CN115477001B - Airfoil upper surface inflation structure and control method - Google Patents
Airfoil upper surface inflation structure and control method Download PDFInfo
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- CN115477001B CN115477001B CN202210988392.1A CN202210988392A CN115477001B CN 115477001 B CN115477001 B CN 115477001B CN 202210988392 A CN202210988392 A CN 202210988392A CN 115477001 B CN115477001 B CN 115477001B
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- 238000000034 method Methods 0.000 title claims abstract description 13
- 239000002344 surface layer Substances 0.000 claims abstract description 47
- 239000010410 layer Substances 0.000 claims description 63
- 230000003014 reinforcing effect Effects 0.000 claims description 16
- 239000000463 material Substances 0.000 claims description 4
- 229920000271 Kevlar® Polymers 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 239000004761 kevlar Substances 0.000 claims description 3
- 239000003566 sealing material Substances 0.000 claims description 3
- 230000008569 process Effects 0.000 abstract description 5
- 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
- 241000272525 Anas platyrhynchos Species 0.000 description 2
- 241001669680 Dormitator maculatus Species 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 210000004712 air sac Anatomy 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/30—Wings comprising inflatable structural components
-
- 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
-
- 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)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to the technical field of aviation airfoil structures, and relates to an airfoil upper surface inflation structure and a control method. The airfoil surface of the invention is divided into two parts, namely the fixed airfoil surface layer and the air bag airfoil surface layer, and the fixed airfoil surface layer is fixedly connected with the aircraft body, so that aerodynamic force can be transmitted to the aircraft body. The air bag wing surface layer consists of a plurality of film air bags, each air bag is provided with a pressurizing valve and a pressure relief valve, and the pressurizing valve and the pressure relief valve are respectively connected with the stamping pump and the pressure relief pump through pipelines. In the whole inflation and deflation process, no mechanical structure moves, and the air inflation and deflation processes are realized by only inflating and deflating the air pump and opening and closing the pressure valve, so that the reliability of the airfoil surface is greatly improved. And the air pump is placed in the machine body and connected to each pressure valve through a pipeline, and the air pump with large air flow is selected, so that the wing section adjusting purpose can be achieved rapidly.
Description
Technical Field
The invention belongs to the technical field of aviation airfoil structures, and relates to an airfoil upper surface inflation structure and a control method.
Background
When the existing fixed wing aircraft performs maneuvering action in flight, most of the fixed wing aircraft adopts a full-wing surface deflection or additional control surface deflection mode, so that 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 steering engines are needed, the structure and the mechanism are relatively complex, and the risk of jamming exists.
There are the following problems:
(1) The control surface/airfoil deflection mechanism has a large weight;
(2) The deflection mechanism has a complex structure, reduces the reliability of the system, and improves the safety risk and the task risk;
(3) The moment or torque required by the deflection of the control surface is larger, and higher requirements are put forward on 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 high.
Therefore, the invention provides a mode of changing the wing profile by adopting ram air aiming at the wing surfaces of the duck wings, the horizontal tail wing, the vertical tail wing and the like, thereby changing the aerodynamic force of the wing surface and achieving the aim of controlling the aircraft.
Disclosure of Invention
The purpose of the invention is that: the invention changes the aerodynamic load on the airfoil by sectionally inflating the film attached to the upper surface of the airfoil, thereby realizing the maneuvering of the aircraft.
The technical scheme of the invention is as follows: an airfoil surface inflating structure divides the airfoil surface into a plurality of air chambers along the span direction, and each air chamber comprises 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 relief valve 6 and an inflating airfoil layer reinforcing belt 5; the lower airfoil surface of the bottommost airbag airfoil layer 1 is fixedly connected with the upper airfoil surface of the fixed airfoil layer 2, and the upper airbag airfoil layer and two adjacent airbag airfoil layers of the lower airbag airfoil layer sequentially share a flexible airbag bonding surface; after being inflated, each air bag wing surface layer 1 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 relief valve 6; three to five air chamber vent holes 3 are arranged between each air chamber, and a plurality of inflatable wing surface layer reinforcing belts 5 are arranged in each air chamber.
Further, each chamber is sized according to the wing position in which it is located.
Further, the lower airfoil surface of the bottommost airbag airfoil 1 is adhesively connected to the upper airfoil surface of the fixed airfoil layer 2.
Further, the fixed airfoil layer 2 is a basic airfoil, and each air bag airfoil layer 1 and the fixed airfoil layer form a new airfoil shape after being inflated, so that a new airfoil aerodynamic coefficient is generated.
Further, after being inflated, each air bag wing surface layer 1 forms a new wing shape with the fixed wing surface layer 2, and other unused air bag wing surface layers are in a negative pressure or zero pressure state and are tightly attached to the lower air bags.
Further, the air bag wing surface layer 1 is made of flexible sealing materials.
Further, the reinforcing strips 5 are sewn on the air chamber wall and fixedly sewn with the upper and lower air bag wing layers 1, and the positions of the reinforcing strips 5 are equally distributed according to the size and shape of each air bag.
Further, the reinforcing belt 5 is a flat belt, and is made of Kevlar material.
A method of controlling an airfoil upper surface plenum comprising the steps of:
1) When the airfoil surface is at the minimum lift force, the pressure release valve 6 in each air chamber is opened, the air pump sucks air outwards, and the air in each air chamber is kept free of air, so that each air-filled airfoil layer 1 is extruded by external air pressure, and the compression state is kept;
2) When the lift force needs to be improved, opening the pressure inlet valve 4 of one or more air chambers, closing the pressure relief valve 6, inflating the air chambers through the air pump, and keeping the pressure greater than one atmosphere pressure to ensure that the air pressure in the airfoil layers is greater than the external air pressure;
3) When the maximum lift force is reached, all air chambers are inflated, so that the internal air pressure is ensured to be larger than the external air pressure, and the inflatable structure reaches the wing section with the maximum lift force;
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 in a negative pressure state, and the airfoil is changed into a small lift force airfoil.
The invention has the beneficial effects that: the airfoil surface of the invention is divided into two parts, namely a fixed airfoil surface layer 1 and an air sac airfoil surface layer, and the fixed airfoil surface layer is fixedly connected with an aircraft body, so that aerodynamic force can be transmitted to the aircraft body. The air bag wing surface layer consists of a plurality of film air bags, each air bag is provided with a pressurizing valve and a pressure relief valve, and the pressurizing valve and the pressure relief valve are respectively connected with the stamping pump and the pressure relief pump through pipelines. In the whole inflation and deflation process, no mechanical structure moves, and the air inflation and deflation processes are realized by only inflating and deflating the air pump and opening and closing the pressure valve, so that the reliability of the airfoil surface is greatly improved. And the air pump is placed in the machine body and connected to each pressure valve through a pipeline, and the air pump with large air flow is selected, so that the wing section adjusting purpose can be achieved rapidly.
Drawings
FIG. 1 is a perspective view of an airfoil upper surface plenum structure of the present invention;
FIG. 2 is a schematic representation of the upper surface plenum structure 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 invention;
FIG. 4 illustrates an embodiment NACA series airfoil;
FIG. 5 illustrates four airfoil lift coefficients for an embodiment of the invention;
FIG. 6 illustrates lift-drag ratios of four airfoils according to an embodiment of the present invention;
FIG. 7 illustrates airfoil lift coefficient variation at 9 angle of attack for an embodiment of the present invention;
FIG. 8 illustrates four airfoil lift coefficient variations at 9 ° angle of attack in accordance with an embodiment of the present invention;
FIG. 9 illustrates flow field changes after modification of four NACA airfoils in accordance with an embodiment of the invention;
FIG. 10 illustrates four variations in aerodynamic lift coefficient of a modified airfoil according to an embodiment of the invention.
Wherein, 1-gasbag wing surface course, 2-fixed wing surface course, 3-air chamber air vent, 4-advance pressure valve, 6-relief valve, 5-gasbag wing surface course reinforcing band.
Detailed Description
The invention is further described below with reference to the accompanying drawings:
1-3, an airfoil upper surface inflatable structure divides the airfoil upper surface into a plurality of air chambers along the span direction, and each air chamber comprises 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 relief valve 6 and an inflatable airfoil layer reinforcing belt 5; the lower airfoil surface of the bottommost airbag airfoil layer 1 is fixedly connected with the upper airfoil surface of the fixed airfoil layer 2, and the upper airbag airfoil layer and two adjacent airbag airfoil layers of the lower airbag airfoil layer sequentially share a flexible airbag bonding surface; after being inflated, each air bag wing surface layer 1 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 relief valve 6; three to five air chamber vent holes 3 are arranged between 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 positioned;
the lower airfoil surface of the bottommost airbag airfoil 1 is connected with the upper airfoil surface of the fixed airfoil surface layer 2 by using an adhesive mode,
The fixed airfoil layer 2 is a basic airfoil of the invention, and each air bag airfoil layer 1 and the fixed airfoil layer form a new airfoil shape after being inflated, so as to generate a new airfoil aerodynamic coefficient. The invention only aims at the design method of the inflatable structure on the upper surface of the airfoil surface, and does not determine the number of layers of a specific airfoil surface and an airbag airfoil surface.
The air bag wing surface layers 1 are made of flexible sealing materials, after being inflated, each air bag wing surface layer 1 and the fixed wing surface layer 2 form a new wing shape, 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 bags.
Each air bag wing layer is provided with a plurality of reinforcing belts 5, so that the air bag wing layer can keep a preset shape after being inflated, and the strength of the wing layer can be improved. The reinforcing belt 5 is flat, is made of Kevlar material, is sewn on the wall of the air chamber, is fixedly sewn with the upper air bag wing surface layer 1 and the lower air bag wing surface layer 1, and is uniformly distributed according to the size and shape of each air bag.
Each air bag wing surface layer of two adjacent air chambers is provided with a vent hole for ensuring equal pressure of the inflated air bag wing surface layers; the size and location of the vents is dependent on the design of each wing and is not explicitly indicated.
The invention adjusts the air pressure in each film airfoil according to the aerodynamic force control requirement of the airplane, thereby achieving the effect of adjusting aerodynamic force, and the control method of the air charging structure on the upper surface of the airfoil comprises the following steps:
1) When the airfoil surface is at the minimum lift force, the pressure release valve 6 in each air chamber is opened, the air pump sucks air outwards, and the air in each air chamber is kept free of air, so that each air-filled airfoil layer 1 is extruded by external air pressure, and the compression state is kept;
2) When the lift force is required to be improved, opening the pressure inlet valve 4 of one or more air chambers, closing the pressure relief valve 6, inflating the air chambers through the air pump, and keeping the pressure greater than one atmosphere pressure to ensure that the air pressure in the airfoil layers is greater than the external air pressure, thereby achieving the shape keeping effect;
3) When the maximum lift force is reached, all air chambers are inflated, so that the internal air pressure is ensured to be larger than the external air pressure, and the inflatable structure reaches the wing section with the maximum lift force;
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 in a negative pressure state, and the airfoil is changed into a small lift force airfoil.
The invention is illustrated with 4 airfoil layers as examples:
4.1 two-dimensional aerodynamic force calculation
When the aircraft is designed as a whole, the airfoil lift force is designed to be the minimum and then designed to be the maximum air bag airfoil, and the aircraft is divided into a plurality of air bag airfoil layers according to the design. For an aircraft with smaller maneuvering requirements, several airbag wing layers can be divided, whereas for an aircraft with higher maneuvering requirements, several airbag wing layers are divided, and the basic wing profiles of the four wing layers are respectively NACA4409, NACA4412, NACA4415 and NACA4418, as shown in fig. 4. The lift coefficient versus angle of attack curve of each airfoil is shown in FIG. 5, and the lift-drag ratio versus angle of attack curve is shown in FIG. 6.
The invention mainly considers the influence of lift force on moment aiming at small wing surfaces such as duck wings, tail wings and the like and ignores the effect of resistance, thus focusing on the influence of lift force. The calculation formula of the aerodynamic lift is as follows:
Wherein ρ is the atmospheric density, V is the airspeed, S is the wing area, C L is the lift coefficient, the other factors are the same, and the influence of different airfoil inflatable structures on the moment of the engine body can be obtained by considering the change of the lift coefficient. As shown in fig. 7 and 8, the lift coefficient change of each airfoil is briefly described taking a 9 ° attack angle as an example.
At 9 ° angle of attack, 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 is calculated that the lift coefficient of NACA4412 is 12.4% higher than NACA4409, the lift coefficient of NACA4415 is 17.4% higher than NACA4409, and the lift coefficient of NACA4418 is 2.6% higher than NACA 4409.
4.2 Fluid mechanics simulation
As shown in fig. 9 and 10, in engineering, the lower airfoils of the plurality of airfoils are combined into one, and in this example, the lower airfoils of the four airfoils are all NACA4412. After airfoil modification, aerodynamic simulations were as follows, with upper airfoils being NACA4409, NACA4412, NACA4415, NACA4418, respectively.
4.3 Structural implementation description
The air-plane wing surface is divided into a plurality of air chambers in the spanwise direction, each air chamber comprises an air-bag wing surface and a fixed wing surface, the air-bag wing surface is divided into a plurality of layers, each air-bag wing surface layer is provided with a pressure inlet valve and a pressure relief valve, three to five vent holes are arranged between each air bag wing surface layer of each adjacent air chamber, so that the air pressure between the air bag wing surface layers is uniform, and the air chamber is shown as a cross section.
In this example, the air bag airfoil of each air chamber is divided into three air-inflated airfoil layers, and for each air-inflated airfoil layer, there is an air-inflated valve, and a pressure release valve, when the air bag airfoil layer works, the air-inflated valve rapidly inflates, and the pressure release valves of the other air bag airfoil layers work, rapidly suck air outwards, and maintain, and ensure that the air bag airfoil layer is under 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), the wing surfaces of the upper air bag wing surface layer and the lower air bag wing surface layer are connected, each wing surface is made of flexible airtight materials, and the air bag wing surface layers can be tightly attached to other wing surface layers when pressure relief and shrinkage are guaranteed.
Claims (8)
1. An airfoil surface inflating structure is characterized in that the airfoil surface is divided into a plurality of air chambers along the span direction, and each air chamber comprises 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 relief valve (6) and an inflating airfoil layer reinforcing belt (5); the lower airfoil surface of the bottommost air bag airfoil surface layer (1) 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 sequentially share a flexible air bag bonding surface; each air bag wing surface layer (1) forms a new wing shape with the wing surface layer below after being inflated, and each air bag wing surface layer is provided with a pressure inlet valve (4) and a pressure relief valve (6); three to five air chamber vent holes (3) are arranged between the air chambers, and a plurality of inflatable wing surface layer reinforcing belts (5) are arranged in each air chamber.
2. An airfoil upper surface inflatable structure according to claim 1, wherein the lower airfoil surface of the bottommost air bag airfoil layer (1) is adhesively connected to the upper airfoil surface of the stationary airfoil layer (2).
3. An airfoil upper surface inflatable structure according to claim 1, wherein the fixed airfoil layer (2) is a basic airfoil, each airbag airfoil layer (1) after inflation forms a new airfoil shape with the fixed airfoil layer, resulting in a new airfoil aerodynamic coefficient.
4. An airfoil upper surface inflation structure according to claim 1, wherein each air bag airfoil layer (1) forms a new airfoil shape with the fixed airfoil layer (2) after inflation, and other unused air bag airfoil layers are in a negative pressure or zero pressure state and are closely attached to the lower air bag airfoil layer.
5. An airfoil upper surface inflatable structure according to claim 1, wherein the air bag airfoil layer (1) is made of a flexible sealing material.
6. An airfoil upper surface inflatable structure according to claim 1, wherein the reinforcing strips (5) are sewn to the wall of the air bag and are fixedly sewn to the upper and lower air bag airfoil layers (1), the positions of the reinforcing strips (5) being equally distributed according to the size and shape of each air bag.
7. An airfoil upper surface plenum structure as claimed in claim 1 in which the stiffening strip (5) is in the form of a flat strip of kevlar material.
8. A method of controlling an airfoil upper surface plenum structure as set forth in claim 1 including the steps of:
1) When the airfoil surface is at the minimum lift force, a pressure release valve (6) in each air chamber is opened, the air pump sucks air outwards, and the air in each air chamber is kept free of air, so that each inflatable airfoil surface layer (1) is extruded by external air pressure, and the compression state is kept;
2) When the lifting force is required to be improved, opening a pressure inlet valve (4) of one or more air chambers, closing a pressure release valve (6), inflating the air chambers through an air pump, and keeping the pressure greater than one atmosphere pressure to ensure that the air pressure in the airfoil layers of the air bags is greater than the external air pressure;
3) When the maximum lift force is reached, all air chambers are inflated, so that the internal air pressure is ensured to be larger than the external air pressure, and the inflatable structure reaches the wing section with the maximum lift force;
4) When the lift force is required to be reduced, the pressure inlet valve (4) of one or more air chambers is closed, the pressure relief valve (6) is opened, the air pump sucks air outwards, the airfoil layer is ensured to have no air, and the airfoil layer is in a negative pressure state and is changed into a small lift force airfoil.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210988392.1A CN115477001B (en) | 2022-08-17 | 2022-08-17 | Airfoil upper surface inflation structure and control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210988392.1A CN115477001B (en) | 2022-08-17 | 2022-08-17 | Airfoil upper surface inflation structure and control method |
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| Publication Number | Publication Date |
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| CN115477001A CN115477001A (en) | 2022-12-16 |
| CN115477001B true CN115477001B (en) | 2024-06-18 |
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| CN202210988392.1A Active CN115477001B (en) | 2022-08-17 | 2022-08-17 | Airfoil upper surface inflation structure and control method |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08244689A (en) * | 1995-03-08 | 1996-09-24 | Mitsubishi Heavy Ind Ltd | Blade thickness variable rotor for hilicopter |
| CN106467163A (en) * | 2015-08-17 | 2017-03-01 | 邵波 | A kind of method and apparatus of speed control wing |
Family Cites Families (8)
| 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 |
| DE3875640D1 (en) * | 1987-03-14 | 1992-12-10 | M T B Manoevriertechnisches Bu | FLOW BODY FLOWED BY AIR OR WATER. |
| 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 |
| US6910661B2 (en) * | 2002-10-10 | 2005-06-28 | The Boeing Company | Geometric morphing wing |
| CN114572403B (en) * | 2022-03-16 | 2023-06-09 | 南京航空航天大学 | Quick-opening parafoil structure and opening method thereof |
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2022
- 2022-08-17 CN CN202210988392.1A patent/CN115477001B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08244689A (en) * | 1995-03-08 | 1996-09-24 | Mitsubishi Heavy Ind Ltd | Blade thickness variable rotor for hilicopter |
| CN106467163A (en) * | 2015-08-17 | 2017-03-01 | 邵波 | A kind of method and apparatus of speed control wing |
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| CN115477001A (en) | 2022-12-16 |
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