Transformable wing unit structure and deformable wing applying same

Abstract

The utility model discloses a deformable wing unit structure and a deformable wing applying the same, and relates to the technical field of flight wings, the deformable wing unit structure comprises a leading edge wing, a trailing edge wing, a driving mechanism and flexible deformable wing ribs, the horizontal two sides of the leading edge wing and the trailing edge wing are connected through the wing ribs, one end of the driving mechanism is connected with the leading edge wing, and the other end of the driving mechanism is connected with the trailing edge wing. Driving mechanisms are correspondingly arranged on the upper side and the lower side of the leading edge wing in the vertical direction, and each driving mechanism comprises fibers and conductive fibers which are wound with each other; when the conductive fibers are electrified, a heat source can be provided, and the fibers generate strain by utilizing the heat source, so that the driving mechanisms arranged on the upper side and the lower side form an antagonism structure to realize upward and downward bending deformation, the weight is light, the structure is simple, and the energy consumption of the aircraft is effectively reduced; the shape of the wings can be changed smoothly, smoothly, autonomously and continuously along with the change of the external environment, so that the performance in the whole flight process is kept optimal, and the cost can be reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of flying wings, in particular to a deformable wing unit structure and a deformable wing using the same. Background Art

[0002] The wing is one of the important parts of an aircraft. The main function of the wing is to generate lift so that the aircraft can fly in the air. In the past, the wing was a fixed structure, and its angle could not be adjusted according to the changes in the flight attitude. The flight performance under different flight attitudes was not optimal, resulting in energy waste. With the development of technology, deformable wings have gradually been developed. Compared with fixed-wing aircraft, aircraft with deformable wings have the advantages of strong adaptability and good mission execution effect. It can ensure that different flight missions can be accurately implemented under different missions, different altitudes and other flight requirements. Under different flight conditions, the wing angle can be adjusted to achieve the optimal flight performance and reduce energy consumption.

[0003] Currently, the deformation of wings is mostly achieved by mechanical transmission, such as the deformable wing disclosed in CN107985546A, which mainly controls the change of the wing by the rotation of the motor. However, the setting of the motor will increase the weight of the entire wing and increase the energy loss of the entire aircraft.

[0004] Therefore, people are in urgent need of a deformable wing unit structure with adjustable wing angle and low weight. Summary of the invention

[0005] The purpose of the utility model is to provide a deformable wing unit structure and a deformable wing using the same, so as to solve the problems existing in the above-mentioned prior art, utilize fiber filaments and conductive fibers to drive the flexible wing ribs, complete the angle change of the wing, and have a light overall weight, which is beneficial to reducing the energy loss of the aircraft.

[0006] To achieve the above-mentioned purpose, the utility model provides the following solution: The utility model provides a deformable wing unit structure, including a leading edge wing, a trailing edge wing, a driving mechanism and a flexible and deformable wing rib, the leading edge wing and the trailing edge wing are connected horizontally on both sides through the wing rib, one end of the driving mechanism is connected to the leading edge wing, and the other end is connected to the trailing edge wing, and along the vertical direction, at least one driving mechanism is correspondingly arranged on the upper and lower sides of the leading edge wing, the driving mechanism includes fiber filaments that shrink when heated and have resilience and conductive fibers, the fiber filaments and the conductive fibers are intertwined, and the conductive fibers are electrically connected to a power supply device.

[0007] Preferably, the wing rib includes a first connecting portion, a flexibly deformable deformation portion and a second connecting portion, the first connecting portion is connected to the leading edge wing, the second connecting portion is connected to the trailing edge wing, one end of the deformation portion is connected to the first connecting portion, and the other end is connected to the second connecting portion.

[0008] Preferably, a strip-shaped groove body for accommodating the driving mechanism is provided on the first connecting portion, the deforming portion and the second connecting portion.

[0009] Preferably, the deformable wing unit structure also includes a variable stiffness mechanism, and the variable stiffness mechanism is arranged on both upper and lower sides of the space between the leading edge wing and the trailing edge wing in the vertical direction, and the variable stiffness mechanisms on both sides are respectively fixedly connected to the leading edge wing and the trailing edge wing at different side ends along the length direction of the driving mechanism, and support members for supporting the variable stiffness mechanisms are arranged on opposite sides of the variable stiffness mechanisms on both sides, and the support members are connected to the wing ribs.

[0010] Preferably, baffles are provided on opposite sides of the variable stiffness mechanisms at both sides, and a channel for the variable stiffness mechanisms to move is formed between the baffles and the support member.

[0011] Preferably, the portion of the wing rib corresponding to the leading edge wing and the trailing edge wing is a wavy structure, and bumps are provided at the troughs and crests of the wavy structure. The bumps include an inner table surface and an outer table surface, and the inner table surface is the support member.

[0012] Preferably, the inner table top and the outer table top are arranged in a stepped shape, and a connecting hole for connecting the baffle is opened on the outer table top.

[0013] Preferably, the connecting hole is in a dovetail groove shape, and the blocking bar matches the connecting hole.

[0014] Preferably, the material of the rib is PLA, and the material of the fiber filament is 840D spandex.

[0015] The utility model also provides a deformable wing using the above-mentioned deformable wing unit structure, wherein a plurality of the deformable wing unit structures are arranged in series along the length direction of the wing, and a shell is arranged outside the plurality of the deformable wing unit structures.

[0016] Compared with the prior art, the utility model mainly achieves the following technical effects:

[0017] When the conductive fiber is energized, it will provide a heat source, and the fiber filaments will use the heat source to generate strain. Therefore, the driving mechanisms arranged on the upper and lower sides form an antagonistic structure to achieve upward and downward bending deformation. Compared with traditional mechanical transmission, the fiber filaments and conductive fibers are light in weight and the overall equipment structure is simple, which effectively reduces the energy consumption of the aircraft. By utilizing this deformable wing unit structure, the wing can change its shape flexibly, smoothly and autonomously as the external environment changes, which not only maintains the optimal performance throughout the flight process, but also reduces costs.

[0018] Compared with the prior art, other solutions of the utility model have achieved the following technical effects:

[0019] The variable stiffness mechanism can lock the current state of the unit structure after the angle is adjusted into place to maintain the stability of the state. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0021] Figure 1 It is a structural schematic diagram of the deformable wing unit structure of the utility model;

[0022] Figure 2 It is a structural schematic diagram of the leading edge wing of the utility model;

[0023] Figure 3 It is a structural schematic diagram of the trailing edge wing of the utility model;

[0024] Figure 4 It is a structural schematic diagram of the driving mechanism of the utility model;

[0025] Figure 5 It is a structural schematic diagram of the wing rib of the utility model;

[0026] Figure 6 It is a structural schematic diagram of the variable stiffness mechanism of the utility model;

[0027] Figure 7 It is a structural schematic diagram of the deformable wing of the utility model;

[0028] Among them, 1. leading edge wing; 2. trailing edge wing; 3. driving mechanism; 4. wing rib; 5. first connecting part; 6. deformation part; 7. second connecting part; 8. strip groove; 9. variable stiffness mechanism; 10. baffle; 11. bump; 12. inner table; 13. outer table; 14. connecting hole; 15. deformable wing unit structure. DETAILED DESCRIPTION

[0029] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0030] The purpose of the utility model is to provide a deformable wing unit structure and a deformable wing using the same, so as to solve the problems existing in the prior art, utilize fiber filaments and conductive fibers to drive the flexible wing ribs, complete the angle change of the wing, and have a light overall weight, which is beneficial to reducing the energy loss of the aircraft.

[0031] In order to make the above-mentioned purposes, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0032] Please refer to Figures 1 to 7 As shown, a deformable wing unit structure is provided, including a leading edge wing 1, a trailing edge wing 2, a driving mechanism 3 and a flexible and deformable wing rib 4. The leading edge wing 1 and the trailing edge wing 2 are connected horizontally on both sides through the wing rib 4. One end of the driving mechanism 3 is connected to the leading edge wing 1, and the other end is connected to the trailing edge wing 2. In the vertical direction, at least one driving mechanism 3 is correspondingly arranged on the upper and lower sides of the leading edge wing 1. In this embodiment, a driving mechanism 3 is arranged on the upper and lower sides, and the two driving mechanisms 3 are symmetrically arranged. When more than two are arranged on each side, the upper and lower driving mechanisms 3 can be arranged symmetrically one by one. The driving mechanism 3 includes fiber filaments and conductive fibers. The fiber filaments are made of 840D spandex, which shrinks when heated and has resilience. The fiber filaments and the conductive fibers are intertwined, that is, the two are twisted and formed, which can increase the connection between the conductive fibers and the fiber filaments. The conductive fibers are electrically connected to the power supply device, which can be a power supply inside the aircraft. When the conductive fibers are energized, a heat source is provided, and the fiber filaments utilize the heat source to generate contraction strain. Therefore, the driving mechanisms 3 arranged on the upper and lower sides form an antagonistic structure to achieve upward and downward bending deformation. Specifically, it is only necessary to control the power supply of one side of the driving mechanism 3. When the upper driving mechanism 3 is energized, the overall structure bends toward the upper side, and when the lower driving mechanism 3 is energized, the overall structure bends toward the lower side. Compared with traditional mechanical transmission, the fiber filaments and the conductive fibers have the characteristics of light weight, and the overall equipment structure is simple, thereby effectively reducing the energy consumption of the aircraft. By utilizing the deformable wing unit structure 15, the wing can change its shape flexibly, smoothly, and autonomously as the external environment changes, which not only maintains the optimal performance during the entire flight process, but also reduces costs.

[0033] The resistance of the conductive fiber can be used to monitor the strain state of the driving mechanism 3, thereby more conveniently realizing the state monitoring and attitude control functions of the wing deformation.

[0034] The rib 4 includes a first connection portion 5, a deformation portion 6 and a second connection portion 7. The first connection portion 5 is connected to the leading edge wing 1, the second connection portion 7 is connected to the trailing edge wing 2, one end of the deformation portion 6 is connected to the first connection portion 5, and the other end is connected to the second connection portion 7.

[0035] In this embodiment, PLA is selected as the material of the deformation part 6, which is formed by 3D printing. At the same time, the first connection part 5, the second connection part 7 and the deformation part 6 can be arranged in one piece, all of which are formed by 3D printing and are made of the same material.

[0036] The first connection portion 5 , the deformation portion 6 and the second connection portion 7 are provided with a strip groove 8 , which matches the driving mechanism 3 and is used to accommodate the driving mechanism 3 to ensure the telescopic direction of the driving mechanism 3 .

[0037] The leading edge wing 1 and the trailing edge wing 2 are provided with side openings, and a pin is used to penetrate the leading edge wing 1, the trailing edge wing 2 and the wing rib 4 to fix the driving mechanism 3 in the strip groove 8. Specifically, the end of the driving mechanism 3 can be bound to the pin, or a hole can be formed between the fiber filaments of the driving mechanism 3 and the conductive fiber for the pin to pass through.

[0038] In order to lock the current state of the deformable wing unit structure 15 after the angle is adjusted to a certain level to maintain the stability of the state, a variable stiffness mechanism 9 is provided. The variable stiffness mechanism 9 is an electrostatic blocking variable stiffness mechanism. In the vertical direction, variable stiffness mechanisms 9 are provided on both upper and lower sides of the space between the leading edge wing 1 and the trailing edge wing 2. The variable stiffness mechanisms 9 on both sides are respectively fixedly connected to the leading edge wing 1 and the trailing edge wing 2 at different side ends along the length direction of the driving mechanism 3. Support members for supporting the variable stiffness mechanisms 9 are provided on opposite sides of the variable stiffness mechanisms 9 on both sides. The support members are connected to the wing ribs 4. The support member serves as the middle layer of the variable stiffness mechanism 9. When the driving mechanism 3 drives the wing rib 4 to produce an angle change, the variable stiffness mechanism 9 is not energized. At this time, since the variable stiffness mechanisms 9 on the upper and lower sides are respectively connected to the leading edge wing 1 and the trailing edge wing 2, the two variable stiffness mechanisms 9 will produce relative sliding, and the overlapping area between the two variable stiffness mechanisms 9 will change; when it is necessary to fix the state of the unit structure, the variable stiffness mechanisms 9 on both sides are energized. After energization, the two variable stiffness mechanisms 9 can complete the adsorption and locking of the wing rib 4 through the support member, thereby realizing the locking of the unit structure state.

[0039] The specific production process of the variable stiffness mechanism 9 is as follows: first prepare a 0.01mmPI film, a silicone rubber tape of a certain size, a conductive ink, an ethyl acetate solution and a PET film, dilute the conductive ink with the ethyl acetate solution, and then use a screen printing process to print the diluted solution on the PI film with a designed pattern, and finally use silicone rubber tape and PET film to encapsulate and lead out the wires.

[0040] In order to realize convenient installation and disassembly, one end of the variable stiffness mechanism 9 is connected to the leading edge wing 1 or the trailing edge wing 2 by means of bolts.

[0041] Baffle bars 10 are provided on opposite sides of the variable stiffness mechanisms 9 on both sides, and a channel for the variable stiffness mechanism 9 to move is formed between the baffle bars 10 and the support members. The movement path of the variable stiffness mechanism 9 is controlled by the baffle bars 10 and the support members to ensure that it can normally complete the locking of the unit structure state.

[0042] In this embodiment, the portion of the rib 4 corresponding to the leading edge wing 1 and the trailing edge wing 2 is a wavy structure to facilitate its contraction or extension. Bumps 11 are provided at the troughs and crests of the wavy structure. The bumps 11 include an inner table 12 and an outer table 13. The inner table 12 is arranged closer to the cavity between the leading edge wing 1 and the trailing edge wing 2 than the outer table 13. The inner table 12 is used as a support member to support the variable stiffness mechanism 9.

[0043] The inner table top 12 and the outer table top 13 are arranged in a stepped shape, and a connecting hole 14 for connecting the blocking bar 10 is opened on the outer table top 13 .

[0044] By providing the protrusion 11, the support member and the separate connecting component between the baffle 10 and the unit structure can be saved, thereby achieving the purpose of reducing weight and saving costs.

[0045] In order to facilitate the installation of the baffle 10 and prevent the baffle 10 from falling out, the connecting hole 14 is arranged in a dovetail groove shape, and the baffle 10 matches the connecting hole 14 .

[0046] The utility model also provides a deformable wing using the above-mentioned deformable wing unit structure 15, wherein a plurality of deformable wing unit structures 15 are arranged in series along the length direction of the wing, and the specific number of the deformable wing unit structures 15 is determined according to the total length of the wing, and an outer shell is arranged outside the plurality of deformable wing unit structures 15.

[0047] In order to save cost and reduce weight, two adjacent deformable wing unit structures 15 share a wing rib 4, and the variable stiffness mechanism 9 is arranged at intervals in multiple deformable wing unit structures 15. That is, when a deformable wing unit structure 15 is provided with a variable stiffness mechanism 9, the variable stiffness mechanism 9 is no longer arranged in the deformable wing unit structure 15 adjacent to it.

[0048] A plurality of deformable wing unit structures 15 may share the blocking bar 10 . Specifically, the blocking bar 10 may pass through the connecting holes 14 on the protrusions 11 of the plurality of deformable wing unit structures 15 in sequence.

[0049] Adaptive changes made according to actual needs are all within the protection scope of this utility model.

[0050] It should be noted that it is obvious to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the present invention can be implemented in other specific forms without departing from the spirit or basic features of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention. Any reference numerals in the claims should not be regarded as limiting the claims involved.

[0051] The present invention uses specific examples to illustrate the principle and implementation of the present invention. The above examples are only used to help understand the method and core idea of ​​the present invention. At the same time, for those skilled in the art, according to the idea of ​​the present invention, there will be changes in the specific implementation and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. A deformable wing unit structure, characterized in that: It includes a leading edge wing, a trailing edge wing, a driving mechanism and a flexible and deformable wing rib. The leading edge wing and the trailing edge wing are connected horizontally on both sides through the wing rib. One end of the driving mechanism is connected to the leading edge wing, and the other end is connected to the trailing edge wing. In the vertical direction, at least one driving mechanism is correspondingly arranged on the upper and lower sides of the leading edge wing. The driving mechanism includes fiber filaments that shrink when heated and have resilience and conductive fibers. The fiber filaments and the conductive fibers are intertwined with each other, and the conductive fibers are electrically connected to a power supply device.

2. The deformable wing unit structure according to claim 1, characterized in that: The wing rib includes a first connecting portion, a flexibly deformable deformation portion and a second connecting portion, the first connecting portion is connected to the leading edge wing, the second connecting portion is connected to the trailing edge wing, one end of the deformation portion is connected to the first connecting portion, and the other end is connected to the second connecting portion.

3. The deformable wing unit structure according to claim 2, characterized in that: The first connecting portion, the deforming portion and the second connecting portion are provided with a strip-shaped groove body for accommodating the driving mechanism.

4. The deformable wing unit structure according to claim 1, characterized in that: The deformable wing unit structure also includes a variable stiffness mechanism. Along the vertical direction, the variable stiffness mechanism is arranged on the upper and lower sides of the space between the leading edge wing and the trailing edge wing. The variable stiffness mechanisms on both sides are respectively fixedly connected to the leading edge wing and the trailing edge wing at different side ends along the length direction of the driving mechanism. Support members for supporting the variable stiffness mechanisms are arranged on opposite sides of the variable stiffness mechanisms on both sides, and the support members are connected to the wing ribs.

5. The deformable wing unit structure according to claim 4, characterized in that: Baffles are arranged on opposite sides of the variable stiffness mechanisms at both sides, and a channel for the variable stiffness mechanisms to move is formed between the baffles and the support members.

6. The deformable wing unit structure according to claim 5, characterized in that: The portion of the wing rib corresponding to the leading edge wing and the trailing edge wing is a wave-shaped structure, and bumps are provided at the troughs and crests of the wave-shaped structure. The bumps include an inner table surface and an outer table surface, and the inner table surface is the support member.

7. The deformable wing unit structure according to claim 6, characterized in that: The inner table top and the outer table top are arranged in a stepped shape, and a connecting hole for connecting the baffle is opened on the outer table top.

8. The deformable wing unit structure according to claim 7, characterized in that: The connecting hole is in a dovetail groove shape, and the blocking bar matches the connecting hole.

9. The deformable wing unit structure according to claim 1, characterized in that: The material of the wing rib is PLA, and the material of the fiber filament is 840D spandex.

10. A morphing wing, characterized in that: A deformable wing unit structure as described in any one of claims 1 to 9 is adopted, a plurality of the deformable wing unit structures are arranged in series along the length direction of the wing, and a shell is arranged outside the plurality of the deformable wing unit structures.

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