Flapping wing structure of flapping wing aircraft

Abstract

The utility model discloses a flapping wing structure of a flapping wing air vehicle, which belongs to the technical field of flapping wing air vehicles and comprises a plurality of flapping wing units, every two adjacent flapping wing units are rotatably connected through a hinge piece, and a connecting piece connected with a flapping wing air vehicle body is arranged on the side wall of the flapping wing unit at the front end. One side of the flapping wing unit at the tail end is gradually narrowed to form an arc-shaped wing tail; each flapping wing unit comprises a main frame body and side frame assemblies arranged on the two sides of the main frame body, the middle part of the main frame body is thickest and is gradually thinned towards the two sides, and the thickness of each side frame assembly is gradually reduced from one side to the other side along with the main frame body until a thin edge is formed. The form of the flapping wing is changed by hinging the flapping wing units, so that the flapping wing can be suitable for posture adjustment under different flight conditions, and the form can be changed in time to maintain the flight stability; and a plurality of repeated unit type structures are adopted, so that production and manufacturing are more convenient, and cost is saved.

Description

Technical Field

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

[0002] In nature, birds or insects can take off, accelerate and hover quickly by flapping wings, and have high maneuverability and flexibility. Flapping-wing aircraft have advantages in small spaces due to their small size and light weight, and have good concealment, and have very broad application prospects in military and civilian fields.

[0003] In the prior art, common flapping-wing aircraft have the following problems: Asymmetric flapping-wing motion. Many flapping-wing aircraft adopt an asymmetric flapping-wing structure, which has a simple structure and insufficient lift, and cannot achieve stable flight of the aircraft.

[0004] Therefore, the flapping-wing structure of a flapping-wing aircraft becomes a problem that needs to be solved urgently. Utility Model Content

[0005] The technical problem to be solved by the utility model is to provide a flapping-wing structure of a flapping-wing aircraft which has a simple structure, low manufacturing cost and can maintain stable flight.

[0006] In order to solve the above technical problems, the technical solution provided by the utility model is as follows: a flapping wing structure of a flapping wing aircraft, comprising a plurality of flapping wing units, two adjacent flapping wing units are rotatably connected by a hinge, a side wall of the flapping wing unit at the front end is provided with a connecting piece connected to the flapping wing aircraft body, and one side of the flapping wing unit at the end is gradually narrowed to form an arc-shaped wing tail;

[0007] The flapping-wing unit includes a main frame and side frame assemblies arranged on both sides of the main frame. The main frame is thickest in the middle and gradually becomes thinner towards the two sides. The thickness of the side frame assemblies gradually narrows from one side to the other side along with the main frame until a thin edge is formed.

[0008] Furthermore, the side frame assembly includes a plurality of grille members and triangular edge members, the grille members are connected to the main frame body via hinges, and the grille members are also connected to each other via hinges, and the triangular edges are also connected to the grille members via hinges.

[0009] The advantages of the utility model compared with the prior art are: the utility model realizes the change of the shape of the flapping wings through the hinge of several flapping wing units, can be suitable for posture adjustment under different flight conditions, and can instantly change the shape to maintain flight stability; it adopts a structure of several repeated units, which is more convenient to produce and manufacture and saves costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1The utility model is a structural schematic diagram of a flapping-wing structure of a flapping-wing aircraft.

[0011] Figure 2 The utility model is a front view of a flapping-wing structure of a flapping-wing aircraft.

[0012] Figure 3 The utility model is a structural schematic diagram of a flapping-wing unit of a flapping-wing structure of a flapping-wing aircraft.

[0013] As shown in the figure: 1. flapping unit, 2. connecting part, 11. main frame, 12. side frame assembly, 121. grille part, 122. triangular edge part. DETAILED DESCRIPTION

[0014] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "inside", "outside", "vertical", "circumferential", etc., indicating orientations or positional relationships, are 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 device or element referred to 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.

[0015] In the present invention, unless otherwise clearly specified and limited, the terms "install", "connect", "connect", "fix" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0016] The flapping-wing structure of a flapping-wing aircraft of the utility model is further described in detail below in conjunction with the accompanying drawings.

[0017] Combined with Figure 1-3 The specific implementation process of the flapping-wing structure of a flapping-wing aircraft of the utility model is as follows:

[0018] A flapping-wing structure of a flapping-wing aircraft, comprising a plurality of flapping-wing units 1, wherein two adjacent flapping-wing units 1 are rotatably connected via hinges, a side wall of the flapping-wing unit 1 at the front end is provided with a connector 2 connected to a flapping-wing aircraft body, and one side of the flapping-wing unit 1 at the end gradually narrows to form an arc-shaped wing tail; the flapping-wing units 1 are connected via hinges, so as to facilitate changing the overall shape and adjusting the attitude of the aircraft;

[0019] The flapping-wing unit 1 includes a main frame 11 and side frame assemblies 12 arranged on both sides of the main frame 11. The main frame 11 is thickest in the middle and gradually becomes thinner towards the two sides. The thickness of the side frame assemblies 12 gradually narrows from one side to the other side along with the main frame 11 until a thin edge is formed. The flapping-wing unit 1 is divided into multiple components, so that each component can be controlled separately, which is conducive to fine control.

[0020] In one embodiment of the present application, the side frame assembly 12 includes a plurality of grille members 121 and triangular edge members 122, the grille members 121 are connected to the main frame body 11 via hinges, and the grille members 121 are also connected to each other via hinges, and the triangular edges are also connected to the grille members 121 via hinges; each structure is connected via hinges to facilitate adjustment of the posture of each component, thereby achieving overall adjustment and fine control.

[0021] Preferably, each side frame assembly 12 includes two grille members 121.

[0022] Preferably, the thickness of the side panels connecting the side frame assemblies 12 on both sides of the main frame 11 is greater than the thickness of the side panels of each grille in the main frame 11. The greater thickness makes it stronger and the connection more stable.

[0023] Preferably, the flapping-wing units 1 are provided with six and the first four have the same structure and are connected in sequence, and one side of the last two gradually narrows inward to form an arc-shaped wing edge. With this number of structures, control is more convenient and an optimal structural state is formed.

[0024] 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 structure of a flapping-wing aircraft, characterized in that: It comprises a plurality of flapping-wing units (1), wherein two adjacent flapping-wing units (1) are rotatably connected via a hinge, a side wall of the flapping-wing unit (1) at the front end is provided with a connecting piece (2) connected to a flapping-wing aircraft body, and one side of the flapping-wing unit (1) at the end is gradually narrowed to form an arc-shaped wing tail; The flapping-wing unit (1) comprises a main frame (11) and side frame assemblies (12) arranged on both sides of the main frame (11); the main frame (11) is thickest in the middle and gradually becomes thinner towards both sides; the thickness of the side frame assemblies (12) gradually becomes narrower from one side to the other side along with the main frame (11) until a thin edge is formed.

2. The flapping-wing structure of a flapping-wing aircraft according to claim 1, characterized in that: The side frame assembly (12) comprises a plurality of grille members (121) and triangular edge members (122); the grille members (121) are connected to the main frame body (11) via hinges, and the grille members (121) are also connected to each other via hinges; the triangular edge members and the grille members (121) are also connected to each other via hinges.

3. The flapping-wing structure of a flapping-wing aircraft according to claim 2, characterized in that: Each side frame assembly (12) includes two grille members (121).

4. The flapping-wing structure of a flapping-wing aircraft according to claim 3, characterized in that: The thickness of the side panels connected to the side frame components (12) on both sides of the main frame (11) is greater than the thickness of the side panels of each grille in the main frame (11).

5. The flapping-wing structure of a flapping-wing aircraft according to claim 4, characterized in that: The flapping wing units (1) are provided with six, and the first four have the same structure and are connected in sequence, while one side of the last two gradually narrows inwards to form an arc-shaped wing edge.

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