CN205469873U - A device for testing small -size unmanned vehicles take -off speed - Google Patents
A device for testing small -size unmanned vehicles take -off speed Download PDFInfo
- Publication number
- CN205469873U CN205469873U CN201620030842.6U CN201620030842U CN205469873U CN 205469873 U CN205469873 U CN 205469873U CN 201620030842 U CN201620030842 U CN 201620030842U CN 205469873 U CN205469873 U CN 205469873U
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- optical axis
- pressure sensor
- speed
- sensor platform
- main shaft
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- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The utility model belongs to a take off data experiment of aircraft lift testing arrangement, the small -size unmanned vehicles of in particular to. A device for testing small -size unmanned vehicles take -off speed, its technical scheme is: it includes: main shaft (1), backup pad (2), optical axis fixing base (3), footstep bearing (4), pressure sensor platform (6) are drawn in GPS module (5), main shaft fixing base (7), optical axis (8), limiting plate (9), the utility model discloses have less volume, the cost is lower, and portable can be used to the test of the minimum lift of unmanned vehicles, for confirming that unmanned aerial vehicle take -off speed provides important experimental data.
Description
Technical field
This utility model belongs to a kind of aircraft lift test device, tests particularly to small-sized unmanned aircraft takeoff data.
Background technology
The mode of taking off of existing small-sized unmanned aircraft mainly has hand throwing type, ejection type, vehicular.Hand throwing type is mainly used in quality
The lightest, to lift requirement than relatively low unmanned vehicle；Relatively big for quality, takeoff speed is required, and higher nobody flies
Row device, generally uses ejection type and vehicular.To small-sized unmanned aircraft, determine that suitable takeoff speed has a following two mode:
1, Engineering Simulation calculates.This mode is quickly succinct, but precision is poor；2, wind tunnel test.This mode can obtain relatively
Accurate lift, resistance coefficient, but experimentation cost is higher.For using dolly takeoff mode small-sized unmanned aircraft, at present
Lift suffered by aircraft under friction speed is not tested and record by apparatus and method, thus cannot determine and suitably take off
Speed.
Summary of the invention
The purpose of this utility model is: provides a kind of for dolly takeoff SUAV, measures the test of lift under friction speed
Device.
The technical solution of the utility model is: a kind of device for testing small-sized unmanned aircraft takeoff speed, and it includes: main
Axle, gripper shoe, optical axis fixes seat, thrust bearing, GPS module, pull pressure sensor platform, and seat fixed by main shaft, optical axis,
Limiting plate；
Main shaft is fixed seat by main shaft and is fixed on gripper shoe center, is used for carrying tested small-sized unmanned aircraft；
Optical axis lower end is provided with limiting plate, and upper end is fixed seat by optical axis and is connected with fixing bottom gripper shoe, and optical axis passes through thrust bearing
Slide axially；
Thrust bearing is arranged on pull pressure sensor platform, and the stress of optical axis is passed to pull pressure sensor platform；
GPS module is for experiencing the movement velocity of pull pressure sensor platform；
Pull pressure sensor platform is fixed on vehicle or other motion carriers, when vehicle or other motion carrier movement velocitys increase
Time, the lift acted on tested small-sized unmanned aircraft increases therewith, and the power that optical axis is downwardly applied to reduces therewith, pressure
Pressure data are experienced and recorded to sensor platform, GPS module writing speed data simultaneously, comprehensive analysis pressure data and speed
Degrees of data, draws the relation of tested small-sized unmanned aircraft lift and speed.
Beneficial effect: this utility model has less volume, cost is relatively low, it is simple to carry, and can be used for the minimum liter of unmanned vehicle
The test of power, for determining that unmanned plane takeoff speed provides important experimental data.
Accompanying drawing explanation
Fig. 1 is this utility model structural representation；
Fig. 2 is this utility model perspective view；
Fig. 3 is that this utility model uses view.
Detailed description of the invention
Develop simultaneously embodiment below in conjunction with the accompanying drawings, is described in detail this utility model.
See accompanying drawing, a kind of device for testing small-sized unmanned aircraft takeoff speed, it includes: main shaft 1, gripper shoe 2,
Optical axis fixes seat 3, thrust bearing 4, GPS module 5, pull pressure sensor platform 6, and seat 7 fixed by main shaft, and optical axis 8 is spacing
Plate 9；
Main shaft 1 is fixed seat 7 by main shaft and is fixed on gripper shoe 2 center, is used for carrying tested small-sized unmanned aircraft；
Optical axis 8 lower end is provided with limiting plate 9, and upper end is fixed seat 3 by optical axis and is connected with fixing bottom gripper shoe 2, and optical axis 8 leads to
Cross thrust bearing 4 to slide axially；
Thrust bearing 4 is arranged on pull pressure sensor platform 6, and the stress of optical axis 8 is passed to pull pressure sensor platform 6；
GPS module 5 is for experiencing the movement velocity of pull pressure sensor platform 6；
Pull pressure sensor platform 6 is fixed on vehicle or other motion carriers, when vehicle or other motion carrier movement velocitys increase
Added-time, the lift acted on tested small-sized unmanned aircraft increases therewith, and the power that optical axis 8 is downwardly applied to reduces therewith, draws
Pressure data are experienced and recorded to pressure transducer platform 6, GPS module 5 writing speed data simultaneously, comprehensively analyzes pressure
Data and speed data, draw the relation of tested small-sized unmanned aircraft lift and speed.
In sum, these are only preferred embodiment of the present utility model, be not intended to limit protection model of the present utility model
Enclose.All within spirit of the present utility model and principle, any modification, equivalent substitution and improvement etc. made, should be included in
Within protection domain of the present utility model.
Claims (1)
1. for testing a device for small-sized unmanned aircraft takeoff speed, it is characterized in that: it includes: main shaft (1), support
Plate (2), optical axis fixes seat (3), thrust bearing (4), GPS module (5), and pull pressure sensor platform (6), main shaft is solid
Reservation (7), optical axis (8), limiting plate (9)；
Described main shaft (1) is fixed seat (7) by described main shaft and is fixed on described gripper shoe (2) center, is used for carrying tested
Small-sized unmanned aircraft；
Described optical axis (8) lower end is provided with described limiting plate (9), and seat (3) and described gripper shoe are fixed by described optical axis in upper end
(2) bottom is fixing connects, and described optical axis (8) is slid axially by described thrust bearing (4)；
Described thrust bearing (4) is arranged on described pull pressure sensor platform (6), the stress of described optical axis (8) is transmitted
To described pull pressure sensor platform (6)；
Described GPS module (5) is used for experiencing the movement velocity of described pull pressure sensor platform (6)；
Described pull pressure sensor platform (6) is fixed on vehicle or other motion carriers, when vehicle or other motion carriers move
When speed increases, the lift acted on tested small-sized unmanned aircraft increases therewith, the power that described optical axis (8) is downwardly applied to
Reducing therewith, pressure data are experienced and recorded to described pull pressure sensor platform (6), and described GPS module (5) is remembered simultaneously
Record speed data, comprehensive analyzes described pressure data and described speed data, draw tested small-sized unmanned aircraft lift with
The relation of speed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620030842.6U CN205469873U (en) | 2016-01-13 | 2016-01-13 | A device for testing small -size unmanned vehicles take -off speed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620030842.6U CN205469873U (en) | 2016-01-13 | 2016-01-13 | A device for testing small -size unmanned vehicles take -off speed |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205469873U true CN205469873U (en) | 2016-08-17 |
Family
ID=56668456
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620030842.6U Expired - Fee Related CN205469873U (en) | 2016-01-13 | 2016-01-13 | A device for testing small -size unmanned vehicles take -off speed |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205469873U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828971A (en) * | 2016-12-13 | 2017-06-13 | 南昌航空大学 | A kind of experimental provision for measuring single duct and single duct aircraft lift |
| CN108639377A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of aircraft lift test device and method |
| CN109094816A (en) * | 2018-07-30 | 2018-12-28 | 成都飞机工业（集团）有限责任公司 | A method of test aircraft aerodynamic lift |
| CN109229421A (en) * | 2018-09-25 | 2019-01-18 | 昆明理工大学 | A kind of unmanned plane power performance test macro and method |
| CN111688951A (en) * | 2020-06-30 | 2020-09-22 | 中国空气动力研究与发展中心 | Multifunctional unmanned aerial vehicle lift force measuring device |
| CN108639377B (en) * | 2018-06-29 | 2024-06-04 | 长沙市云智航科技有限公司 | Device and method for testing lift force of aircraft |
-
2016
- 2016-01-13 CN CN201620030842.6U patent/CN205469873U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828971A (en) * | 2016-12-13 | 2017-06-13 | 南昌航空大学 | A kind of experimental provision for measuring single duct and single duct aircraft lift |
| CN106828971B (en) * | 2016-12-13 | 2019-04-02 | 南昌航空大学 | A kind of experimental provision measuring single duct and single duct aircraft lift |
| CN108639377A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of aircraft lift test device and method |
| CN108639377B (en) * | 2018-06-29 | 2024-06-04 | 长沙市云智航科技有限公司 | Device and method for testing lift force of aircraft |
| CN109094816A (en) * | 2018-07-30 | 2018-12-28 | 成都飞机工业（集团）有限责任公司 | A method of test aircraft aerodynamic lift |
| CN109094816B (en) * | 2018-07-30 | 2022-01-25 | 成都飞机工业（集团）有限责任公司 | Method for testing aerodynamic lift of airplane |
| CN109229421A (en) * | 2018-09-25 | 2019-01-18 | 昆明理工大学 | A kind of unmanned plane power performance test macro and method |
| CN109229421B (en) * | 2018-09-25 | 2023-09-26 | 昆明理工大学 | Unmanned aerial vehicle power performance test system and method |
| CN111688951A (en) * | 2020-06-30 | 2020-09-22 | 中国空气动力研究与发展中心 | Multifunctional unmanned aerial vehicle lift force measuring device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160817 Termination date: 20180113 |