阅读说明：本技术 一种柔性可折叠机翼 (Flexible and foldable wing ) 是由 周运来 毕纪元 许奔 于 2021-09-22 设计创作，主要内容包括：本发明公开的一种柔性可折叠机翼,属于飞行器装置技术领域。机翼基座的一侧与飞行器翼根部连接,机翼基座另一侧的前端与前缘主梁的根部转动连接,机翼基座另一侧的后端与后缘副梁的根部转动连接,折叠伺服传动系统分别与前缘主梁和后缘副梁的根部连接；前缘主梁的梢部与翼梢基座铰接,后缘副梁的梢部与翼梢基座铰接；若干机翼翼肋的两端分别与前缘主梁和后缘副梁铰接；柔性蒙皮分别包覆在机翼基座、翼梢基座、前缘主梁、后缘副梁和若干机翼翼肋外部,形成完整气动翼形。本发明能够实现飞行器机翼的高度折叠化,减少储存运输中飞行器的体积,提高飞行器的灵活性,实现飞行器的微型化。(The invention discloses a flexible and foldable wing, and belongs to the technical field of aircraft devices. One side of the wing base is connected with the root of the aircraft wing, the front end of the other side of the wing base is rotatably connected with the root of the leading edge main beam, the rear end of the other side of the wing base is rotatably connected with the root of the trailing edge auxiliary beam, and the folding servo transmission system is respectively connected with the roots of the leading edge main beam and the trailing edge auxiliary beam; the tip of the front edge main beam is hinged with the wingtip base, and the tip of the rear edge auxiliary beam is hinged with the wingtip base; two ends of a plurality of wing ribs of the wings are respectively hinged with the front edge main beam and the rear edge auxiliary beam; the flexible skin is respectively coated outside the wing base, the wing tip base, the front edge main beam, the rear edge auxiliary beam and the wing ribs of the wings to form a complete aerodynamic wing. The invention can realize the high folding of the aircraft wings, reduce the volume of the aircraft in storage and transportation, improve the flexibility of the aircraft and realize the miniaturization of the aircraft.)

1. A flexible foldable wing is characterized by comprising a wing base (1), a wing tip base (3), a leading edge main beam (5), a trailing edge auxiliary beam (6), a flexible skin (7), a folding servo transmission system (8) and a plurality of wing ribs (2);

one side of the wing base (1) is connected with the root of an aircraft wing, the front end of the other side of the wing base (1) is rotatably connected with the root of the leading edge main beam (5), the rear end of the other side of the wing base (1) is rotatably connected with the root of the trailing edge auxiliary beam (6), and the folding servo transmission system (8) is respectively connected with the roots of the leading edge main beam (5) and the trailing edge auxiliary beam (6); the tip of the front edge main beam (5) is hinged with the wingtip base (3), and the tip of the rear edge auxiliary beam (6) is hinged with the wingtip base (3); two ends of the wing ribs (2) of the wings are respectively hinged with the front edge main beam (5) and the rear edge auxiliary beam (6); the flexible skin (7) is respectively coated outside the wing base (1), the wing tip base (3), the front edge main beam (5), the rear edge auxiliary beam (6) and the wing ribs (2) of the wings to form a complete aerodynamic wing shape.

2. The flexible and foldable wing according to claim 1, characterized in that the folding servo transmission system (8) comprises a first servo motor (8-1), a second servo motor (8-2), a first motor rocker (8-3), a second motor rocker (8-4) and a control module (8-5); the first servo motor (8-1) is connected with the root of the front edge main beam (5) through a first motor rocker arm (8-3), the second servo motor (8-2) is connected with the root of the rear edge auxiliary beam (6) through a second motor rocker arm (8-4), the first servo motor (8-1) and the second servo motor (8-2) are respectively connected to the control module (8-5), and the control module (8-5) is in communication connection with the aircraft control center.

3. The flexible and foldable wing according to claim 2, characterized in that a mounting groove is arranged in the wing base (1), and the first servo motor (8-1), the second servo motor (8-2) and the control module (8-5) are arranged in the mounting groove.

4. The flexible and foldable wing according to claim 1, characterized in that a rotation limiting mechanism is arranged between the folding servo transmission system (8) and the leading edge main beam (5) and the trailing edge auxiliary beam (6).

5. The flexible and foldable wing according to claim 1, characterized in that the root of the leading edge main beam (5) is hinged to the wing base (1) through a first wing root rotating shaft (4-1), and the tip is hinged to the wing tip base (3) through a first wing tip rotating shaft (4-5); the root part of the trailing edge auxiliary beam (6) is hinged with the wing base (1) through a second wing root rotating shaft (4-2), and the tip part is hinged with the wing tip base (3) through a second wing tip rotating shaft (4-6); the front edge of the wing rib (2) is hinged with a front edge main beam (5) through a front edge rib rotating shaft (4-3), and the rear edge of the wing rib (2) is hinged with a rear edge auxiliary beam (6) through a rear edge rib rotating shaft (4-4).

6. The flexible and foldable wing according to claim 5, characterized in that the first wing root rotation axis (4-1), the second wing root rotation axis (4-2), the leading edge rib rotation axis (4-3), the trailing edge rib rotation axis (4-4), the first wing tip rotation axis (4-5) and the second wing tip rotation axis (4-6) are stainless steel damping hinge axes.

7. The flexible and foldable wing according to claim 1, characterized in that the chord lengths of the wing base (1), the wing rib (2) and the wing tip base (3) are all equal.

8. Flexible and foldable wing according to claim 1, characterized in that lightening holes are provided on the wing ribs (2).

9. The flexible and foldable wing of claim 1, characterized in that the wing base (1), the wing ribs (2), the wing tip base (3), the leading edge main girder (5) and the trailing edge auxiliary girder (6) are made of carbon fiber resin-based composite material, 7075 aviation aluminum alloy or titanium alloy material; the flexible skin (7) is made of butadiene-acrylonitrile rubber.

10. The flexible and foldable wing according to claim 1, characterized in that the profile lines of the wing base (1), the wing rib (2) and the wing tip base (3) are laminar profiles in subsonic aircraft and high lift-to-drag ratio low speed profiles in less than subsonic aircraft.

Technical Field

The invention belongs to the technical field of aircraft devices, and particularly relates to a flexible and foldable wing.

Background

The wings are the main devices for providing lift force during the flight of the aircraft, and the wing area of the wings greatly influences the magnitude of the lift force of the aircraft, so the aircraft usually needs a larger wing area to maintain the flight lift force. The general aircraft adopts the high aspect ratio wing to promote flight efficiency, but the high aspect ratio wing makes aircraft structure space occupation volume greatly increased, has reduced the flexibility of the storage transportation of aircraft.

Modern aircrafts pay attention to flexibility, activation and miniaturization, and have strict requirements on the size of the aircrafts, such as shipboard aircrafts, miniature reconnaissance unmanned planes and the like, and the wings of the aircrafts need to be folded to reduce the size of the aircrafts. The outer ends of the wings are turned inwards from the middle of the wingspan in the existing wing folding mode, and for an aircraft with a small aspect ratio, such as a shipboard aircraft, the occupied space reduced by the folding mode is only about half of the wingspan, so that the occupied space is reduced; for the aircraft with a large aspect ratio, the folding mode still has half of the width after being folded, and the flexibility and the miniaturization cannot be realized.

Disclosure of Invention

In order to solve the above problems, an object of the present invention is to provide a flexible foldable wing, which can realize high folding of an aircraft wing, reduce the volume of the aircraft during storage and transportation, improve the flexibility of the aircraft, and realize miniaturization of the aircraft.

The invention is realized by the following technical scheme:

the invention discloses a flexible foldable wing, which comprises a wing base, a wing tip base, a front edge main beam, a rear edge auxiliary beam, a flexible skin, a folding servo transmission system and a plurality of wing ribs, wherein the wing tip base is arranged on the wing base;

one side of the wing base is connected with the root of the aircraft wing, the front end of the other side of the wing base is rotatably connected with the root of the leading edge main beam, the rear end of the other side of the wing base is rotatably connected with the root of the trailing edge auxiliary beam, and the folding servo transmission system is respectively connected with the roots of the leading edge main beam and the trailing edge auxiliary beam; the tip of the front edge main beam is hinged with the wingtip base, and the tip of the rear edge auxiliary beam is hinged with the wingtip base; two ends of a plurality of wing ribs of the wings are respectively hinged with the front edge main beam and the rear edge auxiliary beam; the flexible skin is respectively coated outside the wing base, the wing tip base, the front edge main beam, the rear edge auxiliary beam and the wing ribs of the wings to form a complete aerodynamic wing.

Preferably, the folding servo transmission system comprises a first servo motor, a second servo motor, a first motor rocker arm, a second motor rocker arm and a control module; the first servo motor is connected with the root of the front edge main beam through a first motor rocker arm, the second servo motor is connected with the root of the rear edge auxiliary beam through a second motor rocker arm, the first servo motor and the second servo motor are respectively connected to the control module, and the control module is in communication connection with the aircraft control center.

Further preferably, a mounting groove is formed in the wing base, and the first servo motor, the second servo motor and the control module are all arranged in the mounting groove.

Preferably, a rotation limiting mechanism is arranged between the folding servo transmission system and the front edge main beam and between the folding servo transmission system and the rear edge auxiliary beam.

Preferably, the root part of the leading edge main beam is hinged with the wing base through a first wing root rotating shaft, and the tip part of the leading edge main beam is hinged with the wing tip base through a first wing tip rotating shaft; the root part of the trailing edge auxiliary beam is hinged with the wing base through a second wing root rotating shaft, and the tip part of the trailing edge auxiliary beam is hinged with the wing tip base through a second wing tip rotating shaft; the front edge of the wing rib is hinged with the front edge main beam through a front edge rib rotating shaft, and the rear edge of the wing rib is hinged with the rear edge auxiliary beam through a rear edge rib rotating shaft.

Further preferably, the first wing root rotating shaft, the second wing root rotating shaft, the front edge wing rib rotating shaft, the rear edge wing rib rotating shaft, the first wing tip rotating shaft and the second wing tip rotating shaft are stainless steel damping hinge shafts.

Preferably, the chord lengths of the wing base, wing rib and tip base are all equal.

Preferably, lightening holes are arranged on the wing ribs.

Preferably, the wing base, the wing ribs, the wing tip base, the leading edge main beam and the trailing edge auxiliary beam are made of carbon fiber resin matrix composite materials, 7075 aviation aluminum alloy or titanium alloy materials; the flexible skin is made of butadiene-acrylonitrile rubber.

Preferably, the profile line of the wing base, the wing rib and the wing tip base is a laminar airfoil profile in a subsonic aircraft, and is a high lift-drag ratio low speed airfoil profile in an aircraft with a speed less than subsonic.

Compared with the prior art, the invention has the following beneficial technical effects:

according to the flexible foldable wing disclosed by the invention, two ends of the front edge main beam and the rear edge auxiliary beam are respectively and rotatably connected with the wing base and the wing tip base, and meanwhile, a plurality of wing ribs are hinged between the front edge main beam and the rear edge auxiliary beam, so that a flexible skin forms a complete aerodynamic wing shape. The folding servo transmission system controls the root parts of the front edge main beam and the rear edge auxiliary beam to rotate, so that the folding and the unfolding of the whole wing can be realized. The whole wing has reasonable structural design, can realize high folding of the wing, greatly reduces the size of the aircraft, reduces the size of the aircraft in storage and transportation, improves the flexibility of the aircraft, and realizes the miniaturization of the aircraft.

Furthermore, the folding servo transmission system realizes transmission through the servo motor and the motor rocker arm, has simple structure, high control precision and high response speed, and can realize the flight of different sweepback angles of the wings, thereby enabling the aircraft to be suitable for more complex flight environments.

Furthermore, a placing groove arranged in the wing base is used for placing the folding servo transmission system, so that the folding servo transmission system is safe and reliable, the arrangement of other structures is not influenced, and meanwhile, the maintenance is convenient.

Furthermore, rotation limiting mechanisms are arranged between the folding servo transmission system and the front edge main beam and between the folding servo transmission system and the rear edge auxiliary beam, so that the condition that the subsequent control is influenced by overlarge rotation angle is avoided, and structural failure is prevented.

Furthermore, each hinged part adopts a stainless steel damping hinge shaft, so that the service life is long, the structure is reliable, and the control stability can be improved.

Furthermore, lightening holes are formed in wing ribs of the wings, so that the overall weight is lightened under the condition that the strength of the wing ribs of the wings is ensured, and the flexibility of the aircraft is improved.

Furthermore, the wing base, the front edge main beam, the rear edge auxiliary beam and the wing ribs are made of carbon fiber resin matrix composite materials, 7075 aviation aluminum alloy or titanium alloy materials, so that the structural strength is high, the density is low, and the structural lightweight design can be realized; the flexible skin is made of butadiene-acrylonitrile rubber, so that the reliability is high and the service life is long.

Furthermore, profile molded lines of the wing base, the wing ribs and the wing tip base are laminar airfoil profiles in the subsonic aircraft, and the profile molded lines of the aircraft with the lower speed are high-lift-drag-ratio airfoil profiles in the aircraft with the lower speed than the subsonic speed, so that the flight efficiency of the aircraft can be improved.

Drawings

FIG. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a schematic view of the overall structure of the interior of the flexible skin of the present invention;

fig. 3 is a schematic top view of the overall structure of the interior of the flexible skin of the present invention.

In the figure: the system comprises a wing base 1, a wing rib 2, a wing tip base 3, a wing tip base 4, a first wing root rotating shaft 1, a second wing root rotating shaft 4, a second wing root rotating shaft 2, a leading edge wing rib rotating shaft 4, a trailing edge wing rib rotating shaft 4, a first wing tip rotating shaft 5, a second wing tip rotating shaft 4, a leading edge main beam 5, a trailing edge auxiliary beam 6, a flexible skin 7, a folding servo transmission system 8, a first servo motor 8, a second servo motor 8, a first motor rocker 8, a second motor rocker 8, a first motor rocker 8, a second motor rocker 8 and a control module 8, wherein the first motor rocker 8 is a first motor rocker 8, a second motor rocker 8 and a second motor rocker 8.

Detailed Description

The present invention will now be described in further detail with reference to the accompanying drawings, which are included to illustrate and not to limit the invention:

referring to fig. 1, 2 and 3, the flexible foldable wing of the present invention includes a wing base 1, a wing tip base 3, a leading edge main girder 5, a trailing edge auxiliary girder 6, a flexible skin 7, a folding servo transmission system 8 and a plurality of wing ribs 2;

one side of the wing base 1 is connected with the root of an aircraft wing, the front end of the other side of the wing base 1 is rotatably connected with the root of the leading edge main beam 5, the rear end of the other side of the wing base 1 is rotatably connected with the root of the trailing edge auxiliary beam 6, and the folding servo transmission system 8 is respectively connected with the roots of the leading edge main beam 5 and the trailing edge auxiliary beam 6; the tip of the front edge main beam 5 is hinged with the wingtip base 3, and the tip of the rear edge auxiliary beam 6 is hinged with the wingtip base 3; two ends of the wing ribs 2 of the wings are respectively hinged with a front edge main beam 5 and a rear edge auxiliary beam 6; the flexible skin 7 is respectively coated outside the wing base 1, the wing tip base 3, the leading edge main beam 5, the trailing edge auxiliary beam 6 and the wing ribs 2 to form a complete aerodynamic wing. The leading edge main beam 5 is the same as the leading edge of the wing airfoil profile so as to ensure the aerodynamic shape of the leading edge of the flexible skin 7; the trailing edge secondary beam 6 is identical to the wing airfoil trailing edge to ensure the aerodynamic profile of the flexible skin 7 trailing edge.

In a preferred embodiment of the present invention, the folding servo transmission system 8 comprises a first servo motor 8-1, a second servo motor 8-2, a first motor rocker arm 8-3, a second motor rocker arm 8-4 and a control module 8-5; the first servo motor 8-1 is connected with the root of the front edge main beam 5 through a first motor rocker arm 8-3, the second servo motor 8-2 is connected with the root of the rear edge auxiliary beam 6 through a second motor rocker arm 8-4, the first servo motor 8-1 and the second servo motor 8-2 are respectively connected to the control module 8-5, and the control module 8-5 is in communication connection with an aircraft control center. Preferably, a mounting groove is formed in the wing base 1, and the first servo motor 8-1, the second servo motor 8-2 and the control module 8-5 are all arranged in the mounting groove.

In a preferred embodiment of the invention, a rotation limiting mechanism is arranged between the folding servo transmission system 8 and the front edge main beam 5 and the rear edge auxiliary beam 6.

In a preferred embodiment of the invention, the root of the leading edge main beam 5 is hinged with the wing base 1 through a first wing root rotating shaft 4-1, and the tip is hinged with the wing tip base 3 through a first wing tip rotating shaft 4-5; the root part of the trailing edge auxiliary beam 6 is hinged with the wing base 1 through a second wing root rotating shaft 4-2, and the tip part is hinged with the wing tip base 3 through a second wing tip rotating shaft 4-6; the front edge of the wing rib 2 is hinged with a front edge main beam 5 through a front edge rib rotating shaft 4-3, and the rear edge of the wing rib 2 is hinged with a rear edge auxiliary beam 6 through a rear edge rib rotating shaft 4-4. Preferably, the first wing root rotating shaft 4-1, the second wing root rotating shaft 4-2, the leading edge rib rotating shaft 4-3, the trailing edge rib rotating shaft 4-4, the first wing tip rotating shaft 4-5 and the second wing tip rotating shaft 4-6 are stainless steel damping hinge shafts.

In a preferred embodiment of the invention the chord lengths of the wing base 1, wing rib 2 and tip base 3 are all equal.

In a preferred embodiment of the invention, lightening holes are provided in the wing ribs 2.

The wing base 1, the wing ribs 2, the wing tip base 3, the leading edge main beam 5 and the trailing edge auxiliary beam 6 are made of low-density high-strength materials, such as carbon fiber resin matrix composite materials, 7075 aviation aluminum alloy or titanium alloy materials; the flexible skin 7 is made of high-elasticity corrosion-resistant rubber, such as butadiene-acrylonitrile rubber.

The profile molded lines of the wing base 1, the wing rib 2 and the wing tip base 3 are laminar airfoil profiles in subsonic aircrafts, and low-speed airfoil profiles with high lift-drag ratio in aircrafts with the speed less than subsonic speed.

The flexible foldable wing of the invention is in operation:

the flight control center sends signals to the control module 8-5, the control module 8-5 sends signals to the first servo motor 8-1 and the second servo motor 8-2, the first servo motor 8-1 and the second servo motor 8-2 respectively control the first motor rocker arm 8-3 and the second motor rocker arm 8-4 to rotate, and the first motor rocker arm 8-3 and the second motor rocker arm 8-4 are connected with the front edge main beam 5 and the rear edge auxiliary beam 6, so that the whole flexible transmission mechanism rotates, and the folding and unfolding processes of the wings are realized.

The above description is only a part of the embodiments of the present invention, and although some terms are used in the present invention, the possibility of using other terms is not excluded. These terms are used merely for convenience in describing and explaining the nature of the invention and are to be construed as any additional limitation which is not in accordance with the spirit of the invention. The foregoing is merely an illustration of the present invention for the purpose of providing an easy understanding and is not intended to limit the present invention to the particular embodiments disclosed herein, and any technical extensions or innovations made herein are protected by the present invention.