CN111688950A - Rail carrier gas dynamic test device - Google Patents
Rail carrier gas dynamic test device Download PDFInfo
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- CN111688950A CN111688950A CN202010601780.0A CN202010601780A CN111688950A CN 111688950 A CN111688950 A CN 111688950A CN 202010601780 A CN202010601780 A CN 202010601780A CN 111688950 A CN111688950 A CN 111688950A
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- 238000012360 testing method Methods 0.000 title claims abstract description 63
- 239000012159 carrier gas Substances 0.000 title description 2
- 238000005259 measurement Methods 0.000 claims abstract description 18
- 230000007246 mechanism Effects 0.000 claims description 18
- 238000013016 damping Methods 0.000 claims description 6
- 238000002955 isolation Methods 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 4
- 238000011161 development Methods 0.000 abstract description 5
- 238000005516 engineering process Methods 0.000 abstract description 4
- 230000003137 locomotive effect Effects 0.000 abstract description 4
- 238000010276 construction Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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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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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to the technical field of pneumatic tests of aircrafts, and discloses a rail carrier pneumatic test device which comprises a vehicle body arranged on a rail, wherein the vehicle body is provided with a power traction system for the vehicle body to move, and the vehicle body is provided with a multi-degree-of-freedom mechanical arm; the remote end of the multi-degree-of-freedom mechanical arm is provided with an aircraft model, and a test measurement and control system is arranged in the vehicle body. The invention uses the power traction system to draw the vehicle body to horizontally run on the track at a certain speed to generate stable airflow required by the test; supporting an aircraft model through a multi-degree-of-freedom mechanical arm, and simulating attitude parameters of the model; the flow control of the pneumatic test and the measurement and acquisition of pneumatic parameter signals are realized through the test measurement and control system, the existing technologies of high-speed trains, electric locomotives and turbojet engines are fully utilized, the technical maturity is high, the development and running cost is lower than that of the wind tunnel test device of the same type, and the test device can run under the open air condition to obtain a flow field which is closer to the natural meteorological condition.
Description
Technical Field
The invention relates to the technical field of aircraft pneumatic tests, in particular to a rail carrier pneumatic test device.
Background
The aerodynamic test is an indispensable component in the development work of the aircraft, so the equipment for developing the aerodynamic test is important basic equipment necessary for the design and development of the aircraft. At present, low-speed aircrafts such as rotor unmanned aerial vehicles, low-speed fixed-wing unmanned aerial vehicles and tilt-wing unmanned aerial vehicles become hotspots for research in civil and military fields, but the equipment for carrying out pneumatic tests on the aircrafts has obvious gaps. Generally, a wind tunnel is used for carrying out an aircraft pneumatic test, but at present, the number of wind tunnels special for the pneumatic test of low-speed aircrafts such as a rotor unmanned aerial vehicle is small, and the construction and running costs of wind tunnel equipment are high, so that the development of the aircrafts is greatly limited. Therefore, the test device with lower construction and operation costs for the low-speed aircraft pneumatic test has great market prospect.
The flight speed of aircrafts such as rotor unmanned planes, low-speed fixed wing unmanned planes, tilt wing unmanned planes and the like is below 100m/s, the requirement on the uniformity of an airflow flow field is not high, and the test needs to be carried out on the airflow which is closer to the airflow under the natural meteorological condition.
Disclosure of Invention
Based on the problems, the invention provides a rail carrier pneumatic test device, which is characterized in that a dynamic traction system is used for dragging a vehicle body to horizontally run on a rail at a certain speed to generate stable airflow required by a test; supporting an aircraft model through a multi-degree-of-freedom mechanical arm, and simulating attitude parameters of the model; the flow control of the pneumatic test and the measurement and acquisition of pneumatic parameter signals are realized through the test measurement and control system, the existing technologies of high-speed trains, electric locomotives and turbojet engines are fully utilized, the technical maturity is high, the development and running cost is lower than that of the wind tunnel test device of the same type, and the test device can run under the open air condition to obtain a flow field which is closer to the natural meteorological condition.
In order to realize the technical effects, the invention adopts the technical scheme that:
a rail carrier pneumatic test device comprises a vehicle body arranged on a rail, wherein the vehicle body is provided with a power traction system for the vehicle body to move, and a multi-degree-of-freedom mechanical arm is arranged on the vehicle body; the remote end of the multi-degree-of-freedom mechanical arm is provided with an aircraft model, and a test measurement and control system for realizing flow control of an aircraft model pneumatic test and measurement and acquisition of pneumatic parameter signals is loaded in the vehicle body.
Furthermore, a shockproof isolation mechanism is arranged between the multi-degree-of-freedom mechanical arm and the vehicle body.
Furthermore, the positions of the vehicle body corresponding to the mechanical arm and the aircraft model are provided with airflow rectification and damping mechanisms.
Furthermore, the vehicle body also comprises a wheel set, a vehicle body, a transmission mechanism, a steering mechanism and a brake device.
Furthermore, the power traction system is an electric traction system and mainly comprises a traction control system, a pantograph supporting rod, a pantograph, a rail-matched overhead contact network and a motor.
Furthermore, the power traction system is a turbojet power system and mainly comprises a turbojet engine and a thrust control system.
Compared with the prior art, the invention has the beneficial effects that:
1) compared with a complex wind tunnel, the invention generates airflow to carry out the test by the horizontal movement of the vehicle body, has lower construction and operation cost of the vehicle body and is beneficial to carrying out the test.
2) The invention provides two traction forms, which are suitable for different requirements of customers. When the electric traction is adopted, the existing traction technology of the civil electric locomotive can be fully utilized, the technical difficulty is low, and the cost is low; when the turbojet engine is used for pushing, larger acceleration can be obtained, and the running distance of the test device is reduced.
3) The aircraft model attitude control adopts a multi-degree-of-freedom mechanical arm technology, the technical maturity is high, the acquisition is easy, and compared with model attitude control equipment of loads running in a wind tunnel, the realization technical difficulty is low, and the cost is low.
4) The invention can adapt to the design standard of civil rails, only needs to simply upgrade the abandoned railways to form special test rails, the test conditions are relatively easy to obtain, meanwhile, the test equipment has no limit of meteorological conditions, and the test data which is closer to the actual situation can be obtained when the railway track runs outdoors.
Drawings
Fig. 1 is a schematic structural view of a rail carrier pneumatic test device in which a dynamic traction system is an electric traction system in embodiment 1;
FIG. 2 is a schematic structural view of a rail carrier pneumatic test device in which the power traction system is a turbojet power system in embodiment 1;
wherein, 1, a vehicle body; 2. a multi-degree-of-freedom mechanical arm; 3. an aircraft model; 4. a test measurement and control system; 5. a shockproof isolation mechanism; 6. an airflow rectification and damping mechanism; 7. a wheel set; 8. a motor; 9. a traction control system; 10. a pantograph support rod; 11. a pantograph; 12. a rail is matched with an overhead contact network; 13. a turbojet engine; 14. a thrust control system.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Example 1:
referring to fig. 1, a rail carrier pneumatic test device comprises a vehicle body 1 arranged on a rail, wherein the vehicle body 1 is provided with a power traction system for the vehicle body 1 to move, and a multi-degree-of-freedom mechanical arm 2 is arranged on the vehicle body 1; the remote end of the multi-degree-of-freedom mechanical arm 2 is provided with an aircraft model 3, and a test measurement and control system 4 for realizing flow control of a pneumatic test of the aircraft model 3 and measurement and acquisition of pneumatic parameter signals is mounted in the vehicle body 1.
In this embodiment, the vehicle body 1 is located on a track, the power traction system is used for dragging the vehicle body 1 to horizontally run on the track at a certain speed to generate stable airflow required by a test, the multi-degree-of-freedom mechanical arm 2 is used for supporting the aircraft model 3, attitude parameters of the aircraft model 3 are simulated, the test measurement and control system 4 is used for realizing flow control of a pneumatic test and measurement and acquisition of pneumatic parameter signals, and the pneumatic test of the aircraft model 3 installed at the far end of the multi-degree-of-freedom mechanical arm 2 is realized. The test measurement and control system 4 is mainly arranged in the vehicle body 1, is not limited by the external natural environment, and can operate under various meteorological conditions. In the embodiment, a four-degree-of-freedom mechanical arm is taken as an example, and the adjustment of a plurality of model attitude parameters such as a pitch angle, a sideslip angle and a roll angle is realized through the four-degree-of-freedom mechanical arm. In the implementation process, the number of the degrees of freedom of the mechanical arm can be increased or reduced according to different actual requirements so as to simulate different model attitude parameters.
The pneumatic test effect of the embodiment on the low-speed aircraft with the speed of less than 100m/s is better, the aircraft model 3 in the embodiment is a test model, and the size of the model can be selected to be a proper value according to the actual situation. Generally, smaller aircraft may use full-scale models, and oversized models may require scaled models. The invention runs on civil rails, and when the size of the aircraft is within 2m (height) multiplied by 4m (width) multiplied by 8m (length), a full-size model can be adopted, and when the size exceeds the range, a scaling model is adopted.
In this embodiment, the vehicle body 1 further includes a wheel set 7, a vehicle body, a transmission mechanism, a steering mechanism, and a brake device. The vehicle body 1 can be formed by refitting the existing high-speed train or electric locomotive. A shockproof isolation mechanism 5 is arranged between the multi-degree-of-freedom mechanical arm 2 and the vehicle body 1, the shockproof isolation mechanism 5 is a damper, and the shock transmission between the vehicle body 1 and the multi-degree-of-freedom mechanical arm 2 can be slowed down through the shockproof isolation mechanism 5, so that the more accurate pneumatic test measurement result of the aircraft model 3 is ensured. An airflow rectifying and damping mechanism 6 is arranged on the vehicle body 1 at a position corresponding to the mechanical arm and the aircraft model 3, and the airflow rectifying and damping mechanism 6 is positioned at the front end of the incoming flow direction of the aircraft; in the running process of the vehicle body 1, airflow is rectified by the airflow rectifying and damping mechanism 6, and parameters such as turbulence degree and uniformity of incoming flow are adjusted, so that the airflow parameters meet the requirements of a test.
The power traction system in this embodiment is an electric power traction system, and mainly includes a traction control system 9, a pantograph support rod 10, a pantograph 11, a rail-supporting overhead contact system 12, and a motor 8. The electric traction system obtains electric power from a track matching overhead contact network 12 through a pantograph supporting rod 10 and a pantograph 11 and converts the electric power into a power supply suitable for driving power equipment of the vehicle body 1; the traction system control system adjusts the overall running speed of the test device by controlling the electrical parameters of the motor 8.
Example 2
Referring to fig. 2, the rail carrier pneumatic test device comprises a vehicle body 1 arranged on a rail, wherein the vehicle body 1 is provided with a power traction system for the vehicle body 1 to move, and a multi-degree-of-freedom mechanical arm 2 is arranged on the vehicle body 1; the remote end of the multi-degree-of-freedom mechanical arm 2 is provided with an aircraft model 3, and a test measurement and control system 4 for realizing flow control of a pneumatic test of the aircraft model 3 and measurement and acquisition of pneumatic parameter signals is mounted in the vehicle body 1.
The power traction system in this embodiment is a turbojet power system, which mainly comprises a turbojet engine 13 and a thrust control system 14, and the turbojet power system controls the thrust of the turbojet engine 13 through the thrust control system 14 to realize the speed control of the vehicle body 11.
Other parts in this embodiment are the same as embodiment 1, and are not described herein again.
The above is an embodiment of the present invention. The embodiments and specific parameters in the embodiments are only for the purpose of clearly illustrating the verification process of the invention and are not intended to limit the scope of the invention, which is defined by the claims, and all equivalent structural changes made by using the contents of the specification and the drawings of the present invention should be covered by the scope of the present invention.
Claims (6)
1. The utility model provides a rail carrier dynamic test device which characterized in that: the multi-freedom-degree mechanical arm comprises a vehicle body (1) arranged on a track, wherein the vehicle body (1) is provided with a power traction system for the vehicle body (1) to move, and the vehicle body (1) is provided with a multi-freedom-degree mechanical arm (2); the remote end of the multi-degree-of-freedom mechanical arm (2) is provided with an aircraft model (3), and a test measurement and control system (4) for realizing flow control of a pneumatic test and measurement and acquisition of a pneumatic parameter signal of the aircraft model (3) is loaded in the vehicle body (1).
2. An orbital pneumatic test device according to claim 1, further comprising: and a shockproof isolation mechanism (5) is arranged between the multi-degree-of-freedom mechanical arm (2) and the vehicle body (1).
3. An orbital pneumatic test device according to claim 1, further comprising: and an airflow rectifying and damping mechanism (6) is arranged on the vehicle body (1) at a position corresponding to the mechanical arm and the aircraft model (3).
4. An orbital pneumatic test device according to claim 1, further comprising: the vehicle body (1) further comprises a wheel set (7), a vehicle body, a transmission mechanism, a steering mechanism and a brake device.
5. An orbital pneumatic test device according to any one of claims 1 to 4, characterized in that: the power traction system is an electric traction system and mainly comprises a traction control system (9), a pantograph supporting rod (10), a pantograph (11), a track-matched overhead contact network (12) and a motor (8).
6. An orbital pneumatic test device according to any one of claims 1 to 4, characterized in that: the power traction system is a turbojet power system and mainly comprises a turbojet engine (13) and a thrust control system (14).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010601780.0A CN111688950A (en) | 2020-06-29 | 2020-06-29 | Rail carrier gas dynamic test device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010601780.0A CN111688950A (en) | 2020-06-29 | 2020-06-29 | Rail carrier gas dynamic test device |
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| CN111688950A true CN111688950A (en) | 2020-09-22 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113335558A (en) * | 2021-05-28 | 2021-09-03 | 合肥飞豪通信科技有限公司 | Remote measurement type small unmanned aerial vehicle wind pressure test system |
| CN114152401A (en) * | 2021-11-10 | 2022-03-08 | 中国空气动力研究与发展中心空天技术研究所 | Vehicle-mounted pneumatic test device |
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| RU2084851C1 (en) * | 1994-02-09 | 1997-07-20 | Центральный аэрогидродинамический институт им.проф.Н.Е.Жуковского | Method of measurement of aerodynamic characteristics of model of flying vehicle and device for its implementation |
| JP2003161671A (en) * | 2001-11-26 | 2003-06-06 | Tech Res & Dev Inst Of Japan Def Agency | Dynamic wind tunnel test device |
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| CN109573097A (en) * | 2018-11-13 | 2019-04-05 | 中国航天空气动力技术研究院 | A kind of low-speed operations device aerodynamic parameter on-road emission test method and system |
| CN110082059A (en) * | 2019-04-22 | 2019-08-02 | 南京航空航天大学 | A kind of New Wind Tunnel flow field Jiao Ce mechanism and application method |
| CN213323763U (en) * | 2020-06-29 | 2021-06-01 | 中国空气动力研究与发展中心 | Rail carrier gas dynamic test device |
-
2020
- 2020-06-29 CN CN202010601780.0A patent/CN111688950A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2084851C1 (en) * | 1994-02-09 | 1997-07-20 | Центральный аэрогидродинамический институт им.проф.Н.Е.Жуковского | Method of measurement of aerodynamic characteristics of model of flying vehicle and device for its implementation |
| JP2003161671A (en) * | 2001-11-26 | 2003-06-06 | Tech Res & Dev Inst Of Japan Def Agency | Dynamic wind tunnel test device |
| CN106596033A (en) * | 2016-11-04 | 2017-04-26 | 中国航天空气动力技术研究院 | Testing system and testing method for propeller ground test in near space |
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| CN213323763U (en) * | 2020-06-29 | 2021-06-01 | 中国空气动力研究与发展中心 | Rail carrier gas dynamic test device |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113335558A (en) * | 2021-05-28 | 2021-09-03 | 合肥飞豪通信科技有限公司 | Remote measurement type small unmanned aerial vehicle wind pressure test system |
| CN113335558B (en) * | 2021-05-28 | 2024-03-19 | 西安宇翼星智能科技有限公司 | Remote-measuring type small unmanned aerial vehicle wind pressure test system |
| CN114152401A (en) * | 2021-11-10 | 2022-03-08 | 中国空气动力研究与发展中心空天技术研究所 | Vehicle-mounted pneumatic test device |
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