CN219790515U - Co-rotating vertical take-off and landing film wing aircraft - Google Patents

Abstract

The utility model discloses a co-rotating vertical take-off and landing film wing aircraft, which comprises a fuselage, wherein at least two rows of power wing spars are rotatably connected to the fuselage, and a propeller is arranged on each row of power wing spar; a film wing which is rotationally connected with the machine body is arranged between the adjacent power wing beams; the middle part of the film wing is provided with a folding angle adjusting mechanism; the machine body is provided with a linkage operation device which enables the film wing and the power wing spar to synchronously rotate relative to the machine body. The co-rotating vertical take-off and landing film wing aircraft provided by the utility model has the advantages of simple operation of switching between a lifting state and a flying state, large speed range and low energy consumption.

Description

Co-rotating vertical take-off and landing film wing aircraft

Technical Field

The utility model relates to the field of traffic equipment for providing air transportation service, in particular to a co-rotating vertical take-off and landing film wing aircraft.

Background

The existing aircraft are various in variety according to different classification methods, and are mainly divided into two types according to take-off and landing modes, namely running take-off and landing and vertical take-off and landing. Among them, fixed wing aircraft such as passenger aircraft use roll landing, while helicopter such as helicopter use vertical landing. However, fixed-wing aircraft and propeller-wing aircraft suffer from the following disadvantages:

1) Existing aircraft have a substantially fixed association: the fixed wing aircraft has to adopt a running take-off and landing mode because the orientations of the wings and the engines are fixed; the propeller aircraft has no wings, a vertical take-off and landing mode is needed, and the difficulty of the vertical take-off and landing or the sliding take-off and landing technology of the fixed-wing aircraft is very high;

2) Fixed wing aircraft have high requirements on landing sites, and usually require fixed airports for landing; because the wing and the engine are fixed in orientation, and the speed is low when the aircraft is lifted, the wing with a larger span is required to obtain enough climbing force, and the dead weight is also large;

3) Fixed wing aircraft can hardly safely land once losing power or special conditions such as landing gear failure, forced landing under airport failure and the like

4) The flight of the propeller-type aircraft completely depends on the lift force and the forward power generated by the propeller, so that the rotor wing is huge, and the energy consumption and the noise are also great

5) Helicopter, such as a helicopter, with large rotors providing lift and small rotors at the tail counteracting torsion, and when any rotor fails, it is difficult to safely land and the risk is high

6) The effective area of the lower surface of the wing of the fixed-wing aircraft is fixed, and when the aircraft reaches a certain speed, if the speed is further increased, the fixed-wing aircraft is difficult to maintain at the same height because the speed is in direct proportion to the lifting force.

The prior art scheme capable of solving the problems cannot be searched at present, so the inventor designs a co-rotating vertical take-off and landing film wing aircraft, because a power wing spar provided with a propeller and a film wing can synchronously rotate through a linkage operation device, the aircraft only provides lifting force when in vertical lifting, and provides lifting force mainly through the film wing when in flying from take-off, landing and cruising speed, the propeller provides forward thrust, the required film wing has smaller wing spread, the weight is light, the propeller does not need to work with larger power for most of the time, the noise is smaller, the energy consumption is low, and the aircraft can lift vertically and also slide to take-off and land, and the safety is high. In addition, when the flying wants to further increase the speed, the film wing can be folded at a certain angle through the folding angle adjusting mechanism, so that the effective area of the lower surface of the film wing is reduced, and even if the speed is increased, the further increase of the flying height of the airplane can be avoided.

Disclosure of Invention

The utility model aims to provide a co-rotating vertical take-off and landing film wing aircraft, which is simple in operation of switching between a lifting state and a flying state, wide in speed range and low in energy consumption.

In order to achieve the above purpose, the utility model provides a co-rotating vertical take-off and landing film wing aircraft, which comprises a fuselage, wherein at least two rows of power wing beams are rotatably connected to the fuselage, and a propeller is arranged on each row of power wing beams; a film wing which is rotationally connected with the machine body is arranged between the adjacent power wing beams; the middle part of the film wing is provided with a folding angle adjusting mechanism; the machine body is provided with a linkage operation device which enables the film wing and the power wing spar to synchronously rotate relative to the machine body.

As a further improvement of the utility model, the membrane wing comprises a membrane wing beam and a plurality of membrane wing plates, wherein the membrane wing beam comprises at least two sections of membrane wing beam modules which are arranged along the direction of the membrane wing span, and the membrane wing plates are arranged on the membrane wing beam modules; the folding angle adjusting mechanism is connected between the adjacent membrane wing beam modules.

As a further improvement of the utility model, the adjacent membrane wing beam modules are rotationally connected through a first bearing; the folding angle adjusting mechanism comprises a driving mechanism, a linear translation structure and a rotary connecting rod which are sequentially linked; one end of the rotating connecting rod is rotationally connected with one of the membrane wing beam modules through a second bearing, the other end of the rotating connecting rod is rotationally connected with a linear translation structure positioned on the other membrane wing beam module through a third bearing, and the linear translation structure is movably matched with the membrane wing beam module.

As a further improvement of the utility model, the driving mechanism and the linear translation structure are arranged on the same membrane wing beam module, the driving mechanism comprises a motor, a reduction gear set and a power screw sleeve which are sequentially linked, the outer side wall of the power screw sleeve is linked with the reduction gear set through a gear structure, and the power screw sleeve is rotationally connected with the membrane wing beam module; the linear translation structure is a push-pull screw rod, and the power spiral sleeve is sleeved outside the push-pull screw rod and is in threaded fit with the push-pull screw rod.

As a further improvement of the utility model, one of the membrane wing beam modules of the membrane wing is a fixed membrane wing beam module which is connected with the machine body in a rotating way; the linkage operation device comprises an operation part and a inhaul cable which are linked, and further comprises a power spar co-rotating transmission disc and a film spar co-rotating transmission disc which are sleeved with the inhaul cable; the power wing beam module is fixedly connected with the power wing beam, and the film wing beam module is fixedly connected with the power wing beam co-rotating transmission disc.

As a further improvement of the utility model, at least two rows of film wings which are rotationally connected with the machine body are arranged between the adjacent power wing beams; each row of film wings is linked with the power wing beam through a linkage operation device.

As a further improvement of the utility model, one of the membrane wing beam modules of the membrane wing is a fixed membrane wing beam module, and the fixed membrane wing beam module of the membrane wing is rotationally connected with the machine body; the linkage operation device comprises an operation part and a inhaul cable which are linked, and further comprises a power spar co-rotating transmission disc and a film spar co-rotating transmission disc which are sleeved with the inhaul cable; the power wing beam co-rotating transmission disc is fixedly connected with the power wing beam; the film wing beam module is linked with the fixed film wing beam modules of the other rows of film wings through a connecting rod mechanism.

As a further improvement of the utility model, the connecting rod mechanism comprises a swing arm and a linkage rod, wherein the swing arm is fixedly arranged on each fixed film wing beam module, and the linkage rod is rotationally connected with each swing arm.

As a further improvement of the utility model, the operation part of the linkage operation device comprises a control box shell and a control handle which are rotationally connected through a fixed shaft, wherein a chute is arranged on the control box shell, and a sliding rack is connected on the chute in a sliding way; the inhaul cable is connected with the sliding rack; the control handle is provided with an arc transmission gear meshed with the sliding rack; a handle in-place clamping structure is arranged between the control handle and the control box shell.

As a further improvement of the utility model, the middle part of the power wing spar is provided with a folding structure; wheels are arranged at the bottom of the machine body; the back of the machine body is provided with a tail rotor, the tail rotor is arranged on a tail rotor rotating arm, the tail rotor rotating arm is rotationally connected with the machine body, and the machine body is provided with a second operation part which is linked with the tail rotor rotating arm; a plurality of propellers are arranged on each row of power wing beams.

Advantageous effects

Compared with the prior art, the co-rotating vertical take-off and landing film wing aircraft has the advantages that:

1. the middle part of the film wing is provided with a folding angle adjusting mechanism. During low-speed states such as climbing and gliding of an aircraft, a larger lifting force is required to ensure the stability of the aircraft, and the spanwise opening area of the film is maximum; when the aircraft enters a cruising flight state at a certain height, the membrane wings are folded at a certain angle, and the aircraft can fly at the same height even if the flying speed is further increased, and can not continuously climb due to the fact that the lifting force is increased due to the increase of the speed, so that the flying speed in the cruising state is improved, and the energy consumption is low. In addition, the partially folded film wings can also provide lateral stability to the aircraft at high speeds.

2. When the airplane is switched among the states of lifting, climbing, gliding, cruising and flying, the film wing and the power wing spar can synchronously rotate relative to the airplane body through the linkage operation device, so that the airplane flies by obtaining thrust in the corresponding direction, the operation is simple, a driver does not need to carry out complex operation, the popularization of the co-rotating vertical take-off and landing film wing airplane in the civil field is facilitated, and the training time of the driver is shortened.

3. The angle adjustment is realized through the actuating mechanism, the straight line translation structure and the rotation connecting rod that are equipped with in proper order between the adjacent membrane wing crossbeam module, simple structure, job stabilization is difficult to damage. The linear translation structure is a push-pull screw, the power spiral sleeve is sleeved outside the push-pull screw and is in threaded fit with the push-pull screw, and the precision is higher during adjustment. Because the acting force of air to the membrane wing is big, can reduce the demand to motor torsion through setting up reduction gear set, reduce the impact force to the motor, prolong the life of motor.

4. The membrane wing cross beam and the power wing beam are linked through the operation part, the inhaul cable, the power wing beam co-rotating transmission disc and the membrane wing beam co-rotating transmission disc, so that the structure is simple, and the work is stable.

5. At least two rows of film wings connected with the machine body in a rotating way are arranged between the adjacent power wing beams, and each film wing can be folded, so that the optional cruising speed is increased, and the most economical energy consumption is obtained.

6. The middle part of the power wing spar is provided with a folding structure, and the folding structure is matched with the folding of the film wings, so that the occupied area can be reduced, and the storage is convenient.

7. The power wing spar is provided with a plurality of propellers, the power of each propeller is low, the noise is low, the balance of the aircraft is not seriously affected even if one of the propellers is damaged, the aircraft still keeps certain stability, and the aircraft can safely land for a sufficient time.

The utility model will become more apparent from the following description taken in conjunction with the accompanying drawings which illustrate embodiments of the utility model.

Drawings

In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a top view of a co-rotating vertical takeoff and landing membrane wing aircraft in a lifted condition;

FIG. 2 is a left side view of a co-rotating vertical takeoff and landing membrane wing aircraft in a raised and lowered condition;

FIG. 3 is a front view of a co-rotating vertical takeoff and landing membrane wing aircraft in a raised and lowered condition;

FIG. 4 is one of the top views of a co-rotating vertical takeoff and landing membrane wing aircraft in flight;

FIG. 5 is one of the front views of a co-rotating vertical takeoff and landing membrane wing aircraft in flight;

FIG. 6 is a second top view of a co-rotating vertical takeoff and landing membrane wing aircraft in flight;

FIG. 7 is a second front view of a co-rotating vertical takeoff and landing membrane wing aircraft in flight;

FIG. 8 is a second left side view of a co-rotating vertical takeoff and landing membrane wing aircraft in flight;

FIG. 9 is a left side view of a co-rotating vertical takeoff and landing membrane wing aircraft when in storage;

FIG. 10 is a partial top view of a membrane airfoil beam;

FIG. 11 is a cross-sectional view of a fold angle adjustment mechanism on a membrane flap beam;

FIG. 12 is a schematic partial cross-sectional view of a membrane airfoil beam;

FIG. 13 is a folded state of the membrane flap beam;

FIG. 14 is an expanded state of the membrane flap beam;

FIG. 15 is a front cross-sectional view of the linkage operation device;

FIG. 16 is a top view of the linkage operation device;

FIG. 17 is a view of a fold angle adjustment mechanism and linkage operator arrangement on a membrane flap;

FIG. 18 is a front view of the linkage;

FIG. 19 is a schematic diagram of a swing arm of the linkage;

fig. 20 is a simulated flight process attitude change diagram.

Detailed Description

Embodiments of the present utility model will now be described with reference to the accompanying drawings.

Examples

The embodiment of the utility model is shown in fig. 1 to 20, and a co-rotating vertical take-off and landing film wing aircraft comprises a fuselage 1 adopting an aluminum alloy shell, wherein at least two rows of power spars 2 are rotatably connected to the fuselage 1, and a propeller 3 is arranged on each row of power spars 2. A membrane wing 4 which is rotationally connected with the machine body 1 is arranged between the adjacent power wing beams 2. The middle part of the film wing 4 is provided with a folding angle adjusting mechanism 6. The fuselage 1 is provided with a linkage operation device 7 for synchronously rotating the membrane wing 4 and the power spar 2 relative to the fuselage 1. The machine body 1 is provided with a front glass 11, a rear glass 12 and an organic glass door 13. The fuselage 1 comprises a wing support 14, each membrane 4 being rotatably connected to the wing support 14. The body 1 is internally provided with a high-energy battery for providing power.

The membrane wing 4 comprises a membrane wing cross beam and a number of membrane wings 46, the membrane wing cross beam comprising at least two sections of membrane wing cross beam modules arranged in the spanwise direction of the membrane wing 4, the membrane wings 46 being arranged on the membrane wing cross beam modules. The folding angle adjusting mechanism 6 is connected between the adjacent membrane wing beam modules. In this embodiment, the portion of each row of membrane wings 4 located on one side of the fuselage 1 includes two sections of membrane wing beam modules, namely a fixed membrane wing beam module 43 and a folded membrane wing beam module 44. The membrane flaps 46 are light-frame outer carbon fiber membrane flaps. The fixed film wing beam module 43 penetrates the upper part of the wing bracket 14 and is rotatably connected with the fixed film wing beam module through a bearing. The outer side of the fixed film wing beam module 43 is fixed with a film wing 46, which forms a middle film wing 40 positioned above the fuselage 1 and first outer film wings 41 positioned on two sides of the fuselage 1, the outer side of the folding film wing beam module 44 is fixed with a film wing 46, which forms a second outer film wing 42, and the lengths of the first outer film wing 41 and the second outer film wing 42 are basically the same.

The fixed film wing beam module 43 and the folding film wing beam module 44 are rotatably connected through a first bearing 45. The folding angle adjusting mechanism 6 includes a driving mechanism, a linear translation structure, and a rotation link 66 that are linked in sequence. One end of the rotating connecting rod 66 is rotationally connected with the folding membrane wing beam module 44 through a second bearing 661, and the other end of the rotating connecting rod 66 is rotationally connected with a linear translation structure positioned on the fixed membrane wing beam module 43 through a third bearing 662, and the linear translation structure is movably matched with the fixed membrane wing beam module 43.

In this embodiment, the driving mechanism and the linear translation structure are disposed on the fixed membrane wing beam module 43, and the driving mechanism includes a motor 61, a reduction gear set 62 and a power screw sleeve 63 that are sequentially linked, and the outer side wall of the power screw sleeve 63 is linked with the reduction gear set 62 through a gear structure, and the power screw sleeve 63 is rotationally connected with the fixed membrane wing beam module 43. Wherein, the reduction gear set 62 and the power screw sleeve 63 are both installed in the fixed film wing beam module 43 through the matched structure shell 65, and the fixed film wing beam module 43 is provided with an access cover plate 46. The linear translation structure is a push-pull screw 64, and a power screw sleeve 63 is sleeved outside the push-pull screw 64 and is in threaded fit with the push-pull screw 64. In addition, the driving mechanism and the linear translation structure can be replaced by an air cylinder or a linear motor.

The linkage operation device 7 comprises an operation part and a stay cable 73 which are linked, and further comprises a power spar co-rotating transmission disc 71 and a film spar co-rotating transmission disc 72 which are sleeved with the stay cable 73. The stay 73 is fixedly connected with the power spar co-rotating drive disc 71 by a first screw 711, and the stay 73 is fixedly connected with the film spar co-rotating drive disc 72 by a second screw 721. After passing around the power spar co-rotating drive disc 71 or the film spar co-rotating drive disc 72, the guy cable 73 is slidably passed through the fixed support 78 via the guide pulley 74. The guide pulley 74 and the fixed mount 78 are both mounted within the fuselage 1.

The power spar co-rotating drive disc 71 is fixedly connected with the power spar 2 with the rotation axis. When the membrane wings 4 are in a row, the membrane spar co-rotating drive disc 72 is fixedly connected with the fixed membrane wing beam module 43 with the rotation axis. In this embodiment, at least two rows, specifically three rows, of film wings 4 rotatably connected to the fuselage 1 are provided between adjacent power spars 2. Each row of film wings 4 is linked with the power spar 2 through a linkage operation device 7. The film spar co-rotating driving disc 72 is fixedly connected with the fixed film wing beam module 43 of one row (the first row in the embodiment) of film wings 4, and the fixed film wing beam module 43 is linked with the fixed film wing beam modules 43 of the other two rows of film wings 4 through a link mechanism 79.

The link mechanism 79 includes a swing arm 791 and a linkage rod 792, the swing arm 791 is fixedly installed on each fixed film wing beam module 43, and the linkage rod 792 is two and is respectively connected with two ends of each swing arm 791 in a rotating way.

The operation part of the linkage operation device 7 comprises a control box shell 76 and a control handle 75 which are rotationally connected through a fixed shaft 751, a sliding groove 761 is arranged at the bottom of the control box shell 76, and a sliding rack 77 is connected on the sliding groove 761 in a sliding manner. Both ends of the stay 73 are connected with both ends of the sliding rack 77 by bolts. The control handle 75 is provided with a circular arc transmission gear 753 meshed with the sliding rack 77. A handle in-place clamping structure is arranged between the control handle 75 and the control box shell 76, and specifically comprises an elastic clamping device 752 arranged on the control handle 75 and a plurality of clamping points 762 corresponding to different gears arranged on the control box shell 76, wherein the elastic clamping device 752 is in concave-convex fit with the clamping points 762. Different clamping points 762 correspond to different angles of rotation of the membrane wing 4 and the power spar 2. In this embodiment, from-15 ° to 105 °, every 15 ° is a gear. The membrane wing 4 and the power spar 2 can be operated to rotate synchronously relative to the fuselage 1 by swinging the control handle 75.

The middle part of the power wing spar 2 is provided with a folding structure, and the folding structure is convenient for warehouse entry after folding. Wheels 9 are arranged at the bottom of the machine body 1, and the wheels 9 can be hidden in the machine body 1 after the aircraft takes off. The back of the machine body 1 is provided with a tail rotor 5, the tail rotor 5 is arranged on a tail rotor rotating arm 8, the tail rotor rotating arm 8 is rotationally connected with the machine body 1, and the machine body 1 is provided with a second operation part linked with the tail rotor rotating arm 8. By rotating the tail rotor rotating arm 8, the tail rotor 5 can be directed to the left or right, so that the aircraft can be steered. A plurality of propellers 3 are mounted on each row of power spars 2, in this embodiment, 24 propellers 3 are used for two rows of power spars 2, and propellers 3 are disposed on the upper side and the lower side of the power spars 2.

The co-rotating vertical take-off and landing film wing aircraft comprehensively considers the advantages and disadvantages of various existing aircrafts, and is designed on the premise that the prior technological capability is feasible:

1. breaking the fixed association (fixed wing-rolloff and landing, rotor wing-vertical landing) spells: the helicopter can climb and cruise like a helicopter-like take-off and landing, and can slide and descend like a fixed-wing aircraft.

2. Breaks through the complicated huge incompatible difficult points of the existing fixed wings and propeller wings: the novel film wings (foldable and rotatable) and a plurality of electric-driven propeller engines (rotatable) are adopted, so that a large space is provided for the layout and function expansion of the appearance of the aircraft; meanwhile, the aircraft is more flexible, the safety is higher, and the noise is greatly reduced.

3. Reasonable fuselage arrangement effectively ensures the stability of flight and the safety of special conditions, and thoroughly eradicates the mutual interference of the propeller engine and the membrane wings.

4. Unique designs of a co-rotating system of the power wing spar and the film wing, a tail rotor control system, a folding system of the film wing, manual folding of the power wing spar, automatic telescoping of the wheel legs and the like give an aircraft excellent control performance.

5. The performance of the materials and parts related to the existing high-energy battery, high-strength aluminum alloy aviation material, electric-driven propeller engine, high-strength membrane material and the like can completely meet the design requirement.

In conclusion, the co-rotating vertical take-off and landing film wing aircraft can achieve superior low-altitude (below 1000 m) performance, moderate manufacturing cost, powerful safety guarantee and convenient use and maintenance. Can be used as a man-machine or an unmanned aerial vehicle, and is popularized among common people.

Because the position of the film wing 4 is higher than that of the power wing spar 2, even when special conditions in the air occur and even power is completely lost, the film wing 4 can be completely unfolded like a huge parachute by virtue of the stabilizing effect of the gravity center, and the man-machine safety can be ensured if the falling point is the water surface or the flat ground under the condition that the battery pack is abandoned as much as possible.

The principle of the co-rotating vertical take-off and landing film wing aircraft is as follows:

1. wing function singleization—only to provide lift. The stress working condition of the wing is simple, so that the wing can adopt an ultralight structure of a light framework and a film, and the folding and rotating functions of the film wing can be well realized.

2. The engine is arranged on the power wing spar, and the stress working condition of the power wing spar is simple, so that the power wing spar can easily realize the rotation and folding functions.

3. The power wing spar and the wing are staggered, so that the mutual influence of the engine and the wing when the respective functions are exerted is avoided.

4. Multiple engines are employed to reduce noise and improve safety.

5. Large spans are employed to achieve low-altitude economy and to improve safety.

6. The adoption of the active tail rotor system makes the aircraft easier to operate.

7. The power wing beam and the film wing realize single control and synchronous corotation, so that the engine and the film wing are always in the optimal cooperative state, and the control is simple.

8. The co-rotating vertical take-off and landing membrane wing aircraft should take off and land like a helicopter, climb and cruise like a fixed wing aircraft, slide down like a power glider, and take off and land on the water surface in an emergency.

Details of the scheme are described below:

1. the membrane wing consists of a main beam and a high tensile membrane material covered outside a light framework, and mainly provides the lifting force required by air flight.

The main beam and the light framework are made of light metal materials with good performances (bending resistance, shearing resistance, torsion resistance and the like), and high-strength aluminum alloy aviation materials are generally adopted.

The membrane material is preferably a carbon fiber membrane, and the carbon fiber has excellent tensile property, and the tensile strength of the carbon fiber membrane is about 5000MPa on average and is 10 times that of steel (about 400MPa on average). The tensile strength of the carbon fiber membrane is more than Zhuo Zhuoyou, and the carbon fiber is very light, so the carbon fiber membrane is regarded as the first choice; ultrathin high-strength aluminum alloy plates and other light high-tensile films can be selected as a secondary choice when special needs are considered.

2. An electrically driven propeller engine: the lift force and the forward traction force required during vertical take-off and landing are provided, and the lift force and the forward traction force are formed by adopting a plurality of groups of low-power engines, wherein each group is provided with two back rests.

The purpose is to facilitate the mutual matching between the engine and the film wing when the appearance layout of the airplane is carried out, and reduce the adverse effect between the engine and the film wing; the safety is improved, and the safety flying can be ensured under the condition that the individual engine is stopped suddenly; the noise of the aircraft is reduced, and the aircraft is more environment-friendly; the two back rest sets of each group can offset rotation torque mutually to make the aircraft more stable.

3. High-energy battery pack: with an energy storage density of about 8kg/kw.h now, the weight of the high-energy battery pack is about 50% of the aircraft's own weight (unmanned). Is a major factor affecting aircraft performance and must be properly loaded. The high-energy battery pack is divided into a main battery part (accounting for about 80%) and a standby battery part (accounting for about 20%) so as to improve the safety guarantee of the power supply of the airplane.

4. Power spar, membrane wing linkage operation device 7: the direction of the main power is controlled, so that the engine and the film wings are always in the optimal cooperative state, and the control is simple. The power conversion key point is that the aircraft can take off and land like a helicopter, climb and cruise like a fixed-wing aircraft and glide like a power glider.

5. And the power tail rotor 5 realizes the omnibearing active steering function of the aircraft up, down, left and right. By adopting two small electric-driven propeller engines which are mutually backed, the airplane can be operated more flexibly and simply.

6. Folding angle adjustment mechanism: the folding angle is adjusted according to the requirements in the flight process when the vehicle is in a 90-degree folding state during parking and taking off and landing. The system can greatly improve the navigable range and the flight stability of the aircraft, and expand the optimal cruising speed of the aircraft at a certain altitude (such as 500m altitude) from a point (such as 132 km/h) to a range (such as 132-206 km/h); is a key point for realizing energy-saving stable flight and warehouse-in parking of the co-rotating vertical take-off and landing film wing aircraft.

7. Electric control wheel foot telescopic mechanism: the retraction of the casters is controlled to reduce the flight resistance.

8. Manual folding mechanism of power spar: and the parking of the aircraft is facilitated.

9. The design of the fuselage-like hull enables the fuselage-like hull to have a small flying drag coefficient and the capability of landing on calm water surfaces: the fuselage structure and the outer skin adopt high-strength aluminum alloy aviation materials, and the inner skin adopts carbon fiber cloth. Wherein the inner and outer skins of the floor are made of strong aluminum alloy sheets, and the gaps between the inner and outer skins are filled with hard foam plastics.

10. Avionics system: the device is equipped according to the actual requirements, and comprises a strong current system (propeller, motor and air conditioner power supply and distribution), a weak current system (battery electric quantity induction, caster telescopic induction and control, membrane wing angle induction and control), a communication and information display system (central control computer, world communication, display screen, navigation line, altitude, speed, course, temperature, electric quantity, aircraft attitude angle, load, time and the like)

11. The main calculation formula is as follows:

flight resistance fw=a×cw×v ² /16(Kg)

Wherein A-wind resistance area (m ² )

Cw-wind resistance coefficient (0.3-0.6)

V-speed (m/s)

Lift: y=p×c×s×v ² /2(N)

Wherein: p-atmospheric density (1.2 according to regional atmospheric density curve, 500m below, above gradually decreasing)

C-lift coefficient of about 1

S-wing area (m) ² )

V-speed (m/s)

Taking a double-seat co-rotating vertical take-off and landing film wing aircraft as an example, the following is a simple explanation:

1. performance requirements of a double-seat co-rotating vertical take-off and landing film wing aircraft are as follows:

effective load	200kg	Normal cruising speed	140 to 200km/h
				Maximum load of	250kg	Maximum flying speed	300km/h
Normal fly height	600 to 800 meters	Normal time of flight	More than 1h
				Maximum flying height	1000 meters	Normal course	Greater than 200km

2. The corresponding components are provided by calculation:

3. layout of the appearance: see the attached drawings in the specification.

4. And calculating main parameters and performance of the double-seat vertical take-off and landing film wing aircraft according to the appearance layout and configuration:

the utility model has been described in connection with the preferred embodiments, but the utility model is not limited to the embodiments disclosed above, but it is intended to cover various modifications, equivalent combinations according to the essence of the utility model.

Claims (10)

1. The co-rotating vertical take-off and landing film wing aircraft comprises a fuselage (1), and is characterized in that the fuselage (1) is rotatably connected with at least two rows of power spars (2), and a propeller (3) is arranged on each row of power spars (2); a membrane wing (4) which is rotationally connected with the machine body (1) is arranged between the adjacent power wing beams (2); a folding angle adjusting mechanism (6) is arranged in the middle of the membrane wing (4); the machine body (1) is provided with a linkage operation device (7) which enables the film wing (4) and the power wing spar (2) to synchronously rotate relative to the machine body (1).

2. A co-rotating vertical take-off and landing membrane wing aircraft according to claim 1, characterized in that the membrane wing (4) comprises a membrane wing cross-beam and a number of membrane wings (46), the membrane wing cross-beam comprising at least two sections of membrane wing cross-beam modules arranged in the spanwise direction of the membrane wing (4), the membrane wings (46) being arranged on the membrane wing cross-beam modules; the folding angle adjusting mechanism (6) is connected between the adjacent film wing beam modules.

3. A co-rotating vertical takeoff and landing membrane wing aircraft according to claim 2, characterized in that said adjacent membrane wing beam modules are rotationally connected by a first bearing (45); the folding angle adjusting mechanism (6) comprises a driving mechanism, a linear translation structure and a rotary connecting rod (66) which are sequentially linked; one end of a rotating connecting rod (66) is rotationally connected with one of the membrane wing beam modules through a second bearing (661), the other end of the rotating connecting rod (66) is rotationally connected with a linear translation structure positioned on the other membrane wing beam module through a third bearing (662), and the linear translation structure is movably matched with the membrane wing beam module.

4. A co-rotating vertical take-off and landing membrane aircraft according to claim 3, wherein the driving mechanism and the linear translation structure are arranged on the same membrane wing beam module, the driving mechanism comprises a motor (61), a reduction gear set (62) and a power screw sleeve (63) which are sequentially linked, the outer side wall of the power screw sleeve (63) is linked with the reduction gear set (62) through a gear structure, and the power screw sleeve (63) is rotationally connected with the membrane wing beam module; the linear translation structure is a push-pull screw (64), and the power spiral sleeve (63) is sleeved on the outer side of the push-pull screw (64) and is in threaded fit with the push-pull screw.

5. A co-rotating vertical take-off and landing membrane wing aircraft according to claim 2, characterized in that one of the membrane wing beam modules of the membrane wing (4) is a fixed membrane wing beam module, which is in rotational connection with the fuselage (1); the linkage operation device (7) comprises an operation part and a guy cable (73) which are linked, and also comprises a power spar co-rotating transmission disc (71) and a film spar co-rotating transmission disc (72) which are sleeved with the guy cable (73); and the power wing beam co-rotating transmission disc (71) is fixedly connected with the power wing beam (2), and the film wing beam co-rotating transmission disc (72) is fixedly connected with the fixed film wing beam module.

6. A co-rotating vertical take-off and landing film wing aircraft according to claim 2, characterized in that at least two rows of film wings (4) in rotational connection with the fuselage (1) are arranged between the adjacent power spars (2); each row of film wings (4) is linked with the power wing spar (2) through a linkage operation device (7).

7. The corotation vertical takeoff and landing membrane wing aircraft according to claim 6, characterized in that one of the membrane wing beam modules of the membrane wing (4) is a fixed membrane wing beam module, the fixed membrane wing beam module of the membrane wing (4) is rotatably connected with the fuselage (1); the linkage operation device (7) comprises an operation part and a guy cable (73) which are linked, and also comprises a power spar co-rotating transmission disc (71) and a film spar co-rotating transmission disc (72) which are sleeved with the guy cable (73); the power spar co-rotating transmission disc (71) is fixedly connected with the power spar (2); the film wing beam co-rotating transmission disc (72) is fixedly connected with a fixed film wing beam module of one row of film wings (4), and the fixed film wing beam module is linked with the fixed film wing beam modules of the other rows of film wings (4) through a connecting rod mechanism (79).

8. The corotation vertical takeoff and landing membrane wing aircraft according to claim 7, characterized in that the link mechanism (79) comprises a swing arm (791) and a linkage rod (792), the swing arm (791) is fixedly installed on each fixed membrane wing beam module, and the linkage rod (792) is rotatably connected with each swing arm (791).

9. The co-rotating vertical take-off and landing film wing aircraft according to claim 5 or 7, characterized in that the operation part of the linkage operation device (7) comprises a control box shell (76) and a control handle (75) which are rotatably connected through a fixed shaft (751), a sliding groove (761) is arranged on the control box shell (76), and a sliding rack (77) is connected on the sliding groove (761) in a sliding way; the stay rope (73) is connected with the sliding rack (77); the control handle (75) is provided with an arc transmission gear (753) meshed with the sliding rack (77); a handle in-place clamping structure is arranged between the control handle (75) and the control box shell (76).

10. A co-rotating vertical take-off and landing film wing aircraft according to claim 1, characterized in that the power spar (2) is provided with a folding structure in the middle; wheels (9) are arranged at the bottom of the machine body (1); the back of the machine body (1) is provided with a tail rotor (5), the tail rotor (5) is arranged on a tail rotor rotating arm (8), the tail rotor rotating arm (8) is rotationally connected with the machine body (1), and the machine body (1) is provided with a second operation part linked with the tail rotor rotating arm (8); a plurality of propellers (3) are arranged on each row of power wing spars (2).