Variable wing flexible structure

Abstract

The application relates to a variable wing flexible structure and relates to the technical field of variable aircraft structures. The skin adopts a novel flexible corrugated structure, compared with traditional aircrafts, the variable back-swept angle wing can solve the contradiction between high and low speed performance requirements, improve the aerodynamic characteristics of the aircraft, reduce the flight energy consumption of the aircraft and realize various task requirements. Compared with the existing variable back-swept aircraft, the wing is divided into a flexible area and a rigid area, the skin of the deformation area adopts a novel flexible corrugated structure, the continuous deformation of the deformation area can be realized, and finally the wing can realize large-scale back-swept angle deformation of 30 DEG to 60 DEG.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of variable aircraft structure, in particular to a variable wing flexible structure. BACKGROUND

[0002] Traditional aircrafts are designed for specific flight conditions and flight environment, and can show good flight performance at a certain design state point, but most of the time the performance is poor. However, modern aircrafts need to perform various tasks such as military reconnaissance, large maneuver combat, long-distance transportation, medical disaster relief, etc., not only requiring higher cruising speed, but also facing more complex flight environment.

[0003] Small sweepback angle helps to improve the efficiency of the wing when the aircraft flies at low speed, and large sweepback angle helps to reduce wave resistance when the aircraft flies at high speed. The sweepback angle changes automatically in different flight states, which is the most effective means to consider different aerodynamic performance at high and low speeds. The variable sweep aircraft can change the shape of the aircraft locally, so that the aircraft can adapt to various task requirements in real time and maintain optimal performance and efficiency in various environments.

[0004] However, the existing variable sweep aircraft still has many deficiencies: 1. It mostly uses traditional metal skin, which cannot deform greatly with the wing structure due to its high stiffness; 2. The surface continuity is not good enough, resulting in low aerodynamic efficiency and large resistance. SUMMARY

[0005] In view of the problems of deformation scale limitation and poor continuity in the prior art, the present application provides a variable wing flexible structure with large-scale deformation and continuous skin in the deformation area. The skin uses a new type of flexible corrugated structure, which can finally realize large-scale deformation of the sweepback angle of 30°-60°. The present application is of great significance to improve the design level of aircrafts.

[0006] The purpose of the present application is to provide a variable wing flexible structure, which comprises a rotating shaft 1, an actuating mechanism 2, an outer wing end rib 3, a rigid zone heel rib 4, an intermediate rib 5, an intermediate wall 6, an outer wing heel rib 7, a leading edge wall 8, a connecting wall 9, a support plate 10, a general skin 11, a corrugated skin 12, a rigid zone root rib side double lug 13, a mounting plate 14 and a rigid zone root rib bottom double lug 15.

[0007] The variable wing comprises an outer wing main body and an actuating mechanism 2. The root of the outer wing main body is provided with an outer wing end rib 3, and a hole groove is formed in the outer wing end rib 3. The rigid zone root rib side double lug 13 is fixed on the rigid zone heel rib 4 and extends out of the hole groove of the outer wing end rib 3. One end of the actuating mechanism 2 is hinged to the rigid zone heel rib 4 through the rigid zone root rib side double lug 13, and the other end of the actuating mechanism 2 is hinged to the mounting plate 14.

[0008] The outer wing body comprises a flexible region and a rigid region, the rigid region is connected above the outer wing end rib 3, and the flexible region is connected below the outer wing end rib 3, the outer wing end rib 3 is fixedly connected in the middle of the rotating shaft 1, the rotating shaft 1 is provided with a protruding sliding groove in the middle, and both ends of the rotating shaft 1 are hingedly connected with the rigid region root rib bottom double ear pieces 15.

[0009] The left side of the rigid region is the rigid region root rib 4, the surface of the rigid region root rib 4 has two stepped heights, the surface low flat part is embedded in the inner side of the outer wing end rib 3, and the surface protruding part is connected with the ordinary skin 11; the bottom of the rigid region root rib 4 is provided with the rigid region root rib bottom double ear pieces 15. The right side of the rigid region is provided with the outer wing root rib 7, the intermediate ribs 5 are uniformly distributed between the outer wing end rib 3 and the outer wing root rib 7, one end of the intermediate rib 5 is connected with the leading edge wall 8, and the other end of the intermediate rib 5 is connected with the connecting wall 9, and the intermediate wall 6 is arranged in the direction of the intermediate rib 5 (preferably, the intermediate rib 5 is three, and the intermediate wall 6 is two).

[0010] The outer surface of the flexible region is provided with the corrugated skin 12, the support plates 10 are arranged between the corrugated skins 12 to maintain the shape of the corrugated skin (preferably, the support plates 10 are three), and the corrugated skin 12 and the support plates 10 are fixedly connected; the support plates 10 are rotationally connected with the rotating shaft 1.

[0011] Further, the front end of the support plate 10 is embedded in the protruding sliding groove of the rotating shaft 1, and the support plate 10 can smoothly move in the protruding sliding groove.

[0012] Further, the rigid region and the flexible region are connected through the connecting wall 9, and the connecting wall 9 is fixedly connected with the rigid region root rib 4, the intermediate rib 5 and the outer wing root rib 7 in sequence.

[0013] Further, the surface of the rigid region is provided with the ordinary skin 11, and the fan-shaped area of the ordinary skin 11 is bent downward below the corrugated skin 12.

[0014] Further, the corrugated skin 12 can be elongated and compressed, and when the corrugated skin 12 is deformed, each point on the skin rotates around the rotating shaft 1.

[0015] Further, the rigid region and the flexible region can rotate around the rotating shaft 1; and the support plates 10 can rotate around the rotating shaft 1.

[0016] Compared with the prior art, the beneficial effects of the present application are:

[0017] Compared with the traditional aircraft, the variable sweep angle wing can solve the contradiction between high and low speed performance requirements, improve the aerodynamic characteristics of the aircraft, reduce the flight energy consumption of the aircraft, and realize various task requirements. Compared with the existing variable sweep aircraft, the present application divides the wing into a flexible region and a rigid region, the deformation region skin adopts a new type of flexible corrugated structure, the deformation region can realize continuous deformation, and finally the wing can realize large-scale sweep angle deformation of 30°-60°. BRIEF DESCRIPTION OF DRAWINGS

[0018] Other features, objects, and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments thereof, when read in connection with the following drawings:

[0019] Figure 1 Fig. 1 is a schematic diagram of a variant wing flexible structure; Fig. 2 is a schematic diagram of a rigid zone root rib side double lug; Fig. 3 is a schematic diagram of a rigid zone root rib bottom double lug and a rotating shaft; Fig. 4 is a schematic diagram of a fan-shaped area; Fig. 5 is a schematic diagram of a variant wing flexible structure after deformation; Fig. 6 is a schematic diagram of a support plate and a rotating shaft convex sliding groove.

[0020] Figure 2 Fig. 7 is a schematic diagram of a variant wing flexible structure inside.

[0021] Figure 3 Fig. 8 is a schematic diagram of a variant wing flexible structure after deformation.

[0022] Figure 4 Fig. 9 is a schematic diagram of a support plate and a rotating shaft convex sliding groove.

[0023] In the drawings: 1 rotating shaft, 2 actuating mechanism, 3 outer wing end rib, 4 rigid zone heel rib, 5 middle rib, 6 middle wall, 7 outer wing heel rib, 8 leading edge wall, 9 connecting wall, 10 support plate, 11 ordinary skin, 12 corrugated skin, 13 rigid zone root rib side double lug, 14 mounting plate, 15 rigid zone root rib bottom double lug. DETAILED DESCRIPTION

[0024] The technical solutions of the present application will be further described below in combination with the drawings and specific embodiments. It should be noted that the following described embodiments are only a part of the embodiments of the present application, but not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0025] In the embodiments of the present application, a variant wing flexible structure includes a rotating shaft 1, an actuating mechanism 2, an outer wing end rib 3, a rigid zone heel rib 4, a middle rib 5, a middle wall 6, an outer wing heel rib 7, a leading edge wall 8, a connecting wall 9, a support plate 10, an ordinary skin 11, a corrugated skin 12, a rigid zone root rib side double lug 13, a mounting plate 14, and a rigid zone root rib bottom double lug 15. The variant structure before deformation is shown in Fig. 1, and the variant structure after deformation is shown in Fig. 5. Figure 1 Figure 3

[0026] ​​Specifically, as a preferred embodiment of the present application, the actuating mechanism 2 pushes the rigid zone root rib 4 through the rigid zone root rib side double lug 13, the rigid zone root rib 4 rotates around the rotating shaft 1, the rigid zone root rib 4 drives the whole rigid zone to rotate around the rotating shaft 1 to the corresponding angle; the connecting wall 9 connects the rigid zone and the flexible zone, with the rotation of the rigid zone, the connecting wall 9 drives the corrugated skin 12 to compress, the internal support plate 10 of the corrugated skin 12 slides in the convex sliding groove of the rotating shaft 1 with the compression of the skin, so as to rotate around the rotating shaft 1.

[0027] The above is only a preferred specific embodiment of the present application, but the protection scope of the present application is not limited thereto, any person skilled in the art can make equivalent replacement or change according to the technical scheme and the inventive concept of the present application within the technical range disclosed by the present application, which should be covered in the protection scope of the present application.

Claims

1. A variant wing flexible structure, characterized in that, The variant wing flexible structure comprises a rotating shaft (1), an actuating mechanism (2), an outer wing end rib (3), a rigid area heel rib (4), an intermediate rib (5), an intermediate wall (6), an outer wing heel rib (7), a leading edge wall (8), a connecting wall (9), a support plate (10), a common skin (11), a corrugated skin (12), a rigid area root rib side double lug (13), a mounting plate (14) and a rigid area root rib bottom double lug (15); The variant wing comprises an outer wing main body and an actuating mechanism (2), the root of the outer wing main body is provided with an outer wing end rib (3), a hole groove is formed in the outer wing end rib (3), a rigid area root rib side double lug (13) is fixed on the rigid area heel rib (4) and extends out of the hole groove of the outer wing end rib (3); one end of the actuating mechanism (2) is hinged to the rigid area heel rib (4) through the rigid area root rib side double lug (13), and the other end of the actuating mechanism (2) is hinged to the mounting plate (14); The outer wing main body comprises a flexible area and a rigid area, the outer wing end rib (3) is connected to the rigid area above and connected to the flexible area below, the outer wing end rib (3) is fixedly connected to the rotating shaft (1) in the middle part, the rotating shaft (1) is provided with a protruding sliding groove in the middle part, and the rotating shaft (1) is hinged to the rigid area root rib bottom double lug (15) at both ends; The left side of the rigid area is a rigid area root rib (4), the surface of the rigid area root rib (4) has two stepped heights, the low surface is embedded into the inner side of the outer wing end rib (3), and the protruding surface is connected to the common skin (11); the bottom of the rigid area root rib (4) is provided with the rigid area root rib bottom double lug (15); the right side of the rigid area is provided with an outer wing root rib (7), the intermediate ribs (5) are uniformly distributed between the outer wing end rib (3) and the outer wing root rib (7), one end of the intermediate rib (5) is connected to the leading edge wall (8), the other end of the intermediate rib (5) is connected to the connecting wall (9), and the intermediate wall (6) is arranged along the direction of the intermediate rib (5); The outer surface of the flexible area is provided with the corrugated skin (12), the support plates (10) are arranged between the corrugated skins (12) to maintain the shape of the corrugated skin, and the corrugated skin (12) and the support plate (10) are fixedly connected; the support plate (10) is rotationally connected with the rotating shaft (1).

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