CN115571324B - Composite material bistable skin structure and application thereof to morphing wing - Google Patents
Composite material bistable skin structure and application thereof to morphing wing Download PDFInfo
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- CN115571324B CN115571324B CN202211575669.4A CN202211575669A CN115571324B CN 115571324 B CN115571324 B CN 115571324B CN 202211575669 A CN202211575669 A CN 202211575669A CN 115571324 B CN115571324 B CN 115571324B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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Abstract
The invention belongs to the technical field of aerospace, and discloses a composite material bistable skin structure and application thereof to a morphing wing. The composite material bistable skin structure comprises a composite material plate with bistable performance, a memory alloy plate covered on the upper surface and the lower surface of the composite material plate with bistable performance or embedded in the middle of the composite material plate with bistable performance, and a heating and cooling device for controlling the temperature of the memory alloy plate. The transformable wing with the reversible front edge and the reversible rear edge comprises a support frame, a main connecting rod arranged on the support frame, a series of crossed four-connecting rods arranged on the main connecting rods, and a segmented skin connected to the suspended end of the crossed four-connecting rods, wherein the composite material bistable skin is arranged at the position where the segmented skin is severely deformed, and the front edge and the rear edge of the transformable wing are reversely rotated through the forward and backward movement of the main connecting rod and a heating and cooling device. The composite material bistable skin structure realizes wing deformation, and has the advantages of light structural mass, excellent mechanical property, high space utilization rate and no need of external force maintenance.
Description
Technical Field
The invention belongs to the technical field of aerospace, and particularly relates to a composite material bistable skin structure and application thereof to a morphing wing.
Background
The wing is an important part of the aircraft and determines the overall aerodynamic force of the aircraft. Under different flight environments and tasks, the shapes of the wings are often required to be adjusted so as to achieve the purposes of high efficiency, safety, meeting the task requirements and the like.
The traditional stall-type helicopter mostly adopts the elliptical wing profile with symmetrical middle planes so as to relieve the backflow problem of the stall-type helicopter in the stall state. However, the elliptical wing profile greatly limits the improvement in the flight performance of the stall helicopter, both in the rotor flight mode and in the fixed wing flight mode. Therefore, the research on the wing type structure of the stall helicopter, which can solve the stall backflow problem and does not reduce the flight performance, is the research direction of a plurality of scholars.
With the continuous development of intelligent materials and structures, a good foundation is provided for the development of the morphing wing. The united states department of Defense Advanced Research Planning (DARPA) initiated the "variable aircraft structure (MAS) plan" and "smart wing" projects in tandem in recent years. Meanwhile, research works of different types of morphing wings are also being carried out by universities and research institutions in various universities in the world.
Bistable laminates are a special composite structure with two stable configurations. The bistable composite material structure of the bistable laminate can realize larger deformation through configuration transformation under the action of smaller energy, and can ensure the integrity and reliability of the bistable laminate after the configuration transformation is realized, and meanwhile, the stable configuration can be maintained without continuous energy output. Therefore, the bistable composite material laminate serves as a bearing structure and a deformation member, and the number and complexity of devices of deformation structures in the deformation wing can be greatly reduced.
Currently, there is a need to develop a composite bistable skin structure and its application to morphing wings.
Disclosure of Invention
The invention aims to provide a composite material bistable skin structure and application of the bistable skin structure on a deformable wing capable of reversing front and rear edges, aiming at the problems that the flight performance of a stall-type helicopter is limited due to an elliptical wing profile of the existing stall-type helicopter, and the conventional deformable wing is difficult to realize large deformation, large in weight of a deformation structure, complex in mechanism motion control, difficult in boundary connection and the like.
The composite material bistable skin structure is characterized by comprising a composite material plate with bistable performance, a memory alloy plate covering the upper surface and the lower surface of the composite material plate with bistable performance or embedded in the middle of the composite material plate with bistable performance, and a heating and cooling device for controlling the temperature of the memory alloy plate;
one stable state of the composite plate with bistable performance is in a flat plate shape, and the other stable state of the composite plate with bistable performance is in an arc panel shape;
the memory alloy plate has a flat plate shape and an arc panel shape, the heating and cooling device changes the temperature of the memory alloy plate by heating or cooling the memory alloy plate, and the memory alloy plate displays the flat plate shape or the arc panel shape at different temperatures; when the memory alloy plate is in a flat plate shape, the composite material plate with the bistable performance is driven to reach the flat plate shape, and when the memory alloy plate is in an arc panel shape, the composite material plate with the bistable performance is driven to reach the arc panel shape.
The application of the composite material bistable skin structure on the morphing wing is the morphing wing with reversible front and rear edges, and the morphing wing is symmetrical up and down;
the morphing wing comprises a support frame positioned in a central cavity of the morphing wing, the support frame is a square frame, support seats are symmetrically arranged on the upper surface and the lower surface of the support frame, and the support seats are fixedly supported by hinges to vertically and symmetrically fix the middle section of the skin;
sleeves which are positioned on the horizontal central axis of the morphing wing and are symmetrical left and right are arranged on the left side frame and the right side frame of the supporting frame; a horizontal movement driving module and a heating and cooling device are arranged in the inner cavity of the support frame, and the horizontal movement driving module is provided with a left side working limit and a right side working limit;
the main connecting rod is a circular tube and is positioned on the horizontal central axis of the morphing wing, the main connecting rod is connected with the sleeve in a sliding way, and the main connecting rod is fixedly connected with the output end of the horizontal movement driving module; the left end of the main connecting rod extends out of the left sleeve and extends to the left blunt front edge of the morphing wing, and the right end of the main connecting rod extends out of the right sleeve and extends to the right blunt rear edge of the morphing wing; a connecting rod I, a connecting rod II and a connecting rod IV are sequentially fixed on the main connecting rod from left to right, wherein the connecting rod I and the connecting rod II are fixed on the left side of the support frame, and the connecting rod III and the connecting rod IV are fixed on the right side of the support frame; each connecting rod is of a crossed four-connecting-rod structure which is symmetrical up and down, each connecting rod is provided with two suspension ends, the end heads of the suspension ends are provided with hinges, and the fixed ends of the connecting rods are fixed on the main connecting rod;
the skin of the morphing wing sequentially comprises a front edge fixed skin, a front edge intelligent morphing skin, a middle fixed skin, a rear edge intelligent morphing skin and a rear edge fixed skin which are vertically symmetrical from left to right, wherein the front edge intelligent morphing skin and the rear edge intelligent morphing skin adopt composite material bistable state skin structures; all the sections of skins are fixedly connected, and the interface is fixed on the hinge at the suspended end of the corresponding connecting rod; a front edge inversion deformation compensation block is connected between the upper front edge fixed skin and the lower front edge fixed skin, and a rear edge inversion deformation compensation block is connected between the upper rear edge fixed skin and the lower rear edge fixed skin;
the output end of the horizontal movement driving module drives the main connecting rod to move leftwards until the horizontal movement driving module reaches a left side working limit, the left end of the main connecting rod props against the central point of the front edge reverse deformation compensation block, all the connecting rods synchronously change included angles, the rear edge reverse deformation compensation block is freely suspended to form a sharp rear edge which is symmetrical up and down, and the deformed wing becomes an up-and-down symmetrical wing with a left side blunt front edge and a right side sharp rear edge;
the output end of the horizontal movement driving module drives the main connecting rod to move rightwards until the horizontal movement driving module reaches a right side working limit, the right end of the main connecting rod abuts against the central point of the rear edge reverse deformation compensation block, the connecting rods synchronously change included angles, the front edge reverse deformation compensation block is freely suspended to form a tip front edge which is symmetrical up and down, and the morphing wing becomes an up and down symmetrical wing with a left tip rear edge and a right blunt front edge to realize reversion.
Furthermore, the connecting rod I, the connecting rod II, the connecting rod III and the connecting rod IV are all provided with self-locking mechanisms.
The composite material bistable skin structure overcomes the defects of complex structure, low deformation efficiency and difficulty in adapting to flight environment with large variation range of the traditional deformable wing.
The composite material bistable skin structure can achieve the purpose of local change of the wing surface shape of the wing by changing from one stable state to another stable state, meets the task requirement of the deformed wing, and has the advantages of light structural weight, excellent mechanical property, high space utilization rate, no need of external force to maintain the shape and the like. The composite material bistable skin structure is applied to the deformed wings of the stall-type helicopter, the problem of backflow generated when the stall-type helicopter stalls can be solved by controlling the wing profile change, and meanwhile, the flight performance of the stall-type helicopter in a rotor wing mode and a fixed wing mode is improved.
The composite material bistable skin structure not only can be applied to the deformable wings of the reversible front edge and the reversible rear edge of a stalling helicopter, but also can be applied to the fields of robots, ships, submarines, variable-wing cruise missiles and the like, and the performance of related deformable structures is improved.
Drawings
FIG. 1 is a schematic structural view of a transformable wing of the present invention having reversible leading and trailing edges before transformation;
FIG. 2 is a schematic diagram of a deformed airfoil with reversible leading and trailing edges according to the present invention.
In the figure, 1, a leading edge inversion deformation compensation block; 2. leading edge fixed skin; 3. leading edge intelligent deformation skin; 4. the middle part is fixed with a skin; 5. a trailing edge intelligent deformation skin; 6. fixing a skin at the rear edge; 7. a trailing edge inversion deformation compensation block; 8. a horizontal movement driving module; 9. a support frame; 10. a main link; 11. a connecting rod I; 12. a connecting rod II; 13. a connecting rod III; 14. and a connecting rod IV.
Detailed Description
The technical solution of the present invention will be further described with reference to the accompanying drawings and the specific embodiments thereof.
Example 1
As shown in fig. 1 and 2, the composite bistable skin structure of the present invention includes a composite material plate having bistable properties, a memory alloy plate covering the upper surface and the lower surface of the composite material plate having bistable properties or embedded in the composite material plate having bistable properties, and a heating and cooling device for controlling the temperature of the memory alloy plate;
one stable state of the composite plate with bistable performance is in a flat plate shape, and the other stable state of the composite plate with bistable performance is in an arc panel shape;
the memory alloy plate has a flat plate shape and an arc panel shape, the heating and cooling device changes the temperature of the memory alloy plate by heating or cooling the memory alloy plate, and the memory alloy plate displays the flat plate shape or the arc panel shape at different temperatures; when the memory alloy plate is in the shape of a flat plate, the composite material plate with bistable performance is driven to reach the shape of the flat plate, and when the memory alloy plate is in the shape of an arc panel, the composite material plate with bistable performance is driven to reach the shape of the arc panel.
The application of the composite material bistable skin structure on the morphing wing is the morphing wing with reversible front and rear edges, and the morphing wing is symmetrical up and down;
the morphing wing comprises a support frame 9 positioned in a central cavity of the morphing wing, the support frame 9 is a square frame, support seats are symmetrically arranged on the upper surface and the lower surface of the support frame 9, and the support seats are fixedly supported by hinges to vertically and symmetrically fix the middle section of the skin 4 in the middle;
sleeves which are positioned on the horizontal central axis of the morphing wing and are symmetrical left and right are arranged on the left side frame and the right side frame of the supporting frame 9; a horizontal movement driving module 8 and a heating and cooling device are arranged in the inner cavity of the supporting frame 9, and the horizontal movement driving module 8 is provided with a left side working limit and a right side working limit;
the main connecting rod 10 is a circular tube and is positioned on the horizontal central axis of the morphing wing, the main connecting rod 10 is in sliding connection with the sleeve, and the main connecting rod 10 is fixedly connected with the output end of the horizontal movement driving module 8; the left end of the main connecting rod 10 extends out of the left sleeve and extends to the left blunt front edge of the morphing wing, and the right end of the main connecting rod 10 extends out of the right sleeve and extends to the right blunt rear edge of the morphing wing; a connecting rod I11, a connecting rod II 12 and a connecting rod IV 14 are sequentially fixed on the main connecting rod 10 from left to right, wherein the connecting rod I11 and the connecting rod II 12 are fixed on the left side of the support frame 9, and the connecting rod III 13 and the connecting rod IV 14 are fixed on the right side of the support frame 9; each connecting rod is of a crossed four-connecting-rod structure which is symmetrical up and down, each connecting rod is provided with two suspension ends, the end heads of the suspension ends are provided with hinges, and the fixed ends of the connecting rods are fixed on the main connecting rod 10;
the skin of the morphing wing sequentially comprises a front edge fixed skin 2, a front edge intelligent morphing skin 3, a middle fixed skin 4, a rear edge intelligent morphing skin 5 and a rear edge fixed skin 6 which are vertically symmetrical from left to right, wherein the front edge intelligent morphing skin 3 and the rear edge intelligent morphing skin 5 adopt composite material bistable state skin structures; all the sections of skins are fixedly connected, and the interface is fixed on the hinge at the suspended end of the corresponding connecting rod; a front edge inversion deformation compensation block 1 is connected between the upper front edge fixed skin 2 and the lower front edge fixed skin 2, and a rear edge inversion deformation compensation block 7 is connected between the upper rear edge fixed skin 6 and the lower rear edge fixed skin 6;
the output end of the horizontal movement driving module 8 drives the main connecting rod 10 to move leftwards until the horizontal movement driving module 8 reaches a left side working limit, the left end of the main connecting rod 10 is tightly propped against the central point of the front edge reverse deformation compensation block 1, all the connecting rods synchronously change included angles, the rear edge reverse deformation compensation block 7 is freely suspended to form a tip rear edge which is symmetrical up and down, and the morphing wing becomes an up-down symmetrical wing with a left side blunt front edge and a right side tip rear edge;
the output end of the horizontal movement driving module 8 drives the main connecting rod 10 to move rightwards until the horizontal movement driving module 8 reaches a right side working limit, the right end of the main connecting rod 10 tightly props against the central point of the rear edge reverse deformation compensation block 7, the connecting rods synchronously change included angles, the front edge reverse deformation compensation block 1 is freely suspended to form a tip front edge which is symmetrical up and down, and the morphing wing becomes an up-down symmetrical wing with a left tip rear edge and a right blunt front edge to realize reversion.
Furthermore, the connecting rod I11, the connecting rod II 12, the connecting rod III 13 and the connecting rod IV 14 are all provided with self-locking mechanisms.
The follow-up connecting rod mechanism is made of components capable of moving linearly, and has a locking function when in a non-motion state.
The leading edge smart morphing skin 3 and the trailing edge smart morphing skin 5 in the present embodiment have dimensions of 300mm (span direction) × 80mm (airfoil direction).
Although the embodiments of the present invention have been disclosed above, it is not limited to the applications listed in the description and the embodiments, but it can be applied to various fields suitable for the present invention. Additional modifications and refinements will readily occur to those skilled in the art without departing from the principles of the present invention, and the present invention is not limited to the specific details and illustrations shown and described herein.
Claims (2)
1. The application of the composite material bistable skin structure on the deformable wing is based on the composite material bistable skin structure, and the composite material bistable skin structure comprises a composite material plate with bistable performance, a memory alloy plate which covers the upper surface and the lower surface of the composite material plate with the bistable performance or is embedded in the middle of the composite material plate with the bistable performance, and a heating and cooling device for controlling the temperature of the memory alloy plate;
one stable state of the composite plate with bistable performance is in a flat plate shape, and the other stable state of the composite plate with bistable performance is in an arc panel shape;
the memory alloy plate has a flat plate shape and an arc panel shape, the heating and cooling device changes the temperature of the memory alloy plate by heating or cooling the memory alloy plate, and the memory alloy plate displays the flat plate shape or the arc panel shape at different temperatures; when the memory alloy plate is in a flat plate shape, the composite material plate with the bistable performance is driven to reach the flat plate shape, and when the memory alloy plate is in an arc panel shape, the composite material plate with the bistable performance is driven to reach the arc panel shape;
the application is characterized in that the deformable wing with reversible front and rear edges is symmetrical up and down;
the morphing wing comprises a support frame (9) positioned in a central cavity of the morphing wing, the support frame (9) is a square frame, support seats are symmetrically arranged on the upper surface and the lower surface of the support frame (9), and the support seats are fixedly supported by hinges to vertically and symmetrically fix the middle section of the skin (4) in the middle;
sleeves which are positioned on the horizontal central axis of the morphing wing and are symmetrical left and right are arranged on the left side frame and the right side frame of the support frame (9); a horizontal movement driving module (8) and a heating and cooling device are arranged in the inner cavity of the support frame (9), and the horizontal movement driving module (8) is provided with a left side working limit and a right side working limit;
the main connecting rod (10) is a circular tube and is positioned on the horizontal central axis of the morphing wing, the main connecting rod (10) is connected with the sleeve in a sliding way, and the main connecting rod (10) is fixedly connected with the output end of the horizontal movement driving module (8); the left end of the main connecting rod (10) extends out of the left sleeve and extends to the left blunt front edge of the morphing wing, and the right end of the main connecting rod (10) extends out of the right sleeve and extends to the right blunt rear edge of the morphing wing; a connecting rod I (11), a connecting rod II (12) and a connecting rod IV (14) are sequentially fixed on the main connecting rod (10) from left to right, wherein the connecting rod I (11) and the connecting rod II (12) are fixed on the left side of the support frame (9), and the connecting rod III (13) and the connecting rod IV (14) are fixed on the right side of the support frame (9); each connecting rod is of a crossed four-connecting-rod structure which is symmetrical up and down, each connecting rod is provided with two hanging ends, the end heads of the hanging ends are provided with hinges, and the fixed ends of the connecting rods are fixed on the main connecting rod (10);
the skin of the morphing wing sequentially comprises a front edge fixed skin (2), a front edge intelligent morphing skin (3), a middle fixed skin (4), a rear edge intelligent morphing skin (5) and a rear edge fixed skin (6) which are vertically symmetrical from left to right, wherein the front edge intelligent morphing skin (3) and the rear edge intelligent morphing skin (5) adopt composite material bistable state skin structures; all the sections of skins are fixedly connected, and the interface is fixed on the hinge at the suspended end of the corresponding connecting rod; a front edge reverse deformation compensation block (1) is connected between the upper front edge fixing skin (2) and the lower front edge fixing skin (2), and a rear edge reverse deformation compensation block (7) is connected between the upper rear edge fixing skin (6) and the lower rear edge fixing skin (6);
the output end of the horizontal movement driving module (8) drives the main connecting rod (10) to move leftwards until the horizontal movement driving module (8) reaches a left side working limit, the left end of the main connecting rod (10) tightly props against the central point of the front edge reverse deformation compensation block (1), all connecting rods synchronously change included angles, the rear edge reverse deformation compensation block (7) is freely suspended to form a sharp rear edge which is vertically symmetrical, and the morphing wing becomes a vertically symmetrical wing with a left blunt front edge and a right sharp rear edge;
the output end of the horizontal movement driving module (8) drives the main connecting rod (10) to move rightwards until the horizontal movement driving module (8) reaches a right side working limit, the right end of the main connecting rod (10) tightly pushes against the central point of the rear edge reverse deformation compensation block (7), included angles of the connecting rods are synchronously changed, the front edge reverse deformation compensation block (1) is freely suspended to form a tip front edge which is vertically symmetrical, and the morphing wing becomes a vertically symmetrical wing with a left tip rear edge and a right blunt front edge to realize reverse rotation.
2. The application of the composite material bistable skin structure on the morphing wing, according to claim 1, is characterized in that the connecting rod I (11), the connecting rod II (12), the connecting rod III (13) and the connecting rod IV (14) are provided with self-locking mechanisms.
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| CN115924060B (en) * | 2023-02-22 | 2023-05-16 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Asymmetric airfoil type reversing mechanism based on connecting rod assembly and use method thereof |
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