CN106679930A - Vehicle-mounted aerodynamic force and power test-measurement method and device of small unmanned aerial vehicle (UAV) - Google Patents
Vehicle-mounted aerodynamic force and power test-measurement method and device of small unmanned aerial vehicle (UAV) Download PDFInfo
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- CN106679930A CN106679930A CN201611111940.3A CN201611111940A CN106679930A CN 106679930 A CN106679930 A CN 106679930A CN 201611111940 A CN201611111940 A CN 201611111940A CN 106679930 A CN106679930 A CN 106679930A
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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 invention relates to a vehicle-mounted aerodynamic force and power characteristic test-measurement method and device of a small UAV. A three-foot support (2) is fixed on a wheeled trolley (1), and can move on a vehicle (16) and be locked; a primary support arm (4) is connected to the three-foot support (2) via a primary mechanical holder (3); the primary mechanical holder (3) can adjust the azimuth and pitch angle manually and be locked; a secondary support arm (7) is connected to the front end of the primary support arm (4) via a secondary mechanical holder (6); a balance pole (12) is connected to the front end of the secondary support arm (7) via a universal joint (11); a pitot (15) with a weathercock is arranged on the measured UAV; and tension wires (17) are used to tension the primary mechanical holder (3) and the secondary mechanical holder (6) are tensioned relative to the vehicle (16) to help fix the test-measurement device firmly. According to the invention, the small UAV is tested and measured directly, the test cost is low, the test period is shortened, and the test efficiency is improved.
Description
Technical field
The present invention relates to SUAV aerodynamic test technical field.
Background technology
The test measurement of aerodynamic characteristics and dynamic trait be unmanned plane research and development element task, be collectivity Scheme Design,
Aerodynamic arrangement's type selecting, flight performance optimization and control of flying automatically provide test data.
Traditionally aerodynamic characteristics test measurement and Dynamic Characteristics Test measurement is carried out respectively.Aerodynamic characteristics test measurement
The air-flow of motion is produced using wind-tunnel, is allowed to flow around test model, by the stress of experiment with measuring model, you can obtain 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 SUAV R＆D work that is flexible, quick and being realized with a low cost and not applying to.Spiral shell is adopted SUAV more
Rotation oar power, its dynamic trait change 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 characteristicses HIGHER ALTITUDE TEST FACILITY and oar send out match test, equally face and constrain many, cycle length and high cost
Problem.
The content of the invention
The purpose of the present invention is：A kind of test measurement device is proposed, in the case where wind-tunnel and HIGHER ALTITUDE TEST FACILITY is not used, is measured
The aerodynamic force and dynamic trait data of SUAV, so as to strengthen test motility, shortens the test period, and reduction is tested into
This, improves test efficiency, adapts to SUAV research and development and requires.
The technical scheme is that:1st, vehicle-mounted small unmanned plane aerodynamic force and Dynamic Characteristics Test measurement apparatus, its
It is characterised by：Test measurement device includes movable pulley car 1, three-legged support 2, one-level machinery head 3,4, two grades of machines of one level of support arm
6, two grades of support arms 7 of tool head, electronic rotation actuator 9, electric linear actuator 10, gimbal suspension 11, balance pole 12, six
COMPONENT BALANCE 13, band weathercock pitot 15；The three-legged support 2 of test measurement device is fixed on movable pulley car 1, can be in vehicle 15
Upper shift position locking；One level of support arm 4 is connected on three-legged support 2 by one-level machinery head 3；One-level machinery head 3
Azimuth and the angle of pitch locking can be manually adjusted；Two grades of support arms 7 are connected to one level of support arm by secondary mechanical head 6
4 front ends；The azimuth of secondary mechanical head 6 and the angle of pitch are adjustable, and azimuthal adjustment is by installed in 6 bottom of secondary mechanical head
Electronic rotation actuator 9 drive, the adjustment of the angle of pitch is by electronic between two grades of support arms 7 and level machinery head 6
Linear actuator 10 drives；Balance pole 12 is connected to two grades of 7 front ends of support arm by gimbal suspension 11；Gimbal suspension 11 can
Manually adjust the angle of pitch and roll angle locking；Six COMPONENT BALANCEs 13 connect tested unmanned plane 14 and balance pole 12, band weathercock
Pitot 15 is arranged on tested unmanned plane；One-level machinery head 3 and secondary mechanical head 6 are drawn with vehicle 16 using bracing cable 17
Tightly, auxiliary will be test measurement device fixed.
2nd, the measurement of vehicle-mounted small unmanned plane aerodynamic force as claimed in claim 1 and Dynamic Characteristics Test measurement apparatus
Method, it is characterised in that：Comprise the following steps that：
1) tested unmanned plane is arranged on test measurement device, test measurement device is equipped on vehicle, using car
Advance tested unmanned plane is produced with the relative motion of 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, dynamic trait measurement is carried out in the state of unmanned mechanomotive force is opened；
3) one level of support arm 4 is adjusted by one-level machinery head 3, secondary mechanical head 6 and gimbal suspension 11 before the test
With the angle locking of two grades of support arms 7, tested unmanned plane is supported on is affected little standard uniform by pneumatic the streaming of vehicle itself
Air is flowing region；
4) test measurement device is adjusted in process of the test by electric actuator the angle of pitch and azimuth, make tested nothing
Man-machine relative atmospheric is flowing in the predetermined angle of attack and yaw angle state；
5) three axis force and three-axis force square signal are produced in process of the test using six COMPONENT BALANCEs 13, using band weathercock air speed
Pipe 15 produces static pressure, air speed, the angle of attack, sideslip angle signal in process of the test, carries out signals collecting using capture card 18；
6) process is carried out using 19 pairs of signals for being gathered of computer obtain aerodynamic characteristics tests data, including：Lift, resistance
Power, side force and yawing, rolling moment, pitching moment, and Dynamic Characteristics Test data, including：Thrust, moment of torsion.
It is an advantage of the invention that：The test measurement of aerodynamic characteristics and dynamic trait does not use wind-tunnel and HIGHER ALTITUDE TEST FACILITY, test
Low cost.SUAV is used directly as measurand, it is not necessary to manufacture and design special model in wind tunnel, shorten
Test period.Assay device extraneous air carrys out fluid space greatly, not by wind-tunnel and HIGHER ALTITUDE TEST FACILITY size limitation, to tested unmanned plane layout
The constraint of form and overall dimensions is little, and test motility is strong.The test measurement of aerodynamic characteristics and dynamic trait is in set of device
On carry out, by dynamic regime switching complete two class test measurements, improve test efficiency.
Description of the drawings
Fig. 1 is test measurement device for mechanical schematic diagram；
Fig. 2 is that test measurement device installs carrying figure；
Fig. 3 is test measurement device signal flow diagram.
Specific embodiment
As shown in figure 1, test measurement device includes movable pulley car 1, three-legged support 2, one-level machinery head 3, one level of support
Arm 4, one-level counterweight 5,6, two grades of support arms 7, graduation two of secondary mechanical head weigh 8, electronic rotation actuator 9, electric linear work
Dynamic device 10, gimbal suspension 11, balance pole 12, six COMPONENT BALANCEs 13, tested unmanned plane 14, band weathercock pitot 15.
As shown in Fig. 2 tested unmanned plane is arranged 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 car 1, can on vehicle 15 shift position locking.
One level of support arm 4 is connected on three-legged support 2 by one-level machinery head 3.One-level machinery head 3 can manually adjust azimuth
With the angle of pitch locking.Two grades of support arms 7 are connected to 4 front end of one level of support arm by secondary mechanical head 6.Secondary mechanical head
6 azimuth and the angle of pitch are adjustable, and azimuthal adjustment is by the electronic rotation actuator 9 installed in 6 bottom of secondary mechanical head
Drive, the adjustment of the angle of pitch is driven by the electric linear actuator 10 being arranged between two grades of support arms 7 and secondary mechanical head 6
It is dynamic.Balance pole 12 is connected to two grades of 7 front ends of support arm by gimbal suspension 11.Gimbal suspension 11 can manually adjust the angle of pitch
With roll angle locking.Six COMPONENT BALANCEs 13 connect tested unmanned plane 14 and balance pole 12, and band weathercock pitot 15 is arranged in
On tested unmanned plane.One-level machinery head 3 and secondary mechanical head 6 are tensed with vehicle 16 using bracing cable 17, auxiliary will test
Measurement apparatus are fixed.
The angle of pitch, azimuth and the roll angle of support arm is adjusted by mechanical head and gimbal suspension before the test and is locked
Only, tested unmanned plane is supported on is affected little quasi- homogeneous air to flow region, including vehicle 16 by pneumatic the streaming of vehicle itself
Left side, right side and front upper place.Test measurement device is advanced at different altitude height, with friction speed straight line with vehicle,
Aerodynamic characteristics measurement is carried out in the state of not opening unmanned mechanomotive force, enters action edge in the state of unmanned mechanomotive force is opened special
Property measurement.
As shown in figure 3, six COMPONENT BALANCEs 13 produce three-dimensional force signal in process of the test, i.e., axial force signal, normal force
Signal, lateral force signal, while producing three-axis force square signal, i.e. longitudinal axis torque signals, transverse axis torque signals, vertical shaft torque letter
Number.Band weathercock pitot 15 produces static pressure signal, airspeed signal, angle of attack signal and sideslip angle signal in process of the test.Collection
Signals collecting is converted into digital quantity by card 18, obtains aerodynamic characteristic data by the process of computer 19, including：Lift, resistance, side
Power and yawing, rolling moment, pitching moment, and dynamic trait data, including：Thrust, moment of torsion.
Claims (2)
1. vehicle-mounted small unmanned plane aerodynamic force and Dynamic Characteristics Test measurement apparatus, it is characterised in that：Test measurement device bag
Include movable pulley car (1), three-legged support (2), one-level machinery head (3), one level of support arm (4), secondary mechanical head (6), two grades
Support arm (7), electronic rotation actuator (9), electric linear actuator (10), gimbal suspension (11), balance pole (12), six points
Amount balance (13), band weathercock pitot (15)；The three-legged support (2) of test measurement device is fixed on movable pulley car (1), can be
Shift position locking on vehicle (16)；One level of support arm (4) is connected on three-legged support (2) by one-level machinery head (3)；
One-level machinery head (3) can manually adjust azimuth and the angle of pitch locking；Two grades of support arms (7) are by secondary mechanical head
(6) it is connected to one level of support arm (4) front end；The azimuth of secondary mechanical head (6) and the angle of pitch are adjustable, it is azimuthal adjustment by
Electronic rotation actuator (9) installed in secondary mechanical head (6) bottom drives, and the adjustment of the angle of pitch is by installed in two grades of supports
Electric linear actuator (10) between arm (7) and secondary mechanical head (6) drives；Balance pole (12) is by gimbal suspension
(11) two grades of support arm (7) front ends are connected to；Gimbal suspension (11) can manually adjust the angle of pitch and roll angle locking；Six points
Amount balance (13) connects tested unmanned plane (14) and balance pole (12), and band weathercock pitot (15) is arranged in tested unmanned plane
On；One-level machinery head (3) and secondary mechanical head (6) are tensed with vehicle (16) using bracing cable (17), aid in surveying test
Amount device is fixed.
2. the measurement side of vehicle-mounted small unmanned plane aerodynamic force as claimed in claim 1 and Dynamic Characteristics Test measurement apparatus
Method, it is characterised in that comprise the following steps that：
(1) tested unmanned plane is arranged on test measurement device, test measurement device is equipped on vehicle (16), using car
Advance tested unmanned plane is produced with the relative motion of 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, dynamic trait measurement is carried out in the state of unmanned mechanomotive force is opened；
(3) one level of support is adjusted by one-level machinery head (3), secondary mechanical head (6) and gimbal suspension (11) before the test
The angle of arm (4) and two grades of support arms (7) locking, tested unmanned plane are supported on and streamed impact by vehicle (16) itself is pneumatic
Little quasi- homogeneous air is flowing region；
(4) test measurement device passes through electronic rotation actuator (9) and electric linear actuator (10) is adjusted in process of the test
The angle of pitch and azimuth, make tested unmanned plane relative atmospheric to flow in the predetermined angle of attack and yaw angle state；
(5) three axis force and three-axis force square signal are produced in process of the test using six COMPONENT BALANCEs (13), using band weathercock air speed
Pipe (15) produces static pressure, air speed, the angle of attack, sideslip angle signal in process of the test, carries out signals collecting using capture card (18)；
(6) process is carried out to the signal for being gathered using computer and obtains aerodynamic characteristics tests data, including：Lift, resistance, side
Power and yawing, rolling moment, pitching moment, and Dynamic Characteristics Test data, including：Thrust, moment of torsion.
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN109883642A (en) * | 2018-12-21 | 2019-06-14 | 中国航天空气动力技术研究院 | A kind of vehicle-mounted dynamometric system of low-speed operations device |
| CN111006844A (en) * | 2019-12-25 | 2020-04-14 | 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 |
| CN114111700A (en) * | 2021-11-23 | 2022-03-01 | 江苏徐工工程机械研究院有限公司 | Measuring device, engineering machinery, measuring method and controller |
| CN114516428A (en) * | 2022-03-07 | 2022-05-20 | 重庆大学 | Test method and device for light aircraft engine matching design |
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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 |
| 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 |
| 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 |
| CN109883642A (en) * | 2018-12-21 | 2019-06-14 | 中国航天空气动力技术研究院 | A kind of vehicle-mounted dynamometric system of low-speed operations device |
| CN111006844A (en) * | 2019-12-25 | 2020-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Tension wire resistance measuring device |
| 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 |
| CN114111700A (en) * | 2021-11-23 | 2022-03-01 | 江苏徐工工程机械研究院有限公司 | Measuring device, engineering machinery, measuring method and controller |
| CN114516428A (en) * | 2022-03-07 | 2022-05-20 | 重庆大学 | Test method and device for light aircraft engine matching design |
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