CN205906192U - Two wing flexible aircrafts of front and back double -oar - Google Patents

Abstract

This patented invention a two wing flexible aircrafts of front and back double -oar, two wings around front wing (1) and rear wing (2) constitutes, compact structure rigidity intensity is good, big airfoil provides enough lift, twocouese rudder (3) and four hydrioplanes (4) provide good maneuverability, the applicable big load of low -speed is cruised. Around two wing flexibles, front wing (1) is rotatable, rear wing (2) are collapsible, the complete machine span is adjustable, cruises under the adaptation friction speed, is favorable to also traveling, pull in ground, transport and stock. Make up to a pair of anti - oar aircraft nose tail each one screw (5), produces syntropy thrust and pulling force, and power shaft coincident screw moment of torsion is between two parties offset, and complete machine weight is comparatively placed in the middle, and lift -over inertia is little, and favourable lift -over mobility does not just have the airfoil interference in air flow yet. Adopt the photovoltaic module covering and the technology of the compound material lamination of honeycomb to accomplish on the fuselage shell structure on casing and four wings, two wings and wing body merge provides great illumination area, and favourable photovoltaic for secondary cell charges and the mains power supply in real time, is favorable to long flight time of flight and environmental protection safety.

Description

Double oar double-vane deformable aircrafts before and after one kind

Technical field

The present invention relates to double oar double-vane deformable aircrafts before and after one kind.Double-vane twin vertical fin, favourable low-speed heave-load cruise；Double-vane Deformable, favourable speed change cruise and engineering；Anti- oar drives in front and back, it is to avoid wing root stress concentration and interference in air flow；Photovoltaic and honeycomb Multiple material laminating technology, realizes light structures and real time charging, belongs to Aircraft Conceptual Design field.

Background technology

Freely circling in the air is the dream that the mankind pursue since ancient times, and Lai Te brother pursues flight dream and invented the first airplane, But the World War I, World War II soon, aircraft because technical difficulty is big and its military use of undue weight, suddenly Freely circle in the air depending on the initial hope of the mankind.Although postwar civil aviaton is greatly developed based on military transportation airplane, produce the world two The U.S. of big airline Boeing and European Air Passenger, but General Aviation slower development, the mankind really realize the dream freely circled in the air not yet Think！

During biplane is popular in World War I, because the low-speed performance that it shows was once fashionable for a time, the later stage is because World War II is to height The requirement of fast performance, biplane is not promoted, and current biplane is mainly used in the fields such as stunt, agricultural operation.With Arranging up and down toward biplane because of wing leads to fuselage cross-section to amass very greatly, and upper lower support bar is more, and structural compactness is weaker, for making to put down Tail controls pitching effect substantially, needs head larger with tail longitudinal separation, leads to that fuselage longitudinal size is still larger, and aircraft is whole Body complex structure is heavy, and flight resistance is very big, if being to reduce lateral dimension when depositing, it is that comparison is difficult that wing design becomes deformable , unless after each flight remove wing reached the purpose reducing horizontal space, bring using inconvenience to user.And monoplane For realizing same low speed lift effect, the span will be bigger, and wing chord will be wider, and fuselage cross-section will be thicker, be not suitable for low-speed heave-load Operation.

Generally aviation power is divided into internal combustion, external combustion and electronic three major types, and Aviation Fuel electromotor is that technology contains all the time One of amount highest part, price is very high always, and especially external import aero-engine is expensive, moreover even if the coming years Prices are accepted by General Aviation, add civil aviaton's line, and Aviation Fuel tail gas is directly entered air, and atmospheric pollution level is existing Having become as one of factor weighing regional productive life quality or even Happiness Index, fuel oil aviation future will be reluctant by the common people Accepted with country.Because motor and battery technology tend to ripe, electric airplane, electric automobile will become inevitable, and market is existing electronic The double oar layout of aircraft commonly used single-blade layout or left and right, but under normal circumstances, single-blade layout reliability is weak and needs real-time rudder face Trim propeller torque, and wing nacelle layout is very high to aircraft wing body link strength, rigidity requirement, wing root section requires Very big, and before or after wing, propeller is larger to aerofoil surface interference in air flow, high performance airscrew air-flow often results in aerofoil flow and divides From.

Solar energy is our tellurian ultimate energies, stores in the middle of material through a series of links, then is disappeared by the mankind Consumption, less than 10%, current efficient photovoltaic module photoelectric transformation efficiency surpasses 20% to efficiency, though being directly provided that aircraft power using the sun Immaturity, but be directly that airborne equipment is powered and real time charging technical feasibility with solar energy, effectively lengthen working hours and reduce Atmospheric pollution, solar energy shows promise as the active force energy (as Switzerland's solar impulse circumaviation) of light aerocraft.

Chinese Small-sized personal aircraft, is only accepted by a few peoples because of factors such as technology, price, airport, hangar, policies with front. The Internet globalization at present leads to economic globalization, and value China enters World Trade Organization's tariff reduction and exemption in 15 years again, and the whole world is fair competing Strive gradually ripe with the environment of Techno-sharing, regional development and technology barrier and local price protection will be eliminated, the key of products application Go to the solution of policy, airport, hangar and transportation problem.In recent years, China implements dividend policy, civil aviaton and the navigation in open low latitude It is expected to become China's economic new growing point, and China's cultivated land resource lacks, highway and urban construction have taken a large amount of arable lands, count with tens The navigation airport of ten thousand meters and hangar occupation of land are problems, will be the bottlenecks limiting people's self-driving flight.

Content of the invention

The present invention provides double oar double-vane deformable preliminary design of aircraft before and after one kind, the problem of solution and purpose as follows:

(1) conventional low heavy duty monoplane faces that the span is big, rigidity is weak, single-blade is heavy, aeroelasticity is big, fuselage cross-section is big And the weak problem of reliability, and traditionally descend that biplane fuselage cross-section is big, up-down structure is heavy, sensitive surface is few, conventional airplane is put down Tail or canard area are little, unfavorable low speed maneuverability, and double-vane can solve these problems in front and back.

(2) traditional single-blade or biplane are unlikely to deform, and span lateral dimension and rolling inertia are constant, force speed change cruise It is easily caused pneumatic efficiency to be decreased obviously, and because the span is big, be unfavorable for storing and carry, wing deformable is asked with solving these Topic.

(3) frame head and tail anti-oar driving before and after adopting a pair, propeller rotating shaft is fuselage axis, and dynamical system is placed in machine Inside body.The coaxial wing root stress concentration avoiding traditional wing nacelle motor plane of a pair anti-oar is it is ensured that wing upper and lower surface gas Flow for laminar flow, turn avoid the aircraft rolling moment that traditional single-blade aircraft is led to due to single-blade rotation.

(4) generally airplane avionics system consumes power source, and especially electric airplane is often short of power, loss of weight same When, avionics system often increases independent current source.Nonetheless, still suffer from avionics system energy hidden danger, the present invention adopts Photovoltaic charged+independent current source solves this problem.

(5) one aspect of the present invention wants light-high-strength rigidity complete machine structure, on the other hand wants solar energy to fill for system power supply Electricity, realizes this structure and function by the technique of photovoltaic module eyelid covering and honeycomb multiple material lamination.

Technical scheme is as follows:

Double oar double-vane deformable aircrafts before and after one kind, it is characterized by install two groups of midsetwings, rear blended wing-body before and after fuselage Structure；Double-vane has deformation mechanism in front and back, and front wing passes through turbine and worm and realizes rotation folding and unfolding with bevel gear reducing mechanism, and rear wing leads to Cross fixed axis gear and realize folding and retraction with planetary gear reducing mechanism；Whole machine adopts double oar drive mechanisms before and after fuselage, and power passes Dynamic system is located at fuselage interior, and head drives a pulling force propeller and one thrust propeller of tail-driving；Aircraft skin is adopted Answer material structure with photovoltaic, Wing-Body Configurations upper shell adopts the laminated of the multiple material of outer layer photovoltaic module+intermediate gelatine layer+internal layer honeycomb Structure；Undercarriage adopts pneumatic landing jack, and carries out folding and unfolding using electronic control cylinder, is placed in blended wing-body cabin and head Cabin.Specific as follows:

(1) present invention devises the total arrangement of before and after's double-vane, double oar and left and right twin vertical fin.As Fig. 1, front wing 1, rear wing 2 Rear wing is divided into rear outer wing and interior blended wing-body section two parts, vertical fin nacelle by double-vane before and after composition, twin vertical fin and its anterior nacelle It is connected as a single entity with interior blended wing-body section, after outer wingfold actuator and two, undercarriage hinge is located inside vertical fin nacelle, machine again Twin screw 5 before and after body, four hydroplanes 4 and the overall aerodynamic arrangement of twin vertical fin rear direction rudder 3.During flight, front wing 1 and rear wing 2 It is in the state of being in full swing, double-vane face is applied to low-speed heave-load cruise.During ground, such as Fig. 2, front wing 1 and rear wing 2 are in and receive completely The state of returning, reduces aeroplane span and rolls inertia.Before and after being somebody's turn to do, double-vane fuselage cross-section is little, and whole machine windage is little, and the big aerofoil of double-vane improves Lift, is especially suitable for spraying, the low speed big load operation such as manned, and in front and back double-vane can no horizontal tail or canard, double-vane has bigger Fore-and-aft control face, improves low-speed operations longitudinal controllability and safety.

(2) present invention adopts wing deformable in front and back, as needed adjustment lateral dimension and aircraft rolling inertia.On the one hand, Flight control system control rate instructs according to motor power, revolution speed of propeller, adjust automatically wing-folding and rotary actuator, Thus adjusting the span and the angle of sweep of front wing 1 and rear wing 2, and then adjust whole machine pneumatic efficiency, real-time Optimal ratio of lift over drag, realize becoming Fast cruise efficiency maximizes.On the other hand, the ground span is withdrawn completely and is also allowed for ground run, traction, carrying and store.Front wing 1 can realize front wing rotational deformation by the transmission of the turbine and worm of Fig. 8 and Bevel Gear Transmission, by bevel gear wheel 22, bevel pinion 23, Turbine 24 and worm screw 25 are constituted.Rear wing 2 can be combined wingfold after transmission is realized by the fixed shaft gear train of Fig. 9 and become with planet circular system Shape, by rear wing servomotor 26, pinion frame 27, left planetary gear 28, right planetary gear 30, rear wingfold driving gear 31 Constitute.

(3) dynamical system of the present invention does not adopt the double oar in left and right or four oar layouts, but finally adopts the double oar of frame head and tail Drive, such as Fig. 1, a pair of propeller 5 in front and back, arrow represents steering, this is the anti-oar of a pair of electric drive, the equal side of whole machine torque To cancelling out each other on the contrary, produce to whole machine direction equal in magnitude pulling force forward and thrust simultaneously, to this power arrangement, internal dynamic Force system adopts two schemes: 1), dynamical system be placed in inside head and tail cabin, independent dynamic before and after dual power supply+bi-motor Power drive system；2), it is placed in inside center fuselage compartment using power source, coaxial pair of drive powertrain system of single supply list motor.No By which kind of scheme, power weight and vibrations are all located in fuselage, compare wing nacelle power situation, power weight and vibrations are more Near aircraft axis, roll stability is good, and wing body junction stress concentration is less, and wing rigidity and intensity requirement are lower, Do not need rudder trim propeller produce from moment of torsion.

(4), all using independent lithium electricity secondary cell, photovoltaic is real-time for active force power supply of the present invention and avionics system power supply Power for avionics system and charge for its secondary cell.Before taking off, electrokinetic cell and avionics system battery rise It is full of before flying, capacity was determined by total power and cruising time.As Fig. 4, aircraft upper surface arranges photovoltaic module eyelid covering 8, using list (current photoelectric transformation efficiency is respectively monocrystal silicon 21%, unijunction GaAs 28%, multi-junction gallium arsenide for crystal silicon or the efficient assembly of GaAs 33%), whole of fuselage upper surface is non-once curved surface, whole mould molding, and upper surface of the airfoil is in the same manner.In this regard, in photovoltaic generation list During first Material growth, start to grow using curved substrate, realize curved surface photovoltaic generation unit, then adopt autoclave, pass through Evacuation, pressurization, heating technique make wing body multiple structure, finally overall laminated into type.Photovoltaic eyelid covering passes through photovoltaic controller (mppt) in parallel with avionics system secondary cell, it is avionics system battery real time charging, simultaneously for aviation electronics system System power supply, the avionics system working time can be made to exceed well over the power system operational time, prevent because secondary system battery unexpected Power-off leads to loss of data, such as communicating interrupt, out of control etc..

(5) wing body structure of the present invention adopts composite, such as Fig. 3 and Fig. 4.Fuselage wing upper shell adopts photovoltaic module to cover The laminated composite of skin 8+kevlar cellular board+multi-angle carbon fiber plate, photovoltaic module eyelid covering 8 is outside kevlar cellular board；Machine Body wing lower house, rib, spar, vertical fin and all rudder faces adopt multi-angle carbon fiber plate+kevlar cellular board+multi-angle carbon fine The multiple material laminar structure of plate, head hatchcover adopts the multiple material of glass, and undercarriage main load-bearing part, wing body chaining part and driving member are alloy Steel；Other functors, empty including before and after's undercarriage control motor or electronic control cylinder, wing deformation motor or electronic control cylinder, rubber Heart tire, airborne task device etc., during cruising condition, all functors are respectively positioned on inside body cabin, reduce resistance；

Summary, double-vane deformable in front and back is passed through in this invention, reduces aircraft lateral dimension, is easy to the cruise of aircraft speed change and ground Engineering, and adopt double-vane twin vertical fin, big aerofoil and control surface (rudder face) to realize aircraft low speed lift, high maneuverability.In front and back one Anti- oar, no entering and exhaust channel to electric drive, no air inlet is emission-free, and anti-oar drives the fuselage producing to cancel out each other from moment of torsion, and neutral Surface helix oar air-flow does not affect left and right wing laminar flow.Active force battery is powered for power drive system, independent secondary cell and photovoltaic Power for avionics system.Using the light structures of carbon fibre eyelid covering or the multiple material of photovoltaic eyelid covering+honeycomb, especially suitable low-speed heave-load Application, such as Agriculture, forestry And Animal Husbandry sprinkling, manned low-speed operations etc., cooperation highway landing can greatly reduce runway land used, opens the navigation or air flight beneficial to promoting Private Flight.

The technique effect of the present invention is as follows:

The monoplane of contrast same lift, this biplane fuselage cross-section and horizontal spanwise extent can reduce about 1/3, fuselage Windage reduces about 1/4, makes wingtip amount of deflection reduce half because double-vane rigidity improves, aeroelasticity convergence rate doubles；Double-vane Deformation is withdrawn so that whole machine lateral dimension is reduced to 1/3 when launching, and dramatically saves on horizontal space and rolling of vacillating now to the left, now to the right Inertia, hangar memory space is reduced into original 1/3, and transporting velocity and safety are expected to double；A pair of electricity of frame head and tail Drive anti-oar, anti-oar rotating speed is equal in front and back turns on the contrary, and torque equal direction is contrary, whole machine is not produced with additional rolling and turns round Square, prop-blast between two parties wing is flowed impact little, during low-speed operations, aerofoil surface air-flow remains laminar flow and depletion of QI Flow separation, dynamical system is located at fuselage interior, so that main screw lift is distributed closer to axis, rolling moment of inertia is less；Electronic Machine, without oxygen combustion, is not required to air intake duct, emission-free discharge, and noise is little, and photovoltaic is avionics system independent battery in real time Charge, by the tropic of cancer illumination time in Winter Solstice the weakest, the photovoltaic module of 20% photoelectric efficiency can meet avionics system daytime Voltage stabilizing in 4 hours is powered, and 30% photoelectric efficiency is powered up to voltage stabilizing in 5 hours, finally realizes low noise, environmental protection, safety cruise；Whole machine carbon Fibre and cellular composite material main structure, with all aluminium alloy Structure Comparison, complete machine structure weight saving 1/3, cruising time improves one Times.

Brief description

Fig. 1 is the wing evolutionary operation figure of the present invention；

Fig. 2 is the wing deformation storage figure of the present invention；

Fig. 3 is the multiple material layout drawing of honeycomb of the present invention；

Fig. 4 is the photovoltaic module laying figure of the present invention；

Fig. 5 is the flight operation track figure of the present invention；

Fig. 6 is the wing body structure lamination figure of the present invention；

Fig. 7 is the landing radio and tape player composition of the present invention；

Fig. 8 is the front wing Principle of Rotating figure of the present invention；

Fig. 9 is the rear wing folding principle figure of the present invention；

Figure 10 is the power drive conceptual scheme of the present invention.

In Fig. 1 ~ Figure 10, front wing (1), rear wing (2), rudder (3), hydroplane (4), propeller (5), undercarriage (6), honeybee Gear film (13) after the multiple material (7) of nest, photovoltaic module eyelid covering (8), photovoltaic front film (9), photovoltaic generation unit (11), photovoltaic, Kevlar cellular board (15), glue-line (10) (12) (14) (16), multi-angle carbon fiber plate (17), front electronic control cylinder (18), front buffering Device (19), rear electronic control cylinder (20), posterior bumper (21), bevel gear wheel (22), bevel pinion (23), turbine (24), worm screw (25), rear wing servomotor (26), pinion frame (27), left planetary gear (28), right planetary gear (30), rear wingfold are driven Moving gear (31), single shaft power motor (32), electrokinetic cell (33), double-shaft power motor (34), front line shaft (35), rear power Axle (36), needle roller gear (37), needle roller gear pedestal (38).

Specific embodiment

A, b, c, d and e in concrete flight operation track, such as Fig. 5, and with reference to Fig. 1 and Fig. 2.A)-outbound is slided, before sliding race Wing launches deformation, and, with wing root for axle longitudinal direction rotary expansion, (interior blended wing-body section is fixing not for the laterally folded expansion of rear wing 2 for front wing 1 Become), the anti-oar of a pair of frame head and tail drives, and parameter is equal in magnitude in opposite direction, produces aircraft thrust forward and pulling force, before promotion 3 points of undercarriage 6 accelerated slips, the big aerofoil of double-vane can provide low speed lift, overcome main screw lift to leave ground.B)-aircraft rises Fly, undercarriage 6 sensing no pressure after ten seconds, receive to head cabin, and after two, undercarriage is symmetrically received to blended wing-body by nose-gear forward Cabin, reduces windage, and the rich lift that double-vane produces persistently is mushed, and during adjustment sporting flying parameter, left and right deflects water in the same direction Flat rudder 4(function is equivalent to elevator or the canard of conventional airplane), control aircraft longitudinal attitude, luffing speed and acceleration, left Right reversely deflection level rudder 4(function is equivalent to conventional airplane aileron), control aircraft rolling speed and acceleration, deflect double in the same direction Vertical fin rudder 3, controls aircraft lateral attitude, speed and acceleration.C)-flight cruise, when reaching a certain height with speed, flies Machine enters low cruise state, mission payload normal work, and the big aerofoil of double-vane provides low speed lift, the big manipulation of double-vane twin vertical fin Face quickly adjusts flight attitude.When needing to accelerate cruise, power accelerates, and front wing rotation becomes sweepback angle, and rear wing becomes outer wing folding Folded angle, can enter quick cruising condition.D)-aircraft landing, in face of jump area, aircraft extreme span cruises, and align runway, rises and falls Frame 6 all puts down, and propeller 5 slows down, and four hydroplanes 4 and the whole full-helm of both direction rudder 3 serve as flap, increase windage fast Speed is slowed down.E)-landing ground, after aircraft landing, propeller zero power, hydroplane and rudder holding full-helm continuation increase resistance Slow down, landing gear wheel brake deceleration simultaneously, reduces runway distance, after shutdown, front wing rotation rear wing folded deformation is contracted to Little lateral dimension or minimum rotation inertia state, improve ground lateral stability, prevent from, because of ground injustice aircraft lateral tilt, rising Fall the wheel electric running of frame 6 or quickly put in storage with tractor.

Concrete wing body structure lamination, such as Fig. 6, fuselage and wing upper shell adopt multiple 7 layers of the material of photovoltaic module eyelid covering 8 and honeycomb The mode of pressure, wherein photovoltaic module eyelid covering 8 are kept off after including photovoltaic front film 9, photovoltaic generation unit 11, glue-line 10,12 and photovoltaic Film 13, the multiple material 7 of honeycomb includes kevlar cellular board 15, glue-line 16 and multi-angle carbon fiber plate 17.Fuselage wing upper shell structure is adopted Completed with three moulding processs, particularly as follows: first time molding, using substrate life in large-scale mocvd equipment of non-once curved surface Grow up to fuselage or single wing photovoltaic generation unit 11, for the possible state space of general mocvd equipment not, can adopt and first will This curved surface is divided into many substrate growth of many curved surfaces, after several pieces of generator unit interconnected are completed photovoltaic generation unit 11, then 9,10,11,12,13 are put between upper and lower curve mold, encapsulated photovoltaic module eyelid covering is completed using photovoltaic module lamination 8.Second molding, carries out stretching honeycomb using super thick kevlar plate, cuts further according to numerical control milling or heat and be processed into kevlar honeybee Nest plate 15, multi-angle carbon fiber plate 17 is formed or solidified by numerical control woven carbon fibers prepreg by the lamination solidification of multi-disc multi-angle carbon fiber cloth Form, then adopt autoclave, by evacuation, pressurization, heating technique, kevlar cellular board 15, glue-line 16 and multi-angle carbon is fine Plate 17 is laminated into the multiple material 7 of honeycomb.Third time molding, because front laminating temperature twice is different with pressure, molding twice before institute divides Secondary complete the multiple material 7 of outer layer photovoltaic module eyelid covering 8 and internal layer honeycomb, finally again by photovoltaic module eyelid covering 8, intermediate gelatine layer 14, honeycomb Multiple material 7 low pressure curing type at normal temperatures, completes single wing upper shell structure, other wings and fuselage (blended wing-body section after inclusion) Upper shell structural manufacturing process is identical with this.Fuselage wing lower house and rudder face integrally adopt multi-angle carbon fiber plate+glue-line+kevlar honeybee The symmetrical lamination structure of nest plate+glue-line+multi-angle carbon fiber plate, ibid second molding and third time molding are (polygonal for concrete technology Degree carbon fiber plate replaces photovoltaic module eyelid covering).

Concrete landing jack, such as Fig. 7, x-axis is the public rotating shaft of before and after's propeller, on the aircraft plane of symmetry and machine Inside body, y-axis is the line (intersecting vertically with x-axis) of rear undercarriage hinge centres, positioned at rear blended wing-body section and fuselage interior, Undercarriage hinge centres are located on vertical fin nacelle inside and vertical fin stabilization afterwards, and nose-gear hinge is located in x-axis, in x, y-axis Undercarriage hinge position maintains static relative to fuselage with cylinder hinge position.The folding and unfolding of undercarriage pass through front electronic control cylinder 18 and after Realizing, electronic control cylinder executes gear up and puts down electronic control cylinder 20 as needed, contrasts conventional hydraulic landing, pneumatic letter Single quick, control easily, very big loss of weight, save energy.When taking off liftoff, anterior bumper 19 and posterior bumper 21 are not only It is only used for landing and ground run damping, goes back induction pressure signal and buffering displacement signal, two pulse signals carry out logical AND Computing is liftoff signal, flight control computer confirm liftoff signal after time delay more than 10s, and after reaching safe altitude of taking off, just electric Control cylinder 18 and 20, cylinder rod is whole in the direction of the arrow to be withdrawn, gear up, and nose-gear is received forward to head cabin, two Undercarriage is symmetrically received to blended wing-body cabin afterwards.When aircraft will land, electronic control cylinder 18 and 20, cylinder rod is whole in the direction of the arrow Stretch out, gear down, prepare landing.

Concrete front wing Principle of Rotating, such as Fig. 8, is the interior views that slave Caudad head is seen.Motor is located in fuselage Facade, motor shaft passes through shaft coupling with worm screw 25 grade ratio transmission, and worm screw 25 is engaged with turbine 24, and gear ratio is i₁=100, turbine 24 pass through spline transmitting torque, and two bevel pinions 23 are fixed at turbine 24 place rotating shaft two ends, and bevel pinion 23 is big with front wing rotating shaft Bevel gear 22 engages, and gear ratio is i₂=2, resultant gear ratio i=i₁×i₂=200, it is solid that bearing is passed through at all gear places rotating shaft two ends Due to fuselage.Operation principle: 1), controlled motor according to wing launch instruction be driven forward, motor speed and the time as needed Adjustable, then front wing expansion is realized by this double reduction drive mechanism.2), controlled motor stops turning according to wing fixed instruction Dynamic, front wing aerodynamic moment passes to bevel gear wheel 22 by rotating shaft, and bevel gear wheel 22 passes through this secondary drive mechanism again and realizes subtracting Turn round, pass to worm screw 25, because turbine and worm driven Design is reverse self-locking, so wing aerodynamic moment of torsion rotation reverse self-locking.3), Controlled motor withdraws instruction according to wing and is driven reverse, then realizes front wing withdrawal by this two reduction gear.

Concrete rear wing folding principle, such as Fig. 9, it is right that upper left rear wing 2 folds wingfold driving gear 31 after shown arrow is Arrow shown in side, the motor decelerating mechanism that the folding system of rear wing 2 passes through in vertical fin cabin is realized, and left and right rear wing folding system is only Vertical.Wingfold transmission after specifically: rear wing servomotor 26, through two reduction gear (figure left two is to gear), secondary transmission ratio For i₁=4, by Motor torque amplification, 4 times pass to pinion frame 27, and tooth rest 27 is again through planetary gear speed reducing mechanism, wherein left Planetary gear 28 and right planetary gear 30 coaxial be one group, pinion frame 27 links four groups of planetary gears, left planetary gear altogether The 28(number of teeth 30) with the fixed gear 29(number of teeth 29 in vertical fin cabin) engage, the right planetary gear 30(number of teeth 31) drive with rear wingfold The gear 31(number of teeth 30) engagement, planetary drive ratio is i₂=(30 × 30)/(30 × 30-29 × 31)=900, planetary gear speed reducing mechanism The moment of torsion of tooth rest 27 is amplified 900 times and passes to rear wingfold driving gear 31, resultant gear ratio i=i₁×i₂=3600, after realization The upset of the wing 2 low-speed big folds.For example as motor speed 1800rpm, rear wing 2 launches or the speed that folds is 0.5rpm, Rear wing launches or folds θ degree required time is that θ/6 second deform 120 degree it is assumed that rear wing is whole, and required time is the 120/6=20 second, That is need servo-controlled motor to rotate 20 seconds under 3600rpm and can complete the whole deformation of rear wing, if it is desired to after changing Wing deformation velocity, gear ratio is constant, controls servomotor rotating speed.Launch in figure dotted line level when wing 2 is fully deployed Position, in ground run, traction and storage, needs the outer panel of rear wing 2 to be flipped up whole angle from horizontal deployed position To figure upper left solid line folding position.During aerial cruising flight, usual left and right rear wing deformation parameter identical (wing expanded angle and speed Degree), to ensure the full symmetric favourable cruise of left and right aerodynamic configuration.In the air during maneuvering flight, because of left and right rear wing folding system phase Mutually independent, whole machine passes through rudder 3 and hydroplane 4 changes attitude, also by controlling the asymmetric folding of left and right rear wing 2, realizes left The asymmetric regulation of right aerodynamic configuration, combination controls aircraft pitch, driftage and rolling.

Concrete power drive scheme, such as Figure 10, two kinds of power schemes shown in figure, the first scheme (position on Figure 10) is Using the power scheme of the double oar of bi-motor, frame head and tail respectively arranges a single shaft power motor 32, and parameter is identical, power Battery 33 reclines fuselage bottom beneficial to fuselage stably, controls bi-motor using same controller, drives former and later two propellers 5 (a pair anti-oar, the parameter of former and later two propellers is equal in magnitude in opposite direction), rotating speed and whole machine torque equal direction phase Instead, produce to fuselage push-pull effort forward.Second scheme (in Figure 10 and lower position) is the power side using single-motor double oar Case, it is anterior that double-shaft power motor 34 is located at head, respectively forwardly and backward transmitting torque, twin shaft be same axle i.e. before line shaft 35, front line shaft 35 delivers torque to rear line shaft 36, concrete partial enlarged drawing a and its sectional view by tail deviator B-b, external tooth wheel shaft (number of teeth 100) is processed in front line shaft 35 rear end, and the inner gear shaft (number of teeth is processed in rear line shaft 36 front end 120), on needle roller gear pedestal 38, needle roller gear pedestal 38 is fixed in fuselage and keeps 12 needle rollers needle roller gear 37 Gear 37 is fixed axis gear power train, front line shaft 35 and the needle roller gear 37(number of teeth 10) external toothing, needle roller gear 37 is dynamic with rear Power axle 36 internal messing, before and after realization, line shaft rotates coaxially and turns to contrary, and the rotating speed of rear drive shaft 36 and moment of torsion depend on rolling Pin gear reference diameter, needle roller gear compound graduation circular diameter is less, and rotating speed and moment of torsion are about close in front and back, based on this example number of teeth Calculate, front propeller rotating speed is 120/100=1.2 times (rotating speed moment of torsion is contrary) of rear screw shaft rotating speed, realizes a double-shaft power electricity Machine 34 drive before and after a pair of counterpropeller 5, produce to fuselage thrust forward and pulling force.

Claims (1)

1. double oar double-vane deformable aircrafts before and after one kind, it is characterized by installing two groups of midsetwings before and after fuselage, rear blended wing-body knot Structure；Double-vane has deformation mechanism in front and back, and front wing passes through turbine and worm and realizes rotation folding and unfolding with bevel gear reducing mechanism, and rear wing passes through Fixed axis gear and planetary gear reducing mechanism realize folding and retraction；Whole machine adopts double oar drive mechanisms before and after fuselage, power transmission System is located at fuselage interior, and head drives a pulling force propeller and one thrust propeller of tail-driving；Aircraft skin adopts The multiple material structure of photovoltaic, Wing-Body Configurations upper shell adopts the laminated knot of the multiple material of outer layer photovoltaic module+intermediate gelatine layer+internal layer honeycomb Structure；Undercarriage adopts pneumatic landing jack, and carries out folding and unfolding using electronic control cylinder, is placed in blended wing-body cabin and head Cabin.