CN113581460B - Symmetrical wing vertical take-off and landing intelligent lifting transport aircraft - Google Patents
Symmetrical wing vertical take-off and landing intelligent lifting transport aircraft Download PDFInfo
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- CN113581460B CN113581460B CN202110917021.XA CN202110917021A CN113581460B CN 113581460 B CN113581460 B CN 113581460B CN 202110917021 A CN202110917021 A CN 202110917021A CN 113581460 B CN113581460 B CN 113581460B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
- B64C3/141—Circulation Control Airfoils
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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Abstract
The intelligent lifting transport aircraft with symmetrical wings is characterized in that left and right wings, left and right jet flow pipe groups and left and right load systems are symmetrically arranged on airframes on two sides of a central surface of a bracket, the wing is symmetrically arranged in a head-to-head mode (the head refers to the windward side of the wing, the head-to-head refers to the windward side of the wing, the windward sides of the left and right wings face towards a symmetrical shaft, and the leeward side faces outwards), and the cross section of the wing is rectangular or other shapes. In order to enable the wing to generate lift force, a plurality of jet pipes are arranged on the windward side of each side of the wing, and the lift force can be rapidly and flexibly controlled by controlling the flow rate, the air quantity and the temperature of the air outlet and the position angle of the wing. The intelligent system optimizes flight parameters according to the information of load weight, appearance characteristics, distance of transportation, elevation and the like. The invention can be used in the fields of civil construction, water conservancy and hydropower construction, disaster relief, short-range transportation, port and dock, high-altitude installation, mobile advertisement of large-scale activities and the like.
Description
Technical Field
The invention relates to the technical field of construction machinery, in particular to an intelligent lifting and transporting aircraft with symmetrical wings and vertical take-off and landing, which is used in the fields of construction lifting and emergency transportation.
Background
In civil engineering construction, equipment such as a tower crane, a cable crane, an automobile crane or a concrete pump is often used for transporting building materials and components. Because the modes involve a plurality of links such as ground (stock yard), crane operators, high-level working surfaces and the like, the efficiency is low, the materials can only reach specific positions, and finally the materials are accurately positioned by constructors. The cranes are manually operated, the suspension arm is long, the number of the cranes which can be accommodated on a site is limited, and the cranes are easy to saturate, so that the efficiency of the cranes often determines the construction progress. If a helicopter is adopted, the helicopter has strict safety requirements and high threshold, and is not suitable for common construction sites; if various multi-axis rotary wing civil unmanned aerial vehicles on the market are adopted, the loading capacity is very limited, and the carrying requirements of large-scale components cannot be met. In hydropower construction and flood control and disaster relief, a large amount of materials are required to block the breach instantaneously, and the breach is not accessible to large vehicles, and an air channel is required to provide a large amount of materials.
Disclosure of Invention
The invention aims to provide an intelligent lifting and transporting aircraft with symmetrical wings and vertical take-off and landing, which aims to rapidly transport large objects to a designated place through an air passage.
The purpose of the invention is realized in the following way: an intelligent lifting transport aircraft with symmetrical wings and vertical take-off and landing, wherein the aircraft body is a bracket type aircraft body; the left wing, the right wing, the left jet pipe group, the right jet pipe group and the left load system are arranged on the machine body in a geometrically symmetrical and physically symmetrical way by taking the central plane of the bracket of the machine body as a symmetrical plane; the top view shape of the right wing adopts a rectangle, a curved rectangle or a polygon or a combination of the rectangle and the polygon, the windward side (head) of the right wing faces the central surface of the bracket, the rotating shaft for fixing the right wing is parallel to the central surface of the bracket, the rotating shaft is driven by an actuating mechanism to enable the right wing to deflect back and forth between 90 degrees and 180 degrees and 270 degrees, a plurality of jet pipes of the right jet pipe group between the central surface of the bracket and the right wing are arranged at equal intervals along the length direction of the right wing, the pipe orifices of the plurality of jet pipes are equidistant with the right wing, and the pipe orifices of the plurality of jet pipes are forward to the windward side of the right wing; the height of the jet pipes is adjustable along with the rotation angle of the wing, so that the position change of the windward caused by the rotation of the wing is adapted, the jet gas always hits the windward from the front, and the height adjustment of the jet pipes can be realized by adopting a screw, a rack, a chain, a hydraulic device or an electromagnetic device and the like and is accurately controlled by a control system; the left wing is symmetrical with the right wing, and can deflect back and forth between 90 degrees and 0 degrees and 270 degrees; the power source is arranged at the position of the central surface of the bracket of the machine body, and the power source comprises the following components: air compressors driven by a fuel or gas engine or driven by a battery pack are respectively connected with left and right jet flow pipe groups through left and right pipelines, air quantity control valves are respectively arranged on the left and right pipelines, and the left and right pipelines are symmetrically arranged on the left and right sides of the central surface of the bracket; the lower part of the machine body is provided with a central plane with a bracket a plurality of legs symmetrically disposed; the system also comprises a sensing control system consisting of a driving system and a precise positioning system; the machine body is provided with an alignment sensor, and an output signal of the alignment sensor is transmitted to a sensing control system. The symmetrical wing vertical take-off and landing intelligent lifting transport aircraft is characterized in that the cross section of the wing along the length direction is equal or variable.
The symmetrical wing vertical take-off and landing intelligent hoisting transport aircraft is characterized in that the left and right load systems comprise slings, lifting hooks and a crane, namely a winch.
The wing is provided with a flap which can extend or retract into the wing interior to adjust lift.
The temperature, speed, pressure and other physical parameters of air ejected at a certain flow rate provided by a power source are independently controlled by each jet pipe in the left jet pipe group and the right jet pipe group at each side; the rotation angle of the left wing and the right wing and the telescopic position of the flap can be independently controlled, and the movement of the flying equipment in the front, the back, the left, the right, the up and down directions can be flexibly controlled through the independently controlled parameters.
The sensing control system also comprises video and audio information collecting equipment, weight measuring equipment, distance measuring equipment, a data processing and converting system and an instruction system, and is used for collecting and processing information such as environment, weight, distance, elevation and the like, converting the information into instructions of lifting force and a driving system, and directing an aircraft to fly to a destination by automatic driving or manual driving and accurately aligning.
The two ends of the rotating shaft are arranged on bearing seats through bearings, and the two bearing seats are symmetrically arranged on the machine body left and right; the right wing is divided into a plurality of sections along the direction of the rotation axis, and each section can be independently controlled.
The symmetrical wing vertical take-off and landing intelligent lifting transport aircraft can be provided with wings which are symmetrically arranged along the periphery of the bracket besides left and right wings.
And baffle plates and/or middle rectifying plates are arranged at two ends of the left wing and the right wing in the length direction. The plane of the baffle plate or the rectifying plate is perpendicular to the rotation axis, the contour line exceeds the contour of the wing, and the shape of the baffle plate or the rectifying plate is rectangular or other patterns, which is used for guiding flow, so that the jet flow gas flows along the streamline shape, and the transverse or oblique flow is reduced.
Compared with the prior art, the invention has the beneficial effects that:
1. The brand new intelligent aircraft (hereinafter referred to as aircraft) can vertically take off, land or hover for the lifting and transporting purposes, and can automatically plan a route, accurately transport equipment to a destination, automatically or manually command unloading, and even directly and accurately place components at a designed position by inputting target position coordinates (such as through a Beidou positioning system). In various disaster relief actions, a helicopter is often used for transporting materials, and in wind power plant wind driven generator runner installation, an ultrahigh-speed automobile crane or a helicopter is often used, so that the methods are effective, but have higher cost. The aircraft of the present invention may be advantageous in terms of weight, efficiency, and maneuverability.
2. Bounded by conventional concepts, the industry divides aircraft into rotary wing aircraft and fixed wing aircraft, the former being capable of taking off and landing vertically, such as various multi-axis rotary wing unmanned aerial vehicles and helicopters on the market; the latter must fly at very high horizontal speeds to generate lift, such as in a propeller or jet passenger aircraft. Both aircraft have problems with high transportation costs and limited use at the worksite. The invention has the advantages of vertical lifting capability, large carrying capacity, good maneuverability and lower transportation cost, and can meet the requirements of various emergency transportation occasions.
The intelligent vertical take-off, cruising and landing aircraft has the functions of lifting, transporting and accurately aligning, and can be used in the fields of civil engineering construction, water conservancy and hydropower construction, disaster relief, short-range transportation, ports and wharfs, high-altitude installation, mobile advertisement of large-scale activities and the like.
Drawings
Fig. 1 is a front view (fuselage section in streamline form) of an aircraft of the invention.
Fig. 2 is a top view of fig. 1.
Fig. 3 is a perspective view of an airfoil and a rotating shaft.
Fig. 4 is a simplified schematic diagram of the pressure distribution, the flying force and the component force of the upper and lower surfaces of the wing (the upper side pressure of the wing is small, the lower side pressure of the wing is strong).
Detailed Description
FIG. 1 and FIG. 2 show that the symmetrical wing vertical take-off and landing intelligent lifting transport aircraft of the invention, wherein a fuselage 8 is a bracket type fuselage; the left and right wings, the left and right jet flow pipe 4 groups and the left and right load systems 9 are arranged on the machine body 8 in a geometrically symmetrical and physically symmetrical manner by taking the bracket center plane 3 of the machine body as a symmetrical plane; the overlooking shape of the right wing adopts a rectangle, a curved rectangle or a polygon or a combination of the rectangle and the polygon, the windward side of the right wing faces the central plane 3 of the bracket, namely, the rotating shaft 2 for fixing the right wing towards the jet pipe orifice is parallel to the central plane 3 of the bracket, the rotating shaft 2 is driven by an actuating mechanism to deflect the right wing between 90 degrees and 180 degrees and 270 degrees, a plurality of jet pipes of the right jet pipe group between the central plane 3 of the bracket and the right wing are arranged at equal intervals along the length direction of the right wing, the pipe orifices of the plurality of jet pipes are equidistant with the right wing, and the axial leads of the plurality of jet pipes are perpendicular to the windward side of the wing. The height of the jet pipes is adjustable due to the fact that the windward side changes with the rotation angle of the wing, so that the position of the windward side changes up and down due to the rotation of the wing, and jet gas always hits the windward side from the front. The height adjustment of the jet pipe can be realized by adopting a screw, a rack, a chain, a hydraulic or electromagnetic device and the like, and is accurately controlled by a control system; the left wing and the right wing are symmetrical, and deflect in figure 1 between 90 degrees and 0 degrees and 270 degrees, and the rotation axis is taken as the origin of coordinates; ; the power source 6 is arranged at the position of the bracket center surface 3 of the machine body, and comprises the following components: air compressors driven by a fuel or gas engine or driven by a battery pack are respectively connected with left and right jet flow pipe groups through left and right pipelines, air quantity control valves 5 are respectively arranged on the left and right pipelines, and the left and right pipelines are symmetrically arranged on the left and right sides of the central surface of the bracket; the lower part of the machine body is provided with a plurality of supporting feet which are symmetrically arranged by taking the central surface 3 of the bracket; the system also comprises a sensing control system consisting of a driving system and a precise positioning system; the machine body is provided with an alignment sensor 10, and an output signal of the alignment sensor 10 is transmitted to a sensing control system.
Fig. 1 is an xy plane of a cartesian three-dimensional coordinate system, fig. 2 is a zx plane of the coordinate system, and a bracket center plane is a yz plane of the coordinate system. Referring to fig. 2, all nozzles of the right jet stack are equidistant from the right wing. The rotation axis actuating mechanism is: the shaft of the stepping motor is connected with the rotating shaft through a coupler, or two stepping motors are respectively connected with two ends of the rotating shaft through a coupler, and the rotating shaft is driven by a driving mechanism to deflect the left wing between 90 degrees and 0 degrees 270 degrees (see figure 1).
The lift of the aircraft comes from a set (or sets) of wing-shaped components (hereinafter referred to as "wings" for short) and compressed air jet clusters, which are symmetrically arranged from head to head (hereinafter referred to as "wings" for short; the case of a single set of wings; the case of more than two sets of wings is the same; here the "head to head" symmetry is critical). The wing and the compressed air jet flow pipe group together form a lifting system (figure 1), which is bilaterally symmetrical, namely, the lifting system on one side is a mirror image of the lifting system on the other side, and the symmetrical plane is a longitudinal central plane of the bracket (a line 3 drawn at the middle point in figure 1 is the central plane of the bracket). The aircraft static total centroid is also located within the central plane. The lift system is mounted on the fuselage carrying structure. The fuselage carries legs for carrying the dead weight of the fuselage during a shutdown (see fig. 1). Also arranged on it are on-board sensing control systems (including steering systems, precision alignment systems and video and audio information collection devices, weight measurement devices, distance measurement devices, data processing and conversion systems, instruction systems, which function to collect and process information such as environment, weight, distance and altitude, etc., convert it into instructions for lift and steering systems, autopilot or manual pilot the aircraft to fly to the destination and precision alignment), load systems, power sources (engines, fuel tanks, battery packs, air compressors), etc. The sensing control system collects and records the position and characteristic information of various related targets and obstacles in the aircraft and a certain range around the aircraft, controls the running speed of the aircraft on the basis, optimizes the flight route of the aircraft, enables the aircraft to safely reach the position above a preset position in the shortest time, and accurately aligns the aircraft according to the set front, rear, left, right, upper and lower positions and then releases the load. For example, in building and installation projects, the corner points of each brick or prefab can be used as position control points, and the aircraft rechecks the coordinates of the control points (such as elevation of longitude and latitude, or in combination with a Beidou system/GPS) before releasing the load. The load system comprises slings, hooks, cranes (winches) and the like for connecting the load to the aircraft in one piece and adjusting its position to make it suitable for transport;
The driving system comprises two modes of automatic driving and manual driving, and can be switched according to the requirement. The steering system determines the movement direction of the aircraft, has six directions of front, back, left, right, up and down, and realizes maneuver mainly by adjusting the angle of the wing, the expansion and contraction of the flap and the air flow rate and the flow quantity of the specific jet flow pipe. The small-sized propeller and other devices can be arranged at different positions of the machine body according to the requirements, so that the maneuvering speed of the aircraft is accelerated.
"Symmetrical wing" encompasses geometric and physical symmetry.
Geometric symmetry: the size of the left wing and the right wing and the configuration of functional components (such as compressed air jet pipes or propellers, wing rotating shafts and the like) are completely symmetrical, ③ is a symmetrical axis in fig. 1, the arrow direction represents the flow direction of compressed air, the right jet pipe jets right, the left jet pipe jets left, and the caliber is the same; the wing can rotate a certain angle around the rotation shaft according to the instruction, and can rotate clockwise or anticlockwise (figures 1 and 2); the rotation direction and the angle of the wings at the two sides can be independently controlled.
Physical symmetry: the left and right sides are substantially equally weighted, with the center of the cradle being bounded by (again ③ in fig. 1), and the center of gravity of the entire aircraft being located in or near the center of the cradle.
Based on the symmetry, it can be seen that: when the states of the left wing and the right wing are symmetrical, the air quantity and the air speed of the jet flow pipe are also symmetrical, the aircraft cruises straight line; otherwise, as long as the wing state, the air quantity and the air speed are asymmetric, the aircraft does not linearly cruise any more and does curvilinear motion. According to this feature, the aircraft can be commanded to perform a curvilinear motion in three dimensions.
The jet pipe is used for jetting compressed air to the windward side (head) of the wing to generate lift force (figure 3), so that a propeller can be used for replacing the jet pipe in actual manufacturing (similar to the principle of a propeller plane).
Compressed air is supplied by a power source, which is typically composed of an air compressor, which may be driven by a (fuel, gas) engine or a battery pack, a compressed air container, and a control valve. The same effect can be achieved by arranging the propellers according to a symmetrical principle instead of compressed air.
The fuselage of the aircraft is made of steel or other materials such as carbon fiber to ensure adequate strength. Meanwhile, the size of the bracket is large enough to ensure smooth air supplement.
The aircraft is provided with three or more than four supporting legs and is symmetrically arranged on the center plane of the bracket, and is usually parked on an apron or the like. The front view of which is shown in figure 1. In the figure ① is a wing, ② is a wing rotation axis, and the dotted arrow indicates the rotation direction of the wing around the rotation axis. As can be seen from the figure: when the wing states are symmetrical, the resultant forces born by the left wing and the right wing are symmetrical, the vertical components of the wing are the same in size and direction, lift force is formed, the horizontal components of the wing are equal in size and opposite in direction, and the resultant force is zero.
Since the jet pipes are symmetrically arranged, the resultant force of horizontal thrust to the aircraft is zero as long as the jet speeds, the flow rates and the angles of the left pipe and the right pipe are the same. But if one or more of them are different, there will be a resultant force in the horizontal direction. This can be used to fine tune the attitude or position of the aircraft.
Because of symmetry, all parts in fig. 1 are labeled on one side only (right side).
The cross-sectional shape and the actuation mode of the wing are identical to those of modern aviation wings, including the arrangement of flaps. Along the length of the wing (i.e. the direction of the rotation axis), the invention can flexibly adopt various sections (the cross section of the wing in the length direction is equal or variable), and the profile of the wing (i.e. the overlooking shape in figure 2) can adopt rectangle, curved rectangle, polygon and the like. Baffles are arranged at two ends of the wing in the length direction so as to achieve the rectifying effect. An intermediate rectifying plate can also be arranged; the wing is even divided into several sections along the length, each section being independently controlled and having fairing.
The rotation axis (figure 3) of the wing is the part of the wing that transmits the lift force to the bracket, if the rotation axis is long, a supporting point can be arranged in the middle, or the wing is divided into a plurality of sections along the length, so that the local deformation of the rotation axis is avoided. The number of the middle supporting points is determined according to the requirement.
Arrangement of the jet device: as shown in fig. 1, a plurality of independently controllable jet devices, such as compressed air jets, propellers, etc., are symmetrically arranged in place. The jet device is used for blowing air or mixed gas with certain flow velocity to windward sides of wings at two sides, and the air is divided into an upper part and a lower part after hitting the wings and is blown over the upper surface and the lower surface of the wings respectively, so that the wings generate lift force, and the lift force is shown in fig. 1 and 4.
Because jets flow to the left and right wings (figure 1) simultaneously, the two wings respectively generate resultant forceAndRespectively decomposing the components into a horizontal component and a vertical component:
The letters H and V in the above formula represent horizontal and vertical components, respectively, and a small arrow above the letter indicates that the amount is a vector, and thus the above formula is a vector formula (not an algebraic formula). As can be seen from the figure 1 of the drawings, AndEqual in size and opposite in direction, and cancel each other out (the horizontal resultant force is zero); And Equal in magnitude and in the same direction, thus creating a resultant force (lift) in the vertical direction.
The invention is based on the principle of aerodynamics, namely the principle of generating lift force by an aeroplane wing: the shape of the wing determines the difference in the flow rate of air across the upper and lower surfaces, and according to Bernoulli's principle, the upper surface has a high flow rate, a low pressure, and the lower surface is opposite, thus generating lift. The lift is calculated according to the following formula:
L＝0.5C·ρ·V2·A,
wherein L represents lift in units of cattle (N);
C represents a lift coefficient, dimensionless;
ρ represents the air density, which is related to altitude, and 1.2 kilograms per cubic meter (kg/m 3) is available at low altitudes;
v represents the air flow rate in meters per second (m/s);
A represents the wing area in square meters (m 2).
The direction of the resultant force generated by the wing depends on factors such as the angle of the wing, and the like, and the resultant force is not normally vertically upwards, but has a certain included angle and can be decomposed into a vertical component V and a horizontal component H. Because the wings which are symmetrically arranged head to head are adopted, the horizontal components of the left and right wings are equal in size and opposite in direction, so that the horizontal components are offset; the vertical components are equal in magnitude and the same in direction, and the vertical upward lifting force is synthesized.
It follows that when both geometric and physical symmetry is met, the aircraft will not move in a horizontal direction, but will only rise, hover or fall vertically. The lifting force can be adjusted by controlling the parameters such as the angle of the left wing, the right wing, the air quantity, the air speed and the like, so that the aircraft can lift off with load and land after reaching a destination.
After the aircraft is lifted off, the parameters of each jet flow pipe and the angles of wings can be independently regulated, so that a certain horizontal component force or torque is formed, and the aircraft is pushed to do curvilinear motion (turning) or to rotate in situ, so that the purpose of meeting the front-back, left-right, upper-lower coordinates is realized.
If an engine (such as an oil or gas engine) is used as the power source, exhaust gas may be mixed into the jet gas in addition to the normal jet, thereby increasing the airflow rate at the jet outlet. The optimal allocation can be found by experimental or theoretical analysis.
A lifting appliance such as a lifting hook, a winch and the like is arranged below the aircraft and used for hanging loads, including various components, fresh concrete, rescue tools, containers and the like. Single-point or multi-point hanging is set according to the requirement, so as to maintain the stability and safety of the aircraft and the load during operation.
Application example: in intelligent construction, the aircraft can carry loads to accurately align in a three-dimensional space, and the equipment has an accurate positioning function and comprises two layers of meanings, wherein one of the two layers of meanings is the accurate positioning of a destination unloading position, such as Beidou system position information; secondly, accurately positioning a load receiving design position, such as the design position of a certain prefabricated member in a high-rise building; to ensure that a building element is accurately placed in the design position. If the control point coordinates exceed the allowable error, the aircraft prompts through proper acousto-optic signals, and the load is suspended, so that time and space are reserved for correcting the pre-process. For high-rise building or super-high bridge engineering construction, the aircraft carries load to rise through a control system, automatically seeks to reach the upper part of a working surface, hovers and unloads after accurate alignment, and can also be commanded to unload by field personnel (switchable between intelligent and manual modes). In rescue and fire extinguishing, the aircraft can carry relevant instruments and materials to the scene without being affected by ground conditions.
On construction organization, can combine together with BIM, just consider the construction in planning design stage, make prefabrication piece or on-the-spot preparation part be fit for the high-efficient transportation counterpoint of aircraft to improve efficiency greatly, save the cost.
Claims (8)
1. An intelligent lifting and transporting aircraft with symmetrical wings and vertical take-off and landing is characterized in that a fuselage (8) is a bracket type fuselage; the left and right wings, the left and right jet pipe (4) groups and the left and right load systems (9) are arranged on the machine body (8) in a geometrically symmetrical and physically symmetrical way by taking the bracket center plane (3) of the machine body as a symmetrical plane; the overlooking shape of the right wing adopts a rectangle, a curved rectangle or a polygon or a combination of the rectangle and the polygon, the windward side of the right wing faces the central surface (3) of the bracket, the rotating shaft (2) for fixing the right wing is parallel to the central surface (3) of the bracket, the rotating shaft (2) is driven by an actuating mechanism to enable the right wing to deflect back and forth between 90 degrees to 180 degrees to 270 degrees, a plurality of jet pipes of a right jet pipe group between the central surface (3) of the bracket and the right wing are arranged at equal intervals along the length direction of the right wing, the pipe orifices of the jet pipes are equidistant with the right wing, and the pipe orifices of the jet pipes are forward to the windward side of the right wing; the height of the jet pipes is adjustable along with the rotation angle of the wing, so that the position change of the windward caused by the rotation of the wing is adapted, the jet gas always hits the windward from the front, and the height adjustment of the jet pipes is realized by adopting a screw, a rack, a chain, a hydraulic device or an electromagnetic device and is accurately controlled by a control system; the left wing and the right wing are symmetrical, and the left wing can deflect back and forth between 90 degrees to 0 degrees to 270 degrees; the power source (6) is arranged at the position of the bracket center surface (3) of the machine body, and comprises the following components: air compressors driven by a fuel or gas engine or driven by a battery pack are respectively connected with left and right jet flow pipe groups through left and right pipelines, air quantity control valves (5) are respectively arranged on the left and right pipelines, and the left and right pipelines are symmetrically arranged on the left and right sides of the central surface of the bracket; the lower part of the machine body is provided with a plurality of supporting feet which are symmetrically arranged by taking the central surface (3) of the bracket; the system also comprises a sensing control system consisting of a driving system and a precise positioning system; the machine body is provided with an alignment sensor (10), and an output signal of the alignment sensor (10) is transmitted to a sensing control system; the cross section of the wing along the length is equal or variable; the left and right load systems (9) comprise slings, lifting hooks and cranes.
2. The symmetrical wing vertical take-off and landing intelligent lift transport aircraft of claim 1, wherein the wing has a flap that can extend or retract into the wing interior to adjust lift.
3. The symmetrical wing vertical take-off and landing intelligent jack-up transport aircraft of claim 2, wherein the temperature, speed and pressure of air ejected at a certain flow rate provided by a power source are independently controlled for each jet pipe in the left and right jet pipe groups on each side; the rotation angle of the left wing and the right wing and the telescopic position of the flap can be independently controlled, and the flying equipment is controlled to move up and down in the front-back, left-right and up-down directions through the independently controlled parameters.
4. A symmetrical wing vertical take-off and landing intelligent lift transport aircraft as claimed in claim 3 wherein said sensory control system further comprises video and audio information gathering equipment, weight measuring equipment, ranging equipment, data processing and converting systems, instruction systems operative to gather and process environmental, weight, distance and altitude information, convert it into lift and steering system instructions, autopilot or manodynamic steering directs the aircraft to fly to a destination and to be precisely aligned.
5. The symmetrical wing vertical take-off and landing intelligent lift transport aircraft of claim 4, wherein: the two ends of the rotating shaft are arranged on bearing seats through bearings, and the two bearing seats are symmetrically arranged on the machine body left and right; the right wing is divided into a plurality of sections along the direction of the rotation axis, and each section can be independently controlled.
6. The symmetrical wing vertical take-off and landing intelligent lift transport aircraft of claim 5, wherein: in addition to the left and right wings, there are wings symmetrically arranged along the circumference of the support.
7. The intelligent lifting and transporting aircraft with symmetrical wings and vertical take-off and landing functions as described in claim 6, wherein baffles and/or middle rectifying plates are arranged at two ends of the left and right wings in the length direction, the planes of the baffles or the rectifying plates are perpendicular to the rotating shaft, the outline exceeds the outline of the wings, and the shape is rectangular, which functions as diversion, so that jet gas flows along streamline shape, and the transverse or oblique flow is reduced.
8. Symmetrical wing vertical take-off and landing intelligent lift transport aircraft according to claim 7, characterized in that the centre of gravity of the whole aircraft is located in the centre of support plane (3).
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| CN107176286B (en) * | 2017-05-16 | 2023-08-22 | 华南理工大学 | Foldable fixed-wing vertical take-off and landing unmanned aerial vehicle based on dual-ducted fan power system |
| CN108408045A (en) * | 2018-02-10 | 2018-08-17 | 云南同硕环保科技有限公司 | A kind of slip-stream lift using wing realizes the aircraft of VTOL and flight |
| CN109263930A (en) * | 2018-10-30 | 2019-01-25 | 佛山市神风航空科技有限公司 | A kind of Fixed Wing AirVehicle being vertically moved up or down |
| CN110217391B (en) * | 2019-05-31 | 2021-01-08 | 沈阳迪智科技有限公司 | Oil-electricity hybrid power vertical take-off and landing forward-swept fixed wing unmanned aerial vehicle |
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