CN116461691A - Airfoil continuous deformation mechanism based on slide bar-flexible truss-skin - Google Patents
Airfoil continuous deformation mechanism based on slide bar-flexible truss-skin Download PDFInfo
- Publication number
- CN116461691A CN116461691A CN202310419208.6A CN202310419208A CN116461691A CN 116461691 A CN116461691 A CN 116461691A CN 202310419208 A CN202310419208 A CN 202310419208A CN 116461691 A CN116461691 A CN 116461691A
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- Prior art keywords
- skin
- deformation
- wing
- flexible
- airfoil
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- 239000000463 material Substances 0.000 claims abstract description 9
- 238000005452 bending Methods 0.000 claims description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 4
- 208000002197 Ehlers-Danlos syndrome Diseases 0.000 claims description 2
- 230000005489 elastic deformation Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 claims 1
- 239000004918 carbon fiber reinforced polymer Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 5
- 239000000446 fuel Substances 0.000 description 3
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002146 bilateral effect Effects 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
- B64C2003/142—Aerofoil profile with variable camber along the airfoil chord
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an airfoil continuous deformation mechanism based on a slide bar-flexible truss-skin, which comprises a rigid airfoil box (with a tail end chord length of 40%), a flexible upper skin, 4 independent flexible trusses, slide bars and a rigid trailing edge. The truss is connected with the upper skin, and the whole driving system is used as the lower skin of the wing. The sliding rod slides back and forth on the front edge of the wing, the deformation mechanism stretches or bends, and the curved surface of the wing changes. The upper surface skin of the wing can bear the skin made of the material with large deformation. The motor gives a driving force to the slide bar in a deformation mode, and when the driving force is applied to the front edge direction, the rear edge deflects; when a driving force is applied in the direction of the trailing edge, the trailing edge deflects upward, thereby completing the deformation.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an airfoil continuous deformation mechanism based on a sliding rod, a flexible truss and a skin.
Background
The wing is an important component of the aircraft, and the conventional wing is controlled by adopting a relatively complex hinge system control surface, so that the aircraft has larger mass, is easy to cause vibration and noise during operation, has smaller fatigue damage and lift-drag ratio of the wing structure, and even limits the operability and maneuvering performance of the aircraft.
The continuous seamless deformed wing based on the intelligent material and the structural design has the advantages of improving the wing surface operation efficiency, actively inhibiting flutter, hiding performance and the like. Numerous studies and attempts have been made in various countries on flexible deformation wings. The flexible deformation wings at present mainly comprise: the airfoil surface is deformed in the plane, deformed out of the plane and deformed. The in-plane deformation mainly comprises sweepback wing, span length and chord length, the out-of-plane deformation mainly comprises wing folding, span bending, wing torsion and the like, and the wing section adjustment mainly comprises camber wing and thickness-variable wing.
The smooth and continuous camber-changing wing of the trailing edge can obviously improve the aerodynamic characteristics of the aircraft, and has important significance for low-speed cruising, taking off and landing of the aircraft and the like; the cruising and drag reduction can be realized, so that the fuel is saved, and the range is increased; the novel flexible deformation wing can replace the traditional control surface, is used for flight control to improve performance, and improves the lift-drag characteristic of the whole cruising stage by continuously changing the bending degree of the trailing edge, so that the novel flexible deformation wing research needs to be developed, a novel deformation mode is explored, and technical support is provided for the design of the novel flexible deformation wing of the unmanned aerial vehicle in the future.
Disclosure of Invention
In order to realize continuous deformation of wing camber, the invention provides a wing surface continuous deformation mechanism based on a slide bar-flexible truss-skin, which has the advantages of simple structure, higher reliability, good controllability and simple maintenance.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows:
the invention provides an airfoil continuous deformation mechanism based on a slide bar-flexible truss-skin, which comprises a rigid airfoil leading edge box (end chord length 40%), a flexible upper skin, 4 independent flexible trusses, the slide bar and a rigid trailing edge. The truss is connected with the upper skin, and the whole driving system is used as the lower skin of the wing. The slide bar passes through the fixed plate of the flexible truss. In order to prevent interference between the coupled trusses, the top angle of the truss bottom is designed to be 60 degrees as shown in fig. 2. The number of the fixing plates is the same as that of the trusses, and the fixing plates are equidistantly arranged along the sliding bars. Wherein the truss is 0.5 mm thick, and carbon fiber reinforced plastic can be selected as the material; the slide bar is a cylindrical bar with the diameter of 1mm, and the material can be a carbon fiber reinforced plastic bar; the thickness of the upper skin is 0.25mm, and a carbon fiber reinforced plastic plate is selected as a material; the fixing plate is 5mm3mm, and the material is carbon fiber reinforced plastic plate.
As shown in FIG. 3, a series of small holes are designed on the flat surface of the front edge, and the sliding rod can smoothly pass through the small holes, so that the deformation can be realized, wherein the length of the front edge is 40% of the chord length, and the width is 50mm.
Fig. 4 and 5 are model views of the upper skin, wherein fig. 4 is an isometric view of the upper skin, and fig. 5 is a dimensional parameter view of the upper skin, and the thickness dimension parameter of the upper skin is 0.25mm.
Fig. 6, 7 and 8 are model diagrams of the flexible truss, wherein fig. 6 is a side view of the flexible truss, the general arrangement mode of the flexible truss is seen in the side view, fig. 7 is a transverse arrangement view of the flexible truss, and the flexible truss is arranged in a bilateral symmetry manner in the middle, so that adjacent flexible trusses can be prevented from interfering with each other. Fig. 8 is a dimensional parameter diagram of a flexible truss.
Fig. 9 is a side view of a fixation plate and its dimensional parameters. Fig. 10 is a front view and a size diagram of a fixing plate, which is of a cuboid structure, the number of the fixing plate is 4 as same as that of flexible trusses, and small holes are arranged in the transverse direction of the fixing plate.
FIG. 11 is a side view of a slide bar and its dimensional parameters, the slide bar being a rod-shaped object with a circular cross-section, the cross-section being a circle with a diameter of 1mm and a length of 185mm, a portion being located within the leading edge.
FIG. 12 is a detail view of an airfoil continuous deformation mechanism based on a slide bar-flexible truss-skin.
FIG. 13 is a side view of an airfoil continuous deformation mechanism based on a slide bar-flexible truss-skin in accordance with an embodiment of the invention. NACA4418 was chosen as a benchmark, the designed deformed wing chord length was 280mm and the wing span was 50mm. The whole deformation mechanism is a deformation mechanism of the carbon fiber composite material.
The invention has the following beneficial effects:
1. the truss is connected with the upper skin, the driving system is used as the lower skin of the wing, and the carbon fiber rods penetrating through the flexible truss fixing plates are driven by the motor to realize continuous bending deformation of the rear edge, so that the aerodynamic characteristics of the aircraft are improved.
2. The carbon fiber material has light weight, can reduce the aircraft quality to save fuel and increase voyage, and has important significance for cruising, taking off and landing of the aircraft and the like.
Drawings
FIG. 1 is a conceptual diagram of a flexible truss mechanism with sliding rods according to an embodiment of the invention
FIG. 2 is a structural design
FIG. 3 is a leading edge detail view
Figure 4 is an isometric view of an upper skin
FIG. 5 is a diagram of upper skin design dimensional parameters
FIG. 6 is a side view of a flexible truss
FIG. 7 is a transverse alignment of flexible trusses
FIG. 8 is a graph of parameters of the dimensions of the flexible truss
FIG. 9 is a side view of a mounting plate
FIG. 10 is a transverse view of the fixing plate
FIG. 11 is a side view of a slide bar
FIG. 12 is a detailed view of a continuous deformation mechanism for a airfoil based on a slide bar-flexible truss-skin
FIG. 13 is a side view of a continuous deformation mechanism for an airfoil based on a slide bar-flexible truss-skin
FIG. 14 is a schematic view of the trailing edge downward deflection principle
FIG. 15 is a schematic view of the principle of trailing edge upward deflection
Detailed Description
The present invention will be described in further detail with reference to examples in order to make the objects and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
Referring to fig. 12, an embodiment of the present invention provides an airfoil continuous deformation mechanism based on a sliding rod-flexible truss-skin, which comprises a front edge (a wing box in the following text), an elastic skin on the upper surface of the airfoil, a flexible truss, a rear edge of the airfoil, sliding rods and a fixing plate. The sliding rod can penetrate through the fixed plate, one end of the flexible truss is connected with the upper surface skin of the wing, and the other end of the flexible truss is fixedly connected with the fixed plate; the upper surface skin of the wing needs to be made of a material capable of bearing large deformation, and the deformation undergone by the upper surface is the largest in the bending deformation of the trailing edge of the wing. The sliding rod can slide on the front edge of the wing, and the sliding rod can drive the rear edge to realize deflection deformation up and down. Wherein the deformed motor gives a driving force to the slide bar, and when the driving force is applied towards the front edge, the rear edge deflects; when a driving force is applied in the direction of the trailing edge, the trailing edge deflects upward, thereby completing the deformation. Specific deformation schematics are shown in fig. 14 and 15.
When the sliding rod slides along the fixed plate, the deformation mechanism stretches or bends, and the curved surface of the wing changes. During deformation, the sliding bars on the upper and lower skins of the flexible composite will maintain a smooth curvature to ensure aerodynamic efficiency. During deformation, the flexible truss unit undergoes a small elastic deformation, which can be accommodated by its compliance. Meanwhile, the carbon fiber reinforced plastic truss structure has higher specific stiffness and specific strength, and can provide higher bearing capacity. For approximate reasons, the structure is allowed to have a relatively low bending stiffness and a relatively low resistance to bending deformation.
In summary, by adopting the airfoil continuous deformation mechanism based on the sliding rod-flexible truss-skin, the lift-drag characteristic of the whole cruising stage can be improved through the smooth continuous camber-changing airfoil at the rear edge, the aerodynamic characteristic of the aircraft can be remarkably improved, the cruising drag reduction can be realized, the fuel can be saved, and the range can be increased.
The foregoing is merely a preferred embodiment of the present invention and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present invention, which are intended to be comprehended within the scope of the present invention.
Claims (6)
1. The airfoil continuous deformation mechanism based on the sliding rod-flexible truss-skin is characterized by comprising a front edge (a wing box in the follow-up process of the present invention) 1, an elastic skin on the upper surface of the wing 2, a flexible truss 3, a rear edge of the wing 4, a sliding rod 5 and a fixing plate 6. The sliding rod can penetrate through the fixed plate, one end of the flexible truss is connected with the upper surface skin of the wing, and the other end of the flexible truss is fixedly connected with the fixed plate; a series of small holes are designed on the straight surface of the front edge, and the sliding rod can smoothly pass through the small holes.
2. The continuous deformation mechanism for the airfoil surface based on the sliding rod-flexible truss-skin according to claim 1, wherein the fixing plate is designed into a cuboid structure, the number of the cuboid structures is the same as that of the flexible trusses, and the whole deformation mechanism is made of carbon fiber composite materials.
3. An airfoil continuous deformation mechanism based on a slide bar-flexible truss-skin is characterized by comprising the following steps: when the sliding rod slides along the fixed plate, the deformation mechanism stretches or bends, and the curved surface of the wing changes. During deformation, the sliding bars on the upper and lower skins of the flexible composite will maintain a smooth curvature to ensure aerodynamic efficiency.
4. A continuous deformation mechanism for a sliding bar-flexible truss-skin based airfoil as claimed in claim 3 wherein the flexible truss unit undergoes a small elastic deformation during deformation, adjustable by its compliance.
5. A continuous deformation mechanism for airfoils based on slide bar-flexible truss-skin according to claim 3 wherein the upper surface skin of the airfoil is required to be made of a material capable of withstanding large deformation, the deformation experienced by the upper surface being greatest during bending deformation of the trailing edge of the airfoil. The sliding rod can slide on the front edge of the wing, and the sliding rod can drive the rear edge to realize deflection deformation up and down.
6. A continuous deformation mechanism for a sliding bar-flexible truss-skin based airfoil as claimed in claim 3 wherein the deformation mode motor imparts a driving force to the sliding bar, the trailing edge being deflected by the force when the driving force is applied in the direction of the leading edge; when a driving force is applied in the direction of the trailing edge, the trailing edge deflects upward, thereby completing the deformation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310419208.6A CN116461691A (en) | 2023-04-19 | 2023-04-19 | Airfoil continuous deformation mechanism based on slide bar-flexible truss-skin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310419208.6A CN116461691A (en) | 2023-04-19 | 2023-04-19 | Airfoil continuous deformation mechanism based on slide bar-flexible truss-skin |
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| Publication Number | Publication Date |
|---|---|
| CN116461691A true CN116461691A (en) | 2023-07-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310419208.6A Pending CN116461691A (en) | 2023-04-19 | 2023-04-19 | Airfoil continuous deformation mechanism based on slide bar-flexible truss-skin |
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| CN (1) | CN116461691A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117553700A (en) * | 2023-12-28 | 2024-02-13 | 成都电科星拓科技有限公司 | Method for detecting bending deformation and stress of sliding rod based on force-induced luminescent material |
-
2023
- 2023-04-19 CN CN202310419208.6A patent/CN116461691A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117553700A (en) * | 2023-12-28 | 2024-02-13 | 成都电科星拓科技有限公司 | Method for detecting bending deformation and stress of sliding rod based on force-induced luminescent material |
| CN117553700B (en) * | 2023-12-28 | 2024-04-02 | 成都电科星拓科技有限公司 | Method for detecting bending deformation and stress of sliding rod based on force-induced luminescent material |
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