CN109515750B - Unloading weight type lift force simulation device for overwater forced landing model of rotor aircraft - Google Patents
Unloading weight type lift force simulation device for overwater forced landing model of rotor aircraft Download PDFInfo
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- CN109515750B CN109515750B CN201811579599.3A CN201811579599A CN109515750B CN 109515750 B CN109515750 B CN 109515750B CN 201811579599 A CN201811579599 A CN 201811579599A CN 109515750 B CN109515750 B CN 109515750B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
Abstract
The utility model provides a rotor type aircraft model uninstallation weight formula lift analogue means that compels to land on water, belongs to rotor type aircraft model test field that compels to land on water. Aiming at the problems that the simulation rotor lift force in the prior art is unstable, and the rotor lift force simulation device is not separated from a model to influence the motion attitude and safety of the model after water landing, the invention provides a weight-unloading lift force simulation device of a forced landing model of a rotor aircraft, which comprises: by adopting the combination of the linear guide rail and the electromagnet, the simulation lift force is always over the gravity center and is constant in size, and after the model finishes the process of water landing and water sliding, the unloading is separated from the model through the action of the electromagnet. The invention simulates the constant lift force of the rotor wing and ensures the safety of the test.
Description
Technical Field
The invention belongs to the field of test of a forced landing model of a rotary wing aircraft on water, and relates to a weight-unloading lift force simulation device of the forced landing model of the rotary wing aircraft on water.
Background
The research on the overwater forced landing technology of the helicopter is started earlier abroad, and a model test and a real machine test are carried out on helicopters with partial models. Related helicopter overwater forced landing model lift force simulation devices are designed and developed by British ground-effect aircraft research companies in the 50 th century, and mainly a scaled rotor wing is installed on a model, and a motor installed outside the model drives the rotor wing to rotate through a claw-shaped clutch to simulate lift force. After the claw clutch is loosened, the model is separated from the falling of the test device, and the lifting force of the rotor wing is maintained by the rotation inertia of the rotor wing and is continuously reduced all the time. The device has the defects that the lifting force is not constant, is reduced all the time in the falling process of the model and is not easy to quantify.
The research on the overwater forced landing technology of the helicopter in China starts late, and the research on the rotor lift simulation technology is developed late and is few. In 2006, a contact type rotor lift simulation device is designed and developed by the hydrodynamic research center of the 605 th research institute of the aviation industry, the rotor lift is simulated mainly by utilizing the extension of a spring in the dropping process of a helicopter model, and the device has the advantage that the rotor lift can be kept to pass through the center of gravity of the model all the time. It also has two problems: firstly, the lift force of the simulated rotor wing is unstable; and secondly, the rotor lift force simulation device is not separated from the model, so that the moving posture and the safety of the model after the model is wetted are easily influenced.
Disclosure of Invention
The technical problem to be solved by the invention is that the lift force of the simulation rotor wing is unstable; and secondly, the rotor lift force simulation device is not separated from the model.
In order to solve the technical problems, the technical scheme of the invention is as follows: .
A weight-unloading lift force simulation device of a forced landing model on water of a rotor type airplane is composed of a posture adjusting device 2, an electromagnetic detacher 3, a rotor type airplane connecting part 4, a linear guide rail 5, an electromagnet 6, a balancing weight 7, a pulley 9, a linear sliding block 10, a circular iron block 11 and a time delay relay 12; the linear guide rail 5 is fixed at the bottom of the trailer side bridge, the round pipe fitting 8 is installed in the middle of the trailer side bridge through a screw, the upper end of the attitude adjusting device 2 is fixed at the bottom of the round pipe fitting 8, and the electromagnetic unhooking device 3 is fixed at the lower end of the attitude adjusting device 2; the rotor type airplane connecting part 4 is arranged on the rotor type model 1, and a hook of the electromagnetic detacher 3 is hooked on an electromagnetic detacher hanging point 4-6 in the middle point of the rotor type airplane connecting part 4; the circular iron block 11 is fixed on the connecting part 4 of the rotor type airplane; the linear slide block 10 slides on the linear guide rail 5, the pulley 9 is installed on the linear slide block 10, the lower end of the electromagnet 6 is sucked on the round iron block 11, and the upper end is connected with the balancing weight 7 through a steel wire; the time delay relay 12 is connected with the electromagnet 6.
Attitude adjustment device 2 is used for adjusting the initial gesture of rotor type aircraft model, electromagnetic trip 3 is connected the model with attitude adjustment device, rotor type aircraft adapting unit 4 mainly used model connection electromagnetic trip and model connection uninstallation balancing weight, linear guide 5 is mainly as the slip interval of uninstallation balancing weight, electro-magnet 6 mainly is used for the connection of uninstallation balancing weight and model, the separation, balancing weight 7 guarantees the size of model rotor lift simulation, pulley 9 guarantees the free slip of uninstallation balancing weight in the vertical direction, linear slider 10 guarantees the uninstallation balancing weight and follows the model and freely slide in the horizontal direction, time delay relay 12 is used for controlling the model and accomplishes the electro-magnet after the hydroplaning state and discharges.
The front end of a roll lower mounting plate 2-9 of the attitude adjusting device 2 is provided with a model attitude front limiting plate 2-11, and the rear end of the lower part of the roll lower mounting plate is provided with a model attitude rear limiting plate 2-10; a connecting part 4 of a rotor type airplane connecting part is connected with a mounting base plate 4-2, the front end of the upper part of the mounting base plate is provided with a model attitude front limiting plate base 4-5, and the rear end of the upper part of the mounting base plate is provided with a model attitude rear limiting plate base 4-1; the model attitude rear limiting plate 2-10 and the model attitude front limiting plate 2-11 are respectively matched with the model attitude rear limiting plate base 4-1 and the model attitude front limiting plate base 4-5 on the rotor wing type airplane connecting part 4 to limit the model.
The upper mounting plate of the attitude adjusting device 2 is fixed with the pitching adjusting plate 2-2, the pitching angle plate 2-3 is connected with the pitching adjusting plate 2-2 through a pitching angle locking pin 2-4, and the pitching angle plate 2-3 can rotate around the pitching angle locking pin 2-4 relative to the pitching adjusting plate 2-2; the upper roll mounting plate 2-5 is fixedly connected with the lower end of the pitching angle plate 2-3, the two ends of the upper roll mounting plate 2-5 are respectively fixedly connected with the roll adjusting plates 2-7, the roll angle plate 2-8 is connected with the roll adjusting plates 2-7 through roll angle locking pins 2-6, and the roll angle plate 2-8 can rotate around the roll angle locking pins 2-6 relative to the roll adjusting plates 2-7; after the model is limited, the initial attitude angle of the model is adjusted by adjusting the pitch adjusting plate 2-2 and the roll adjusting plate 2-7 on the attitude adjusting device 2 and locking the pitch angle locking pin 2-4 and the roll angle locking pin 2-6.
Two 4-7 unloading connecting rod mounting bases are fixed in the middle of a connecting part mounting bottom plate 4-2 of a connecting part 4 of a rotor wing type airplane, and unloading connecting rod mounting bearings 4-4 and 4-3 unloading connecting rods are respectively mounted in the 4-7 unloading connecting rod mounting bases and penetrate through the two unloading connecting rod mounting bearings 4-4; 4-3 the two ends of the unloading connecting rod are respectively fixed with a round iron block 11.
During the test, the electromagnetic release 3 acts to release the hook and separate from a hanging point of a 4-6 electromagnetic release on the connecting part 4 of the rotor type airplane, the rotor type model 1 moves downwards, and the model attitude rear limiting plate 2-10 and the model attitude front limiting plate 2-11 on the attitude adjusting device 2 are separated from the model attitude rear limiting plate base 4-1 and the model attitude front limiting plate base 4-5 on the connecting part 4 of the rotor type airplane. Meanwhile, the rotor wing type model 1 attracts the electromagnet 6 on the circular iron block 11 in the downward movement process, the counterweight block 7 is driven to move together through the steel wire locked on the electromagnet 6, and the rotor wing lift force simulated by the counterweight block 7 passes through the center of gravity of the model and is constant in size. The speed reduction sliding is started after the rotor wing type model 1 is watered, the electromagnet 6 attracted on the circular iron block 11 drives the linear sliding block 10 and the balancing weight 7 to move towards the rear part of the trailer on the linear guide rail 5, and the simulated rotor wing lift force of the rotor wing type model 1 is over the gravity center and is constant in size at the moment. After the process of gliding on the water of rotor type model 1 is accomplished, time delay relay 12 begins to move, and electro-magnet 6 discharges and circular iron plate 11 separation, and rotor type model 1 and device complete separation, the safety stop is at the surface of water.
The combination of the linear guide rail and the electromagnet is adopted, so that the simulation lift force is always over the gravity center and is constant in size; and after the model finishes the process of water sliding, the unloading is separated from the model through the action of the electromagnet, so that the safety of the test model is ensured.
Drawings
FIG. 1 is an unloaded lift force simulator;
FIG. 2 is a schematic view of an attitude adjustment apparatus;
figure 3 a rotorcraft attachment component.
Wherein, 1 is a helicopter model, 2 is an attitude adjusting device, 3 is an electromagnetic detacher, 4 is a connecting part of a rotary wing aircraft, 5 is a linear guide rail, 6 is an electromagnet, 7 is a counterweight block, 8 is a circular pipe fitting, 9 is a pulley, 10 is a linear slide block, 11 is a circular iron block, 12 is a time delay relay, 2-1 is an upper mounting plate, 2-2 is a pitching adjusting plate, 2-3 is a pitching angle plate, 2-4 is a pitching angle locking pin, 2-5 is a rolling upper mounting plate, 2-6 is a rolling angle locking pin, 2-7 is a rolling adjusting plate, 2-8 is a rolling angle plate, 2-9 is a rolling lower mounting plate, 2-10 is a model attitude rear limiting plate, 2-11 is a model attitude front limiting plate, 4-1 is a model attitude rear limiting plate base, 4-2 is a connecting part mounting base plate, 2, 4-3 is an unloading connecting rod, 4-4 is an unloading connecting rod mounting bearing, 4-5 is a model attitude front limiting plate base, 4-6 is an electromagnetic detacher hanging point, and 4-7 is an unloading connecting rod mounting base.
Detailed Description
A weight-unloading lift force simulation device of a forced landing model on water of a rotor type airplane is composed of a posture adjusting device 2, an electromagnetic detacher 3, a rotor type airplane connecting part 4, a linear guide rail 5, an electromagnet 6, a balancing weight 7, a pulley 9, a linear sliding block 10, a circular iron block 11 and a time delay relay 12; the linear guide rail 5 is fixed at the bottom of the side bridge, the upper end of the attitude adjusting device 2 is fixed at the bottom of the round pipe fitting 8, and the electromagnetic unhooking device 3 is fixed at the lower end of the attitude adjusting device 2; a connecting part 4 of the rotor type airplane is arranged on the rotor type model 1, and a hook of the electromagnetic unhooking device 3 is hooked on an electromagnetic unhooking device hanging point 4-6 in the middle point of the connecting part 4 of the rotor type airplane; the circular iron block 11 is fixed on the connecting part 4 of the rotor type airplane; the linear sliding block 10 slides on the linear guide rail 5, the pulley 9 is installed on the linear sliding block 10, the lower end of the electromagnet 6 is sucked on the round iron block 11, and the upper end is connected with the balancing weight 7 through a steel wire.
Attitude adjusting device 2 is used for adjusting the initial gesture of rotor type aircraft model, electromagnetic trip 3 is connected the model with attitude adjusting device, rotor type aircraft adapting unit 4 mainly used model connection electromagnetic trip and model connection uninstallation balancing weight, linear guide 5 is mainly as the slip interval of uninstallation balancing weight, electro-magnet 6 mainly used uninstallation balancing weight and model be connected, the separation, balancing weight 7 guarantees the size of model rotor lift simulation, pulley 9 guarantees the free slip of uninstallation balancing weight in the vertical direction, linear slider 10 guarantees that the uninstallation balancing weight follows the model and freely slides in the horizontal direction, time delay relay 12 is used for controlling the model and accomplishes the electro-magnet after the aquaplaning state and discharges.
The front end of a roll lower mounting plate 2-9 of the attitude adjusting device 2 is provided with a model attitude front limiting plate 2-11, and the rear end of the lower part of the roll lower mounting plate is provided with a model attitude rear limiting plate 2-10; a connecting part 4 of a rotor type airplane connecting part is connected with a mounting base plate 4-2, the front end of the upper part of the mounting base plate is provided with a model attitude front limiting plate base 4-5, and the rear end of the upper part of the mounting base plate is provided with a model attitude rear limiting plate base 4-1; the model attitude rear limiting plate 2-10 and the model attitude front limiting plate 2-11 are respectively matched with the model attitude rear limiting plate base 4-1 and the model attitude front limiting plate base 4-5 on the rotor type aircraft connecting part 4 to limit the model.
The upper mounting plate of the attitude adjusting device 2 is fixed with the pitching adjusting plate 2-2, the pitching angle plate 2-3 is connected with the pitching adjusting plate 2-2 through a pitching angle locking pin 2-4, and the pitching angle plate 2-3 can rotate around the pitching angle locking pin 2-4 relative to the pitching adjusting plate 2-2; the upper roll mounting plate 2-5 is fixedly connected with the lower end of the pitching angle plate 2-3, the two ends of the upper roll mounting plate 2-5 are respectively fixedly connected with the roll adjusting plates 2-7, the roll angle plate 2-8 is connected with the roll adjusting plates 2-7 through roll angle locking pins 2-6, and the roll angle plate 2-8 can rotate around the roll angle locking pins 2-6 relative to the roll adjusting plates 2-7; after the model is limited, the initial attitude angle of the model is adjusted by adjusting the pitch adjusting plate 2-2 and the roll adjusting plate 2-7 on the attitude adjusting device 2 and locking the pitch angle locking pin 2-4 and the roll angle locking pin 2-6.
Two 4-7 unloading connecting rod mounting bases are fixed in the middle of a connecting part mounting bottom plate 4-2 of a connecting part 4 of a rotor wing type airplane, and unloading connecting rod mounting bearings 4-4 and 4-3 unloading connecting rods are respectively mounted in the 4-7 unloading connecting rod mounting bases and penetrate through the two unloading connecting rod mounting bearings 4-4; 4-3 the two ends of the unloading connecting rod are respectively fixed with a round iron block 11.
When the test device is installed, the round pipe fitting 8 is installed in the middle of a side bridge of a trailer through a screw, the linear guide rail 5 is clamped at the bottom of the side bridge through channel steel, the upper installation plate 2-1 of the posture adjusting device 2 is fixed at the bottom of the round pipe fitting 8 through the screw, and the electromagnetic unhooking device 3 is fixed on the lower transverse-rolling installation plate 2-9 on the posture adjusting device 2 through the screw. Then a rotor wing type airplane connecting part 4 is installed on a rotor wing type model 1 through a screw, a hook of an electromagnetic unhooking device 3 is hooked on a 4-6 electromagnetic unhooking device hanging point on the rotor wing type airplane connecting part 4, a model posture rear limiting plate 2-10 and a model posture front limiting plate 2-11 on a posture adjusting device 2 are respectively propped against a model posture rear limiting plate base 4-1 and a model posture front limiting plate base 4-5 on the rotor wing type airplane connecting part 4, and the initial attitude angle of the model can meet the test requirements by adjusting a pitching adjusting plate 2-2 and a rolling adjusting plate 2-7 on the posture adjusting device 2, locking a pitching angle locking pin 2-4 and locking a rolling angle locking pin 2-6. Then, sliding a linear slide block 10 into a linear guide rail 5, installing a pulley 9 on the linear slide block 10, fixing a circular iron block 11 on a 4-3 unloading connecting rod on a connecting part 4 of the rotor type aircraft through a screw rod, pulling down an electromagnet 6 to be sucked on the circular iron block 11, and finally sleeving a steel wire on a balancing weight 7 on the electromagnet 6 through a lock catch to set time parameters of a delay relay 12.
Before the test, the overwater forced landing model of the rotor-wing aircraft is connected with a connecting part of the rotor-wing aircraft through an electromagnetic detacher, then the initial posture of the model is adjusted through a posture adjusting device, and then a balancing weight hung on a linear slide rail sliding block is attracted with a round iron block on the model through an electromagnet. At this moment, the lift force of the rotor wing is ensured to pass through the center of gravity of the model under the initial state, and the lift force of the rotor wing is constant.
In the test process, after the model is released through the electromagnetic hook, the model is driven to unload and move downwards, the posture of the model is not changed, and the lift force of the rotor wing always passes through the center of gravity of the model and is constant in size. The model begins to slow down after the waterlogging, and relative trailer rearward movement, uninstallation balancing weight follow the model through linear slider and move to the trailer rear together this moment, has guaranteed that rotor lift size is invariable and just passes through the model focus. After the model finishes the water sliding process, the time delay relay acts, the electromagnet discharges, the model is separated from the unloading balancing weight and then stops on the water surface, and the trailer continues to move forwards, so that the safety of the model is ensured.
During the test, the electromagnetic release 3 acts to release the hook and separate from a hanging point of a 4-6 electromagnetic release on the connecting part 4 of the rotor type airplane, the rotor type model 1 moves downwards, and the model attitude rear limiting plate 2-10 and the model attitude front limiting plate 2-11 on the attitude adjusting device 2 are separated from the model attitude rear limiting plate base 4-1 and the model attitude front limiting plate base 4-5 on the connecting part 4 of the rotor type airplane. Meanwhile, the rotor wing type model 1 attracts the electromagnet 6 on the circular iron block 11 in the downward movement process, the counterweight block 7 is driven to move together through the steel wire locked on the electromagnet 6, and the rotor wing lift force simulated by the counterweight block 7 passes through the center of gravity of the model and is constant in size. The speed reduction sliding is started after the rotor wing type model 1 is watered, the electromagnet 6 attracted on the circular iron block 11 drives the linear sliding block 10 and the balancing weight 7 to move towards the rear part of the trailer on the linear guide rail 5, and the simulated rotor wing lift force of the rotor wing type model 1 is over the gravity center and is constant in size at the moment. After the process of gliding on the water of rotor type model 1 is accomplished, time delay relay 12 begins to move, and electro-magnet 6 discharges and circular iron plate 11 separation, and rotor type model 1 and device complete separation, the safety stop is at the surface of water.
Claims (4)
1. The utility model provides a rotor class aircraft model uninstallation weight formula lift analogue means that compels to land on water which characterized in that: the device comprises an attitude adjusting device (2), an electromagnetic detacher (3), a connecting part (4) of a rotor type airplane, a linear guide rail (5), an electromagnet (6), a balancing weight (7), a pulley (9), a linear sliding block (10), a circular iron block (11) and a time delay relay (12); the linear guide rail (5) is fixed at the bottom of a side bridge of the trailer, the round pipe fitting (8) is installed in the middle of the side bridge of the trailer through a screw rod, the upper end of the attitude adjusting device (2) is fixed at the bottom of the round pipe fitting (8), and the electromagnetic unhooking device (3) is fixed at the lower end of the attitude adjusting device (2); the rotor type airplane connecting part (4) is arranged on the rotor type model (1), and a hook of the electromagnetic detacher (3) is hooked on an electromagnetic detacher hanging point (4-6) on the middle point of the rotor type airplane connecting part (4); the circular iron block (11) is fixed on the connecting part (4) of the rotor wing type airplane; the linear sliding block (10) slides on the linear guide rail (5), the pulley (9) is installed on the linear sliding block (10), the lower end of the electromagnet (6) is sucked on the round iron block (11), and the upper end of the electromagnet is connected with the balancing weight (7) through a steel wire; the time delay relay (12) is connected with the electromagnet (6).
2. The weight-off-load lift simulation device of the forced landing model on water of a rotary-wing aircraft according to claim 1, characterized in that: the front end of a roll lower mounting plate (2-9) of the attitude adjusting device (2) is provided with a model attitude front limiting plate (2-11), and the rear end of the lower part of the roll lower mounting plate is provided with a model attitude rear limiting plate (2-10); the front end of the upper part of a connecting part mounting bottom plate (4-2) of a connecting part (4) of a rotor type airplane is provided with a model attitude front limiting plate base (4-5), and the rear end of the upper part is provided with a model attitude rear limiting plate base (4-1); the model attitude rear limiting plate (2-10) and the model attitude front limiting plate (2-11) are respectively matched with a model attitude rear limiting plate base (4-1) and a model attitude front limiting plate base (4-5) on the rotor type airplane connecting component (4) to limit the model.
3. The rotorcraft forced landing model unloading weight-based lift simulation device of claim 1, wherein: an upper mounting plate of the attitude adjusting device (2) is fixed with a pitching adjusting plate (2-2), the pitching angle plate (2-3) is connected with the pitching adjusting plate (2-2) through a pitching angle locking pin (2-4), and the pitching angle plate (2-3) can rotate around the pitching angle locking pin (2-4) relative to the pitching adjusting plate (2-2); the upper roll mounting plate (2-5) is fixedly connected with the lower end of the pitching angle plate (2-3), the two ends of the upper roll mounting plate (2-5) are respectively fixedly connected with the roll adjusting plates (2-7), the roll angle plate (2-8) is connected with the roll adjusting plates (2-7) through roll angle locking pins (2-6), and the roll angle plate (2-8) can rotate around the roll angle locking pins (2-6) relative to the roll adjusting plates (2-7); after the model is limited, the initial attitude angle of the model is adjusted by adjusting the pitch adjusting plate (2-2) and the roll adjusting plate (2-7) on the attitude adjusting device (2) and locking the pitch angle locking pin (2-4) and the roll angle locking pin (2-6).
4. The rotorcraft forced landing model unloading weight-based lift simulation device of claim 1, wherein: two unloading connecting rod mounting bases (4-7) are fixed in the middle of a connecting part mounting base plate (4-2) of a connecting part (4) of a rotor wing type airplane, unloading connecting rod mounting bearings (4-4) are respectively mounted in the unloading connecting rod mounting bases (4-7), and unloading connecting rods (4-3) penetrate through the two unloading connecting rod mounting bearings (4-4); the two ends of the unloading connecting rod (4-3) are respectively fixed with a round iron block (11).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811579599.3A CN109515750B (en) | 2018-12-21 | 2018-12-21 | Unloading weight type lift force simulation device for overwater forced landing model of rotor aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811579599.3A CN109515750B (en) | 2018-12-21 | 2018-12-21 | Unloading weight type lift force simulation device for overwater forced landing model of rotor aircraft |
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| CN109515750A CN109515750A (en) | 2019-03-26 |
| CN109515750B true CN109515750B (en) | 2022-03-15 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110979731B (en) * | 2019-12-10 | 2023-04-14 | 中国特种飞行器研究所 | Dynamic constant force unloading device |
| CN112607052B (en) * | 2020-12-24 | 2022-07-12 | 中国特种飞行器研究所 | Rotor craft buoy water-skiing load model |
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| CN103158887A (en) * | 2012-08-08 | 2013-06-19 | 中国特种飞行器研究所 | Fixed wing aircraft open-water-area ditching test apparatus |
| KR20150015723A (en) * | 2013-08-01 | 2015-02-11 | 한국항공우주산업 주식회사 | Cargo Hook Load manifesting system of Helicopter and Controlling Method for the Same |
| CN106323593A (en) * | 2016-11-07 | 2017-01-11 | 中国特种飞行器研究所 | Helicopter ditching test device |
| CN106525388A (en) * | 2016-11-07 | 2017-03-22 | 中国特种飞行器研究所 | Rotor type aircraft water landing model test method |
| CN108088638A (en) * | 2017-11-29 | 2018-05-29 | 中国直升机设计研究所 | A kind of fuselage skin dampening experimental rig |
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2018
- 2018-12-21 CN CN201811579599.3A patent/CN109515750B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103158887A (en) * | 2012-08-08 | 2013-06-19 | 中国特种飞行器研究所 | Fixed wing aircraft open-water-area ditching test apparatus |
| KR20150015723A (en) * | 2013-08-01 | 2015-02-11 | 한국항공우주산업 주식회사 | Cargo Hook Load manifesting system of Helicopter and Controlling Method for the Same |
| CN106323593A (en) * | 2016-11-07 | 2017-01-11 | 中国特种飞行器研究所 | Helicopter ditching test device |
| CN106525388A (en) * | 2016-11-07 | 2017-03-22 | 中国特种飞行器研究所 | Rotor type aircraft water landing model test method |
| CN108088638A (en) * | 2017-11-29 | 2018-05-29 | 中国直升机设计研究所 | A kind of fuselage skin dampening experimental rig |
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