阅读说明：本技术 一种基于连杆驱动弯度可变的变形机翼 (Deformable wing with variable bending degree based on connecting rod driving ) 是由 高鑫宇 蔡清青 聂旭涛 张伟 唐萍 于 2020-12-16 设计创作，主要内容包括：本发明公开了一种基于连杆驱动弯度可变的变形机翼包括机翼本体、连杆驱动组件以及转轴连接组件,机翼本体由多段机翼模块组成,机翼模块之间一次通过转轴连接组件转动连接,连杆驱动组件将各机翼模块进行有机结合,使各机翼模块能在直线运动驱动下形成指关节式的弯度变形,采用的连杆驱动组件驱动效率高,可实现机翼大范围弯度变形。(The invention discloses a deformable wing with variable camber based on connecting rod driving, which comprises a wing body, a connecting rod driving assembly and a rotating shaft connecting assembly, wherein the wing body is composed of a plurality of sections of wing modules, the wing modules are rotationally connected through the rotating shaft connecting assembly at one time, and the connecting rod driving assembly organically combines the wing modules, so that the wing modules can form finger joint type camber deformation under the driving of linear motion.)

1. The deformable wing with variable camber based on the link driving is characterized by comprising a wing body, a link driving assembly and a rotating shaft connecting assembly, wherein the wing body comprises a wing module I (1), a wing module II (2), a wing module III (3) and a wing module IV (4), and the wing module I (1) is a fixed section; the connecting rod driving component is arranged in the wing body and comprises a sliding block (5), a driving connecting rod (6), a first connecting rod (7) and a second connecting rod (8); the rotating shaft connecting assembly comprises a first rotating shaft (9), a second rotating shaft (10) and a third rotating shaft (11);

the wing module II (2) is hinged with the wing module I (1) through a first rotating shaft (9), the wing module III (3) is hinged with the wing module II (2) through a second rotating shaft (10), the wing module IV (4) is hinged with the wing module III (3) through a third rotating shaft (11),

the sliding block (5) is installed on the wing module I (1) and is connected with the wing module I (1) in a sliding mode; one end part of the driving connecting rod (6) is hinged with the sliding block (5), and the other end part of the driving connecting rod is hinged with the second rotating shaft (10); one end part of the first connecting rod (7) is hinged to the wing module I (1), and the other end part of the first connecting rod is hinged to the wing module III (3); one end part of the second connecting rod (8) is hinged to the wing module II (2), and the other end part of the second connecting rod is hinged to the wing module IV (4);

when the sliding block (5) does linear motion in the horizontal direction relative to the wing module I (1) under the action of an external force, the wing module II (2), the wing module III (3) and the wing module IV (4) rotate around the first rotating shaft (9), the second rotating shaft (10) and the third rotating shaft (11) at certain angles respectively under the action of the connecting rod driving assembly, and the wing body forms bending deformation of finger joint type motion.

2. The linkage-driven variable camber-based morphing wing according to claim 1, characterized in that the first linkage (7) and the second linkage (8) form a cross structure.

3. The morphing wing with variable camber based on link drive according to claim 1, characterized in that the drive link (6) forms a cross structure with the first link (7).

Technical Field

The invention belongs to the technical field of aerospace equipment, relates to a wing structure, and particularly relates to a connecting rod-driven variable-camber-based deformable wing.

Background

The wing is a key part determining the overall aerodynamic force of the airplane, and the shape of the wing has an important influence on the comprehensive performance of the airplane. Under different flight environments and flight tasks, the performance parameters of the airplane, such as lift-drag ratio, take-off and landing distance, oil consumption, voyage, maneuverability, invisibility and the like, can be changed by changing the aerodynamic shape of the wings according to actual conditions, so that the airplane keeps the optimal overall performance in the flight process.

Since the morphing wing has various advantages, a great deal of research work has been carried out abroad since the last century. After world war II, a series of variable sweepback airplanes were developed in the United states, such as X5 (1951-. In recent years, variable sweepback wings and variable camber wings have been developed in the united states with the fundamentation of "flexible aircraft structure (MAS)" polarization and "smart wings" by the Department of Advanced Research and Planning (DARPA) of the department of defense. In addition, many foreign universities and companies also develop various types of research work on deformable wings, including folding wings, sweepback-variable wings, extended-length-variable wings, camber-variable wings, chord-variable wings, variable-thickness wings, variable-tip wings, and the like. Although the research work on the morphing wing starts later than abroad in China, corresponding research works are also carried out by high-efficiency research institutes, such as Harbin industry university, northwest industry university, Nanjing aerospace university, Beijing aerospace university, Shenyang aircraft design research institute of China aviation industry group company, and the like.

For the variable camber wing, the camber change in the wing flying process brings the change of lift force and resistance, and the change of the camber of the wing according to the different flying stages is beneficial to improving the wing flying efficiency and achieving the purposes of increasing lift and reducing drag. At present, a plurality of mechanisms are used for wing bending deformation, but the mechanisms have advantages and disadvantages, the deformation range, the mechanism weight, the mechanism efficiency and the like are difficult to achieve the best and the best, and particularly, the problems of difficult wing large-range bending deformation and low driving mechanism efficiency exist.

Disclosure of Invention

Aiming at the problems of difficult deformation of large-range camber of the wing, low efficiency of a driving mechanism and the like in the prior art, the invention aims to provide the connecting rod-driven variable-camber-based deformable wing, which can realize finger-joint-type camber deformation of a wing mechanism under linear motion driving by utilizing a connecting rod driving assembly based on a crank-slider mechanism principle.

In order to achieve the purpose, the invention adopts the following technical scheme:

a deformable wing with variable camber based on connecting rod driving comprises a wing body, a connecting rod driving assembly and a rotating shaft connecting assembly, wherein the wing body comprises a wing module I, a wing module II, a wing module III and a wing module IV, and the wing module I is a fixed section; the connecting rod driving assembly is arranged in the wing body and comprises a sliding block, a driving connecting rod, a first connecting rod and a second connecting rod; the rotating shaft connecting assembly comprises a first rotating shaft, a second rotating shaft and a third rotating shaft;

the wing module II is hinged with the wing module I through a first rotating shaft, the wing module III is hinged with the wing module II through a second rotating shaft, the wing module IV is hinged with the wing module III through a third rotating shaft,

the sliding block is mounted on the wing module I and is in sliding connection with the wing module I; one end part of the driving connecting rod is hinged with the sliding block, and the other end part of the driving connecting rod is hinged with the second rotating shaft; one end part of the first connecting rod is hinged to the wing module I, and the other end part of the first connecting rod is hinged to the wing module III; one end part of the second connecting rod is hinged to the wing module II, and the other end part of the second connecting rod is hinged to the wing module IV;

when the sliding block does linear motion in the horizontal direction relative to the wing module I under the action of an external force, the wing module II, the wing module III and the wing module IV rotate around the first rotating shaft, the second rotating shaft and the third rotating shaft respectively for a certain angle under the action of the connecting rod driving assembly, and the wing body forms bending deformation of finger joint type motion.

According to the deformable wing with the variable camber driven by the connecting rods, the first connecting rod and the second connecting rod form a cross structure, so that the rotating directions of the wing module II, the wing module III and the wing module IV around the first rotating shaft, the second rotating shaft and the third rotating shaft are consistent, the wing structure is only subjected to camber deformation, and the wing profile cannot be subjected to large sudden change. Further preferably, the driving link and the first link form a cross structure.

Specifically, the connecting position of the sliding block and the wing module I is located at the rear half section of the wing module I and above the central line of the transverse shaft of the wing module I, and the connecting position of the driving connecting rod and the wing module II (namely the position of the second rotating shaft) is located at the rear end of the wing module II and below the central line of the transverse shaft of the wing module III; the connecting position of the first connecting rod and the wing module I is positioned at the rear end of the wing module I and below the central line of the cross shaft of the wing module I, and the connecting position of the first connecting rod and the wing module III is positioned at the front end of the wing module III and above the central line of the cross shaft of the wing module III; the connecting position of the second connecting rod and the wing module II is located in the middle of the wing module II and below the center line of the cross shaft of the wing module II, and the connecting position of the second connecting rod and the wing module IV is located at the front end of the wing module IV and below the center line of the cross shaft of the wing module IV.

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

1. the deformable wing based on the connecting rod drive and with variable camber comprises a wing body, a connecting rod drive assembly and a rotating shaft connecting assembly, wherein the wing body is composed of a plurality of sections of wing modules, the wing modules are rotationally connected through the rotating shaft connecting assembly at one time, and the connecting rod drive assembly organically combines the wing modules, so that the wing modules can form finger joint type camber deformation under the drive of linear motion.

2. According to the deformable wing with variable camber based on the connecting rod driving, the connecting rod driving component comprehensively utilizes the crank-slider mechanism principle and the cross connecting rod structure, so that one linear motion drives the three sections of wing structures to respectively rotate around three rotating shafts to perform camber deformation motion, the wing structures can be driven to generate large camber deformation by small displacement, and the deformable wing based on the variable camber of the connecting rod driving mechanism is compact in structure and few in driving elements.

3. The deformable wing based on the variable camber driven by the connecting rod is reasonable in structural design, simple and reliable in principle, capable of effectively improving the driving deformation efficiency, high in practicability and worthy of being popularized and applied to mechanism design of wing camber deformation.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other embodiments and drawings can be obtained according to the embodiments shown in the drawings without creative efforts.

Fig. 1 is a structural schematic diagram of a deformable wing with variable camber based on link rod driving, and arrows show the moving direction of a sliding block relative to a wing module I.

Fig. 2 is a schematic diagram of the working principle of the deformable wing with variable camber based on the link drive of the invention.

Description of reference numerals: 1. a wing module I; 2. a wing module II; 3. a wing module III; 4. a wing module IV; 5. a slider; 6. a drive link; 7. a first link; 8. a second link; 9. a first rotating shaft; 10. a second rotating shaft; 11. and a third rotating shaft.

Detailed Description

The technical solutions of the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings, and it is to be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In this embodiment, a transformable wing with variable camber based on link drive is shown in fig. 1 and includes a wing body, a link drive assembly and a rotating shaft connecting assembly.

The wing body comprises a wing module I1, a wing module II 2, a wing module III 3 and a wing module IV 4, wherein the wing module I1 is a fixed section.

The connecting rod driving component is arranged in the wing body and comprises a sliding block 5, a driving connecting rod 6, a first connecting rod 7 and a second connecting rod 8; the rotating shaft connecting assembly comprises a first rotating shaft 9, a second rotating shaft 10 and a third rotating shaft 11.

The wing module II 2 is hinged with the wing module I1 through a first rotating shaft 9, and the hinged position of the wing module II 2 and the wing module I1 is positioned on the central line of the transverse shafts of the wing module I and the wing module II 2; the wing module III 3 is hinged with the wing module II 2 through a second rotating shaft 10, and the hinged position of the wing module II 2 and the wing module III 3 is positioned below the central line of the transverse shafts of the wing module III 3 and the wing module II 2; the wing module IV 4 is hinged with the wing module III 3 through a third rotating shaft 11, and the hinged position of the wing module IV 4 and the wing module III 3 is positioned above the central line of the transverse shafts of the wing module III 3 and the wing module IV 4.

The slider 5 is installed on the wing module I1 to with I1 sliding connection of wing module, the hookup location of slider 5 and wing module I1 is located wing module I1 back half section and above I1 cross axle central line of wing module. One end of the driving connecting rod 6 is hinged with the sliding block 5, and the other end is hinged with the second rotating shaft 10. One end part of the first connecting rod 7 is hinged to the wing module I1, and the other end part of the first connecting rod is hinged to the wing module III 3; the connecting position of the first connecting rod 7 and the wing module I1 is located at the rear end of the wing module I1 and below the central line of the cross shaft of the wing module I1, and the connecting position of the first connecting rod 7 and the wing module III 3 is located at the front end of the wing module III 3 and above the central line of the cross shaft of the wing module III 3. One end part of the second connecting rod 8 is hinged to the wing module II 2, and the other end part of the second connecting rod is hinged to the wing module IV 4; the connecting position of the second connecting rod 8 and the wing module II 2 is located in the middle of the wing module II 2 and below the center line of the cross shaft of the wing module II 2, and the connecting position of the second connecting rod 8 and the wing module IV 4 is located at the front end of the wing module IV 4 and below the center line of the cross shaft of the wing module IV 4. Therefore, the first connecting rod and the second connecting rod form a cross structure, and the driving connecting rod and the first connecting rod form a cross structure.

As shown in fig. 2, when the slider 5 makes a linear motion in the horizontal direction relative to the wing module i 1 under the action of an external force, the wing modules ii 2, iii 3, and iv 4 rotate around the first rotating shaft 9, the second rotating shaft 10, and the third rotating shaft 11 by a certain angle respectively under the action of the link driving assembly, and the wing body forms a curvature deformation of a finger joint type motion.

In summary, according to the deformable wing based on variable camber driven by the connecting rod provided by this embodiment, the connecting rod driving assembly serves as the driving mechanism for camber deformation of the wing structure, so that the design requirement for large-range camber deformation of the wing model is met, the overall camber deformation of the wing can reach 15% under the condition of 5mm linear driving displacement of the slider, the purpose of large-range deformation through displacement driving is achieved, the characteristics of compact structure and high utilization rate of the wing model deformation mechanism are met, and the problem faced by the design of the wing model deformation mechanism is well solved.