CN114152401A - Vehicle-mounted pneumatic test device - Google Patents
Vehicle-mounted pneumatic test device Download PDFInfo
- Publication number
- CN114152401A CN114152401A CN202111326208.9A CN202111326208A CN114152401A CN 114152401 A CN114152401 A CN 114152401A CN 202111326208 A CN202111326208 A CN 202111326208A CN 114152401 A CN114152401 A CN 114152401A
- Authority
- CN
- China
- Prior art keywords
- test
- vehicle body
- vehicle
- data
- module
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 71
- 238000012545 processing Methods 0.000 claims abstract description 13
- 238000002955 isolation Methods 0.000 claims abstract description 10
- 238000013016 damping Methods 0.000 claims description 5
- 230000008447 perception Effects 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 5
- 238000013461 design Methods 0.000 abstract description 2
- 238000011161 development Methods 0.000 description 4
- 208000027418 Wounds and injury Diseases 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 208000014674 injury Diseases 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012857 repacking Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a vehicle-mounted pneumatic test device, and particularly relates to the technical field of aircraft pneumatic tests. The device comprises a test vehicle body, a rubber vibration isolation platform is arranged on the test vehicle body, a six-component force measuring balance is fixedly connected to the rubber vibration isolation platform, a three-degree-of-freedom supporting device is arranged at the top of the six-component force measuring balance, an aircraft model is installed on the three-degree-of-freedom supporting device, an environment sensing system is further arranged in the moving direction of the aircraft model, a data acquisition and storage module and a data processing module are arranged, the environment sensing system comprises an image acquisition module, an anemorumbometer, a GPS and a barometer, and the data acquisition and storage module is used for acquiring and storing relevant data obtained by the image acquisition module, the anemorumbometer, the GPS and the barometer. By adopting the technical scheme, the problem that no low-cost test device aiming at the low-speed aircraft pneumatic test exists at present is solved, and the method can be used for the test design of the low-speed aircraft.
Description
Technical Field
The invention relates to the technical field of aircraft pneumatic tests, in particular to a vehicle-mounted 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 a rotor unmanned aerial vehicle, a low-speed fixed wing unmanned aerial vehicle and a tilt wing unmanned aerial vehicle become hotspots for civil and military field research, but the number of special wind tunnels for pneumatic tests of the low-speed aircrafts such as the rotor unmanned aerial vehicle is small at present, and the construction and running cost of wind tunnel equipment are higher, so that the development of the aircrafts is greatly limited. Therefore, the low-cost test device for the aerodynamic test of the low-speed aircraft has great market prospect.
Disclosure of Invention
The invention aims to provide a vehicle-mounted pneumatic test device, and solves the problem that no low-cost test device for a low-speed aircraft pneumatic test exists at present.
In order to achieve the purpose, the technical scheme of the invention is as follows: a vehicle-mounted pneumatic test device comprises a test vehicle body, wherein a rubber vibration isolation platform is arranged on the test vehicle body, a six-component force measuring balance is fixedly connected onto the rubber vibration isolation platform, a three-degree-of-freedom supporting device capable of providing three-direction freedom degrees for an aircraft model is arranged at the top of the six-component force measuring balance, the aircraft model is installed on the three-degree-of-freedom supporting device, an environment sensing system, a data acquisition and storage module and a data processing module are further arranged on the aircraft model in the moving direction, the environment sensing system comprises an image acquisition module for identifying the surrounding environment, an air speed and wind direction sensor for measuring wind field data, a GPS and a barometer for determining the current position information, the data acquisition and storage module is used for acquiring and storing relevant data obtained by the image acquisition module, the air speed and wind direction sensor, the GPS and the barometer, the data processing module is used for analyzing and processing the data collected and stored in the data collecting and storing module.
Furthermore, a streamline balancing weight is installed on the three-degree-of-freedom supporting device.
Through the arrangement, the three-degree-of-freedom supporting device can be balanced by utilizing the streamline-shaped balancing weight, and the reliability of the scheme is enhanced.
Furthermore, the test vehicle body is provided with airflow damping equipment positioned in the motion direction of the aircraft model.
Through the arrangement, parameters such as turbulence degree and uniformity of incoming flow are adjusted, and the air flow parameters meet the requirements of tests.
Furthermore, an automatic driving system is installed on the test vehicle body.
Through the arrangement, the test path and speed can be planned in advance, and the risk of injury of a driver is avoided at a high running speed.
Further, the test vehicle body adopts a gasoline vehicle or a new energy vehicle.
Compared with the prior art, the beneficial effect of this scheme:
1. according to the scheme, the horizontal movement of the test vehicle body generates the airflow to carry out the test, the transformation and running cost of the test vehicle body is lower, and the development of the test is facilitated.
2. The scheme has extremely low requirement on a test site, and only needs to run on an outdoor flat road or on an open ground, so that the limitation of test conditions is greatly reduced. Meanwhile, the scheme is not limited by meteorological conditions, and test data closer to actual conditions can be obtained when the system is operated outdoors.
3. The test vehicle body of the scheme can adopt two power forms, the existing vehicle driving technology can be referenced no matter the test vehicle body adopts oil engine driving or motor driving, and the transformation difficulty is small. According to different requirements, different power forms can be adopted, and when the motor is adopted for driving, the test vehicle body has faster response and is more environment-friendly; when the piston engine is adopted for driving, larger acceleration can be obtained, and the running distance of the test vehicle body is reduced.
4. This scheme adopts two kinds of driving methods, and the user can select driving method through needs. The manned driving mode is adopted, the driving system is low in modification cost, and the prior art can be fully utilized; by adopting an unmanned mode, a test path and speed can be planned in advance, and the risk of injury of a driver is avoided at a higher running speed.
5. The aircraft model of this scheme adopts the branch that has released three rotational degrees of freedom to support, can wind triaxial free rotation, compares the model attitude control equipment of the load of operation in the wind-tunnel, more approaches true flight situation.
Drawings
Fig. 1 is a schematic structural view of a vehicle-mounted pneumatic test apparatus according to embodiment 1.
Detailed Description
The present invention will be described in further detail below by way of specific embodiments:
reference numerals in the drawings of the specification include: the test vehicle comprises a test vehicle body 1, a rubber vibration isolation platform 2, a six-component force measuring balance 3, a three-degree-of-freedom supporting device 4, a streamline balancing weight 5, an aircraft model 6, an environment sensing system 7 and an airflow damping device 8.
Example 1
As shown in figure 1: the utility model provides a vehicle-mounted pneumatic test device, includes test automobile body 1, and test automobile body 1 adopts the ordinary freight train repacking of carrying gasoline engine among the prior art to form in this embodiment. The rubber vibration isolation platform 2 is installed on the test vehicle body 1, and the vibration force between the test vehicle body 1 and the three-degree-of-freedom supporting device 4 is relieved by the rubber vibration isolation platform 2. The rubber vibration isolation platform 2 is fixedly connected with a six-component force measuring balance 3, and the six-division force measuring balance adopts a six-division box type force measuring balance and can measure three axial forces and three moments rotating around a shaft. Meanwhile, the six-graduation force measuring balance has high rigidity, thorough mechanical decomposition of force and moment and small mutual interference. The top of the six-component force measuring balance 3 is provided with a three-degree-of-freedom supporting device 4, the three-degree-of-freedom supporting device 4 is composed of a supporting rod front section, a supporting rod middle section, a supporting rod rear section and a universal hinge, and the supporting rod front section is connected to the belly of the aircraft model 6 through the universal hinge. The front section of the supporting rod is hinged with the middle section of the supporting rod, the middle section of the supporting rod is provided with a streamline balancing weight 5, and the balance of the three-degree-of-freedom supporting device 4 is kept by means of the streamline balancing weight 5. The rear section of the supporting rod is hinged on the test vehicle body 1. The three-freedom-degree supporting device 4 can be used for realizing the rotation of the aircraft model 6 in three axes of pitching, rolling and yawing.
The universal hinge is provided with an aircraft model 6, if the size of the aircraft model 6 is smaller, a full-size model is adopted, and if the size of the aircraft model 6 is overlarge, a scaling model is adopted. The present embodiment is operated in an open field outside, and when the size of the aircraft model 6 is within 6m (height) × 4m (width) × 3m (length), a full-size model can be adopted, and when the size exceeds the range, a scaling model is adopted. An environment sensing system 7, a data acquisition and storage module and a data processing module which are arranged on the test vehicle body 1 are also arranged right ahead of the right side of the aircraft model 6. The environment sensing system 7 comprises an image acquisition module for identifying the surrounding environment, a wind speed and direction sensor for measuring wind field data, a GPS and a barometer for determining the current position information, wherein the image acquisition module adopts a camera. The data acquisition and storage module is used for acquiring and storing relevant data obtained by the image acquisition module, the wind speed and direction sensor, the GPS and the barometer, the data acquisition and storage module adopts a memory, and the data acquisition and storage module is respectively and electrically connected with the image acquisition module, the wind speed and direction sensor, the GPS and the barometer. The data processing module is used for analyzing and processing the data acquired and stored in the data acquisition and storage module, and the data processing module adopts a singlechip. The data processing module is also electrically connected with an inertial navigation system.
The working process of the scheme is as follows:
the scheme utilizes the carried image acquisition module to carry out environment shooting to form an environment detection image; measuring the wind speed and the wind direction of the unmanned aerial vehicle model in the environment by using the carried wind speed and wind direction sensor; and the position and the posture of the unmanned aerial vehicle are judged by utilizing a GPS, a barometer, an inertial navigation system and the like. The test vehicle body 1 is also provided with an airflow damping device 8 positioned in the motion direction of the aircraft model 6, and the airflow damping device 8 is used for adjusting parameters such as turbulence degree and uniformity of incoming flow, so that the airflow parameters meet the test requirements.
When the test device works, whether each part in the test device is in a good running state or not is firstly calibrated, then a test route and a task are planned, then the test vehicle body 1 is started, the test vehicle body runs according to a preset task route and speed, data generated in the process are stored in the data acquisition and storage module, the test is finished, and the data are extracted and analyzed by the data processing module.
Example 2
This example differs from example 1 only in that: the test vehicle body 1 of the embodiment is formed by refitting a new energy automobile.
Example 3
This example differs from example 1 only in that: the test vehicle body 1 of the present embodiment is provided with an automatic driving system of an automobile, thereby realizing unmanned driving of the test vehicle body 1.
The foregoing are merely examples of the present invention and common general knowledge of known specific structures and/or features of the schemes has not been described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (5)
1. The utility model provides a vehicle-mounted pneumatic test device which characterized in that: comprises a test vehicle body, wherein a rubber vibration isolation platform is arranged on the test vehicle body, a six-component force measuring balance is fixedly connected to the rubber vibration isolation platform, the top of the six-component force measuring balance is provided with a three-degree-of-freedom supporting device which can provide three-direction freedom degrees for the aircraft model, the three-degree-of-freedom supporting device is provided with an aircraft model, an environment sensing system, a data acquisition and storage module and a data processing module which are arranged on a test vehicle body are further arranged in the moving direction of the aircraft model, the environment perception system comprises an image acquisition module for identifying surrounding environment, a wind speed and direction sensor for measuring wind field data, a GPS and a barometer for determining current position information, the data acquisition and storage module is used for acquiring and storing relevant data obtained by the image acquisition module, the wind speed and direction sensor, the GPS and the barometer, the data processing module is used for analyzing and processing the data collected and stored in the data collecting and storing module.
2. A vehicle pneumatic test apparatus according to claim 1, wherein: and a streamline-shaped balancing weight is arranged on the three-degree-of-freedom supporting device.
3. A vehicle pneumatic test apparatus according to claim 1, wherein: and the test vehicle body is provided with airflow damping equipment positioned in the motion direction of the aircraft model.
4. A vehicle pneumatic test apparatus according to claim 1, wherein: and an automatic driving system is arranged on the test vehicle body.
5. A vehicle pneumatic test apparatus according to any one of claims 1 to 4, wherein: the test vehicle body adopts a gasoline vehicle or a new energy vehicle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111326208.9A CN114152401A (en) | 2021-11-10 | 2021-11-10 | Vehicle-mounted pneumatic test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111326208.9A CN114152401A (en) | 2021-11-10 | 2021-11-10 | Vehicle-mounted pneumatic test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114152401A true CN114152401A (en) | 2022-03-08 |
Family
ID=80459913
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111326208.9A Pending CN114152401A (en) | 2021-11-10 | 2021-11-10 | Vehicle-mounted pneumatic test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114152401A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117686176A (en) * | 2024-02-04 | 2024-03-12 | 中国空气动力研究与发展中心高速空气动力研究所 | Temporary flushing supersonic wind tunnel flutter test device and method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2017132461A (en) * | 2016-01-25 | 2017-08-03 | 大分県 | Unmanned flying body characteristic measurement device and unmanned flying body evaluation system using the same |
| CN109307581A (en) * | 2018-12-06 | 2019-02-05 | 中国科学院工程热物理研究所 | The vehicle-mounted wind tunnel system of unmanned plane |
| 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 |
| CN111688950A (en) * | 2020-06-29 | 2020-09-22 | 中国空气动力研究与发展中心 | Rail carrier gas dynamic test device |
-
2021
- 2021-11-10 CN CN202111326208.9A patent/CN114152401A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2017132461A (en) * | 2016-01-25 | 2017-08-03 | 大分県 | Unmanned flying body characteristic measurement device and unmanned flying body evaluation system using the same |
| 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 |
| CN109307581A (en) * | 2018-12-06 | 2019-02-05 | 中国科学院工程热物理研究所 | The vehicle-mounted wind tunnel system of unmanned plane |
| CN111688950A (en) * | 2020-06-29 | 2020-09-22 | 中国空气动力研究与发展中心 | Rail carrier gas dynamic test device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117686176A (en) * | 2024-02-04 | 2024-03-12 | 中国空气动力研究与发展中心高速空气动力研究所 | Temporary flushing supersonic wind tunnel flutter test device and method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108645425B (en) | Small-size rotor unmanned aerial vehicle gyroscope structure test system based on six-dimensional force sensor | |
| Pounds et al. | Design of a four-rotor aerial robot | |
| CN102180270B (en) | Microminiature rotorcraft experiment platform and application thereof | |
| CN106882341B (en) | A kind of Self-Balancing vehicle device waterborne | |
| CN203365672U (en) | A millimeter wave radar test system | |
| CN110488863A (en) | Air-ground amphibious unmanned platform | |
| CN103144770A (en) | Full-automatic indoor environment control, obstacle avoidance and navigation type micro aerial vehicle | |
| CN109606732B (en) | Efficient airplane quality characteristic measuring method | |
| CN112357078B (en) | Method for carrying out patrol operation in abnormal seepage area of earth-rock dam by unmanned aerial vehicle | |
| CN205899386U (en) | Flight of many rotor unmanned aerial vehicle is with external safety control and system | |
| CN107101636B (en) | A method of more rotor dynamics model parameters are recognized using Kalman filter | |
| CN109573097B (en) | Vehicle-mounted test method and system for aerodynamic parameters of low-speed aircraft | |
| CN112986612B (en) | Low-altitude movable wind speed measurement method based on four-rotor unmanned aerial vehicle | |
| CN108225809B (en) | Ground test system for flight performance of unmanned aerial vehicle | |
| US4862739A (en) | Wind tunnel model support mechanism | |
| CN107472554A (en) | A kind of unmanned plane vehicle-mounted pneumatic force test system | |
| CN109850173B (en) | Multifunctional vehicle-mounted mode platform device based on six-degree-of-freedom parallel posture adjusting mechanism | |
| CN108163229A (en) | Flapping wing robot lift thrust detecting system synchronous with wing movable information and method | |
| CN111137082A (en) | Single-duct land air cross-domain robot and control method thereof | |
| CN114152401A (en) | Vehicle-mounted pneumatic test device | |
| JP2017007603A (en) | Operation support controlling apparatus | |
| US10883852B1 (en) | Simulating inertial motion using true inertial motion | |
| CN109823566A (en) | A kind of vertically taking off and landing flyer flight control system test platform | |
| CN213323763U (en) | Rail carrier gas dynamic test device | |
| Papa et al. | Conceptual design of a small hybrid unmanned aircraft system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |