CN216374999U - A profiling flapper - Google Patents

Abstract

The utility model discloses a profiling flapper, comprising a frame, an adjustable wing, an adjustable tail, a take-off and landing damping mechanism and a driving mechanism. A wing fixing frame is arranged on the frame, and the adjustable aircraft The wing includes a driving gear and a connecting rod driving mechanism, the connecting rod driving mechanism includes an adjusting crank, a wing connecting rod and a connecting rod, the adjusting crank is fixed on the driving gear, and the connecting rod is respectively connected with the adjusting crank and the engine. The wing link is hinged and fixed, the adjustable tail includes a tail frame and a tail slide rod, the tail frame is hingedly fixed with a tail adjustment block and a tail crank, and the landing shock absorption mechanism includes a landing frame and a guide rod chute. , guide rod and connecting rod damping mechanism, the guide rod chute is hingedly fixed to the landing frame, one end of the guide rod is fixed with the guide rod chute and can move in the chute, and the other end is hinged to the connecting rod reducing shock mechanism.

Description

A profiling flapper

technical field

The utility model relates to the technical field of flying equipment, in particular to a profiling flapper.

Background technique

In 1997, DARPA invested $35 million to begin a four-year MAV research program. Caltech, University of Toronto, Georgia Institute of Technology, University of Florida, Vanderbilt University and other units have developed flapping-wing MAVs with different structures. The wingspan is generally about 15cm. Most of them use batteries to provide energy, and the flight time is about a few minutes. to ten minutes. At present, the flapping aircraft is still mainly in the laboratory testing stage, and there are some typical research results, such as the Hummingbird flying robot of the DARPA program in the United States, the Phoenix flapping aircraft of the Massachusetts Institute of Technology, and the Microbat of the California Institute of Technology. The domestic research status started relatively late, but domestic scientists have always paid attention to its development and started basic and research work in this area.

The power required by the bionic flapper at low speed is much smaller than that of ordinary aircraft, and it has excellent vertical take-off and landing capability. The biggest feature of flapper in the military is that it can be used for reconnaissance and can be well disguised as a bird Or insects approach the target to detect. The difference between flapping flight and other flying methods is that it uses the up and down flapping of the wings to generate lift and thrust, and concentrates hovering, propulsive flight and flight steering in a flapping wing system, so it is designed with high efficiency. A reliable flapping drive mechanism is particularly important.

Utility model content

(1) Technical problems to be solved

In order to overcome the deficiencies of the prior art, a profiling flapper is proposed. The design of the connecting rod wing can fit rich connecting rod curves by changing the relative length of each component, so as to realize the effective bionic of the flight attitude of birds. , and is also provided with an adjustable tail, which can assist the flapping aircraft to complete the conversion of flight attitudes such as pitch and yaw, and ensure the stable flight of the aircraft. The structure is simple and easy to manufacture.

(2) Technical solutions

The utility model is realized by the following technical solutions: the utility model proposes a profiling flapper, including a frame, an adjustable wing, an adjustable tail, a take-off and landing damping mechanism and a driving mechanism, and an organic A wing fixing frame, the adjustable wing is arranged on the wing fixing frame, the adjustable wing includes a driving gear and a connecting rod driving mechanism, and the connecting rod driving mechanism includes an adjusting crank, a wing connecting rod and a connecting link. rod, the adjusting crank is fixed on the drive gear, the connecting rod is hingedly fixed with the adjusting crank and the wing connecting rod respectively, the adjustable tail fin includes a tail fin frame and a tail fin sliding rod, and the tail fin frame is hinged and fixed respectively There is a tail wing adjusting block and a tail wing crank, one end of the tail wing sliding rod is provided with a tail wing, and the other end passes through the chute on the tail wing adjusting block and is hingedly fixed with the tail wing crank. A rod chute, a guide rod and a connecting rod damping mechanism, the guide rod chute is hingedly fixed to the landing frame, one end of the guide rod is fixed with the guide rod chute and can move in the chute, and the other end is hinged to the Link damping mechanism.

Further, the adjusting crank and the wing connecting rod are provided with several adjusting holes, the adjusting crank and the driving gear are rotatably and fixedly connected to the center of the gear, and the wing connecting rod is hinged with the wing fixing frame.

Further, the driving gears include two intermeshing gears and are rotatably fixed on the wing fixing frame.

Further, the wing fixing frame is a U-shaped rod-shaped structure.

Further, the tail includes a horizontal tail and a vertical tail, the horizontal tail is a V-shaped mechanism, and the vertical tail is a fin-shaped structure.

Further, the landing gear fixed on the frame includes a front landing gear and a rear landing gear, and the rear landing gear includes two fixed links parallel to each other and a rear wing is also fixed thereon.

Further, the linkage damping mechanism includes an upper damping connecting block, a lower damping connecting block, and a damping connecting rod, the upper damping connecting block is hingedly fixed to the frame, and the damping connecting rod is respectively connected with the upper damping connecting block. The connecting block and the lower shock-absorbing connecting block are hinged. A shock-absorbing spring is also connected between the upper shock-absorbing connecting block and the lower shock-absorbing connecting block.

Further, a landing wheel is connected to the end of the shock-absorbing link.

(3) Beneficial effects

Compared with the prior art, the utility model has the following beneficial effects:

The profiling flapper mentioned in the utility model is provided with an adjustable wing structure and uses the adjustment holes on the connecting rods to change the relative length of each component, so as to realize the bionic of the flying posture of birds, thereby making the flapper It can adapt to different environments, and is also equipped with an adjustable tail that can assist the flapper to complete the conversion of pitch, yaw and other flight attitudes, and ensure the stable flight of the aircraft. In addition to the first time, the setting of the damping mechanism can absorb the landing of the flapper. and the impact energy during sliding, so as to reduce the load acting on the body to an acceptable level; at the same time, it can also ensure that the vibration is quickly attenuated, and can achieve strong reliability. Its structure is simple, easy to manufacture and maintain.

Description of drawings

FIG. 1 is a schematic structural diagram of the present utility model.

FIG. 2 is a schematic diagram of the adjustable wing structure of the present invention.

Figure 3 is a schematic diagram of the structure of the adjustable tail in the present invention.

FIG. 4 is a schematic structural diagram of the connecting rod damping mechanism in the present invention.

1-frame; 2-adjustable wing; 3-adjustable tail; 4-take-off and landing damping mechanism; 5-rear wing; 6-landing wheel; 11-wing fixing frame; 21-drive gear; 22- Connecting rod drive mechanism; 31-tail frame; 32- tail slide; 33- tail adjusting block; 34- tail crank; 35- tail; 41- landing gear; 42- guide rod chute; 43- guide rod; 44- Connecting rod damping mechanism; 221-adjusting crank; 222-wing connecting rod; 223-connecting connecting rod; 411-front landing gear; 412-rear landing gear; 441-upper damping connection block; 442-lower damping connection block; 443 - shock linkage; 444 - shock spring.

Detailed ways

In order to make the purpose, technical solutions and advantages of the present utility model more clearly understood, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention, and are not intended to limit the present invention.

As shown in Figures 1 to 4, a profiling flapper includes a frame 1, an adjustable wing 2, an adjustable tail 3, a take-off and landing damping mechanism 4 and a driving mechanism. The frame 1 is provided with an organic The wing fixing frame 11, the adjustable wing 2 is arranged on the wing fixing frame 1, the adjustable wing 2 includes a driving gear 21 and a connecting rod driving mechanism 22, and the connecting rod driving mechanism 22 includes an adjusting crank 221 , a wing connecting rod 222 and a connecting connecting rod 223, the adjusting crank 221 is fixed on the drive gear 21, the connecting connecting rod 223 is hingedly fixed with the adjusting crank 221 and the wing connecting rod 222, the adjustable tail 3 It includes a tail wing frame 31 and a tail wing sliding rod 32. The tail wing frame 31 is hingedly fixed with a tail wing adjusting block 33 and a tail wing crank 34. One end of the tail wing sliding rod 32 is provided with a tail wing 35, and the other end passes through the tail wing adjusting block. The chute on 33 is hingedly fixed with the tail crank 34. The landing damping mechanism 4 includes a landing mount 41, a guide rod chute 42, a guide rod 43 and a connecting rod damping mechanism 44. The guide rod chute 42 The guide rod 43 is hingedly fixed to the landing mount 41 , one end of the guide rod 43 is fixedly engaged with the guide rod chute 42 and can move in the chute, and the other end is hinged to the connecting rod damping mechanism 44 .

Wherein, the adjusting crank 221 and the wing connecting rod 222 are provided with several adjusting holes, the adjusting crank 221 and the driving gear 22 are rotatably and fixedly connected to the center of the gear, and the wing connecting rod 222 is fixed to the wing The frame 11 is hinged, the driving gear 21 includes two intermeshing gears and is rotatably fixed on the wing fixing frame 11, the wing fixing frame 11 is a U-shaped rod structure, and the tail 35 includes a horizontal tail and a vertical tail. The tail, the horizontal tail is a V-shaped mechanism, the vertical tail is a fin structure, the landing gear 41 is fixed on the frame 1 and includes a front landing gear 411 and a rear landing gear 412, and the rear landing gear 412 includes The two fixed connecting rods are parallel to each other and the rear wing 5 is also fixedly arranged on them. The upper shock-absorbing connecting block 441 is hingedly fixed to the frame 1, and the shock-absorbing connecting rod 443 is hinged with the upper shock-absorbing connecting block 441 and the lower shock-absorbing connecting block 442, respectively, and the upper shock-absorbing connecting block 441 and the lower shock-absorbing connecting block are respectively hinged A shock-absorbing spring 444 is also connected between 442 , and a landing wheel 6 is connected to the end of the shock-absorbing link 443 .

Specifically, the frame 1 is provided with a receiving slot for the take-up and landing damping mechanism 4 to be retracted, the wing fixing frame 11 is vertically fixed on the frame 1, and the wing link 222 is hinged to the aircraft. At the upper end of the U-shaped rod on the wing fixing frame 11, the wing connecting rod 222 is hingedly fixed by two identical connecting rods head-to-tail. The relative length can realize the bionic of different bird flight attitudes. The outside of the adjustable wing 2 is wrapped with canvas, which can be used as the bionic of the bird's wings. The driving gear 21 is connected to the driving mechanism, and the driving mechanism is a driving motor. , the front landing gear 411 is arranged at the center of the front side of the frame 1, the rear landing gear 412 is arranged at both sides of the rear side of the frame 1, the tail frame 31 is fixed on the frame, and the tail is sliding The rod 32 passes through the notch on the tail adjustment block 33 and can rotate with the rotation of the tail adjustment block 33 on the tail frame 31, thereby adjusting the direction of the tail, and can assist the flapper to complete the pitch, yaw and other flight attitudes. To ensure the stable flight of the aircraft, the guide rod chute 42 is provided with a limit hole, through which the stable maintenance of the take-off and landing attitude can be achieved. The upper shock-absorbing connecting block 441 and the lower shock-absorbing connecting block 442 are provided with notches and hinge holes for connecting rods to be engaged.

The profiling flapper mentioned in the present utility model, in specific use, is driven by the drive motor to make the drive gear 21 rotate, and drive the adjustment crank 221 to move, so as to make the connecting rod hinged with it move, so that the The entire adjustable wing 2 moves up and down to realize the bionic flight action of the bird's wings. It is worth mentioning that the relative length of the connecting rod can be adjusted through the adjustment hole on the wing link 222, so as to realize the adjustment of the relative length of the connecting rod. The bionic flight attitude-like, so that the flapper can adapt to different environments, and the adjustable tail 3 can assist the flapper to complete the conversion of pitch, yaw and other flight attitudes, so as to ensure the stable flight of the aircraft. Secondly, when taking off and landing The take-off and landing damping mechanism 4 can effectively absorb the impact energy during the landing and sliding of the flapper, so that the load acting on the body can be reduced to an acceptable level; Strong reliability, simple structure, easy to manufacture and routine maintenance.

The above-mentioned embodiments merely describe the preferred embodiments of the present invention, and do not limit the concept and scope of the present invention. Under the premise of not departing from the design concept of the present invention, various modifications and improvements made by ordinary persons in the art to the technical solutions of the present invention shall fall within the protection scope of the present invention. The content has been fully described in the claims.

Claims (6)

1. A profiling flapper, characterized in that: comprising a frame (1), an adjustable wing (2), an adjustable tail (3), a take-off and landing damping mechanism (4) and a drive mechanism, the aircraft A wing fixing frame (11) is arranged on the frame (1), the adjustable wing (2) is arranged on the wing fixing frame (11), and the adjustable wing (2) comprises a driving gear (21) and A connecting rod driving mechanism (22), the connecting rod driving mechanism (22) comprises an adjusting crank (221), a wing connecting rod (222) and a connecting rod (223), the adjusting crank (221) is fixed to the driving gear (21), the connecting link (223) is hingedly fixed with the adjusting crank (221) and the wing link (222), respectively, and the adjustable tail (3) includes a tail frame (31) and a tail sliding rod ( 32), a tail adjusting block (33) and a tail crank (34) are respectively hingedly fixed on the tail frame (31), a tail (35) is provided at the end of one end of the tail slide rod (32), and the other end passes through The chute on the tail adjusting block (33) is hingedly fixed with the tail crank (34). and a connecting rod damping mechanism (44), the guide rod chute (42) is hingedly fixed to the landing mount (41), and one end of the guide rod (43) is fixedly engaged with the guide rod chute (42) and can be It moves in the chute, and the other end is hinged to the connecting rod damping mechanism (44). 2. A profiling flapper according to claim 1, characterized in that: a plurality of adjustment holes are provided on the adjustment crank (221) and the wing connecting rod (222), and the adjustment crank (221) 221) is rotatably and fixedly connected with the drive gear (21) at a position deviating from the center of the gear, and the wing link (222) is hinged with the wing fixing frame (11). 3 . The profiling flapper according to claim 2 , wherein the driving gear ( 21 ) comprises two intermeshing gears and is rotatably fixed on the wing fixing frame ( 11 ). 4 . 4 . The profiling flapper according to claim 3 , wherein the wing fixing frame ( 11 ) is a U-shaped rod-shaped structure. 5 . 5. a kind of profiling flapper according to claim 1, is characterized in that: described tail (35) comprises horizontal tail and vertical tail, described horizontal tail is V-shaped mechanism, and described vertical tail is fin-shaped structure. 6. A profiling flapper according to claim 1, characterized in that: the landing gear (41).

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