Variable geometry wing using a scalable linkage mechanism and aircraft applying the same

Abstract

The application provides a deformable wing using a telescopic connecting rod mechanism, comprising: a plurality of frames; a plurality of connecting rod mechanisms, each of which is arranged on a frame, each of which comprises a telescopic first connecting rod, a non-telescopic second connecting rod and a connecting rod for connecting the first connecting rod and the second connecting rod; and a plurality of driving devices, each of which has a frame on the upper side and the lower side respectively, and each of which is connected with the first connecting rod in the two corresponding connecting rod mechanisms, so as to control the two first connecting rods to synchronously stretch and retract. The application can realize the length adjustment of the aircraft wing in the wing profile section direction, so as to change the wing profile area and the angle of attack, thereby enabling the aircraft to adjust the lift-drag ratio by controlling the movement of the four connecting rod mechanisms to adjust the wing area and the angle of attack when the lift needs to be adjusted. The application has the advantages of simple structure, stable control, high safety factor and the like.

Description

Technical Field

[0001] This invention relates to the field of aircraft structural design technology, and more specifically to a deformable wing employing a telescopic linkage mechanism and an aircraft using the same. Background Technology

[0002] The wing is one of the most important components of an aircraft, mounted on the fuselage. Its primary function is to generate lift, which, together with the tail, contributes to good stability and handling. Additionally, munitions, equipment, and fuel tanks can be stored internally in the wing, while landing gear, engines, missiles, auxiliary fuel tanks, and other external stores can be mounted on the wing.

[0003] Generally, wing area is directly proportional to the lift provided. For example, during takeoff, a larger wing area results in greater lift, shortening the takeoff distance; while a smaller wing provides better maneuverability, facilitating maneuvers. Furthermore, the angle of attack (ATO) is generally proportional to the lift provided. For instance, within a certain angle of attack range, lift increases with the angle of attack. However, when the angle of attack exceeds this range and continues to increase, stall occurs. Stall refers to the situation where, despite the increase in lift, the angle of attack reaches a certain point where airflow begins to separate from the wing's leading edge, creating a large vortex region at the tail, causing a sudden drop in lift and a rapid increase in drag. The angle of attack at which stall just begins is called the "critical angle of attack."

[0004] As humanity's exploration of space deepens, the airspace and speed range required for future aircraft are constantly expanding, and they must be capable of performing multiple flight missions. In multi-mission flight environments, traditional fixed-shape aircraft, due to the immutable angle of attack, area, or length of their overall wing structure, struggle to maintain consistently good flight and handling performance. However, deformable aircraft, whose shape can change according to flight missions and environments, can meet diverse needs with different aerodynamic configurations, thus improving flight performance. Among these, the wing, being one of the most crucial components of an aircraft, is key to achieving wing deformation. Current technology typically uses small-angle variable control surfaces to alter lift, but this method provides limited lift. Therefore, an aircraft with an adjustable wing area and angle of attack is needed to meet the operational requirements under different conditions. Summary of the Invention

[0005] The present invention was made to solve the above-mentioned problems, and its purpose is to provide a deformable wing using a telescopic linkage mechanism and an aircraft using the same.

[0006] This invention provides a deformable wing utilizing a retractable linkage mechanism, mounted on the tail edge of an aircraft wing, for changing the wing area and angle of attack. It is characterized by comprising: multiple frames, all mounted on the tail edge of the aircraft wing; and multiple linkage mechanisms, each mounted on one frame. Each linkage mechanism includes a first connecting rod, a second connecting rod, and a connecting rod. The first connecting rod is retractable, and the second connecting rod is non-retractable. One end of each of the first and second connecting rods is rotatably connected to a corresponding connecting rod. The frame is connected at both ends by an arc-shaped connecting rod. One end of the connecting rod is connected to the other end of the first connecting rod, and the other end is connected to the other end of the second connecting rod. The bending direction of the connecting rod is towards the aircraft wing. Multiple drive units are installed on the aircraft and arranged along the span of the wing. Each drive unit has a frame on its upper and lower sides. Each drive unit is connected to the first connecting rod of its two corresponding linkage mechanisms, thereby controlling the synchronous extension and retraction of the two first connecting rods. A flexible skin covers the overall exterior of the multiple frames and multiple linkage mechanisms.

[0007] The deformable wing using a telescopic linkage mechanism provided by the present invention also has the following feature: multiple drive devices are arranged along the chord of the aircraft wing.

[0008] In the deformable wing using a telescopic linkage mechanism provided by the present invention, it can also have the following features: each first link has a main link and a secondary link, one end of the main link is connected to the corresponding frame, and the other end is provided with a groove, the secondary link is slidably disposed in the groove, one end of the secondary link is always located in the groove, and the other end is connected to one end of the connecting rod.

[0009] In the deformable wing using a telescopic linkage mechanism provided by the present invention, it can also have the following feature: two adjacent frames and the drive device disposed between the two frames are all located on the same plane.

[0010] In the deformable wing using a telescopic linkage mechanism provided by the present invention, it can also have the following feature: both the first link and the second link are rotatably connected to the corresponding frame via a pivot.

[0011] The deformable wing using a telescopic linkage mechanism provided by the present invention can also have the following feature: the number of drive devices is at least two.

[0012] The deformable wing using a telescopic linkage mechanism provided by this invention also has the feature that multiple drive devices operate synchronously.

[0013] The deformable wing using a telescopic linkage mechanism provided by the present invention can also have the following feature: the driving device is a hydraulic actuator.

[0014] An aircraft is characterized by having two deformable wings as described above, which are respectively mounted on the two wings of the aircraft and are symmetrically arranged about the fuselage axis.

[0015] The role and effect of invention

[0016] The deformable wing utilizing a retractable linkage mechanism according to the present invention, because the linkage mechanism includes a retractable first linkage, a non-retractable second linkage, and a connecting rod for connecting the first and second linkages, and the drive device can control the retraction and extension of the first linkage, enables the length of the aircraft wing to be adjustable in the airfoil section direction, thereby changing the wing area and angle of attack. This allows the aircraft to adjust its lift ratio by controlling the movement of the four-bar linkage when lift needs to be adjusted. It has the advantages of simple structure, stable control, and high safety factor. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the frame and linkage mechanism in a deformable wing using a telescopic linkage mechanism in an embodiment of the present invention;

[0018] Figure 2 This is a schematic diagram showing the positional relationship between the frame and the drive device on the wing in a deformable wing using a telescopic linkage mechanism in an embodiment of the present invention.

[0019] Figure 3 This is a motion envelope diagram of a deformable wing using a telescopic linkage mechanism in an embodiment of the present invention.

[0020] Explanation of reference numerals in the attached figures:

[0021] 1. Frame; 2. First connecting rod; 21. Main rod; 22. Secondary rod; 3. Second connecting rod; 4. Connecting rod; 5. Drive unit; A. Aircraft wing. Detailed Implementation

[0022] To make the technical means, creative features, objectives and effects of this invention easier to understand, the following embodiments are described in detail with reference to the accompanying drawings.

[0023] Example

[0024] Figure 1 This is a schematic diagram of the frame and linkage mechanism in a deformable wing that utilizes a telescopic linkage mechanism in this invention. Figure 2 This is a schematic diagram showing the positional relationship between the frame and the drive device on the wing in the deformable wing using a telescopic linkage mechanism in this invention.

[0025] like Figure 1and Figure 2 As shown, this embodiment provides a deformable wing using a telescopic linkage mechanism, comprising: multiple frames 1, multiple linkage mechanisms, multiple drive devices 5, and a flexible skin; wherein the flexible skin covers the overall exterior of the multiple frames 1 and the multiple linkage mechanisms.

[0026] like Figure 2 As shown, multiple frames 1 are mounted on the tail edge of the aircraft wing. In this embodiment, the multiple frames 1 are arranged along a straight line parallel to the chord of the aircraft wing, and each frame 1 is rectangular.

[0027] like Figure 1 As shown, each linkage mechanism is mounted on a frame 1. Each linkage mechanism includes a first connecting rod 2, a second connecting rod 3, and a connecting rod 4. The first connecting rod 2 is a telescopic connecting rod, and the second connecting rod 3 is a non-telescopic connecting rod. One end of the first connecting rod 2 and the second connecting rod 3 are rotatably connected to the two ends of the corresponding frame 1. The connecting rod 4 is an arc-shaped connecting rod 4. One end of the connecting rod 4 is connected to the other end of the first connecting rod 2, and the other end is connected to the other end of the second connecting rod 3. The bending direction of the connecting rod 4 is towards the aircraft wing.

[0028] In this embodiment, each first connecting rod 2 has a main rod 21 and a secondary rod 22. One end of the main rod 21 is connected to the corresponding frame 1, and the other end is provided with a groove. The secondary rod 22 is slidably disposed in the groove, with one end of the secondary rod 22 always located in the groove, and the other end connected to one end of the connecting rod 4. Specifically, there is a limiting fit between one end of the secondary rod 22 and the groove. For example, the groove has a stepped structure, that is, the groove has a large diameter section and a small diameter section. In this case, the diameter of the secondary rod 22 is the same as the diameter of the small diameter section, but one end of the secondary rod 22 is the same as the diameter of the large diameter section of the groove, thereby preventing the secondary rod 22 from slipping off the main rod 21, thus ensuring the practical effect of the deformable wing in this invention from the side.

[0029] In this embodiment, both the first connecting rod 2 and the second connecting rod 3 are rotatably connected to the corresponding frame 1 via pivots. Each pivot has anti-detachment components, such as nuts, at both ends to prevent the pivots from detaching during rotation, thereby improving the stability of the deformable wing in this invention during use.

[0030] like Figure 2As shown, multiple drive devices 5 are mounted on the aircraft and arranged along the spanwise direction of the wing. Each drive device 5 has a frame 1 on its upper and lower sides, and each drive device 5 is connected to the first connecting rod 2 in its two corresponding linkage mechanisms, thereby controlling the synchronous extension and retraction of the two first connecting rods 2. In this embodiment, the drive device 5 is preferably a hydraulic actuator, and each drive device 5 adopts a triangular fixing method, which makes the deformable wing more stable in terms of use and drive, thereby further improving the stability of the deformable wing in this invention.

[0031] In this embodiment, all of the driving devices 5 are arranged along the chord of the aircraft wing.

[0032] In this embodiment, the number of drive devices 5 is at least two.

[0033] In this embodiment, multiple drive devices 5 operate synchronously. Therefore, it is possible to ensure that the support mechanisms on multiple frames 1 can move synchronously, thereby guaranteeing the practical effect of the deformable wing in this invention.

[0034] Figure 3 This is a motion envelope diagram of a deformable wing using a telescopic linkage mechanism in an embodiment of the present invention.

[0035] In this embodiment, the deformable wing employing a telescopic linkage mechanism uses a drive device 5 to control the motion trajectory of the linkage mechanism. Specifically, the drive device 5 can drive the corresponding first connecting rod 2 to extend and retract. Because the second connecting rod 3 and the arc-shaped connecting rod 4 are directly or indirectly connected, forming a linkage mechanism, the second connecting rod 3 and the connecting rod 4 can move accordingly with the extension and retraction of the first connecting rod 2, i.e., the second connecting rod 3 and the connecting rod 4 rotate. Thus, the drive device 5 controls the motion trajectory of the linkage mechanism in terms of both angle and length. Furthermore, because the length and angle changes of the linkage mechanism are mutually constrained, and because the linkage mechanism and the frame 1 are covered with a flexible skin, and as... Figure 3 The MATLAB trajectory range diagram of the linkage mechanism in this invention shows that, under the condition of ensuring motion, after the driving device 5 controls the movement of the linkage structure in this invention, the flexible skin can maximize the lift-to-drag ratio of the aircraft, thereby ensuring the practical effect of the deformable wing in this invention.

[0036] This embodiment also provides an aircraft equipped with deformable wings using a telescopic linkage mechanism. Both wings of the aircraft are equipped with the aforementioned deformable wings using a telescopic linkage mechanism, and the two deformable wings are symmetrically arranged about the fuselage axis, thereby enabling the aircraft to have better lift.

[0037] The role and effect of the embodiments

[0038] According to the deformable wing using a telescopic linkage mechanism involved in this embodiment, since the linkage mechanism includes a telescopic first linkage, a non-telescopic second linkage, and a connecting rod for connecting the first linkage and the second linkage, and the drive device can control the telescopic extension and retraction of the first linkage, the length of the aircraft wing can be adjusted in the airfoil section direction to change the wing area and angle of attack. Thus, when the aircraft needs to adjust lift, the airfoil section area and angle of attack of the wing can be adjusted by controlling the movement of the four-bar linkage to adjust the lift-to-drag ratio. It has the advantages of simple structure, stable control, and high safety factor.

[0039] Furthermore, because the first connecting rod and the second connecting rod in the deformable wing using the telescopic linkage mechanism in this invention are rotatably connected to the corresponding frame via a pivot, and each pivot is provided with anti-detachment components at both ends, the situation of the pivot falling off during the rotation of the first connecting rod and the second connecting rod is prevented, thereby improving the stability of the deformable wing in this invention during use.

[0040] Furthermore, because each drive device in the deformable wing using the telescopic linkage mechanism in this invention adopts a triangular fixing method, the deformable wing is more stable in terms of use and drive, thereby further improving the stability of the deformable wing in this invention.

[0041] Furthermore, because multiple drive devices in the deformable wing using the telescopic linkage mechanism in this invention operate synchronously, it is possible to ensure that the support rod mechanisms on multiple frames can move synchronously, thereby ensuring the practical effect of the deformable wing in this invention.

[0042] Furthermore, in this invention, the deformable wing utilizing a telescopic linkage mechanism employs a drive device to control the motion trajectory of the linkage mechanism. Specifically, the drive device can extend and retract the corresponding first connecting rod. Since the second connecting rod and the arc-shaped connecting rod are directly or indirectly connected, forming a linkage mechanism, the second connecting rod and the connecting rod can move accordingly with the extension and retraction of the first connecting rod, i.e., the second connecting rod and the connecting rod rotate. Thus, the drive device controls the motion trajectory of the linkage mechanism in terms of both angle and length. Additionally, because the length and angle changes of the linkage mechanism are mutually constrained, and because the linkage mechanism and the frame are covered with a flexible skin, it is understood that, under the condition of ensuring motion, the drive device controlling the movement of the linkage structure in this invention, combined with the flexible skin, can maximize the lift-to-drag ratio of the aircraft, thereby ensuring the practical effect of the deformable wing in this invention.

[0043] The aircraft described in this embodiment, which is equipped with deformable wings using a telescopic linkage mechanism, has better lift because both wings are equipped with the aforementioned deformable wings using a telescopic linkage mechanism, and the two deformable wings are symmetrically arranged about the fuselage axis.

[0044] The above embodiments are preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention.

Claims

1. A deformable wing employing a telescopic linkage mechanism, mounted on the tail edge of an aircraft wing, for changing the wing area and the wing's angle of attack, characterized in that... include: Multiple racks are mounted on the tail edge of the aircraft wing; Multiple linkage mechanisms are provided, each linkage mechanism is mounted on a frame, and each linkage mechanism includes a first connecting rod, a second connecting rod, and a connecting rod. The first connecting rod is a telescopic connecting rod, and the second connecting rod is a non-telescopic connecting rod. One end of the first connecting rod and the second connecting rod are rotatably connected to the two ends of the corresponding frame. The connecting rod is an arc-shaped connecting rod, one end of which is connected to the other end of the first connecting rod, and the other end of which is connected to the other end of the second connecting rod. The bending direction of the connecting rod is towards the aircraft wing. Multiple drive devices are installed on the aircraft and arranged along the spanwise direction of the wing. Each drive device has a frame on its upper and lower sides. Each drive device is connected to the first link in its two corresponding linkage mechanisms, thereby controlling the two first link to extend and retract synchronously. as well as A flexible skin covers the overall exterior of the plurality of said frames and the plurality of said linkage mechanisms.

2. The deformable wing employing a telescopic linkage mechanism according to claim 1, characterized in that: in, The multiple drive units are all arranged along the chord of the aircraft wing.

3. The deformable wing employing a telescopic linkage mechanism according to claim 1, characterized in that: in, Each of the first connecting rods has a main rod and a secondary rod. One end of the main rod is connected to the corresponding frame, and the other end is provided with a groove. The auxiliary rod is slidably disposed in the groove, with one end of the auxiliary rod always located in the groove and the other end connected to one end of the connecting rod.

4. The deformable wing employing a telescopic linkage mechanism according to claim 1, characterized in that: in, The two adjacent racks and the drive unit disposed between the two racks are all located on the same plane.

5. The deformable wing employing a telescopic linkage mechanism according to claim 1, characterized in that: in, Both the first connecting rod and the second connecting rod are rotatably connected to the corresponding frame via a pivot.

6. The deformable wing employing a telescopic linkage mechanism according to claim 1, characterized in that: in, The number of drive devices is at least two.

7. The deformable wing employing a telescopic linkage mechanism according to claim 1, characterized in that: in, Multiple drive devices operate synchronously.

8. The deformable wing employing a telescopic linkage mechanism according to claim 1, characterized in that: in, The driving device is a hydraulic actuator.

9. An aircraft, characterized in that: The aircraft is equipped with two deformable wings as described in any one of claims 1 to 8. The two deformable wings are respectively mounted on the two wings of the aircraft and are symmetrically arranged with the aircraft fuselage as the axis.

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