CN115477001A - Wing surface upper surface inflation structure and control method - Google Patents
Wing surface upper surface inflation structure and control method Download PDFInfo
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- CN115477001A CN115477001A CN202210988392.1A CN202210988392A CN115477001A CN 115477001 A CN115477001 A CN 115477001A CN 202210988392 A CN202210988392 A CN 202210988392A CN 115477001 A CN115477001 A CN 115477001A
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- 238000000034 method Methods 0.000 title claims abstract description 11
- 239000002344 surface layer Substances 0.000 claims abstract description 66
- 239000010410 layer Substances 0.000 claims description 50
- 230000003014 reinforcing effect Effects 0.000 claims description 16
- 229920000271 Kevlar® Polymers 0.000 claims description 3
- 239000004761 kevlar Substances 0.000 claims description 3
- 239000003566 sealing material Substances 0.000 claims description 3
- 230000002787 reinforcement Effects 0.000 claims 2
- 230000006835 compression Effects 0.000 claims 1
- 238000007906 compression Methods 0.000 claims 1
- 230000007246 mechanism Effects 0.000 description 5
- UJCHIZDEQZMODR-BYPYZUCNSA-N (2r)-2-acetamido-3-sulfanylpropanamide Chemical class CC(=O)N[C@@H](CS)C(N)=O UJCHIZDEQZMODR-BYPYZUCNSA-N 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 241000272517 Anseriformes Species 0.000 description 2
- 241001669680 Dormitator maculatus Species 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 2
- 238000009958 sewing Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/30—Wings comprising inflatable structural components
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/08—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like adjustable
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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
- B64C3/44—Varying camber
- B64C3/46—Varying camber by inflatable elements
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention belongs to the technical field of aviation airfoil surface structures, and relates to an upper surface inflation structure of an airfoil surface and a control method. The airfoil of the invention is divided into two parts, namely a fixed airfoil surface layer and an air bag airfoil surface layer, wherein the fixed airfoil surface layer is fixedly connected with an airplane body, so that aerodynamic force can be transmitted to the airplane body. The air bag wing surface layer is composed of a plurality of film air bags, and each air bag is provided with a pressurizing valve and a pressure release valve which are respectively connected with a pressurizing pump and a pressure release pump through pipelines. In the whole inflation and deflation process, no mechanical structure moves, the inflation and deflation of the air pump are only carried out, and the adjustment is realized by the opening and closing of the pressure valve, so that the reliability of the airfoil is greatly improved. And the air pump is placed inside the machine body, is connected to each pressure valve through a pipeline, and can quickly achieve the purpose of wing-shaped adjustment by selecting the air pump with large air flow.
Description
Technical Field
The invention belongs to the technical field of aviation airfoil surface structures, and relates to an upper surface inflation structure of an airfoil surface and a control method.
Background
When the existing fixed wing aircraft does maneuvering action during flying, the mode of full wing surface deflection or additional control surface deflection is mostly adopted, the aerodynamic load of the wing surface is changed, the balance of the aircraft is broken, and six-degree-of-freedom maneuvering is realized. In the process, control mechanisms such as a steering engine and the like are required, the structure and the mechanism are relatively complex, and the clamping risk exists.
There are the following problems:
(1) The control surface/airfoil surface deflection mechanism has a heavy weight;
(2) The deflection mechanism has a complex structure, reduces the system reliability and improves the safety risk and the task risk;
(3) The moment or torque required by deflection of the control surface is large, and high requirements are provided for the development of the steering engine;
(4) In order to improve the reliability of the steering engine and the transmission mechanism, the economic cost is higher.
Therefore, the invention provides a mode of changing wing shapes by adopting ram air aiming at wing surfaces such as canards, horizontal tail wings, vertical tail wings and the like, thereby changing the aerodynamic force of the wing surfaces and achieving the aim of controlling the airplane.
Disclosure of Invention
The purpose of the invention is as follows: the invention changes the aerodynamic load on the airfoil by inflating the film attached to the upper surface of the airfoil in a segmented manner, thereby realizing the maneuvering of the aircraft.
The technical scheme of the invention is as follows: an upper surface of an airfoil is divided into a plurality of air chambers along the wingspan direction, and each air chamber comprises one or more air bag airfoil layers 1, a fixed airfoil layer 2, an air chamber vent hole 3, a pressure inlet valve 4, a pressure release valve 6 and an inflatable airfoil layer reinforcing belt 5; the lower airfoil surface of the air bag airfoil surface layer 1 at the bottommost end is fixedly connected with the upper airfoil surface of the fixed airfoil surface layer 2, and the upper air bag airfoil surface layer and two adjacent air bag airfoil surface layers of the lower air bag airfoil surface layer share a flexible air bag joint surface; each air bag wing surface layer 1 is inflated and then forms a new wing shape with the wing surface layer below, and each air bag wing surface layer is provided with a pressure inlet valve 4 and a pressure release valve 6; three to five air chamber vent holes 3 are arranged among the air chambers, and a plurality of air inflation wing surface layer reinforcing belts 5 are arranged in each air chamber.
Further, the size of each air chamber is determined according to the position of the wing where the air chamber is located.
Further, the lower airfoil surface of the bottommost airbag airfoil 1 and the upper airfoil surface of the fixed airfoil layer 2 are connected in an adhesive manner.
Further, the fixed wing surface layer 2 is a basic wing profile, and each air bag wing surface layer 1 and the fixed wing surface layer form a new wing surface shape after being inflated, so that a new wing aerodynamic coefficient is generated.
Furthermore, each air bag wing surface layer 1 forms a new wing shape with the fixed wing surface layer 2 after being inflated, and other air bag wing surface layers which are not used are in a negative pressure or zero pressure state and are tightly attached to the air bags on the lower layer.
Further, the air bag wing surface layer 1 is made of flexible sealing materials.
Further, the reinforcing belts 5 are sewn on the air chamber wall and fixedly connected with the upper air bag airfoil layer 1 and the lower air bag airfoil layer 1 in a sewing mode, and the positions of the reinforcing belts 5 are distributed equally according to the size and the shape of each air bag.
Furthermore, the shape of the reinforcing belt 5 is a flat belt, and Kevlar materials are selected.
A method of controlling an airfoil upper surface plenum, comprising the steps of:
1) When the airfoil surface has the minimum lift force, the pressure release valves 6 in the air chambers are opened, the air pump sucks air outwards to keep the air chambers free of air, and the air-filled airfoil surface layers 1 are extruded by the external air pressure to keep a compressed state;
2) When the lift force needs to be improved, the pressure inlet valves 4 of one or more air chambers are opened, the pressure release valves 6 are closed, the air chambers are inflated through the air pump, and the air pressure is kept to be higher than the atmospheric pressure, so that the air pressure in the airfoil layer is higher than the external air pressure;
3) When the maximum lift force is reached, all the air chambers are inflated to ensure that the internal air pressure is greater than the external air pressure, and the inflatable structure reaches a maximum lift force wing shape;
4) When the lift force needs to be reduced, the pressure inlet valve 4 of one or more air chambers is closed, the pressure release valve 6 is opened, the air pump sucks air outwards, the airfoil layer is ensured to be free of air and in a negative pressure state, and the airfoil layer is changed into a low-lift force airfoil shape.
The invention has the beneficial effects that: the wing surface of the invention is divided into two parts, namely a fixed wing surface layer 1 and an air bag wing surface layer, wherein the fixed wing surface layer is fixedly connected with an airplane body, and the aerodynamic force can be transmitted to the airplane body. The air bag wing surface layer is composed of a plurality of film air bags, and each air bag is provided with a pressurizing valve and a pressure relief valve which are respectively connected with a pressurizing pump and a pressure relief pump through pipelines. In the whole inflation and deflation process, no mechanical structure moves, the inflation and deflation of the air pump are only carried out, and the adjustment is realized by the opening and closing of the pressure valve, so that the reliability of the airfoil is greatly improved. And the air pump is placed inside the machine body, is connected to each pressure valve through a pipeline, and can quickly achieve the purpose of wing-shaped adjustment by selecting the air pump with large air flow.
Drawings
FIG. 1 is a perspective view of the upper surface plenum of the airfoil of the present invention;
FIG. 2 is a schematic illustration of the upper surface inflation configuration of the airfoil of the present invention;
FIG. 3 is an enlarged view of a portion of the upper surface plenum of the airfoil of the present invention;
FIG. 4 an embodiment of the present invention NACA series airfoil;
FIG. 5 illustrates four airfoil lift coefficients for an embodiment of the present invention;
FIG. 6 illustrates lift-to-drag ratios of four airfoils of an embodiment of the present invention;
FIG. 7 shows the variation of lift coefficient of an airfoil at an angle of attack of 9 degrees according to an embodiment of the present invention;
FIG. 8 shows four airfoil lift coefficient variations at an angle of attack of 9 degrees according to an embodiment of the present invention;
FIG. 9 illustrates modified flow field changes for four NACA airfoils in accordance with an embodiment of the present invention;
FIG. 10 shows four cases of changing the aerodynamic lift coefficient of an airfoil according to the embodiment of the present invention.
The air bag comprises an air bag airfoil surface layer 1, an air bag airfoil surface layer 2, a fixed airfoil surface layer 3, an air chamber vent hole 3, a pressure inlet valve 4, a pressure release valve 6 and an air bag airfoil surface layer reinforcing belt 5.
Detailed Description
The invention is further described below with reference to the accompanying drawings:
as shown in fig. 1-3, an upper surface of an airfoil is divided into a plurality of air chambers along a wingspan direction, and each air chamber includes one or more air bag airfoil layers 1, a fixed airfoil layer 2, air chamber vent holes 3, a pressure inlet valve 4, a pressure release valve 6 and an inflatable airfoil layer reinforcing belt 5; the lower airfoil surface of the air bag airfoil surface layer 1 at the bottommost end is fixedly connected with the upper airfoil surface of the fixed airfoil surface layer 2, and the upper air bag airfoil surface layer and two adjacent air bag airfoil surface layers of the lower air bag airfoil surface layer share a flexible air bag joint surface; each air bag wing surface layer 1 is inflated and then forms a new wing shape with the wing surface layer below, and each air bag wing surface layer is provided with a pressure inlet valve 4 and a pressure release valve 6; three to five air chamber vent holes 3 are arranged among the air chambers, and an inflatable airfoil layer reinforcing belt 5 is arranged in each air chamber.
The size of each air chamber is determined according to the position of the wing where the air chamber is located;
the lower airfoil surface of the air bag airfoil surface 1 at the bottommost end is connected with the upper airfoil surface of the fixed airfoil surface layer 2 in an adhesive way,
the fixed wing surface layer 2 is a basic wing profile of the invention, and each air bag wing surface layer 1 forms a new wing surface shape with the fixed wing surface layer after being inflated, so as to generate a new wing aerodynamic coefficient. The invention only aims at the design method of the upper surface inflation structure of the airfoil, and does not clearly determine the number of specific airfoil and air bag airfoil layers.
The air bag wing surface layer 1 is made of flexible closed materials, each air bag wing surface layer 1 is inflated to form a new wing shape with the fixed wing surface layer 2, and other air bag wing surface layers which are not used are in a negative pressure or zero pressure state and are tightly attached to the lower air bag.
Each layer of the air bag wing surface layer is provided with a plurality of reinforcing belts 5, so that the air bag wing surface layer is ensured to keep a preset shape after being inflated, and the strength of the wing surface layer is improved. The reinforcing belt 5 is in a flat belt shape, made of Kevlar materials and sewn on the air chamber wall and fixedly connected with the upper air bag airfoil layer 1 and the lower air bag airfoil layer 1 in a sewing mode, and the positions of the reinforcing belt 5 are distributed equally according to the size and the shape of each air bag.
Each air bag wing surface layer of two adjacent air chambers is provided with a vent hole for ensuring the equal pressure of the air bag wing surface layers inflated; the size and location of the vent holes is dependent on the design of each wing and is not explicitly indicated.
The invention adjusts the air pressure in each film wing surface according to the aerodynamic force control requirement of the airplane to achieve the effect of adjusting the aerodynamic force, and the control method of the upper surface inflation structure of the wing surface comprises the following steps:
1) When the airfoil surface has the minimum lift force, the pressure release valves 6 in the air chambers are opened, the air pump sucks air outwards to keep the air chambers free of air, and the air-filled airfoil surface layers 1 are extruded by the external air pressure to keep a compressed state;
2) When the lift force needs to be improved, the pressure inlet valves 4 of one or more air chambers are opened, the pressure release valves 6 are closed, the air chambers are inflated through the air pump, and the air pressure is kept to be higher than one atmospheric pressure, so that the air pressure in the airfoil layer is higher than the external air pressure, and the shape-preserving effect is achieved;
3) When the maximum lift force is reached, all the air chambers are inflated to ensure that the internal air pressure is greater than the external air pressure, and the inflatable structure reaches a maximum lift force wing shape;
4) When the lift force needs to be reduced, the pressure inlet valve 4 of one or more air chambers is closed, the pressure release valve 6 is opened, the air pump sucks air outwards, the airfoil layer is ensured to have no air, is in a negative pressure state, and is changed into a low-lift airfoil shape.
The invention is illustrated with 4 airfoil layers as an example:
4.1 two-dimensional aerodynamic force calculation
When the airplane is designed in a general way, the airfoil is designed to be a fixed airfoil when the lift force is minimum, then the airfoil is designed to be a maximum airbag airfoil when the lift force is maximum, and the middle part of the airfoil is divided into a plurality of airbag airfoil layers according to the design. For less maneuverable aircraft, it is possible to divide a few airbag airfoil layers, whereas for more maneuverable aircraft, it is possible to divide a few airbag airfoil layers, the base airfoils of the four airfoil layers being NACA4409, NACA4412, NACA4415 and NACA4418, respectively, as shown in fig. 4. The variation curve of the lift coefficient of each airfoil along the attack angle is shown in FIG. 5, and the variation relation of the lift-drag ratio along the attack angle is shown in FIG. 6.
Aiming at small wing surfaces such as canard wings and empennages, the invention mainly considers the influence of the lift force on the moment and neglects the resistance effect, so the influence of the lift force is considered emphatically. The calculation formula of the aerodynamic lift force is as follows:
where ρ is the atmospheric density, V is the airspeed, S is the wing area, C L The lift coefficient is considered, the other factors are the sameThe influence of different wing-shaped air charging structures on the moment of the engine body can be obtained. As shown in fig. 7 and 8, the change in the lift coefficient of each airfoil will be briefly described using an angle of attack of 9 ° as an example.
At an angle of attack of 9 °, the lift coefficient of NACA4409 is 1.1421, the lift coefficient of NACA4412 is 1.2841, the lift coefficient of NACA4415 is 1.3409, and the lift coefficient of NACA4418 is 1.1717.
It was calculated that the lift coefficient of NACA4412 was 12.4% higher than NACA4409, that of NACA4415 was 17.4% higher than NACA4409, and that of NACA4418 was 2.6% higher than NACA 4409.
4.2 hydromechanical simulation
As shown in fig. 9 and 10, in engineering implementation, the lower surfaces of a plurality of airfoils are combined into one, and in this example, NACA4412 is adopted for the lower surfaces of all four airfoils. After the airfoil is modified, the aerodynamic simulation is as follows, and the upper airfoil surfaces are NACA4409, NACA4412, NACA4415 and NACA4418 respectively.
4.3 structural implementation Explanation
The air chamber is divided into a plurality of air chambers in the unfolding direction, each air chamber comprises an air bag airfoil and a fixed airfoil, the air bag airfoil is divided into a plurality of layers, each air bag airfoil layer is provided with a pressure inlet valve and a pressure release valve, three to five vent holes are arranged between each air bag airfoil layer of the adjacent air chambers, and the air pressure between the air bag airfoil layers is ensured to be uniform, wherein the cross section of one air chamber is shown in the figure.
In this example, the air pocket airfoil of each air chamber is divided into three inflation airfoil layers, each inflation airfoil layer has an inflation valve and a pressure release valve, when the air pocket airfoil layer works, the inflation valve inflates rapidly, the pressure release valves of the other air pocket airfoil layers work to suck air rapidly outwards and maintain to ensure that the air pocket airfoil layer is in negative pressure or zero pressure.
Each air bag wing surface layer is internally provided with a plurality of flexible reinforcing ribs (air bag wing surface layer reinforcing belts) which are connected with the wing surfaces of the upper air bag wing surface layer and the lower air bag wing surface layer, and each wing surface is made of flexible sealing materials, so that the air bag wing surface layers can be tightly attached to other wing surface layers when the pressure is released and contracted.
Claims (9)
1. The upper surface of the airfoil is divided into a plurality of air chambers along the wingspan direction, and each air chamber comprises one or more air bag airfoil layers (1), fixed airfoil layers (2), air chamber vent holes (3), a pressure inlet valve (4), a pressure release valve (6) and an inflatable airfoil layer reinforcing belt (5); the lower airfoil surface of the air bag airfoil surface layer (1) at the bottom end is fixedly connected with the upper airfoil surface of the fixed airfoil surface layer (2), and the upper air bag airfoil surface layer and two adjacent air bag airfoil surface layers of the lower air bag airfoil surface layer share a flexible air bag joint surface in sequence; each air bag wing surface layer (1) is inflated to form a new wing shape with the wing surface layer below, and each air bag wing surface layer is provided with a pressure inlet valve (4) and a pressure release valve (6); three to five air chamber vent holes (3) are arranged among the air chambers, and a plurality of air inflation wing surface layer reinforcing belts (5) are arranged in each air chamber.
2. The airfoil upper surface plenum of claim 1, wherein each plenum is sized according to the location of the airfoil in which it is located.
3. An airfoil upper surface inflation structure according to claim 1, characterized in that the lower airfoil of the bottommost bladder airfoil (1) is adhesively connected to the upper airfoil of the fixed airfoil layer (2).
4. The airfoil upper surface inflation structure as claimed in claim 1, characterized in that the fixed airfoil layer (2) is a base airfoil, and each air bag airfoil layer (1) is inflated to form a new airfoil shape with the fixed airfoil layer, resulting in a new airfoil aerodynamic coefficient.
5. The upper surface inflation structure of an airfoil according to claim 1, wherein each air pocket airfoil layer (1) forms a new airfoil shape with the fixed airfoil layer (2) after inflation, and other unused air pocket airfoil layers are in a negative pressure or zero pressure state and are closely attached to the lower air pocket.
6. The airfoil upper surface inflation structure according to claim 1, characterized in that the bladder airfoil layer (1) is of a flexible sealing material.
7. The airfoil upper surface inflation structure according to claim 1, characterized in that the reinforcement strip (5) is sewn on the air chamber wall and is fixedly sewn with the upper and lower air bag airfoil layers (1), and the positions of the reinforcement strip (5) are equally distributed according to the size and shape of each air bag.
8. The airfoil upper surface plenum structure of claim 1, characterized in that the reinforcing strip (5) is in the shape of a flat strip, selected from kevlar.
9. The method of controlling an airfoil upper surface plenum configuration of claim 1, including the steps of:
1) When the airfoil has the minimum lift force, the pressure release valves (6) in the air chambers are opened, the air pump sucks air outwards to keep that no air exists in the air chambers, and then the inflatable airfoil layers (1) are extruded by external air pressure to keep a compression state;
2) When the lift force needs to be improved, opening one or more air inlet valves (4) of the air chambers, closing the pressure release valves (6), inflating the air chambers through the air pump, and keeping the pressure to be more than one atmospheric pressure so as to enable the air pressure in the airfoil layer to be more than the external air pressure;
3) When the maximum lift force is reached, all the air chambers are inflated, the internal air pressure is ensured to be greater than the external air pressure, and the inflatable structure reaches the maximum lift force wing type;
4) When the lift force needs to be reduced, the pressure inlet valve (4) of one or more air chambers is closed, the pressure release valve (6) is opened, the air pump sucks air outwards, the airfoil layer is guaranteed to be free of air and in a negative pressure state, and the airfoil layer is changed into a low-lift airfoil shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210988392.1A CN115477001A (en) | 2022-08-17 | 2022-08-17 | Wing surface upper surface inflation structure and control method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210988392.1A CN115477001A (en) | 2022-08-17 | 2022-08-17 | Wing surface upper surface inflation structure and control method |
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| CN115477001A true CN115477001A (en) | 2022-12-16 |
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| CN202210988392.1A Pending CN115477001A (en) | 2022-08-17 | 2022-08-17 | Wing surface upper surface inflation structure and control method |
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2120250A (en) * | 1936-03-07 | 1938-06-14 | Claude M Houston | Aerofoil |
| FR2246444A1 (en) * | 1973-10-05 | 1975-05-02 | Morin Bernard | Aircraft with slow landing speed - wing section is variable between thin and thick in flight |
| US4102519A (en) * | 1977-05-11 | 1978-07-25 | The United States Of America As Represented By The Secretary Of The Air Force | Variable lift inflatable airfoil for tethered balloons |
| EP0283730A1 (en) * | 1987-03-14 | 1988-09-28 | Mtb Manövriertechnisches Büro | Aerodynamic body surrounded with air or water |
| JPH08244689A (en) * | 1995-03-08 | 1996-09-24 | Mitsubishi Heavy Ind Ltd | Blade thickness variable rotor for hilicopter |
| US6015115A (en) * | 1998-03-25 | 2000-01-18 | Lockheed Martin Corporation | Inflatable structures to control aircraft |
| US20020100406A1 (en) * | 2000-12-12 | 2002-08-01 | Costa Ronald D. | Chambered structure for wing sail |
| US20040069907A1 (en) * | 2002-10-10 | 2004-04-15 | Dockter Gregory E. | Geometric morphing wing |
| CN106467163A (en) * | 2015-08-17 | 2017-03-01 | 邵波 | A kind of method and apparatus of speed control wing |
| CN114572403A (en) * | 2022-03-16 | 2022-06-03 | 南京航空航天大学 | Fast opening parafoil structure and opening method thereof |
-
2022
- 2022-08-17 CN CN202210988392.1A patent/CN115477001A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2120250A (en) * | 1936-03-07 | 1938-06-14 | Claude M Houston | Aerofoil |
| FR2246444A1 (en) * | 1973-10-05 | 1975-05-02 | Morin Bernard | Aircraft with slow landing speed - wing section is variable between thin and thick in flight |
| US4102519A (en) * | 1977-05-11 | 1978-07-25 | The United States Of America As Represented By The Secretary Of The Air Force | Variable lift inflatable airfoil for tethered balloons |
| EP0283730A1 (en) * | 1987-03-14 | 1988-09-28 | Mtb Manövriertechnisches Büro | Aerodynamic body surrounded with air or water |
| JPH08244689A (en) * | 1995-03-08 | 1996-09-24 | Mitsubishi Heavy Ind Ltd | Blade thickness variable rotor for hilicopter |
| US6015115A (en) * | 1998-03-25 | 2000-01-18 | Lockheed Martin Corporation | Inflatable structures to control aircraft |
| US20020100406A1 (en) * | 2000-12-12 | 2002-08-01 | Costa Ronald D. | Chambered structure for wing sail |
| US20040069907A1 (en) * | 2002-10-10 | 2004-04-15 | Dockter Gregory E. | Geometric morphing wing |
| CN106467163A (en) * | 2015-08-17 | 2017-03-01 | 邵波 | A kind of method and apparatus of speed control wing |
| CN114572403A (en) * | 2022-03-16 | 2022-06-03 | 南京航空航天大学 | Fast opening parafoil structure and opening method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 王永超等: "充气式机翼设计分析", 航空科学技术, vol. 25, no. 2, 15 February 2014 (2014-02-15), pages 28 - 33 * |
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