A morphing wing, aircraft and morphing control method

Abstract

The application discloses a deformable wing, an aircraft and a deformation control method, and relates to the field of aircraft design.

Description

TECHNICAL FIELD

[0001] The present application relates to a deformable wing, an aircraft and a deformation control method, and belongs to the technical field of aerospace flight. BACKGROUND

[0002] With the deepening of human space exploration, the future aircraft is required to continuously expand the airspace and speed domain, and to be able to realize various flight missions, i.e., a single aircraft to complete low-speed take-off and landing on the ground, high-speed penetration, hypersonic cruise, flexible maneuvering and other tasks. In the multi-task flight environment, the traditional fixed shape aircraft is difficult to maintain good flight performance and maneuvering performance at all times.

[0003] The deformable aircraft can change its shape according to the flight mission and flight environment to meet different needs in different aerodynamic layout forms and improve the flight performance of the aircraft. As one of the most important parts of the aircraft, the deformation design of the wing is the key to realizing the deformation of the aircraft. Currently, the research on deformable wings mainly focuses on small and medium scale deformation, such as changing the wing section shape, chord length or leading and trailing edges to realize flow control and improve maneuvering performance.

[0004] Patent CN201910684613.4 (a spanwise telescopic deformable wing) proposes to change the area of the wing through a telescopic structure; patent CN201711299675.0 (a deformable wing) proposes to change the wing section shape by changing the angle of attack of the leading and trailing ends of the wing; patent CN201811315911.8 (a deformable wing with variable chord length and camber) proposes to change the chord length and camber of the wing through deformable ribs; patent CN202010859908.3 (a fixed-wing-beam variable sweep wing) proposes to change the sweep angle, span length and wing area of the wing through a fixed wing beam; patent CN201810937483.6 (a wing contraction folding device for a deformable aircraft) proposes to change the wing span and sweep angle by being retracted into the fuselage through a contraction folding device; and patent CN201921408791.6 (a wing, a deformation device and an aircraft) proposes to cause the first wing to deform by inflating and deflating the air bag to change the wing span and sweep angle. These mainly change the wing span length or sweep angle through telescoping or rotating, and do not change the wing configuration in a large scale.

[0005] However, for future ultra-wide domain flight, the flow field characteristics differ significantly at different speed domains: at low speed, the main features are attachment flow and vortex flow; at supersonic and hypersonic speeds, the main features are complex wave system structures such as shock waves and expansion waves; and when the flight speed is further increased, the drag characteristics gradually become the main contradiction in aircraft design. Therefore, the design of a deformable wing only for the wing section cannot meet the needs of future ultra-wide domain flight. SUMMARY

[0006] The purpose of the present invention is to overcome the shortcomings of the existing technology and provide a deformable wing, aircraft and deformation control method that can cope with an ultra-wide range of flight conditions (Ma0~15+), realize continuous sweep angle changes of the wing, change the wing configuration, take into account the lift and drag characteristics under different flight speed ranges, and realize maneuverable, flexible and efficient flight of the aircraft in a limited internal space of the aircraft.

[0007] The technical solution of the present invention is: a deformable wing, comprising a combined wing and a combined wing connection structure, wherein the combined wing is mounted on the fuselage through the combined wing connection structure and can be expanded and retracted;

[0008] The combined wing comprises an active rear wing, a following front wing and a telescopic overlapping wing, which are symmetrically distributed on both sides of the fuselage, the following front wing is arranged in front of the active rear wing, and the telescopic overlapping wing is arranged at the root of the active rear wing. When the combined wing is fully unfolded, the active rear wing, the following front wing and the telescopic overlapping wing form a complete, continuous and smoothly transitioned straight wing airfoil configuration. When the combined wing connection structure drives the active rear wing to rotate backward, the following front wing rotates backward accordingly and is retracted into the fuselage. The telescopic overlapping wing is partially to completely folded and retracted into the fuselage, and the wing surface configuration is transformed from a straight wing airfoil configuration to a swept wing airfoil configuration, and finally to a waverider configuration.

[0009] An aircraft using any of the above-mentioned deformable wings.

[0010] A deformation control method for a deformable wing is implemented by the following steps:

[0011] In the first step, the deformable wing is fully deployed, the telescopic overlapping wings are extended to the maximum, and the active rear wing, the following front wing and the telescopic overlapping wings form a complete, continuous and smoothly transitioned straight wing surface configuration;

[0012] In the second step, the active rear wing rotates backward, and the following front wing rotates backward accordingly, and the telescopic overlapping wing parts shrink and overlap, changing the straight wing airfoil configuration to a swept wing airfoil configuration;

[0013] In the third step, the active rear wing continues to rotate backward, sweeping back until it connects with the retractable tail wing. The following front wing rotates backward accordingly, and the retractable overlapping wings are completely retracted and overlapped and retracted into the fuselage, transforming the swept wing configuration into a waverider configuration.

[0014] In the fourth step, the active rear wing continues to rotate backward and the retractable tail retracts into the fuselage.

[0015] The beneficial effects of the present invention compared with the prior art are as follows:

[0016] (1) The present application realizes the continuous wing configuration deformation of the whole aircraft shape by the special combined wing structure, and adapts to the super wide range flight working condition and different flight tasks;

[0017] (2) The present application adopts the telescopic overlapping wing, which not only can participate in the wing configuration deformation, but also can completely overlap when the wing is contracted, so as to reduce the space occupied by the deformed wing and ensure the strength of the wing at high speed;

[0018] (3) The present application adopts the combined wing structure, realizes the large-scale change of the wing configuration from the flat wing to the backward swept wing and then to the waverider configuration, adapts to the flow characteristics at different speed ranges, and ensures the lift-drag characteristics in the whole speed range;

[0019] (4) The present application adopts the organic combination of intelligent deformation and mechanical mechanism, further realizes the seamless and smooth transition of the aircraft wing, and ensures the aerodynamic performance;

[0020] (5) The present application fully considers the requirements of aerodynamic heat and aerodynamic force on the strength of the deformed structure at high speed, and realizes the continuous and smooth deformation with the smallest occupation of the internal space of the aircraft in the process of the wing deformation with such a large scale, so as to balance the flight performance and practical performance. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 It is the overall schematic diagram of the present application;

[0022] Figure 2 It is the extension and contraction state diagram of the combined wing connecting structure of the present application, a is the extension state, b is the extension-contraction process state, and c is the contraction state;

[0023] Figure 3 It is the extension and contraction state diagram of the telescopic overlapping wing of the present application, a is the extension state, b is the extension-contraction process state, and c is the contraction state;

[0024] Figure 4 It is the smooth transition diagram of the flow surface between the wing surfaces of the present application, a is before the flow surface control, and b is after the flow surface control;

[0025] Figure 5 It is the continuous deformation process diagram of the present application, a, b, c and d are four typical states;

[0026] Figure 6 It is the deformation control flowchart of the present application. DETAILED DESCRIPTION

[0027] The present application will be described in detail below in combination with specific examples and drawings.

[0028] The present application is as follows Figure 1As shown in the figure, a deformable wing is provided, comprising a combined wing and a combined wing connecting structure, the combined wing is installed on the fuselage through the combined wing connecting structure, and the combined wing is unfolded and retracted.

[0029] As shown in the figure, Figure 1 The combined wing comprises a leading wing, a trailing wing and a telescopic overlapping wing. The leading wing, the trailing wing and the telescopic overlapping wing are symmetrically distributed on both sides of the fuselage. The trailing wing is arranged in front of the leading wing, and the telescopic overlapping wing is arranged at the root of the leading wing. When the combined wing is fully unfolded, the leading wing, the trailing wing and the telescopic overlapping wing form a complete continuous and smooth wing surface.

[0030] The combined wing connecting structure comprises a leading wing skeleton, a trailing wing skeleton and a telescopic overlapping wing connecting structure, as shown in the figure, Figure 2 The leading wing is fixedly installed on the leading wing skeleton and is rotated by the leading wing skeleton. One end of the leading wing skeleton is connected to the fuselage and can rotate around the connection point. The middle part of the leading wing skeleton is connected to the fuselage through a connecting rod, and the connection points at both ends of the connecting rod can rotate. The connecting rod can move forward and backward along the fuselage, and the position of the connecting rod on the fuselage can be moved to pull the leading wing skeleton to rotate forward and backward, thereby realizing the forward and backward rotation of the leading wing.

[0031] The trailing wing is fixedly installed on the trailing wing skeleton and is rotated by the trailing wing skeleton. One end of the trailing wing skeleton is connected to the fuselage and can rotate around the connection point, and the other end is connected to the middle part of the leading wing skeleton. The connection point can move on the leading wing skeleton, and when the leading wing skeleton rotates, the trailing wing skeleton is correspondingly rotated.

[0032] Further, the forward and backward distance between the leading wing skeleton and the trailing wing skeleton is the wing span length of the trailing wing root.

[0033] The telescopic overlapping wing is fixedly installed on the telescopic overlapping wing connecting structure and is folded or stretched by the telescopic overlapping wing connecting structure. The telescopic overlapping wing connecting structure is installed at the root of the leading wing skeleton. The telescopic overlapping wing of the present application is composed of not less than two overlapping wing blades, as shown in the figure, Figure 3 The adjacent overlapping wing blades are arranged densely, and the edges of the adjacent overlapping wing blades are pressed tightly when stretched, and the overlapping wing blades are overlapped and pressed tightly when retracted.

[0034] The telescopic overlapping wing connecting structure is composed of a plurality of overlapping wing blade connecting structures, and the number of overlapping wing blade connecting structures corresponds to the number of overlapping wing blades. Each overlapping wing blade connecting structure is provided with a torsion structure at the connection point with the leading wing skeleton, so that the overlapping wing blades rotate around the connection point, and the rotation direction of the overlapping wing blades is opposite to that of the leading wing. When the leading wing rotates backward, the rotation angles of the innermost to the outermost overlapping wing blades decrease in turn, so that the overlapping wing blades overlap with each other, and the telescopic overlapping wing is retracted.

[0035] The overlapping wing blades of the present application contract or expand when the active rear wing rotates, realizing continuous change of the wing sweepback angle. At the same time, through the deformation of the telescopic overlapping, the space occupied by the deformed wing is effectively reduced, and the strength of the wing is ensured in a mutually compressed manner.

[0036] Further, during the contraction of the combined wing, the passive front wing and the telescopic overlapping wing part or all enter the fuselage, and the active rear wing part enters the fuselage. In the final contracted state, the passive front wing and the telescopic overlapping wing all enter the fuselage, and the leading edge of the passive front wing maintains the fuselage profile outside the leading edge of the active rear wing.

[0037] Further, the present application also includes telescopic tail wings symmetrically arranged at the tail of the fuselage, which can be fully or partially contracted into the fuselage. Preferably, the telescopic tail wings can be provided with a separate telescopic connection structure, and the telescopic tail wings can be controlled separately according to flight requirements, or only the connection structure can be designed, and the telescopic tail wings are pushed into the fuselage by the active rear wing when the active rear wing rotates backward to the telescopic tail wings.

[0038] Further, as shown in Figure 4 , a smooth transition design is performed at the connection between the passive front wing and the active rear wing. By embedding intelligent deformable materials in the trailing edge of the passive front wing and the leading edge of the active rear wing, the shape of the trailing edge of the passive front wing and the leading edge of the active rear wing can be controlled. When the sweepback angle of the combined wing changes, a gap may exist when the passive front wing slides on the skeleton of the active rear wing. The intelligent deformable material deforms in a small size to ensure that the trailing edge of the passive front wing and the leading edge of the active rear wing are always in close contact, realizing smooth transition of the wing surface between the front and rear wings. Similarly, the same design is performed at the trailing edge of the active rear wing to ensure smooth transition of the wing surface between the trailing edge of the active rear wing and the telescopic overlapping wing; the same design is performed between the overlapping wing blades to ensure that the overlapping wing blades are pressed tightly against each other, thereby ensuring smooth transition of the wing surface of the telescopic overlapping wing and enhancing the strength of the telescopic overlapping wing.

[0039] Further, the present application also provides a flying vehicle using a deformable wing.

[0040] Further, the present application also provides a deformation control method for a deformable wing as shown in Figure 6 , which is realized by the following steps:

[0041] Firstly, the deformable wing is fully deployed, the telescopic overlapping wing is expanded to the maximum, and the active rear wing, the passive front wing and the telescopic overlapping wing form a complete continuous and smooth transition wing surface.

[0042] In this step, the wing is in a state of large aspect ratio and small sweepback angle, which is suitable for low-speed flight (Ma0~2.5).

[0043] Secondly, the active rear wing rotates backward, the passive front wing rotates backward accordingly, and the telescopic overlapping wing partially contracts and overlaps.

[0044] In this step, the wing sweep angle is increased and the aspect ratio is reduced, which is suitable for high-speed flight (Ma2.5~4).

[0045] In the third step, the active rear wing continues to rotate backward, and the active rear wing is swept back to connect with the retractable tail wing. The following front wing rotates backward accordingly, and the retractable overlapping wings are completely retracted and overlapped and retracted into the fuselage.

[0046] In this step, the aircraft as a whole takes on a waverider configuration, suitable for hypersonic flight (Ma4 to 7.5).

[0047] In the fourth step, the active rear wing continues to rotate backward and the retractable tail retracts into the fuselage.

[0048] In this step, the sweep angle is further increased, and the overall aircraft is in a low-drag configuration, adapting to higher speeds and even extreme speeds (Ma7.5~15+).

[0049] Example 1

[0050] like Figures 1 to 5 As shown, the active front wing and active rear wing are arranged in a front-to-back arrangement, with the roots of both wing frames hinged to the fuselage and rotatable around the hinge point. The root area of ​​the active rear wing frame is the mounting location for the telescopic overlapping wing, and the middle of the active rear wing frame is connected to the tip of the active front wing frame via a front and rear wing slider mechanism. The wing sweep angle is changed by a connecting rod connected between the fuselage and the active rear wing. One end of the connecting rod is hinged to the active rear wing frame, and the other end is connected to the fuselage via a fuselage slider mechanism. When the fuselage slider mechanism slides back and forth on the fuselage, the active rear wing is driven to rotate by the connecting rod. Under the action of the front and rear wing slider mechanism, the active front wing also rotates, achieving a change in the sweep angle of the combined wing.

[0051] Example 2

[0052] The deformation control method of the deformable wing is described by four typical states during continuous deformation, such as Figure 5 、 6 As shown in Figure 1. In state (a), the wings are fully extended, the retractable overlapping wings are extended to their maximum extent, and the wings are in a state with a large aspect ratio and a small sweep angle, which is suitable for low-speed flight. In state (b), the active rear wing rotates backward, the retractable overlapping wings partially retract and overlap, the wing sweep angle increases, and the aspect ratio decreases, which is suitable for high-speed flight. In state (c), the active rear wing retracts to connect with the tail wing, the retractable overlapping wings completely overlap and retract into the fuselage, and the entire aircraft has a waverider configuration, which is suitable for hypersonic flight. In state (d), the tail wing retracts into the fuselage, the sweep angle further increases, and the entire aircraft has a low-drag configuration, which is suitable for higher speeds and even extreme speed flight.

[0053] With the increase of flight speed, the overlapping degree of the overlapping wing blade is higher, and the structural strength of the telescopic overlapping wing is higher, so that the strength requirement of high-speed flight can be met; meanwhile, when the combined wings contact each other, the smooth transition structure of the flow surface deforms through the intelligent material, so that the wing surface is smooth during the deformation process, and the flight performance requirement can be met.

[0054] The part not described in detail in the present application is the technology known to those skilled in the art.

Claims

1. A deformable wing, characterized by: The combined wing comprises a combined wing and a combined wing connection structure, wherein the combined wing is mounted on the fuselage through the combined wing connection structure and realizes the expansion and contraction of the combined wing; The combined wing comprises an active rear wing, a following front wing and a retractable overlapping wing, wherein the active rear wing, the following front wing and the retractable overlapping wing are symmetrically distributed on both sides of the fuselage, the following front wing is arranged in front of the active rear wing, and the retractable overlapping wing is arranged at the root of the active rear wing. When the combined wing is fully deployed, the active rear wing, the following front wing and the retractable overlapping wing form a complete, continuous and smoothly transitioned straight wing airfoil configuration. When the combined wing connection structure drives the active rear wing to rotate backward, the following front wing rotates backward accordingly and is retracted into the fuselage. The retractable overlapping wing is partially to completely folded and retracted into the fuselage, and the airfoil configuration is transformed from a straight wing airfoil configuration to a swept wing airfoil configuration, and finally to a waverider configuration. The combined wing connection structure includes an active rear wing frame, a follower front wing frame and a telescopic overlapping wing connection structure. The active rear wing is fixedly mounted on the active rear wing frame and is driven to rotate thereby. The follower front wing is fixedly mounted on the follower front wing frame and is driven to rotate thereby. The telescopic overlapping wing is fixedly mounted on the telescopic overlapping wing connection structure and is driven to fold or extend thereby. The telescopic overlapping wing connection structure is mounted at the root of the active rear wing frame.

2. The deformable wing according to claim 1, characterized in that: The telescopic overlapping wing is composed of no less than two overlapping wing blades, and the adjacent overlapping wing blades are densely arranged. When extended, the edges of the adjacent overlapping wing blades are pressed against each other, and when retracted, the overlapping wing blades are overlapped and pressed against each other.

3. The deformable wing according to claim 1, characterized in that: One end of the active rear wing frame is connected to the fuselage and can rotate around the connection point. The front part of the active rear wing frame is connected to the fuselage through a connecting rod. The connection points at both ends of the connecting rod can rotate, and the connection point between the connecting rod and the fuselage can move forward and backward along the fuselage.

4. The deformable wing according to claim 1, characterized in that: One end of the follower front wing frame is connected to the fuselage and can rotate around the connection point, and the other end is connected to the middle part of the active rear wing frame. The connection point can move on the active rear wing frame. When the active rear wing frame rotates, it drives the follower front wing frame to rotate accordingly.

5. The deformable wing according to claim 1, characterized in that: The telescopic overlapping wing connection structure is composed of multiple overlapping wing blade connection structures. The number of overlapping wing blade connection structures corresponds to the number of overlapping wing blades. Each overlapping wing blade connection structure is provided with a torsion structure at the connection point with the active rear wing skeleton, so that the overlapping wing blades rotate around the connection point, and the rotation direction of the overlapping wing blades is opposite to that of the active rear wing.

6. The deformable wing according to claim 5, characterized in that: The torsion structure rotates backward when the active rear wing rotates, controlling the rotation angles of the overlapping wing blades from the innermost to the outermost to decrease sequentially, so that the overlapping wing blades overlap each other, completing the contraction of the telescopic overlapping wing.

7. The deformable wing according to claim 4, characterized in that: The front-to-back distance between the active rear wing frame, the follower front wing frame and the fuselage connection point is the wingspan length of the follower front wing root.

8. The deformable wing according to claim 1, characterized in that: The combined wing also includes a telescopic tail wing symmetrically arranged at the tail of the fuselage, and the telescopic tail wing can be fully or partially retracted into the fuselage.

9. The deformable wing according to claim 8, characterized in that: The telescopic tail is provided with a telescopic connection structure, and the telescopic tail is independently controlled to be extended or retracted according to flight requirements.

10. The deformable wing according to claim 8, characterized in that: The telescopic tail rotates backward to the telescopic tail when the active rear wing is in operation, and is pushed into the fuselage by the active rear wing.

11. The deformable wing according to claim 1, characterized in that: Intelligent deformable materials are embedded in the trailing edge of the follow-up front wing, the leading edge of the active rear wing and the trailing edge of the active rear wing.

12. The deformable wing according to claim 1, characterized in that: The leading edge and the trailing edge of the overlapping wing blades are embedded with intelligent deformable materials.

13. An aircraft using the deformable wing according to any one of claims 1 to 12.

14. A deformation control method for a deformable wing according to any one of claims 1 to 12, characterized in that: This is achieved by following these steps: In the first step, the deformable wing is fully deployed, the telescopic overlapping wings are extended to the maximum, and the active rear wing, the following front wing and the telescopic overlapping wings form a complete, continuous and smoothly transitioned straight wing surface configuration; In the second step, the active rear wing rotates backward, and the following front wing rotates backward accordingly, and the telescopic overlapping wing parts shrink and overlap, changing the straight wing airfoil configuration to a swept wing airfoil configuration; In the third step, the active rear wing continues to rotate backward, sweeping back until it connects with the retractable tail wing. The following front wing rotates backward accordingly, and the retractable overlapping wings are completely retracted and overlapped and retracted into the fuselage, transforming the swept wing configuration into a waverider configuration. In the fourth step, the active rear wing continues to rotate backward and the retractable tail retracts into the fuselage.

15. The deformation control method of a deformable wing according to claim 14, characterized in that: The first step is applicable to low-speed flight of Ma0-2.5, the second step is applicable to high-speed flight of Ma2.5-4, the third step is applicable to hypersonic flight of Ma4-7.5, and the fourth step is applicable to higher-speed flight or even extreme speed flight of Ma7.5-15+.

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