Attack angle single parameter control bionic butterfly aircraft

Abstract

According to the attack angle single-parameter control bionic butterfly aircraft, a direct-acting driving motor is adopted to drive a flapping part to swing in a reciprocating mode through a transmission part, so that wing parts are driven to swing up and down, the direct-acting flight function of the aircraft is achieved, the traditional mode that gears are directly driven by a motor is abandoned, high-precision gear matching is not needed, and the transmission efficiency is greatly improved; the two turning driving motors are adopted to change the attack angles of the wings through the swing arms, the parameters of the attack angles are only determined by the output pace of the turning driving motors, it is guaranteed that the attack angles of the wings are not changed in the flapping process, and good operability and stability are achieved in the flying process. Therefore, the two motion modes of direct motion and turning do not interfere with each other, the conversion of motion states is realized, and the maneuverability is excellent.

Description

Technical Field

[0001] The utility model relates to the technical field of bionic aircraft, in particular to a bionic butterfly aircraft with single-parameter control of attack angle. Background Art

[0002] Bionic aircraft play an indispensable role in national defense, military, environmental monitoring and other fields. Currently, bionic aircraft has become a new research hotspot. This type of aircraft has unique advantages such as small shape, low cost, ability to start and stop at any time and ability to hover. It is a new type of flapping wing system that integrates propulsion and hovering functions. Due to its light weight and low mass, it can achieve long-distance flight with very little energy input.

[0003] Existing bionic butterfly aircraft mostly use dual servos to drive wings, or use motors to drive gears to drive wings. The driving efficiency is low. Although the flight effect can be achieved, the energy loss of the aircraft driven by dual servos is extremely large during the actual flight. The two gears of the aircraft directly driven by gears cannot achieve precise step meshing during the flight, so the energy loss is extremely large, such as Chinese patents CN202311601857.4 and CN202310501831.6. Butterflies in nature can achieve long-distance flight without too much energy input. Therefore, the existing butterfly bionic aircraft is far from butterflies in nature, and there is still a lot of room for improvement.

[0004] In addition, existing bionic butterfly aircraft mostly use a cable-type steering mechanism to achieve the differential speed of the left and right wing surfaces, thereby realizing the turning function. Although the turning radius can be controlled, during the differential control, the wing surfaces on both sides will have unequal lift and different flapping amplitudes, thereby causing instability during flight. Utility Model Content

[0005] In view of the shortcomings of the background technology, the purpose of the utility model is to provide a bionic butterfly aircraft with single-parameter control of the angle of attack.

[0006] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0007] A single-parameter controlled bionic butterfly aircraft with an angle of attack comprises a frame, one end of the frame is provided with a direct-acting control device and a turning control device respectively provided on both sides of the frame, and the other end of the frame is provided with a power supply for providing electric energy to the direct-acting control device and the turning control device; and further comprises wings provided on both sides of the frame, one end of the wing is connected to the direct-acting control device, and the other end of the wing is connected to the frame;

[0008] The direct-acting control device comprises a direct-acting drive motor, a transmission part and a flapping device which are sequentially connected in transmission, the flapping device comprises a first flapping part and a second flapping part which are mutually connected in transmission, one end of the transmission part is connected to the output end of the direct-acting drive motor, and the other end of the transmission part is connected to the first flapping part or the second flapping part, so that the first flapping part and the second flapping part flap back and forth, the first flapping part and the second flapping part are respectively provided with a rotatable swinging part outside, and one end of the wing part is connected to the swinging part;

[0009] The turning control device includes a turning drive motor and a swing arm rotatably connected to the frame, the output end of the turning drive motor is connected to one end of the swing arm, and the other end of the swing arm is connected to the swinging part, so that the angle of attack of the wing part is changed by the turning drive motor.

[0010] Furthermore, at least part of the outer surfaces of the first flapping part and the second flapping part are provided with mutually meshing teeth, and the first flapping part and the second flapping part are respectively provided with a slot for inserting the swing part.

[0011] Furthermore, the transmission part includes a first connecting rod, a second connecting rod and a third connecting rod which are rotatably connected to each other in sequence, the first connecting rod is connected to the output end of the direct-acting drive motor, the third connecting rod is connected to the first flapping part or the second flapping part, and the first connecting rod is a crank, and the third connecting rod is a rocker, so as to drive the first flapping part and the second flapping part to flap reciprocally.

[0012] Furthermore, the swinging part includes a pivot seat and a rocker arm, one end of the pivot seat is provided with a convex portion inserted into the slot, and the other end of the pivot seat is provided with a circular boss for rotatably connecting the rocker arm.

[0013] Furthermore, the output end of the turning drive motor is connected to one end of the swing arm through a first pull rod, and the swing arm is connected to the other end of the swing arm through a second pull rod.

[0014] Furthermore, the direct-acting drive motor is a coreless motor, the turning drive motor is a steering gear, the output end of the steering gear is a slider, and the slider is connected to one end of the swing arm through the first pull rod.

[0015] Furthermore, the wing portion includes a front wing and a hind wing, the front wing includes a front wing membrane and a front wing bracket arranged at the edge of the front wing membrane, the hind wing includes a hind wing membrane and a hind wing bracket arranged at the edge of the hind wing membrane, the front wing bracket is rotatably connected to the rocker arm, one end of the hind wing bracket is rotatably connected to the rocker arm, and the other end of the hind wing bracket is rotatably connected to the frame.

[0016] Furthermore, the front wing membrane and the rear wing membrane are made of P31N kite cloth.

[0017] Furthermore, fixed seats are provided on both sides of the frame, and the other end of the rear wing bracket is rotatably connected to the fixed seat.

[0018] Furthermore, the frame is provided with a control unit, which is electrically connected to the turning drive motor and the power supply; and also includes a remote control, which is communicatively connected to the control unit, and the output step of the output end of the turning drive motor is controlled by the remote control to change the degree of the angle of attack.

[0019] The beneficial effects of the utility model are:

[0020] The utility model proposes a bionic butterfly aircraft with single-parameter control of angle of attack. It adopts a direct-acting drive motor to drive the flapping part to swing back and forth through the transmission part, thereby driving the wing part to swing up and down, realizing the direct-acting flight function of the aircraft, abandoning the traditional motor direct-drive gear method, and does not require high-precision gear matching, which greatly improves the transmission efficiency; two turning drive motors are used to change the angle of attack of the wing part through the swing arm, and the parameters of the angle of attack are only determined by the output pace of the turning drive motor, ensuring that the angle of attack of the wing will not change during the flapping process, and achieving good operability and stability during the flight process. Therefore, it can achieve the two motion modes of direct motion and turning without interfering with each other, realize the conversion of motion state, and have excellent maneuverability. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0022] Figure 1 It is a schematic diagram of a bionic butterfly aircraft with single-parameter control of attack angle according to the utility model;

[0023] Figure 2 This is a schematic diagram of a bionic butterfly aircraft with single-parameter control of attack angle according to the utility model (the front wing membrane and the rear wing membrane are omitted);

[0024] Figure 3 This is a schematic diagram of a bionic butterfly aircraft with single-parameter control of attack angle according to the utility model (wings omitted);

[0025] Figure 4 It is a front view of a bionic butterfly aircraft with single-parameter control of attack angle according to the utility model;

[0026] Figure 5It is a side view of a bionic butterfly aircraft with single-parameter control of attack angle according to the utility model;

[0027] Figure 6 This is an exploded view of a bionic butterfly aircraft with single-parameter control of angle of attack according to the utility model;

[0028] Figure 7 for Figure 6 A partial enlarged view of the middle part;

[0029] In the figure, 10, frame; 201, mounting seat; 202, direct drive motor; 2031, first connecting rod; 2032, second connecting rod; 2033, third connecting rod; 2041, first flapping part; 2042, second flapping part; 301, tooth part; 302, slot; 401, pivot seat; 4011, convex part; 4012, circular boss; 402, rocker arm; 501, turning drive motor; 5012, slider; 502, swing arm; 60 , power supply; 70, fixing seat; 801, front wing; 8011, front wing membrane; 8012, front wing bracket; 802, hind wing; 8021, hind wing membrane; 8022, hind wing bracket; 901, first connecting hole; 902, second connecting hole; 903, third connecting hole; 904, fourth connecting hole; 905, fifth connecting hole; 906, sixth connecting hole; 907, seventh connecting hole; 1001, first pull rod; 1002, second pull rod. DETAILED DESCRIPTION

[0030] Combine the following Figure 1-6 The utility model is described in detail.

[0031] A single-parameter controlled bionic butterfly aircraft with an angle of attack includes a frame 10, on which are provided a plurality of mounting holes for connecting various components. A direct-acting control device and a turning control device respectively provided on both sides of the frame 10 are provided at one end of the frame 10, and a power supply 60 for providing electric energy to the direct-acting control device and the turning control device is provided at the other end of the frame 10; and further includes wings provided on both sides of the frame 10, one end of the wing is connected to the direct-acting control device, and the other end of the wing is connected to the frame 10;

[0032] The direct-acting control device includes a mounting base 201 fixedly connected to a base, and a direct-acting drive motor 202, a transmission part, and a flapping device are provided on the mounting base 201, and the flapping device includes a first flapping part 2041 and a second flapping part 2042 which are transmission-connected to each other, one end of the transmission part is connected to the output end of the direct-acting drive motor 202, and the other end of the transmission part is connected to the first flapping part 2041 or the second flapping part 2042, so that the first flapping part 2041 and the second flapping part 2042 flap back and forth, and a rotatable swinging part is provided outside the first flapping part 2041 and the second flapping part 2042, respectively, and one end of the wing part is connected to the swinging part;

[0033] The turning control device includes a turning drive motor 501 and a swing arm 502 rotatably connected to the frame 10, the output end of the turning drive motor 501 is connected to one end of the swing arm 502, and the other end of the swing arm 502 is connected to the swinging part, so that the angle of attack of the wing is changed by the turning drive motor 501.

[0034] The utility model proposes a bionic butterfly aircraft with single-parameter control of angle of attack. It adopts a direct-acting drive motor 202 to drive the flapping part to swing back and forth through the transmission part, thereby driving the wing part to swing up and down, realizing the direct-acting flight function of the aircraft, abandoning the traditional motor direct-drive gear method, and does not require high-precision gear matching, which greatly improves the transmission efficiency; two turning drive motors 501 are used to change the angle of attack of the wing part through the swing arm 502, and the parameters of the angle of attack are only determined by the output pace of the turning drive motor 501, ensuring that the angle of attack of the wing will not change during the flapping process, and achieving good operability and stability during the flight process. Therefore, it can be achieved that the two motion modes of direct motion and turning do not interfere with each other, realize the conversion of motion state, and have excellent maneuverability.

[0035] In this embodiment, at least part of the outer surface of the first flapping part 2041 and the second flapping part 2042 is provided with mutually meshing teeth 301, and the first flapping part 2041 and the second flapping part 2042 are respectively provided with a slot 302 for inserting the swing part. The swing part includes a pivot seat 401 and a rocker arm 402, one end of the pivot seat 401 is provided with a protrusion 4011 inserted in the slot 302, and the other end of the pivot seat 401 is provided with a circular boss 4012 for rotatably connecting the rocker arm 402.

[0036] In this embodiment, the transmission part includes a first connecting rod 2031, a second connecting rod 2032 and a third connecting rod 2033 which are rotatably connected to each other in sequence. The first connecting rod 2031 is connected to the output end of the direct-acting drive motor 202, and the third connecting rod 2033 is connected to the first flapping part 2041 or the second flapping part 2042. Specifically, the third connecting rod 2033 is pivotally connected to the first flapping part 2041. When in use, the length L1 of the first connecting rod 2031, the length of the second connecting rod 2032, the length of the third connecting rod 2033, and the distance L4 between the axis of the first flapping part 2041 and the axis of the direct-acting drive motor 202 constitute a planar four-bar mechanism. In order to make the first flapping part 2041 have the motion characteristics of reciprocating flapping, the aforementioned planar four-bar mechanism needs to constitute a crank-rocker mechanism. Therefore, the first connecting rod 2031 is a crank and the third connecting rod 2033 is a rocker to drive the first flapping part 2041 and the second flapping part 2042 to flap reciprocally, thereby realizing the reciprocating flapping of the wings and realizing the direct-acting function of the aircraft.

[0037] In this embodiment, the direct-acting drive motor 202 is a coreless motor, the output end of the turning drive motor 501 is connected to one end of the swing arm 502 through the first tie rod 1001, further, the turning drive motor 501 is a steering gear, the output end of the steering gear is a slider 5012, the slider 5012 is connected to one end of the swing arm 502 through the first tie rod 1001, and the swing arm 402 is connected to the other end of the swing arm 502 through the second tie rod 1002. Specifically, the slider 5012 is provided with a first connection hole 901, the two ends of the swing arm 502 are respectively provided with a second connection hole 902 and a third connection hole 903, the rocker arm 402 is provided with a fourth connection hole 904, the two ends of the first tie rod 1001 are respectively connected to the first connection hole 901 and the second connection hole 902, and the two ends of the second tie rod 1002 are respectively connected to the third connection hole 903 and the fourth connection hole 904.

[0038] In this embodiment, the wing portion includes a front wing 801 and a rear wing 802, the front wing 801 includes a front wing membrane 8011 and a front wing bracket 8012 arranged at the edge of the front wing membrane 8011, the rear wing 802 includes a rear wing membrane 8021 and a rear wing bracket 8022 arranged at the edge of the rear wing membrane 8021, the front wing bracket 8012 is rotatably connected to the rocker arm 402, one end of the rear wing bracket 8022 is rotatably connected to the rocker arm 402, and the other end of the rear wing bracket 8022 is rotatably connected to the frame 10. The front wing membrane 8011 and the rear wing membrane 8021 are made of P31N kite cloth.

[0039] In this embodiment, fixing seats 70 are provided on both sides of the frame 10, and the other end of the rear wing 802 bracket is rotatably connected to the fixing seat 70. The rocker arm 402 is provided with a fifth connection hole 905 for rotatably connecting the front wing 801 bracket and a sixth connection hole 906 at one end of the rear wing 802 bracket, respectively, and the fixing seat 70 is provided with a seventh connection hole 907 for rotatably connecting the other end of the rear wing 802 bracket.

[0040] In this embodiment, the frame 10 is provided with a control unit, which is electrically connected to the turning drive motor 501 and the power supply 60; it also includes a remote control, which is connected to the control unit through remote control to control the output pace of the output end of the turning drive motor 501 to change the degree of the angle of attack.

[0041] In this embodiment, there are a total of 24 types of parts, including 35 parts that are symmetrical on both sides, of which 28 parts can be produced using photocuring. Photocuring is superior to additive manufacturing technology in that it can manufacture multiple parts at the same time, and can achieve rapid mass production in a short time, greatly reducing the manufacturing time cost and raw material cost.

[0042] The utility model proposes a bionic butterfly aircraft with single-parameter control of attack angle, and its motion state is as follows:

[0043] The direct-acting drive motor 202 drives the first connecting rod 2031 to rotate, and drives the first flapping part 2041 to reciprocate up and down through the second connecting rod 2032 and the third connecting rod 2033, thereby driving the wings to flap up and down to realize the direct-acting flight of the aircraft. The movement of the slider 5012 of the turning drive motor 501 is controlled by remote control, thereby pulling the swing arm 502 to rotate through the first pull rod 1001, and the swing arm 502 pulls the swing arm 402 to rotate through the second pull rod 1002, thereby realizing the change of the attack angle of the rear wing 802, thereby realizing the turning flight of the aircraft. The direct-acting drive motor 202 and the turning drive motor 501 can be controlled simultaneously or separately, so that the two motion modes of direct motion and turning do not interfere with each other, realize the conversion of motion state, and have excellent maneuverability.

[0044] The above embodiments are only for illustrating the technical concept and features of the utility model, and their purpose is to enable those skilled in the art to understand the content of the utility model and implement it, and they cannot be used to limit the protection scope of the utility model. Any equivalent changes or modifications made according to the spirit of the utility model should be included in the protection scope of the utility model.

Claims

1. A bionic butterfly aircraft with single-parameter control of angle of attack, comprising a frame, characterized in that: The frame is provided with a direct-acting control device at one end and a turning control device respectively arranged at two sides of the frame, and a power supply for providing electric energy to the direct-acting control device and the turning control device at the other end of the frame; and further comprises wings arranged at two sides of the frame, one end of the wing is connected to the direct-acting control device, and the other end of the wing is connected to the frame; The direct-acting control device comprises a direct-acting drive motor, a transmission part and a flapping device which are sequentially connected in transmission, the flapping device comprises a first flapping part and a second flapping part which are mutually connected in transmission, one end of the transmission part is connected to the output end of the direct-acting drive motor, and the other end of the transmission part is connected to the first flapping part or the second flapping part, so that the first flapping part and the second flapping part flap back and forth, the first flapping part and the second flapping part are respectively provided with a rotatable swinging part outside, and one end of the wing part is connected to the swinging part; The turning control device includes a turning drive motor and a swing arm rotatably connected to the frame, the output end of the turning drive motor is connected to one end of the swing arm, and the other end of the swing arm is connected to the swinging part, so that the angle of attack of the wing part is changed by the turning drive motor.

2. The angle of attack single parameter controlled bionic butterfly aircraft according to claim 1, characterized in that: At least part of the outer surfaces of the first flapping part and the second flapping part are provided with mutually meshing teeth, and the first flapping part and the second flapping part are respectively provided with a slot for inserting the swing part.

3. The angle of attack single parameter controlled bionic butterfly aircraft according to claim 2, characterized in that: The transmission part includes a first connecting rod, a second connecting rod and a third connecting rod which are rotatably connected to each other in sequence, the first connecting rod is connected to the output end of the direct-acting drive motor, the third connecting rod is connected to the first flapping part or the second flapping part, and the first connecting rod is a crank, and the third connecting rod is a rocker to drive the first flapping part and the second flapping part to flap reciprocally.

4. The angle of attack single parameter controlled bionic butterfly aircraft according to claim 2, characterized in that: The swinging part comprises a pivot seat and a rocker arm, one end of the pivot seat is provided with a convex portion inserted into the slot, and the other end of the pivot seat is provided with a circular boss for rotatably connecting the rocker arm.

5. The angle of attack single parameter controlled bionic butterfly aircraft according to claim 4, characterized in that: The output end of the turning drive motor is connected to one end of the swing arm through a first pull rod, and the swing arm is connected to the other end of the swing arm through a second pull rod.

6. The angle of attack single parameter controlled bionic butterfly aircraft according to claim 5, characterized in that: The direct-acting drive motor is a coreless motor, the turning drive motor is a steering gear, the output end of the steering gear is a slider, and the slider is connected to one end of the swing arm through the first pull rod.

7. The angle of attack single parameter controlled bionic butterfly aircraft according to claim 4, characterized in that: The wing part includes a front wing and a hind wing, the front wing includes a front wing membrane and a front wing bracket arranged at the edge of the front wing membrane, the hind wing includes a hind wing membrane and a hind wing bracket arranged at the edge of the hind wing membrane, the front wing bracket is rotatably connected to the rocker arm, one end of the hind wing bracket is rotatably connected to the rocker arm, and the other end of the hind wing bracket is rotatably connected to the frame.

8. The angle of attack single parameter controlled bionic butterfly aircraft according to claim 7, characterized in that: The front wing membrane and the rear wing membrane are made of P31N kite cloth.

9. The angle of attack single parameter controlled bionic butterfly aircraft according to claim 7, characterized in that: Fixed seats are arranged on both sides of the frame, and the other end of the rear wing bracket is rotatably connected to the fixed seat.

10. The angle of attack single parameter controlled bionic butterfly aircraft according to claim 1, characterized in that: The frame is provided with a control unit, which is electrically connected to the turning drive motor and a power source; and further comprises a remote control, which is communicatively connected to the control unit, and controls the output pace of the output end of the turning drive motor through the remote control to change the degree of the angle of attack.

Images