position and orientation of the camera with respect to an external (world) coordinate system. It depends on six parameters, called extrinsic parameters.
  • the rows of R are unit vectors that, together with the optical center, define the camera reference frame, expressed in world coordinates.
  • K is the camera calibration matrix; it encodes the transformation in the image plane from the so-called normalized camera coordinates to pixel coordinates.
  • the ratio sy/sx is the aspect ratio (usually close to 1).
  • the camera matrix in general, is the product of three matrices:
  • the camera projection matrix is a 3 x4 full-rank matrix and, being homogeneous, it has 11 degrees of freedom.
  • any 3 x4 full rank matrix P can be factorized as:
  • the camera projection center C is the only point for which the projection is not defined, i.e. :
  • C ⁇ is a 3-D vector containing the Cartesian (non-homogeneous) coordinates of the optical center.
  • the projection can be geometrically modelled by a ray through the optical center and the point in space that is being projected onto the image plane (see Fig. 2).
  • the optical ray of an image point m is the locus of points in space that projects onto m.
  • DLT Direct Linear Transform
  • any image on the flexible-display around any shape can be software programmed to provide the appearance of a flat "plane” image by programing the flexible display to illuminate pixels within the "projected” image from a camera observation point plane to all the curves and overlapping flexible display edges, and joining edges, including during motion.
  • a sensor could be worn on the bar between the eyeglass lenses, a neckless, or other sensors to replicate a camera observation point onto a flexible display of any shape by applying the Direct Linear Transform (DLT) algorithm.
  • DLT Direct Linear Transform
  • 3D printing, printed documents or colored clothing, painting, posters, billboard imaging, lighting, LED sourced images (colored LED elements), retroreflecting materials, and architecture designs can all apply this imaging technology on any shape to provide a flat plane image appearance to the observer.
  • All the displays are mobile, so this invention teaches that when the display is rotated in any direction ( any orientation relative to spacetime), pre-selected programs relative to spacetime position changes program functions on the display, providing programs providing: flight weather, forward and reverse views from cameras, emails, networks, 360-degree views around the aircraft or land, sports, flight paths, and include any functional program of a computer is programed for its orientation (or a sensors orientation and location) GPS location. Even hang up phone call or shut down the computer, just by the pre-programed orientation, including setting the tolerances of movement relative to coordinates point, and then GPS or other sensor functions. A custom "orientation" changes programs and the tolerance and GPS (relative to environment sensors too) location can change which programs turn on relative to which orientation, without restrictions to any angle.
  • FIG 66 illustrates rotating wings for all drone with or without wings.
  • Wings Wl, W2, and W3 fold down on a hinged area (which could be materials folding) near the three blades providing a glider when in the plane of rotation, and then wings and tail when nearly connected together at the circle-arc tips in right hand view.
  • Circle-arcs could be cycloid curves joining together at all three midpoints where relative air will reach at same time during a period of time, including shapes that direct air along the curve.
  • Other number of arrays, two, four, five, and six, including adapting to any number of blade poles, can have relative circle-arcs of folding wings illustrated in FIG 66.
  • a clearance is provided between the edges of wings and poles for the propellers to turn when needed.

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Abstract

L'invention concerne la vitesse de rotation de la pale de voilure tournante (1) la plus basse à proximité du moyeu (5) et qui augmente vers l'extérieur en direction du trajet d'extrémité (15) de la pale de rotor (1) pendant la rotation. Le déplacement de la poussée vers le trajet d'extrémité (1) d'une voilure tournante (2, 3 et 4) fournit un aéronef qui est plus efficace que l'état de la technique des systèmes à entraînement axial central : des moteurs, moteurs électriques, jets ou turbines qui entraînent une rotation forcée (11) par le biais d'un mât d'axe central (5) et (6), le couple transféré (11) par le biais d'un moyeu (5) raccordé au corps de l'aéronef à l'axe central (16) de la voilure tournante (1) tournant dans le plan du sens de rotation. En quelques millisecondes, des plaquettes piézoélectriques montées sur des pales de profil aérodynamique d'hélice (2, 3 et 4) passent d'un profil aérodynamique symétrique à un profil aérodynamique non symétrique (à chambres ou sous une forme quelconque) afin d'augmenter la densité d'air pour une plus grande portance pendant une rotation d'hélice à grande vitesse.
PCT/US2018/043196 2017-07-20 2018-07-20 Production de poussée de profil aérodynamique de trajet d'extrémité dans un aéronef à voilure tournante WO2019018832A2 (fr)

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PCT/US2019/033009 WO2019222718A2 (fr) 2018-05-17 2019-05-17 Modèle tridimensionnel d'interactions de particules appliquant des règles de diagrammes de feynman en deux dimensions qui appliquent uniquement des lignes en arc de cercle pour des flèches d'électrons ou de positrons, connectées chacune à des lignes ondulées de photons, puis les rejoignent uniquement à l'aide de sommets croisés définissant la théorie universelle d'électrons et de photons dans une matrice tridimensionnelle hexagonale de trois éléments

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CN115071350A (zh) * 2022-07-22 2022-09-20 西华大学 一种滚翼飞行汽车
CN116873188A (zh) * 2023-07-10 2023-10-13 中国商用飞机有限责任公司 一种用于改变翼梢小翼的倾斜角的驱动机构
CN117699046A (zh) * 2024-02-05 2024-03-15 成都以太航空保障工程技术有限责任公司 基于位置敏感探测器的直升机旋翼椎体检测系统和方法

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