Flapping wing aircraft adopting bionic feathers as flapping wings

Abstract

The utility model discloses a flapping wing aircraft adopting bionic feathers as flapping wings. The flapping wing aircraft comprises a main beam assembly, a power assembly, a wing assembly and an empennage assembly, the power assembly is connected with one end of the main beam assembly, the empennage assembly is connected with the other end of the main beam assembly, and the wing assemblies are connected with the two sides of the power assembly in a mirror image mode and are in spherical hinge joint with the main beam assembly. The wing assembly comprises a wing main rod, a plurality of feather shafts and a plurality of feather pieces, one end of the wing main rod is connected with the power assembly, the feather shafts are connected to the wing main rod at intervals, and the feather pieces are rotationally connected to the feather shafts respectively; with the feather pieces and the rotating point of the feather shaft as a boundary, the feather pieces on the two sides of the rotating point are bent towards the two sides in opposite directions, and the adjacent feather pieces are in lap joint. The utility model has the beneficial effects that the flapping resistance of the wings is small, and the wings have the capability of flying in rainy days.

Description

Technical Field

[0001] The utility model relates to an aircraft, in particular to a flapping-wing aircraft. Background Art

[0002] In recent years, the rapid development of science and technology has greatly expanded the scope of human activities and spawned the demand for high-performance sea, land and air unmanned systems for various auxiliary operations. Flapping-wing aircraft have set off a research boom with their bionic characteristics and high energy utilization rate, but most of the current flapping-wing aircraft use materials such as aviation parachute cloth for wing skin to simulate the flapping of bird wings to provide power for flapping-wing aircraft. However, the wings made of parachute cloth cannot achieve the flight efficiency that can be achieved by bird feather wings, and the flapping resistance is large on rainy days, which is not conducive to the flight of parachute cloth wing flapping-wing aircraft. When flapping-wing aircraft flap up, the wings mainly bring resistance.

[0003] In the prior art, such as patent CN114435590A, a variable angle of attack flapping wing aircraft with wing rotation function, relates to the technical field of flapping wing aircraft. It includes a fuselage frame, a first wing rod and a rotating connecting rod, which are located on both sides of the fuselage frame; a second wing rod, the second wing rod is respectively rotatably connected to the first wing rod and the rotating connecting rod, and a feather piece is fixed on one side of the second wing rod; a hollow cup motor is fixedly connected to the fuselage frame, and is used to provide power to the crank rocker mechanism, and the crank rocker mechanism is used to drive the first wing rod to reciprocate up and down. This patent drives the gear transmission part to rotate by the hollow cup motor, and then drives the crank rocker mechanism to rotate periodically by the gear transmission part, and finally drives the feather part to partially realize the flapping and twisting of the aircraft by the rocker member, and the crank rocker mechanism is reasonably designed to make the aircraft structure more compact and the transmission more reasonable. This patent realizes partial twisting of the feather part through the active control of the motor through the mechanical structure, and the control is cumbersome, the system reliability is low, and it is not conducive to the long-term and efficient flight of the flapping wing aircraft.

[0004] The information disclosed in this background technology section is only intended to increase the understanding of the overall background of the present invention, and should not be regarded as acknowledging or suggesting in any form that the information constitutes the prior art known to those skilled in the art. Utility Model Content

[0005] The technical problem to be solved by the utility model is: how to solve the problem of large resistance of the current flapping-wing aircraft.

[0006] The utility model solves the above technical problems through the following technical means:

[0007] A flapping-wing aircraft using bionic feathers as flapping wings comprises a main beam assembly, a power assembly, a wing assembly and a tail assembly; the power assembly is connected to one end of the main beam assembly, the tail assembly is connected to the other end of the main beam assembly, the wing assembly is connected to both sides of the power assembly in a mirrored manner and is ball-hinged with the main beam assembly; the wing assembly comprises a wing main rod, a plurality of feather shafts and a plurality of feathers, one end of the wing main rod is connected to the power assembly, a plurality of feather shafts are connected to the wing main rod at intervals, and the feathers are rotatably connected to the feather shafts respectively; the feathers are divided by a rotation point between the feathers and the feather shafts, the feathers on both sides of the rotation point are bent in opposite directions to both sides, and adjacent feathers are overlapped.

[0008] The utility model realizes the reciprocating motion of the wing assemblies on both sides to swing up and down through the power assembly, and the tail assembly realizes the pitching and turning effects; in the utility model, when the wings flap up, the adjacent feathers overlap each other to form a seal, and at this time the feathers of the entire wing are tightly overlapped, which is beneficial to catching the wind when flapping down and providing lift for the wings; and when the wings flap down, the adjacent feathers are separated, and there are gaps between the feathers, and the existence of the gap is beneficial to reducing the resistance of the wings when flapping up; the utility model provides power for the flight of the flapping-wing aircraft, so that the flapping resistance of the wings is small, and the aircraft has the ability to fly in rainy days.

[0009] Preferably, the vane extends in the positive direction Y and the negative direction Y with the rotation point as the boundary to form a first vane split and a second vane split respectively, the curve length of the first vane split is smaller than the curve length of the second vane split, and the vane is generally S-shaped.

[0010] Preferably, when looking from one end of the wing assembly close to the main beam assembly toward the end, the length of the vane gradually decreases.

[0011] The bionic feathers are made of a whole piece of plastic that is vacuum-formed and waterproof, so the wings can still fly normally even on rainy days.

[0012] The bionic feather is organically combined with the flapping-wing machine, and a fixed structure of the bionic feather wing is designed, which ensures that the bionic feather has the characteristics of flapping upward and opening, and flapping downward and closing, of a real feather, while also taking into account the strength of the wing.

[0013] Preferably, the wing assembly also includes a diagonal tie rod assembly, one end of which is connected to one end of the wing main rod away from the power assembly, and the other end is ball-jointed to the main beam assembly, and the diagonal tie rod assembly forms an angle with the wing main rod.

[0014] Preferably, the diagonal tie rod assembly includes a diagonal tie rod body, a diagonal tie rod fixing block, a diagonal tie rod seat, and a diagonal tie rod ball head. The diagonal tie rod fixing block is connected to the end of the wing main rod, the diagonal tie rod seat is fixedly connected to the main beam assembly, the diagonal tie rod ball head is ball-hinged with the diagonal tie rod seat, and the two ends of the diagonal tie rod body are respectively connected to the diagonal tie rod fixing block and the diagonal tie rod ball head.

[0015] Preferably, the power assembly includes a power bracket, a power front cover, a motor, and a swing arm. The power bracket and the power front cover are arranged at intervals and connected in parallel through a plurality of support rods. The swing arm is located in the space between the power bracket and the power front cover. The swing arm can rotatably connect the power bracket and the power front cover. The opposite ends of the two swing arms are linked, and the other ends are connected to the wing main rod. The motor is fixedly connected to the power bracket, and the power output shaft of the motor is drivingly connected to one of the swing arms.

[0016] Preferably, the power assembly also includes a crank and a connecting rod. The power output shaft of the motor passes through the power front cover and is connected to one end of the crank. The other end of the crank is rotatably connected to one end of the connecting rod. The power front cover includes a sliding groove. The other end of the connecting rod passes through the sliding groove and is eccentrically connected to one of the swing rods.

[0017] Preferably, one end of the swing lever comprises an incomplete gear, the incomplete gear portions of the two swing levers are meshed, and the other end of the swing lever has a slot, which is fixedly connected to the wing main rod.

[0018] Preferably, the tail assembly includes a tail bracket, a tail support plate, and a tail deflection assembly, one end of the tail bracket is connected to the main beam assembly, the other end of the tail bracket is in a V-shaped structure, the tail support plate is a V-shaped plate, the tail support plate is fit and fixedly connected to the V-shaped structure of the tail bracket, and the two tail deflection assemblies are respectively connected to the two sides of the tail bracket and the tail support plate in a mirrored manner.

[0019] Preferably, the tail deflection assembly includes a servo, a tail pull rod, a tail flip block, and a tail deflection plate, the servo is connected to the tail bracket, the tail flip block is hinged to the end of the tail bracket through a pin, the tail deflection plate is fixedly connected to the tail flip block, and the two ends of the tail pull rod are respectively connected to the servo and the tail flip block.

[0020] The deflection function of the direction of the flapping-wing aircraft is achieved by controlling the rotation of two servos to drive the flipping of the tail deflector.

[0021] The advantages of the utility model are:

[0022] The utility model realizes the reciprocating motion of the wing assemblies on both sides to swing up and down through the power assembly, and the tail assembly realizes the pitching and turning effects; in the utility model, when the wings flap up, the adjacent feathers overlap each other to form a seal, and at this time the feathers of the entire wing are tightly overlapped, which is beneficial to catching the wind when flapping down and providing lift for the wings; and when the wings flap down, the adjacent feathers are separated, and there are gaps between the feathers, and the existence of the gap is beneficial to reducing the resistance of the wings when flapping up; the wings of the utility model have low resistance when flapping up, and have the ability to fly in rainy days.

[0023] The bionic feathers are made of a whole piece of plastic that is vacuum-formed and waterproof, so the wings can still fly normally even on rainy days.

[0024] The bionic feather is organically combined with the flapping-wing machine, and a fixed structure of the bionic feather wing is designed, which ensures that the bionic feather has the characteristics of flapping upward and opening, and flapping downward and closing, of a real feather, while also taking into account the strength of the wing.

[0025] The deflection function of the direction of the flapping-wing aircraft is achieved by controlling the rotation of two servos to drive the flipping of the tail deflector. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 This is a schematic structural diagram of a flapping-wing aircraft using bionic feathers as flapping wings in an embodiment of the utility model;

[0027] Figure 2 This is a schematic structural diagram of a flapping-wing aircraft using bionic feathers as flapping wings in an embodiment of the utility model;

[0028] Figure 3 It is a schematic diagram of the structure of the feather of the embodiment of the utility model;

[0029] Figure 4 It is a side view of the feather of the utility model embodiment;

[0030] Figure 5 It is a schematic diagram of the overlapping of the feathers in the embodiment of the utility model;

[0031] Figure 6 It is a schematic diagram of the separation of the pinnae in an embodiment of the utility model;

[0032] Figure 7 yes Figure 2 Enlarged view of point A in the middle;

[0033] Figure 8 It is an enlarged schematic diagram of the ball head of the inclined tie rod of the embodiment of the utility model;

[0034] Fig. 9 It is a partial enlarged view of the power assembly of the embodiment of the utility model;

[0035] Fig.10It is a partial enlarged view of the power assembly of the embodiment of the utility model;

[0036] Fig.11 It is a structural schematic diagram of the tail assembly of the embodiment of the utility model;

[0037] Fig.12 It is a structural schematic diagram of the tail assembly of the embodiment of the utility model;

[0038] Fig.13 This is a schematic structural diagram of a tail wing support piece according to an embodiment of the utility model;

[0039] Fig.14 is a schematic structural diagram of a tail wing deflection assembly according to an embodiment of the utility model;

[0040] Fig.15 This is a schematic diagram of the remote control process of the embodiment of the utility model;

[0041] Numbers in the figure:

[0042] 1. Main beam assembly;

[0043] 2. Power assembly; 21. Power bracket; 22. Power front cover; 23. Motor; 24. Swing rod; 25. Crank; 26. Connecting rod;

[0044] 3. Wing assembly; 31. Wing main rod; 32. Feather shaft; 33. Feather; 331. First feather split; 332. Second feather split; 34. T-shaped fixing block; 35. Diagonal tie rod assembly; 351. Diagonal tie rod body; 352. Diagonal tie rod fixing block; 353. Diagonal tie rod seat; 354. Diagonal tie rod ball head;

[0045] 4. Tail assembly; 41. Tail bracket; 42. Tail support plate; 43. Tail deflection assembly; 431. Servo; 432. Tail pull rod; 433. Tail flip block; 434. Tail deflection plate. DETAILED DESCRIPTION

[0046] In order to make the purpose, technical solution and advantages of the embodiments of the utility model clearer, the technical solution in the embodiments of the utility model will be clearly and completely described below in combination with the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0047] Embodiment 1:

[0048] like Figure 1 , Figure 2As shown, a flapping-wing aircraft using bionic feathers as flapping wings includes a main beam assembly 1, a power assembly 2, a wing assembly 3, and a tail assembly 4; the power assembly 2 is connected to one end of the main beam assembly 1, the tail assembly 4 is connected to the other end of the main beam assembly 1, and the wing assembly 3 is connected to both sides of the power assembly 2 in a mirror manner and is ball-hinged with the main beam assembly 1.

[0049] The main beam assembly 1 may be composed of a plurality of parallel beams, and some balancing structural parts may be added. This embodiment does not impose any specific limitation, and the design may be adapted according to the weight of the entire flapping-wing aircraft.

[0050] The wing assembly 3 includes a wing main rod 31, multiple feather shafts 32, and multiple feathers 33. One end of the wing main rod 31 is connected to the power assembly 2, and multiple feather shafts 32 are connected to the wing main rod 31 at intervals. The feathers 33 are respectively rotatably connected to the feather shafts 32; the feathers 33 and the feather shafts 32 are divided by the rotation point, and the feathers 33 on both sides of the rotation point are bent in opposite directions to both sides, and adjacent feathers 33 are overlapped.

[0051] Specifically, the wing assembly 3 also includes a T-shaped fixing block 34, and the wing main rod 31 can pass through the T-shaped fixing block 34 and be fixed thereto, and the fixing method can be glue fixing; the T-shaped fixing block 34 has a mounting hole that matches the wing main rod 31 and the feather shaft 32, and the shaft and the hole can be matched with a square shaft to reduce rotation. In this embodiment, there are eight feather shafts 32 and eight T-shaped fixing blocks 34. The feather piece 33 has a long mounting hole, and the feather shaft 32 is inserted into the long mounting hole, and the end of the feather shaft 32 is connected to the T-shaped fixing block 34. In this way, the bionic feather is arranged and fixed to the left and right wing main rods 31 through the feather shaft 32 and the T-shaped fixing block 34 to form the main structure of the wing; the wing main rod 31 can be a carbon steel part.

[0052] like Figure 3 , Figure 4 As shown, the vane 33 extends in the positive direction Y and the negative direction Y with the rotation point boundary (i.e., the center of the vane axis 32) to form a first vane body 331 and a second vane body 332, respectively. The curve length of the first vane body 331 is less than the curve length of the second vane body 332, and the vane 33 is generally S-shaped. Figure 1 As shown, adjacent pinnae 33 overlap each other, and one first pinnae segment 331 overlaps another second pinna segment 332. Figure 5 and Figure 6As shown, when the wing flaps up, with the feather shaft 32 as the center, the first feather body 331 of the feather 33 and the second feather body 332 of the other feather 33 overlap each other to form a seal. At this time, the feathers 33 of the entire wing assembly 3 are tightly overlapped, which is beneficial to catching the wind when flapping down and providing lift for the wing; and when the wing flaps down, with the feather shaft 32 as the center, the first feather body 331 of the feather 33 and the second feather body 332 of the other feather 33 are separated from each other, and there is a gap between the feathers 33 and the feathers 33. The existence of this gap is beneficial to reducing the resistance when the wing flaps up.

[0053] The bionic feathers in this embodiment are formed by vacuum forming a whole piece of plastic, which is waterproof, and the wings can still fly normally on rainy days.

[0054] The bionic feather is organically combined with the flapping-wing machine, and a fixed structure of the bionic feather wing is designed, which ensures that the bionic feather has the characteristics of flapping upward and opening, and flapping downward and closing, of a real feather, while also taking into account the strength of the wing.

[0055] Among them, the length of the feather 33 gradually decreases when the wing assembly 3 is close to the main beam assembly 1 and looks toward the end. In this embodiment, the gradual decrease is also to simulate the general shape of bird wings. The gradual decrease can be understood as the feathers 33 are smaller one by one, or it can be understood as presenting a decreasing trend, that is, the lengths of the first two or three feathers 33 close to the main beam assembly 1 do not change, and the lengths of the subsequent ones become smaller.

[0056] The left and right wing assemblies 3 are arranged in a mirror-image manner, which is equivalent to the wings of birds. The wing assemblies 3 on both sides flap up and down simultaneously to achieve flight.

[0057] In this embodiment, the wing assemblies 3 on both sides realize the reciprocating motion of up and down swinging through the power assembly 2, and the tail assembly 4 realizes the pitching and turning effects; in this embodiment, when the wings flap up, the adjacent feathers 33 overlap each other to form a seal, and at this time the feathers 33 of the entire wing are tightly overlapped, which is beneficial to catching the wind when flapping down and providing lift for the wings; and when the wings flap down, the adjacent feathers 33 are separated, and there is a gap between the feathers 33 and the feathers 33, and the existence of this gap is beneficial to reducing the resistance when the wings flap up; this embodiment provides power for the flight of the flapping-wing aircraft, so that the wing flapping resistance is small, and the aircraft has the ability to fly in rainy days.

[0058] Embodiment 2:

[0059] like Figure 2 , Figure 7 , Figure 8As shown, on the basis of the above-mentioned embodiment 1, the wing assembly 3 also includes a diagonal rod assembly 35, one end of the diagonal rod assembly 35 is connected to one end of the wing main rod 31 away from the power assembly 2, and the other end is ball-hinged with the main beam assembly 1, and the diagonal rod assembly 35 forms an angle with the wing main rod 31.

[0060] Specifically, the diagonal tie rod assembly 35 includes a diagonal tie rod body 351, a diagonal tie rod fixing block 352, a diagonal tie rod seat 353, and a diagonal tie rod ball head 354. The diagonal tie rod fixing block 352 is connected to the end of the wing main rod 31, the diagonal tie rod seat 353 is fixedly connected to the main beam assembly 1, the diagonal tie rod ball head 354 is ball-hinged with the diagonal tie rod seat 353, and the two ends of the diagonal tie rod body 351 are respectively connected to the diagonal tie rod fixing block 352 and the diagonal tie rod ball head 354.

[0061] One end of the inclined rod ball head 354 is fixed to the inclined rod seat 353 by screws, and the other end of the inclined rod ball head 354 is a ball head, which can be ball-hinged with the inclined rod body 351, so that the inclined rod body 351 can swing around the inclined rod ball head 354.

[0062] The inclined rod body 351 forms a roughly acute angle with the wing main rod 31, and the design of the inclined rod assembly 35 is added to the wing assembly 3 to ensure the stability of the bionic feather. The inclined rod assembly 35 and the neatly arranged bionic feather structure constitute the wing assembly 3.

[0063] Embodiment three:

[0064] like Fig. 9 , Fig.10 As shown, on the basis of the above-mentioned embodiment 2, the power assembly 2 includes a power bracket 21, a power front cover 22, a motor 23, a swing rod 24, a crank 25, and a connecting rod 26. The power bracket 21 and the power front cover 22 are arranged at intervals and connected in parallel through a plurality of support rods, and an installation space is formed between the power bracket 21 and the power front cover 22. The swing rod 24 is located in the installation space. The two sides of the middle part of the swing rod 24 can rotatably connect the power bracket 21 and the power front cover 22 by means of a pin shaft, etc., and the opposite ends of the two swing rods 24 are linked and the other ends are fixedly connected to the wing main rod 31. The motor 23 is fixedly connected to the power bracket 21, and the power output shaft of the motor 23 passes through the power front cover 22 and is fixedly connected to one end of the crank 25, and the other end of the crank 25 is rotatably connected to the connecting rod 26. The power front cover 22 includes a sliding groove, and the other end of the connecting rod 26 passes through the sliding groove and is eccentrically connected to one of the swing rods 24.

[0065] like Fig.10As shown, there are two swing rods 24, one end of each of the two swing rods 24 includes an incomplete gear, the incomplete gear portions of the two swing rods 24 are meshed, and the other end of the swing rod 24 has a slot, which is fixedly connected to the wing main rod 31.

[0066] When the motor 23 outputs power, the motor 23 drives the crank 25 to rotate, driving the connecting rod 26 to move, and the connecting rod 26 slides along the slide groove, driving one of the swing rods 24 to rotate. Due to the inner core of the incomplete gear, this swing rod 24 synchronously drives the other swing rod 24 to rotate. The swing rod 24 rotates, thereby realizing the reciprocating up and down swinging of the wing assemblies 3 on both sides, thereby completing the flapping action of the wings of the flapping-wing aircraft.

[0067] Embodiment 4:

[0068] like Fig.11 , Fig.12 As shown, based on the above embodiment, the tail assembly 4 includes a tail bracket 41, a tail support plate 42, and a tail deflection component 43, combined with Fig.13 As shown, one end of the tail bracket 41 is connected to the main beam assembly 1, the other end of the tail bracket 41 is in a V-shaped structure, the tail support piece 42 is a V-shaped piece, and the front end of the tail support piece 42 is fitted and fixedly connected with the V-shaped structure of the tail bracket 41, and the fixed connection method can be connected by bolts or screws. The two tail deflection assemblies 43 are respectively connected to the two sides of the tail bracket 41 and the tail support piece 42 in a mirrored manner.

[0069] like Fig.13 As shown, the left end of the tail support piece 42 includes two installation grooves, and the right end is a rectangular frame. The rectangular frame is bent to form a V-shaped structure. The installation groove is used to install the servo 431, and the V-shaped structure is closely connected to the tail bracket 41.

[0070] Specific, combined Fig.14 As shown, the tail deflection assembly 43 includes a servo 431, a tail tie rod 432, a tail flip block 433, and a tail deflection piece 434. The servo 431 is connected to the mounting grooves on both sides of the tail bracket 41, and the servo 431 can be installed by screws. The tail flip block 433 is a concave structure, one end of which is hinged to the end of the tail bracket 41 through a pin, and the tail deflection piece 434 is fixedly connected to the tail flip block 433. The tail flip block 433 can rotate along the pin at the end of the tail bracket 41, so as to flip with the tail deflection piece 434, and the two ends of the tail tie rod 432 are respectively connected to the servo 431 and the tail flip block 433.

[0071] The left tail flip block 433 and the right tail flip block 433 are connected to the tail bracket 41 through a pin structure, and can rotate up and down around the center of the pin shaft, and the other ends are respectively connected to the left tail deflection piece 434 and the right tail deflection piece 434; the left servo 431 and the right servo 431 are respectively connected to the left tail flip block 433 and the right tail flip block 433 through the left tail pull rod 432 and the right tail pull rod 432, so that the left servo 431 and the right servo 431 can respectively control the up and down flipping of the left tail deflection piece 434 and the right tail deflection piece 434, thereby realizing the steering and pitch control of the flapping-wing aircraft.

[0072] In actual use, such as Fig.15 As shown, the flight can also be controlled by remote control, such as when a flapping-wing aircraft with bionic feathers as flapping wings is flying, the remote control command is given to the controller, and the controller controls the driver to drive the motor 23 to rotate, and the motor 23 rotates to drive the wing assemblies 3 on both sides to flap through the power assembly 2, thereby realizing the flapping of the wings during air flight. In addition, when it is necessary to control the flapping-wing aircraft to turn, the remote control gives the controller through the command to drive the servo 431 of the tail wing to work, the left servo 431 controls the left turn, and the right servo 431 controls the right turn.

[0073] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A flapping-wing aircraft using bionic feathers as flapping wings, characterized in that: It includes a main beam assembly, a power assembly, a wing assembly, and a tail assembly; the power assembly is connected to one end of the main beam assembly, the tail assembly is connected to the other end of the main beam assembly, the wing assembly is connected to both sides of the power assembly in a mirror manner and is ball-hinged with the main beam assembly; the wing assembly includes a wing main rod, multiple feather shafts, and multiple feathers, one end of the wing main rod is connected to the power assembly, multiple feather shafts are connected to the wing main rod at intervals, and the feathers are rotatably connected to the feather shafts respectively; the feathers are divided by the rotation point of the feathers and the feather shafts, and the feathers on both sides of the rotation point are bent in opposite directions to both sides, and adjacent feathers are overlapped.

2. A flapping-wing aircraft using bionic feathers as flapping wings according to claim 1, characterized in that: The vane extends in the positive direction Y and the negative direction Y with the rotation point as the boundary to form a first vane split and a second vane split respectively. The curve length of the first vane split is smaller than the curve length of the second vane split. The vane is generally S-shaped.

3. The flapping-wing aircraft using bionic feathers as flapping wings according to claim 1, characterized in that: When viewed from one end of the wing assembly close to the main beam assembly toward the end, the length of the feathers gradually decreases.

4. The flapping-wing aircraft using bionic feathers as flapping wings according to claim 1, characterized in that: The wing assembly also includes a diagonal tie rod assembly, one end of which is connected to one end of the wing main rod away from the power assembly, and the other end is ball-hinged with the main beam assembly, and the diagonal tie rod assembly forms an angle with the wing main rod.

5. The flapping-wing aircraft using bionic feathers as flapping wings according to claim 4, characterized in that: The diagonal tie rod assembly includes a diagonal tie rod body, a diagonal tie rod fixing block, a diagonal tie rod seat, and a diagonal tie rod ball head. The diagonal tie rod fixing block is connected to the end of the wing main rod, the diagonal tie rod seat is fixedly connected to the main beam assembly, the diagonal tie rod ball head is ball-hinged with the diagonal tie rod seat, and the two ends of the diagonal tie rod body are respectively connected to the diagonal tie rod fixing block and the diagonal tie rod ball head.

6. The flapping-wing aircraft using bionic feathers as flapping wings according to claim 1, characterized in that: The power assembly includes a power bracket, a power front cover, a motor, and a swing arm. The power bracket and the power front cover are arranged at intervals and connected in parallel through a plurality of support rods. The swing arm is located in the space between the power bracket and the power front cover. The swing arm can rotatably connect the power bracket and the power front cover. The opposite ends of the two swing arms are linked, and the other ends are connected to the wing main rod. The motor is fixedly connected to the power bracket, and the power output shaft of the motor is drivingly connected to one of the swing arms.

7. The flapping-wing aircraft using bionic feathers as flapping wings according to claim 6, characterized in that: The power assembly also includes a crank and a connecting rod. The power output shaft of the motor passes through the power front cover and is connected to one end of the crank. The other end of the crank is rotatably connected to one end of the connecting rod. The power front cover includes a sliding groove. The other end of the connecting rod passes through the sliding groove and is eccentrically connected to one of the swing rods.

8. The flapping-wing aircraft using bionic feathers as flapping wings according to claim 6, characterized in that: One end of the swing rod comprises an incomplete gear, and the incomplete gears of the two swing rods are partially meshed. The other end of the swing rod has a slot, and the slot is fixedly connected to the wing main rod.

9. The flapping-wing aircraft using bionic feathers as flapping wings according to claim 1, characterized in that: The tail assembly includes a tail bracket, a tail support plate, and a tail deflection assembly. One end of the tail bracket is connected to the main beam assembly, and the other end of the tail bracket is in a V-shaped structure. The tail support plate is a V-shaped plate. The tail support plate is fitted and fixedly connected to the V-shaped structure of the tail bracket. The two tail deflection assemblies are respectively connected to the two sides of the tail bracket and the tail support plate in a mirrored manner.

10. The flapping-wing aircraft using bionic feathers as flapping wings according to claim 9, characterized in that: The tail deflection assembly includes a servo, a tail pull rod, a tail flip block, and a tail deflection piece. The servo is connected to the tail bracket. The tail flip block is hinged to the end of the tail bracket through a pin shaft. The tail deflection piece is fixedly connected to the tail flip block. The two ends of the tail pull rod are respectively connected to the servo and the tail flip block.

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