CN106679930B - Vehicle-mounted small unmanned plane aerodynamic force and Dynamic Characteristics Test measurement method and device - Google Patents
Vehicle-mounted small unmanned plane aerodynamic force and Dynamic Characteristics Test measurement method and device Download PDFInfo
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- CN106679930B CN106679930B CN201611111940.3A CN201611111940A CN106679930B CN 106679930 B CN106679930 B CN 106679930B CN 201611111940 A CN201611111940 A CN 201611111940A CN 106679930 B CN106679930 B CN 106679930B
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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Abstract
The present invention relates to vehicle-mounted small unmanned plane aerodynamic force and Dynamic Characteristics Test measurement method and device, three-legged support (2) is fixed on movable pulley vehicle (1), can on vehicle (16) shift position and locking；One level of support arm (4) is connected on three-legged support (2) by level-one machinery holder (3)；Level-one machinery holder (3) can manually adjust azimuth and pitch angle and locking；Second level support arm (7) is connected to one level of support arm (4) front end by secondary mechanical holder (6)；Balance strut (12) is connected to second level support arm (7) front end by gimbal suspension (11)；Band weathercock pitot (15) is arranged on tested unmanned plane；Level-one machinery holder (3) and secondary mechanical holder (6) and vehicle (16) are tensed using bracing cable (17), assisted test measurement device is fixed.The present invention directly uses small drone as measurand, and experimentation cost is low, and it is short to shorten the test period, improves test efficiency.
Description
Technical field
The present invention relates to small drone aerodynamic test technical fields.
Background technique
The test measurement of aerodynamic characteristics and dynamic characteristics be unmanned plane research and development element task, be collectivity Scheme Design,
Aerodynamic arrangement's type selecting, flight performance optimization and automatic flight control provide test data.
Traditionally aerodynamic characteristics test measurement and Dynamic Characteristics Test measurement carry out respectively.Aerodynamic characteristics test measurement
The air-flow that movement is generated using wind-tunnel is allowed to flow around test model, by measuring the stress of test model, can be obtained gas
Dynamic lift, resistance, side force and rolling moment, pitching moment, yawing data.But wind tunnel test measurement is born by special unit
Duty needs to follow tunnel size requirement and manufactures and designs Special test model, and constraint is more, and the preparatory period is long, and experimentation cost is high,
For requiring small drone R&D work that is flexible, quick and being realized with a low cost and being not suitable for.Small drone mostly uses spiral shell
Paddle power is revolved, dynamic characteristics changes with speed of incoming flow and working depth, and Dynamic Characteristics Test measurement needs to carry out propeller spy
Property wind tunnel test, the test of engine characteristics HIGHER ALTITUDE TEST FACILITY and paddle send out match test, equally face constraint more, period length and at high cost
Problem.
Summary of the invention
The purpose of the present invention is: it proposes a kind of test measurement device, in the case where not using wind-tunnel and HIGHER ALTITUDE TEST FACILITY, measures
The aerodynamic force and dynamic characteristics data of small drone shorten the test period to enhance test flexibility, reduce test at
This, improves test efficiency, adapts to small drone research and development and requires.
The technical scheme is that 1, vehicle-mounted small unmanned plane aerodynamic force and Dynamic Characteristics Test measuring device,
Be characterized in that: test measurement device includes movable pulley vehicle 1, three-legged support 2, level-one machinery holder 3, one level of support arm 4, second level machine
Tool holder 6, second level support arm 7, electronic rotation actuator 9, electric linear actuator 10, gimbal suspension 11, balance strut 12, six
COMPONENT BALANCE 13, band weathercock pitot 15；The three-legged support 2 of test measurement device is fixed on movable pulley vehicle 1, can be in vehicle 16
Upper shift position and locking；One level of support arm 4 is connected on three-legged support 2 by level-one machinery holder 3；Level-one machinery holder 3
Azimuth and pitch angle and locking can be manually adjusted；Second level support arm 7 is connected to one level of support arm by secondary mechanical holder 6
4 front ends；The azimuth of secondary mechanical holder 6 and pitch angle are adjustable, and azimuthal adjustment is by being mounted on 6 lower part of secondary mechanical holder
Electronic rotation actuator 9 drive, the adjustment of pitch angle is electronic between second level support arm 7 and grade machinery holder 6 by being mounted on
Linear actuator 10 drives；Balance strut 12 is connected to 7 front end of second level support arm by gimbal suspension 11；Gimbal suspension 11 can
Manually adjust pitch angle and roll angle and locking；Six COMPONENT BALANCEs 13 connect tested unmanned plane 14 and balance strut 12, band weathercock
Pitot 15 is arranged on tested unmanned plane；Level-one machinery holder 3 and secondary mechanical holder 6 are drawn with vehicle 16 using bracing cable 17
Tightly, it assists test measurement device is fixed.
The measurement method of the vehicle-mounted small unmanned plane aerodynamic force and Dynamic Characteristics Test measuring device, specific steps
It is as follows:
1) tested unmanned plane is mounted on test measurement device, test measurement device is equipped on vehicle, vehicle is utilized
It advances and to generate the relative motion of tested unmanned plane and air；
2) test measurement device is advanced at different altitude height, with friction speed with vehicle, and not opening, nobody is motor-driven
Aerodynamic characteristics measurement is carried out in the state of power, and dynamic characteristics measurement is carried out in the state of opening unmanned mechanomotive force；
3) one level of support arm 4 is adjusted by level-one machinery holder 3, secondary mechanical holder 6 and gimbal suspension 11 before the test
With the angle and locking of second level support arm 7, tested unmanned plane, which is supported on, pneumatically to be streamed by vehicle itself influences small standard uniformly
Air incoming flow region；
4) test measurement device passes through the pitch angle and azimuth that electric actuator adjusts during the test, makes tested nothing
Man-machine relative atmospheric incoming flow is in the scheduled angle of attack and yaw angle state；
5) three axis force and three-axis force square signal are generated during the test using six COMPONENT BALANCEs 13, use band weathercock air speed
Pipe 15 generates static pressure, air speed, the angle of attack, sideslip angle signal during the test, carries out signal acquisition using capture card 18；
6) signal collected is handled using computer 19 to obtain aerodynamic characteristics tests data, comprising: lift, resistance
Power, side force and yawing, rolling moment, pitching moment and Dynamic Characteristics Test data, comprising: thrust, torque.
The invention has the advantages that the test measurement of aerodynamic characteristics and dynamic characteristics does not use wind-tunnel and HIGHER ALTITUDE TEST FACILITY, test
It is at low cost.It directly uses small drone as measurand, does not need to manufacture and design special model in wind tunnel, shorten
Test period.It is big that experimental rig outside air carrys out fluid space, is not limited by wind-tunnel and HIGHER ALTITUDE TEST FACILITY size, to subject unmanned plane layout
The constraint of form and outer dimension is small, tests strong flexibility.The test measurement of aerodynamic characteristics and dynamic characteristics is in set of device
Upper progress is switched by dynamic regime and completes two class test measurements, improves test efficiency.
Detailed description of the invention
Fig. 1 is test measurement device for mechanical schematic diagram；
Fig. 2 is that figure is carried in the installation of test measurement device；
Fig. 3 is test measurement device signal flow diagram.
Specific embodiment
As shown in Figure 1, test measurement device includes movable pulley vehicle 1, three-legged support 2, level-one machinery holder 3, one level of support
Arm 4, level-one counterweight 5, secondary mechanical holder 6, second level support arm 7, second level counterweight 8, electronic rotation actuator 9, electric linear are made
Dynamic device 10, gimbal suspension 11, balance strut 12, six COMPONENT BALANCEs 13, tested unmanned plane 14, band weathercock pitot 15.
As shown in Fig. 2, tested unmanned plane is mounted on test measurement device, test measurement device is equipped on vehicle 16.
The three-legged support 2 of test measurement device is fixed on movable pulley vehicle 1, can on vehicle 16 shift position and locking.
One level of support arm 4 is connected on three-legged support 2 by level-one machinery holder 3.Level-one machinery holder 3 can manually adjust azimuth
With pitch angle and locking.Second level support arm 7 is connected to 4 front end of one level of support arm by secondary mechanical holder 6.Secondary mechanical holder
6 azimuth and pitch angle are adjustable, azimuthal electronic rotation actuator 9 adjusted by being mounted on 6 lower part of secondary mechanical holder
Driving, the adjustment of pitch angle are driven by the electric linear actuator 10 being mounted between second level support arm 7 and secondary mechanical holder 6
It is dynamic.Balance strut 12 is connected to 7 front end of second level support arm by gimbal suspension 11.Gimbal suspension 11 can manually adjust pitch angle
With roll angle and locking.Six COMPONENT BALANCEs 13 connect tested unmanned plane 14 and balance strut 12, and band weathercock pitot 15 is arranged in
On tested unmanned plane.Level-one machinery holder 3 and secondary mechanical holder 6 are tensed with vehicle 16 using bracing cable 17, auxiliary will test
Measuring device is fixed.
Pitch angle, azimuth and the roll angle of support arm are adjusted by mechanical holder and gimbal suspension before the test and locked
Only, tested unmanned plane is supported on pneumatically to be streamed by vehicle itself and influences small quasi- homogeneous air incoming flow region, including vehicle 16
Left side, right side and front upper place.Test measurement device is advanced at different altitude height, with friction speed straight line with vehicle,
It does not open and carries out aerodynamic characteristics measurement in the state of unmanned mechanomotive force, it is special that power is carried out in the state of opening unmanned mechanomotive force
Property measurement.
As shown in figure 3, six COMPONENT BALANCEs 13 generate three-dimensional force signal during the test, i.e., axial force signal, normal force
Signal, lateral force signal, while generating three-axis force square signal, i.e., longitudinal axis torque signals, horizontal axis torque signals, vertical shaft torque are believed
Number.Band weathercock pitot 15 generates static pressure signal, airspeed signal, angle of attack signal and sideslip angle signal during the test.Acquisition
Signal acquisition is converted into digital quantity by card 18, is handled by computer 19 and is obtained aerodynamic characteristic data, comprising: lift, resistance, side
Power and yawing, rolling moment, pitching moment and dynamic characteristics data, comprising: thrust, torque.
Claims (2)
1. vehicle-mounted small unmanned plane aerodynamic force and Dynamic Characteristics Test measuring device, it is characterised in that: test measurement device packet
Include movable pulley vehicle (1), three-legged support (2), level-one machinery holder (3), one level of support arm (4), secondary mechanical holder (6), second level
Support arm (7), electronic rotation actuator (9), electric linear actuator (10), gimbal suspension (11), balance strut (12), six points
Measure balance (13), band weathercock pitot (15)；The three-legged support (2) of test measurement device is fixed on movable pulley vehicle (1), can be
Shift position and locking on vehicle (16)；One level of support arm (4) is connected on three-legged support (2) by level-one machinery holder (3)；
Level-one machinery holder (3) can manually adjust azimuth and pitch angle and locking；Second level support arm (7) passes through secondary mechanical holder
(6) it is connected to one level of support arm (4) front end；The azimuth of secondary mechanical holder (6) and pitch angle are adjustable, it is azimuthal adjustment by
It is mounted on electronic rotation actuator (9) driving of secondary mechanical holder (6) lower part, the adjustment of pitch angle is by being mounted on second level support
Electric linear actuator (10) driving between arm (7) and secondary mechanical holder (6)；Balance strut (12) passes through gimbal suspension
(11) it is connected to second level support arm (7) front end；Gimbal suspension (11) can manually adjust pitch angle and roll angle and locking；Six points
It measures balance (13) and connects tested unmanned plane (14) and balance strut (12), band weathercock pitot (15) is arranged in tested unmanned plane
On；Level-one machinery holder (3) and secondary mechanical holder (6) and vehicle (16) are tensed using bracing cable (17), auxiliary surveys test
It is fixed to measure device.
2. the measurement side of vehicle-mounted small unmanned plane aerodynamic force and Dynamic Characteristics Test measuring device as described in claim 1
Method, which is characterized in that specific step is as follows:
(1) tested unmanned plane is mounted on test measurement device, test measurement device is equipped on vehicle (16), vehicle is utilized
It advances and to generate the relative motion of tested unmanned plane and air；
(2) test measurement device is advanced at different altitude height, with friction speed with vehicle (16), and not opening, nobody is motor-driven
Aerodynamic characteristics measurement is carried out in the state of power, and dynamic characteristics measurement is carried out in the state of opening unmanned mechanomotive force；
(3) one level of support is adjusted by level-one machinery holder (3), secondary mechanical holder (6) and gimbal suspension (11) before the test
The angle of arm (4) and second level support arm (7) and locking, tested unmanned plane is supported on and itself is pneumatically streamed influence by vehicle (16)
Small quasi- homogeneous air incoming flow region；
(4) test measurement device is adjusted during the test by electronic rotation actuator (9) and electric linear actuator (10)
Pitch angle and azimuth make tested unmanned plane relative atmospheric incoming flow be in the scheduled angle of attack and yaw angle state；
(5) three axis force and three-axis force square signal are generated during the test using six COMPONENT BALANCEs (13), use band weathercock air speed
It manages (15) and generates static pressure, air speed, the angle of attack, sideslip angle signal during the test, carry out signal acquisition using capture card (18)；
(6) signal collected is handled using computer to obtain aerodynamic characteristics tests data, comprising: lift, resistance, side
Power and yawing, rolling moment, pitching moment and Dynamic Characteristics Test data, comprising: thrust, torque.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107472554A (en) * | 2017-07-31 | 2017-12-15 | 中国航空工业集团公司西安飞机设计研究所 | A kind of unmanned plane vehicle-mounted pneumatic force test system |
| CN107588922A (en) * | 2017-08-31 | 2018-01-16 | 北京电子工程总体研究所 | The analogue measurement device of the direction aerodynamic force of unmanned plane three and three direction aerodynamic moments |
| CN109573097B (en) * | 2018-11-13 | 2021-02-09 | 中国航天空气动力技术研究院 | Vehicle-mounted test method and system for aerodynamic parameters of low-speed aircraft |
| 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 |
| CN109883642B (en) * | 2018-12-21 | 2021-03-26 | 中国航天空气动力技术研究院 | Vehicle-mounted force measuring system of low-speed aircraft |
| CN111006844B (en) * | 2019-12-25 | 2021-10-15 | 中国航空工业集团公司西安飞机设计研究所 | Tension wire resistance measuring device |
| 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 |
| CN114111700B (en) * | 2021-11-23 | 2023-07-04 | 江苏徐工工程机械研究院有限公司 | Measuring device, engineering machine, measuring method and controller |
| CN114516428B (en) * | 2022-03-07 | 2024-06-14 | 重庆大学 | Test method and device for matching design of light aircraft engine |
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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 |
| CN2869834Y (en) * | 2005-12-26 | 2007-02-14 | 黄野 | Air power experiment cantilever rotary table |
| CN201575932U (en) * | 2009-12-29 | 2010-09-08 | 贵州贵航无人机有限责任公司 | General simulation test device with real pilotless system |
| CN102507128B (en) * | 2011-09-29 | 2014-12-24 | 中国航天空气动力技术研究院 | Prediction method of dynamic aerodynamic characteristics of morphing aircraft |
| CN102519701B (en) * | 2011-12-06 | 2014-12-17 | 北京航空航天大学 | Vehicle-mounted aeroelastic test platform system |
| CN104990719B (en) * | 2015-07-08 | 2018-04-27 | 国网山东省电力公司电力科学研究院 | A kind of unmanned plane test bench system for being used to examine detection |
| CN205300829U (en) * | 2016-01-13 | 2016-06-08 | 深圳九星智能航空科技有限公司 | Rotor unmanned aerial vehicle's motor impeller device for comprehensive test |
| CN205670022U (en) * | 2016-06-08 | 2016-11-02 | 广东容祺智能科技有限公司 | A kind of unmanned plane dynamical system test platform |
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