Adjusting structure device for flapping wing form of flapping wing air vehicle

Abstract

The utility model relates to the technical field of flapping wing aircrafts, in particular to an adjusting structure device for the flapping wing form of a flapping wing aircraft, which comprises a plurality of main frameworks, a plurality of auxiliary frameworks and a plurality of wing edge plates, and angle adjustment can be realized between the corresponding main frameworks, between the main frameworks and the auxiliary frameworks and between the auxiliary frameworks. The corresponding main frameworks are fixedly connected with the wing edge plates, and the corresponding auxiliary frameworks are hinged or fixedly connected with the wing edge plates. The flapping wing is reasonable in structure, the angles of the main framework, the auxiliary framework and the wing edge plate can be changed through stretching and retracting of the telescopic blocks, the shape of the flapping wing can be changed, the flapping wing can better simulate wing waving flying of birds, the better bionic effect is achieved, and therefore the aerodynamic performance of an aircraft is improved, and the service life of the aircraft is prolonged. The flight efficiency and the flight flexibility and stability are improved, so that more complex flight actions can be completed, and the requirement of executing various high-difficulty tasks in various different complex environments can be met.

Description

Technical Field

[0001] The utility model relates to the technical field of flapping-wing aircraft, in particular to a flapping-wing aircraft flapping morphology adjustment structure device. Background Art

[0002] Flapping-wing aircraft is a bionic aircraft that imitates the flapping of birds' wings, following fixed-wing aircraft and rotorcraft. It has the characteristics of good flexibility, high efficiency, light weight, low noise and good concealment.

[0003] Existing bionic flapping-wing aircraft generally adopt single-wing flapping or double-wing flapping, but generally can only achieve simple overall flapping up and down flapping, cannot achieve real-time adjustment of flight status, and cannot achieve the morphological change of the flapping wing itself. The degree of bionics is low, resulting in low flight efficiency, poor flexibility and poor stability of the aircraft. Utility Model Content

[0004] The technical problem to be solved by the utility model is to overcome the defects of the above-mentioned technology and provide a structural device for adjusting the flapping wing shape of a flapping-wing aircraft.

[0005] A flapping-wing aircraft flapping morphology adjustment structural device comprises a plurality of mutually hinged main frames, a plurality of sub-frames are hinged on the front and rear sides of each main frame, the sub-frames located on the same side of each main frame are hinged, the sub-frames located at the edge of each main frame are hinged with wing side panels, and rotation control devices are provided between adjacent hinged main frames, between adjacent hinged sub-frames, between the main frame and the adjacent hinged sub-frames, between the wing side panels and the adjacent hinged sub-frames, and on the upper and lower sides of the hinge points, and the corresponding rotation control devices control the angles between adjacent hinged main frames, the angles between adjacent hinged sub-frames, the angles between the main frame and the adjacent hinged sub-frames, and the angles between the wing side panels and the adjacent hinged sub-frames.

[0006] Furthermore, the rotation control device includes a shell, one side of the shell is provided with an entrance and exit, a telescopic block is provided at the entrance and exit, a wedge-shaped push block capable of moving linearly is provided on the inner side of the shell, the wedge-shaped push block is in contact with the telescopic block through an inclined surface, a return spring is provided between one end of the telescopic block away from the wedge-shaped push block and the inner wall of the shell, and the wedge-shaped push block is connected to a power device for controlling the linear movement of the wedge-shaped push block.

[0007] Furthermore, the power device includes a drive motor, a nut, and a screw. The drive motor is connected to the screw through a worm gear box. The nut is fixed in the housing. The screw is threadedly connected to the nut. One end of the screw is rotationally connected to the axis of the wedge-shaped push block.

[0008] Furthermore, the wedge-shaped push block is provided with a cylindrical groove at one end close to the screw rod, and the screw rod is provided with a circular plate at one end close to the wedge-shaped push block. The circular plate is arranged in the cylindrical groove, and the cylindrical groove is configured with a limiting plate to limit the circular plate in the cylindrical groove.

[0009] Furthermore, the cross section of the main frame is in a symmetrical trapezoidal shape, and the cross section of the auxiliary frame is in a trapezoidal shape.

[0010] Furthermore, the main frame located at the wing tip of the flapping wing of the aircraft is fixedly connected to the wing side panel, the sub-frame located at the rear side of the main frame at the wing tip is fixedly connected to the corresponding wing side panel, the sub-frame located at the front side of the main frame at the wing tip is fixedly connected to the wing side panel corresponding to the end away from the fuselage of the aircraft, and the sub-frame located at the outermost edge of the front side of the main frame at the wing tip is hinged to the front wing side panel.

[0011] The beneficial effects of the utility model compared with the prior art are as follows: the utility model has a reasonable structure, and the angle changes of the main frame, the auxiliary frame and the wing edge panels are achieved through the extension and retraction of the telescopic blocks, so that the flapping wings can achieve their own morphological changes, and can change their morphology during the flight process to meet the flight mechanics requirements, better simulate the flight of flying animals, such as the flapping wings of birds, and have better bionic effects, thereby improving the aerodynamic performance of the aircraft, improving the flight efficiency as well as the flexibility and stability of the flight, so that it can complete more complex flight movements to meet the needs of being able to perform various difficult tasks in various complex environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 It is a schematic diagram of a flapping wing configuration adjustment structural device of a flapping wing aircraft of the utility model;

[0013] Figure 2 This is a schematic diagram of the connection and angle change of each main skeleton of a flapping-wing aircraft flapping-wing adjustment structure device of the utility model;

[0014] Figure 3 It is a schematic diagram of the connection between a single main frame and a corresponding secondary frame and a wing side plate of a flapping-wing aircraft flapping-wing shape adjustment structure device of the utility model;

[0015] Figure 4 It is a schematic diagram of a rotation control device of a flapping-wing aircraft flapping-wing configuration adjustment structural device of the utility model;

[0016] Figure 5 The utility model is a schematic diagram of a single main frame and connected auxiliary frames and wing side panels of a flapping-wing aircraft flapping-wing shape adjustment structural device.

[0017] As shown in the figure: 1. Main frame; 2. Sub-frame; 3. Wing plate; 4. Rotation control device; 401. Shell; 402. Entrance and exit; 403. Telescopic block; 404. Wedge-shaped push block; 405. Reset spring; 406. Drive motor; 407. Nut; 408. Screw; 409. Worm gear box; 410. Cylindrical groove; 411. Circular plate; 412. Limit plate. DETAILED DESCRIPTION

[0018] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0019] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present utility model, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0020] In the description of the embodiments of the present utility model, if a feature is referred to as being "set", "fixed", "connected" or "installed" on another feature, it may be directly set, fixed, connected to another feature, or indirectly set, fixed, connected, or installed on another feature.

[0021] In the description of the embodiments of the present utility model, if "several" is involved, it means more than one, if "multiple" is involved, it means more than two, if "greater than", "less than" or "exceed" is involved, it should be understood as not including the number itself, if "above", "below" or "within" is involved, it should be understood as including the number itself. If "first" or "second" is involved, it should be understood as being used to distinguish technical features, and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features or implicitly indicating the order of the indicated technical features.

[0022] The utility model is further described in detail below in conjunction with the accompanying drawings.

[0023] like Figure 1 , 2As shown in and 3, a flapping-wing aircraft flapping morphology adjustment structural device comprises a plurality of mutually hinged main skeletons 1, a plurality of sub-skeletons 2 are hinged on the front and rear sides of each main skeleton 1, the sub-skeletons 2 located on the same side of each main skeleton 2 are hinged, the sub-skeleton 2 located at the edge of each main skeleton 1 is hinged with a wing side panel 3, and rotation control devices 4 are provided between adjacent hinged main skeletons 1, between adjacent hinged sub-skeletons 2, between the main skeleton 1 and the adjacent hinged sub-skeleton 2, between the wing side panel 3 and the adjacent hinged sub-skeleton 2, and on both sides above and below the hinge point, and the corresponding rotation control devices 4 control the angle between adjacent hinged main skeletons 1, the angle between adjacent hinged sub-skeletons 2, the angle between the main skeleton 1 and the adjacent hinged sub-skeleton 2, and the angle between the wing side panel 3 and the adjacent hinged sub-skeleton 2.

[0024] like Figure 4 As shown, the rotation control device 4 includes a shell 401, a port 402 is provided on one side of the shell 401, a telescopic block 403 is provided at the port 402, a wedge-shaped push block 404 capable of linear movement is provided on the inner side of the shell 401, the wedge-shaped push block 404 is in contact with the telescopic block 403 via an inclined surface, a return spring 405 is provided between one end of the telescopic block 403 away from the wedge-shaped push block 404 and the inner wall of the shell 401, and the wedge-shaped push block 401 is connected to a power device for controlling the linear movement of the wedge-shaped push block 404;

[0025] The power device includes a driving motor 406, a nut 407, and a screw 408. The driving motor 404 is connected to the screw 408 through a worm gear box 409. The nut 407 is fixed in the housing 401. The screw 408 is screwed to the nut 407. One end of the screw 408 is connected to the axis of the wedge-shaped push block 404 for rotation.

[0026] The wedge-shaped push block 404 is provided with a cylindrical groove 410 at one end close to the screw rod 408, and the screw rod 408 is provided with a circular plate 411 at one end close to the wedge-shaped push block 404. The circular plate 411 is arranged in the cylindrical groove 410, and the cylindrical groove 410 is configured with a limiting plate 412 to limit the circular plate 411 in the cylindrical groove 410.

[0027] like Figure 3 As shown, the cross section of the main frame 1 is a symmetrical trapezoidal shape, and the cross section of the auxiliary frame 2 is a trapezoidal shape.

[0028] like Figure 1 As shown, the main frame 1 located at the wing tip of the flapping wing of the aircraft is fixedly connected to the wing side panel 3, the sub-frame 2 located at the rear side of the main frame 1 at the wing tip is fixedly connected to the corresponding wing side panel 3, the sub-frame 2 located at the front side of the main frame 1 at the wing tip is fixedly connected to the wing side panel 3 corresponding to the end away from the aircraft fuselage, and the sub-frame 2 located at the front edge of the main frame 1 at the wing tip is hinged to the front wing side panel 3.

[0029] When the utility model is used, the distance between two adjacent components is controlled by controlling the extension length of the telescopic block 403 of the rotation control device 4 between adjacent hinged main frames 1, between adjacent hinged sub-frames 2, between the main frame 1 and the adjacent hinged sub-frames 2, between the wing side panels 3 and the adjacent hinged sub-frames 2, and located on the upper and lower sides of the hinge point, and then the angle change between the two adjacent components is realized by the rotation connection between the two adjacent components, so that the flapping wing shape changes in the front and rear directions of the flapping wing during the flight of the aircraft, such as Figure 5 As shown, the change of the flapping wing shape in the left and right directions of the flapping wing is realized, such as Figure 2 As shown, the degree of angle change is achieved by adjusting the degree of extension of the extension block 403 located above and below the hinge point between the two components, thereby achieving the degree of change in the shape of the flapping wing.

[0030] The utility model for adjusting the flapping wing morphology structure can change the practical function of the flapping wings of existing aerial vehicles, greatly improve the performance of flapping wings in various flight states, and make flapping wing aircraft have a wide range of uses in the future in the fields of air-to-ground transportation, tourism, leisure, entertainment, competition, transportation, military, etc.

[0031] The flapping-wing morphology structure adjustment device can realize various change states of the flapping wings to cope with the flapping-wing aircraft adapting to various flight states.

[0032] The above description of the utility model and its implementation methods is not restrictive. The drawings show only one implementation method of the utility model, and the actual structure is not limited thereto. In short, if ordinary technicians in this field are inspired by it and design structural methods and embodiments similar to the technical solution without creativity without departing from the purpose of the invention of the utility model, they should all fall within the protection scope of the utility model.

Claims

1. A flapping wing aircraft flapping wing morphology adjustment structure device, characterized in that: The invention comprises a plurality of mutually hinged main frames (1), a plurality of sub-frames (2) are hinged on the front and rear sides of each main frame (1), the sub-frames (2) located on the same side of each main frame (1) are hinged to each other, the sub-frames (2) located at the edge of each main frame (1) are hinged to a wing plate (3), and rotation control devices (4) are provided between adjacent hinged main frames (1), between adjacent hinged sub-frames (2), between the main frame (1) and adjacent hinged sub-frames (2), between the wing plate (3) and adjacent hinged sub-frames (2), and on both sides above and below the hinge point. The corresponding rotation control devices (4) control the angle between adjacent hinged main frames (1), the angle between adjacent hinged sub-frames (2), the angle between the main frame (1) and adjacent hinged sub-frames (2), and the angle between the wing plate (3) and adjacent hinged sub-frames (2).

2. The flapping wing morphology adjustment structure device of a flapping-wing aircraft according to claim 1, characterized in that: The rotation control device (4) comprises a housing (401), one side of the housing (401) is provided with an entrance (402), a telescopic block (403) is provided at the entrance (402), a wedge-shaped push block (404) capable of linear movement is provided inside the housing (401), the wedge-shaped push block (404) and the telescopic block (403) are in contact with each other via an inclined surface, a return spring (405) is provided between one end of the telescopic block (403) away from the wedge-shaped push block (404) and the inner wall of the housing (401), and the wedge-shaped push block (404) is connected to a power device for controlling the linear movement of the wedge-shaped push block (404).

3. The flapping wing morphology adjustment structure device of a flapping-wing aircraft according to claim 2, characterized in that: The power device comprises a driving motor (406), a nut (407), and a screw (408); the driving motor (406) is drivingly connected to the screw (408) via a worm gear box (409); the nut (407) is fixed in a housing (401); the screw (408) is threadedly connected to the nut (407); and one end of the screw (408) is rotationally connected to the axis of the wedge-shaped push block (404).

4. The flapping wing morphology adjustment structure device of a flapping-wing aircraft according to claim 3, characterized in that: The wedge-shaped push block (404) is provided with a cylindrical groove (410) at one end close to the screw rod (408), and the screw rod (408) is provided with a circular plate (411) at one end close to the wedge-shaped push block (404). The circular plate (411) is arranged in the cylindrical groove (410), and the cylindrical groove (410) is provided with a limiting plate (412) for limiting the circular plate (411) in the cylindrical groove (410).

5. A flapping wing morphology adjustment structural device according to any one of claims 1 to 4, characterized in that: The cross section of the main frame (1) is in a symmetrical trapezoidal shape, and the cross section of the secondary frame (2) is in a trapezoidal shape.

6. The flapping wing morphology adjustment structure device of a flapping-wing aircraft according to claim 5, characterized in that: A main frame (1) located at the wing tip of a flapping wing of an aircraft is fixedly connected to a wing edge panel (3), a sub-frame (2) located at the rear side of the main frame (1) at the wing tip is fixedly connected to a corresponding wing edge panel (3), a sub-frame (2) located at the front side of the main frame (1) at the wing tip is fixedly connected to a corresponding wing edge panel (3) away from an end of a fuselage of the aircraft, and a sub-frame (2) located at the front edge of the main frame (1) at the wing tip is hinged to the front wing edge panel (3).

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