CN115723939A - Morphing wing based on bistable superstructure - Google Patents
Morphing wing based on bistable superstructure Download PDFInfo
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- CN115723939A CN115723939A CN202211546952.4A CN202211546952A CN115723939A CN 115723939 A CN115723939 A CN 115723939A CN 202211546952 A CN202211546952 A CN 202211546952A CN 115723939 A CN115723939 A CN 115723939A
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Abstract
The invention discloses a morphing wing based on a bistable superstructure, and belongs to the technical field of airplane wing morphing. The invention comprises an upper skin, a lower skin, a driver, a wing rib, a cross beam, a deformation assembly and a motor. The driver is a telescopic rod and is used for driving the deformation assembly to regulate and control the thickness change of the skin. The deformation component is a bistable periodic structure variable density arrangement cell element, and the bistable structure comprises a curved beam and a side wall; each row is formed by a plurality of deformation cell elements and telescopic rods to form a driving row, and the driving rows are symmetrically arranged to form the deformation assembly. The crossbeam is used for connecting the deformation components on both sides, transmits the driving force and regulates the deformation of the left side and the right side to keep the deformation of both sides of the wing consistent, and the wing profile deforms stably. The upper skin and the lower skin are respectively arranged in an upper layer and a lower layer, wing ribs are arranged on the left side and the right side, and the driving cell elements are arranged in a gradient-changing staggered mode in the inner space surrounded by the upper skin, the lower skin and the wing ribs. The method can realize the continuity of the deformation process of the morphing wing and reduce the influence on the stability of the aircraft.
Description
Technical Field
The invention belongs to the technical field of airplane wing morphing, and particularly relates to a morphing wing based on a bistable superstructure.
Background
The morphing wing aims to realize the self-adaptive shape change of the aircraft according to different flight environments and flight tasks, further change the flight attitude and obtain the optimal aerodynamic performance. The area and the shape of the lifting body of the morphing wing are adjusted by changing the position of the front edge, the position of the rear edge, the camber line radian and the thickness of the wing, so that the lift-drag ratio of the airplane can be effectively improved, and the oil consumption and the noise are reduced.
However, the conventional morphing wing seriously affects the stability of the aircraft during morphing, resulting in large changes in trim resistance of the aircraft; meanwhile, a large variant driving force is required due to the deformation process, and the self-adaptive switching is difficult to realize and the state is difficult to maintain; furthermore, the wing has poor flexibility and weight characteristics.
Disclosure of Invention
The invention mainly aims to provide a morphing wing based on a bistable superstructure, which realizes the continuity of the morphing wing deformation process and reduces the influence on the stability of an aircraft, reduces the driving force by combining the switching of the bistable structure between two states, improves the capability of keeping the states to adapt to different task requirements, improves the flexibility of the wing, and has the advantages of light structure, quick response time, smooth wing surface deformation result, maintainable molded surface, excellent fatigue performance and the like.
The purpose of the invention is realized by the following technical scheme:
the invention discloses a morphing wing based on a bistable superstructure, which comprises an upper skin, a lower skin, a driver, a wing rib, a cross beam, a morphing assembly and a motor.
The driver is a telescopic rod and is used for driving the deformation assembly to regulate and control the thickness change of the skin. The telescopic link is under the drive of motor, and the crossbeam upwards or moves down, drives power transmission drive deformation subassembly.
The deformation component is a bistable structure variable-density arrangement cell element, and the bistable structure comprises a curved beam and a side wall; each row is formed by a plurality of deformation cell elements and telescopic rods to form a driving row, and the driving rows are symmetrically arranged to form the deformation component. The bistable structure implementation method comprises the following steps: starting from an initial first stable equilibrium state, when the applied force F exceeds a critical buckling load Fcr, the bi-stable member will buckle and snap into another second stable equilibrium state and retain its deformed shape after unloading. The bi-stable member is capable of rapidly returning to the first stable equilibrium state upon application of a counter force. Accordingly, the bi-stable member exhibits a similar highly non-linear force-displacement curve under displacement control loads, exhibiting a positive slope and a positive stiffness with increasing displacement or force during pull-in from a first stable equilibrium state with local minimum strain energy U1 to a second stable equilibrium state. Beyond Fcr, the force rapidly drops to zero and reaches a peak negative value, indicating a negative stiffness. A zero force corresponds to an unstable or fast passing point with a local maximum strain energy Umax. After the peak is exceeded, the negative force increases to zero and above, again showing positive stiffness and reducing strain energy. The second zero force point represents a second stable equilibrium state with a local minimum strain energy U2, indicating that the bi-stable element can remain in this state without any external force or actuation being applied.
The crossbeam is used for connecting the deformation subassembly of both sides, and the drive power that the telescopic link provided transmits drive power in the crossbeam midpoint department, and left and right sides atress symmetry guarantees that both sides warp unanimously, and the wing section face steadily warp.
The upper skin and the lower skin are arranged in an upper layer and a lower layer respectively, wing ribs are arranged on the left side and the right side, and the driving cell elements are arranged in a gradient-changing staggered mode in an inner space surrounded by the upper skin, the lower skin and the wing ribs.
Preferably, the width of the curved beam of the bistable structure is 0.8mm, the width of the side wall is 2mm, and the width of the driving cell is 18mm.
Preferably, the driving cells are distributed in the inner space of the variable wing in a non-periodic variable density mode, and the transverse position of the wing is not changed while the longitudinal wing thickness is changed due to the zero Poisson's ratio characteristic of the bistable structure.
The invention discloses a working method of a variant wing based on a bistable superstructure, which comprises the following steps:
step 1), when the thickness of the morphing wing needs to be thickened, the telescopic rod is driven by the motor to move upwards, the cross beam moves upwards, the driving force is transmitted to the bistable structure, when the driving force is larger than the critical driving force Fcr, the upper layer of cell elements deform rapidly, the force is transmitted to the side wall along the curved beam to drive the next stage of cell elements until the last layer of cell elements is reached, and the wing deformation is completed.
And 2) when the wing variant state is required to be maintained, the telescopic rod keeps an extension mode, and the mechanical factors of the aircraft running state need to overcome the critical load of the whole bistable superstructure and the supporting force of the driving rod to enable the wing to fail, so that the wing variant state maintaining performance is higher.
And 3) when the morphing wing needs to return to the initial state, the telescopic rod drives the cross beam to move downwards, and the forced curved beams on one layer move downwards until the last stage returns to the initial state.
The invention discloses a manufacturing method of a variant wing based on a bistable superstructure, which comprises the following steps:
the method comprises the following steps: the bistable superstructure drive row and the splicing unit are both manufactured by adopting laser Fused Deposition (FDM), the splicing unit and the drive row are separately printed by adopting a slot type structure, the printing time and the printing material are saved, and the printed drive row and the splicing unit are assembled to realize the manufacture of the bistable superstructure.
Step two: and the deformation assembly and the lower skin are bonded in an adhesive mode, the cross beam is connected with the telescopic rod to transmit driving force, the lower skin is riveted with the wing rib through a rivet, and then the lower skin and the upper skin are fixed by a countersunk head screw to form a closed space, so that a forming unit of the morphing wing is formed.
Has the advantages that:
1. the invention discloses a morphing wing based on a bistable superstructure, which is characterized in that a variable-density staggered mesh structure of the bistable structure is arranged inside the morphing wing to serve as a morphing component of the morphing wing, the bistable structure is rapidly switched between a first stable balance state and a second stable balance state by utilizing the telescopic deformation of a driving rod to provide driving force, and the wing can be rapidly deformed in a short time. The combination of the switching of the bistable structure between two states reduces the driving force and improves the ability of maintaining the state to adapt to different task requirements and improve the maneuverability of the wing.
2. The invention discloses a morphing wing based on a bistable superstructure, wherein driving cell elements are arranged in a variable gradient staggered manner in an internal space defined by an upper skin, a lower skin and a wing rib, and the cell elements in a morphing component are made of porous materials and have light weight.
3. According to the morphing wing based on the bistable superstructure, disclosed by the invention, the internal structure of the wing adopts a net layout, the wing skin is divided into a plurality of small blocks, and the smooth morphing profile can be ensured through the programmed deformation.
4. According to the variant wing based on the bistable superstructure, disclosed by the invention, due to the fact that the structural customized deformation is realized by utilizing the zero Poisson ratio characteristic of the bistable superstructure, only the thickness of the wing is changed, and the sizes of the rest directions are not changed.
5. According to the morphing wing based on the bistable superstructure, disclosed by the invention, as the thickness deformation is formed by accumulating the local deformation of the multilayer structure, the requirement of large deformation scale in the thickness direction of the wing is met.
6. According to the variant wing based on the bistable superstructure, the bistable superstructure driving column and the splicing unit are both manufactured by adopting laser Fused Deposition (FDM), and in order to avoid the problems of difficulty in 3D printing forming, support removal and the like of a space structure, the splicing unit and the driving column are printed separately by adopting a clamping groove type structure, so that the printing time and the printing material are saved.
Drawings
FIG. 1-schematic filling of a multi-stable structure of a morphing wing;
FIG. 2 is a schematic diagram of a single-cell deformation, FIG. 2 a) showing a first stable equilibrium state and FIG. 2 b) showing a second stable equilibrium state;
FIG. 3-force-displacement curve for a multistable structure under pressure;
FIG. 4-drive train Overall deformation diagram;
FIG. 5-schematic view of the assembled structure;
FIG. 6-schematic diagram of unit cell assembly;
wherein: 1-upper skin, 2-lower skin, 3-wing rib, 4-driving row, 5-splicing unit, 6-driving rod, 7-cross beam, 8-curved beam and 9-side wall.
Detailed Description
To better illustrate the objects and advantages of the present invention, the following further description is made with reference to the accompanying drawings and examples.
Example 1:
as shown in fig. 1, the morphing wing based on the bistable superstructure disclosed in the present embodiment includes an upper skin 1, a lower skin 2, drivers, a wing rib 3, a cross beam 7, and a deformation assembly. The present invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, components are exaggerated for clarity.
The driver is a telescopic rod and is used for driving the deformation assembly to regulate and control the thickness change of the skin.
The deformation component is a bistable structure variable density arrangement cell, and the bistable structure comprises a curved beam 8 and a side wall 9; each row is composed of a plurality of deformation cell elements and telescopic rods to form a driving row 4, and the driving rows 4 are symmetrically arranged to form deformation components. The bistable structure implements the mechanism: starting from an initial first stable equilibrium state, as shown in fig. 2, when the applied force F exceeds the critical buckling load Fcr, the bi-stable elements will buckle and snap into another second stable equilibrium state, as shown in fig. 2, and retain their deformed shape after unloading. They quickly return to the first stable equilibrium state upon application of a counter force. Accordingly, they exhibit similar highly nonlinear force-displacement curves under displacement-controlled loads as shown in fig. 3, the bistable element exhibiting positive slope and positive stiffness with increasing displacement or force during pull-in from a first stable equilibrium state with local minimum strain energy U1 to a second stable equilibrium state. Beyond Fcr, the force rapidly drops to zero and reaches a peak negative value, indicating a negative stiffness. Zero force corresponds to an unstable or fast passing point with a local maximum strain energy Umax. After exceeding the peak, the negative force increases to zero and above, again showing positive stiffness and reducing strain energy. The second zero force point represents a second stable equilibrium state with a local minimum strain energy U2, indicating that it can remain in that state without any external force or actuation applied.
The cross beam 7 is used for connecting the deformation components on the two sides, transmitting driving force and regulating the deformation of the left side and the right side to keep the deformation of the two sides of the wing consistent, and the wing profile is stably deformed.
The upper skin 1 and the lower skin 2 are respectively arranged in an upper layer and a lower layer, the wing ribs 3 are arranged on the left side and the right side, and the driving cell elements are arranged in a gradient-changing staggered mode in the inner space surrounded by the upper skin 1, the lower skin 2 and the wing ribs 3.
The width of the curved beam 8 of the bistable structure is 0.8mm, the width of the side wall 9 is 2mm, and the width of the driving cell element is 18mm.
The driving cells are distributed in the inner space of the variable wing in an aperiodic variable density mode, and the transverse position of the wing is not changed while the thickness of the longitudinal wing is changed due to the zero Poisson ratio characteristic of the bistable structure.
As shown in fig. 4, as a result of the deformation driving row 4, the skin is deformed by the elongation of the deformation row under the driving of the driving arm.
The embodiment discloses a manufacturing method of a variant wing based on a bistable superstructure, which comprises the following steps:
the method comprises the following steps: bistable superstructure drive is listed as 4 and splice unit 5 all adopts laser Fused Deposition (FDM) to make, for avoiding spatial structure 3D to print the shaping difficulty and go the support scheduling problem, adopts the draw-in groove formula structure to separately print splice unit 5 and drive and is listed as 4, saves printing time and printing material, and the drive that will print out is listed as 4 and the equipment of splice unit 5 again, realizes the preparation of bistable superstructure.
Step two: and the deformation assembly is adhered to the lower skin 2 in an adhesive mode, the cross beam 7 is connected with the telescopic rod to transmit driving force, the lower skin 2 is riveted with the wing rib 3 through a rivet, and then the lower skin and the upper skin 1 are fixed by a countersunk head screw to form a closed space, so that a component unit of the morphing wing is formed.
Step three: and (4) taking one component unit of the morphing wing manufactured in the step (a) as a wing to be installed on an aircraft to realize wing installation.
The working method of the morphing wing based on the bistable superstructure disclosed by the embodiment comprises the following steps:
step 1), when the thickness of the morphing wing needs to be thickened, the telescopic rod is driven by the motor, the cross beam 7 moves upwards, the driving force is transmitted to the bistable structure, when the driving force is larger than the critical driving force Fcr, the upper layer of cell elements deform rapidly, the force is transmitted to the side wall 9 along the curved beam 8 to drive the next stage of cell elements, and the wing deformation is completed until the last layer of cell elements.
And 2) when the wing variant state is required to be maintained, the telescopic rod keeps an extension mode, and the mechanical factors of the aircraft running state need to overcome the critical load of the whole bistable superstructure and the supporting force of the driving rod 6 to enable the wing to be invalid, so that the state retentivity is stronger.
And 3) when the morphing wing needs to return to the initial state, the telescopic rod drives the cross beam 7 to move downwards, and the forced curved beams 8 on one layer move downwards until the last stage returns to the initial state.
The above detailed description is further intended to illustrate the objects, technical solutions and advantages of the present invention, and it should be understood that the above detailed description is only an example of the present invention and should not be used to limit the scope of the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (6)
1. A morphing wing based on a bistable superstructure, characterized in that: the device comprises an upper skin, a lower skin, a driver, a wing rib, a cross beam, a deformation assembly and a motor;
the driver is a telescopic rod and is used for driving the deformation assembly to regulate and control the thickness change of the skin; the telescopic rod is driven by the motor, the beam moves upwards or downwards, and the driving force is transmitted to drive the deformation component;
the deformation component is a bistable structure variable density arrangement cell element, and the bistable structure comprises a curved beam and a side wall; each row is formed by a plurality of deformation cell elements and telescopic rods to form a driving row, and the driving rows are symmetrically arranged to form a deformation component;
the cross beam is used for connecting the deformation components on the two sides, transmitting driving force and regulating the deformation of the left side and the right side to keep the deformation of the two sides of the wing consistent, and the wing profile surface deforms stably;
the upper skin and the lower skin are arranged in an upper layer and a lower layer respectively, wing ribs are arranged on the left side and the right side, and the driving cell elements are arranged in a gradient-changing staggered mode in an inner space surrounded by the upper skin, the lower skin and the wing ribs.
2. The morphing wing based on a bistable superstructure of claim 1, wherein: the bistable structure realization method starts from an initial first stable equilibrium state, when an applied force F exceeds a critical buckling load Fcr, the bistable element can buckle and rapidly buckle to another second stable equilibrium state and keep the deformed shape after being unloaded; the bistable element is capable of rapidly returning to a first stable equilibrium state upon application of a counter force; the bistable element exhibits a similar highly nonlinear force-displacement curve under displacement control load, and exhibits a positive slope and positive stiffness with increasing displacement or force during the capture from a first stable equilibrium state with local minimum strain energy U1 to a second stable equilibrium state; beyond Fcr, the force drops rapidly to zero and reaches a peak negative value, indicating negative stiffness; zero force corresponds to an unstable or fast passing point with a local maximum strain energy Umax; after the peak value is exceeded, the negative force is increased to zero or above, the positive stiffness is displayed again, and the strain energy is reduced; the second zero force point represents a second stable equilibrium state with a local minimum strain energy U2, indicating that the bi-stable element can remain in this state without any external force or actuation being applied.
3. A morphing wing based on a bistable superstructure as claimed in claim 1 or 2, wherein: the width of the curved beam of the bistable structure is 0.8mm, the width of the side wall is 2mm, and the width of the driving cell element is 18mm.
4. A morphing wing based on a bistable superstructure as claimed in claim 1 or 2, wherein: the driving cells are distributed in the inner space of the variable wing in a non-periodic variable density mode, and the transverse position of the wing is not changed while the thickness of the longitudinal wing is changed due to the zero Poisson's ratio characteristic of the bistable structure.
5. The morphing wing based on a bistable superstructure of claim 1, 2 or 3, wherein: the working method comprises the following steps of,
step 1), when the thickness of the morphing wing needs to be thickened, the telescopic rod is driven by a motor, the cross beam moves upwards, the driving force is transmitted to the bistable structure, when the driving force is larger than a critical driving force Fcr, the upper layer of cell elements deform rapidly, the force is transmitted to the side wall along the curved beam to drive the next stage of cell elements until the last layer of cell elements is reached, and the wing deformation is finished;
step 2), when the wing variant state is required to be maintained, the telescopic rod keeps in an extension mode, and the mechanical factors of the operation state of the aircraft can enable the wing to fail by overcoming the critical load of the whole bistable superstructure and the supporting force of the driving rod, so that the wing variant state maintaining performance is higher;
and 3) when the morphing wing needs to return to the initial state, the telescopic rod drives the cross beam to move downwards, and the forced curved beams on one layer move downwards until the last stage returns to the initial state.
6. The morphing wing of claims 1, 3, or 4, wherein: the manufacturing method comprises the following steps of,
the method comprises the following steps: the bistable superstructure driving column and the splicing unit are both manufactured by adopting laser Fused Deposition (FDM), the splicing unit and the driving column are separately printed by adopting a slot type structure, the printing time and the printing material are saved, and then the printed driving column and the splicing unit are assembled to realize the manufacture of the bistable superstructure;
step two: and the deformation component and the lower skin are bonded in an adhesive mode, the beam is connected with the telescopic rod to transmit driving force, the lower skin is riveted with the wing rib through a rivet, and then the lower skin and the upper skin are fixed through a countersunk head screw to form a closed space, so that a forming unit of the morphing wing is formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211546952.4A CN115723939A (en) | 2022-12-05 | 2022-12-05 | Morphing wing based on bistable superstructure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211546952.4A CN115723939A (en) | 2022-12-05 | 2022-12-05 | Morphing wing based on bistable superstructure |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015190124A1 (en) * | 2014-06-13 | 2015-12-17 | 独立行政法人宇宙航空研究開発機構 | Morphing wing |
| CN106827991A (en) * | 2017-02-10 | 2017-06-13 | 哈尔滨工业大学 | A kind of empty amphibious aircraft bistable state wing of water |
| CN210258812U (en) * | 2019-04-17 | 2020-04-07 | 陶伟灏 | Morphing wing based on active deformation negative Poisson ratio honeycomb structure |
| CN112278237A (en) * | 2019-07-26 | 2021-01-29 | 香港城市大学深圳研究院 | Deformable wing and aircraft |
| CN115285335A (en) * | 2022-07-04 | 2022-11-04 | 北京航空航天大学 | Deformable wing capable of being designed digitally |
-
2022
- 2022-12-05 CN CN202211546952.4A patent/CN115723939A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015190124A1 (en) * | 2014-06-13 | 2015-12-17 | 独立行政法人宇宙航空研究開発機構 | Morphing wing |
| CN106827991A (en) * | 2017-02-10 | 2017-06-13 | 哈尔滨工业大学 | A kind of empty amphibious aircraft bistable state wing of water |
| CN210258812U (en) * | 2019-04-17 | 2020-04-07 | 陶伟灏 | Morphing wing based on active deformation negative Poisson ratio honeycomb structure |
| CN112278237A (en) * | 2019-07-26 | 2021-01-29 | 香港城市大学深圳研究院 | Deformable wing and aircraft |
| CN115285335A (en) * | 2022-07-04 | 2022-11-04 | 北京航空航天大学 | Deformable wing capable of being designed digitally |
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