CN207197776U - Coaxial tilting type rotor aeroperformance test platform - Google Patents
Coaxial tilting type rotor aeroperformance test platform Download PDFInfo
- Publication number
- CN207197776U CN207197776U CN201720321816.3U CN201720321816U CN207197776U CN 207197776 U CN207197776 U CN 207197776U CN 201720321816 U CN201720321816 U CN 201720321816U CN 207197776 U CN207197776 U CN 207197776U
- Authority
- CN
- China
- Prior art keywords
- rotor
- microprocessor
- motor
- parameter
- coaxial
- 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.)
- Expired - Fee Related
Links
Abstract
The utility model discloses coaxial tilting type rotor aeroperformance test platform, including parameter automatic regulation system, microprocessor, wireless communication module and computer system.Parameter automatic regulation system includes base, T-shaped support, rotor, motor, electric pushrod, force snesor, support arm, steering wheel and linear electric motors.Computer system gives test parameters, parameter is sent to by microprocessor by wireless communication module, parameter value is transferred to parameter automatic regulation system by microprocessor, according to being tested in default parameter adjustment coaxial double-rotary wing after the spacing of upper and lower rotor, rotor inclination angle, rotor rotating speed and rotor spacing, test result carries out signal conversion by microprocessor and is transferred to computer system progress data processing by wireless communication module regulating system.The device not only ensure that the high reliability and high efficiency of multivariable test, and full-automatic operation improves security performance.
Description
Technical field
Small-sized rotor craft aeromechanics technology field is the utility model is related to, is verted more particularly to one kind is coaxial
Formula rotor aeroperformance test platform.
Background technology
Tilting type rotor has compared to the aeroperformance of conventional planar rotor significantly to be improved.The characteristics of tilting type rotor
It is：Be present the tilt angle of certain angle, i.e. rotor with body plane in the Plane of rotation of rotor, define by horizontal level by the inverse time
The tilt angle that pin direction obtains be on the occasion of, the tilt angle obtained in the direction of the clock by horizontal level is negative value, then adjacent two
Individual tilting rotor can be defined as the rotor pair of surface-to-surface and the back of the body-back of the body.In this tilting type rotor, two of rotor centering incline
Switch rotor is coaxial double-rotary wing, the reversion of rotor up and down in coaxial double-rotary wing, much bigger than single rotor of caused pulling force, but
Aerodynamic interference in upper and lower rotor overlapping region is more serious, and the size of overlapping region is directly determined by the spacing of upper and lower rotor
It is fixed.The aeroperformance of coaxial tilting type rotor is weighed, it is necessary to upper and lower rotor spacing, rotor inclination angle, rotor rotating speed, rotor
Voltage, electric current away from, data of force snesor and motor etc. carry out repetitious measurement.Coaxial tilting type rotor system
The aeroperformance test of system is related to substantial amounts of parameter, and for present rotor aeroperformance test system, is merely capable of pair
Single rotor or coaxial double-rotary wing are tested, and can not complete the test to coaxial tilting type rotor aeroperformance at all.Not only such as
This, also there is the shortcomings of low testing efficiency, complicated, easy break-down in present rotor aeroperformance test system.
The content of the invention
In order to overcome the above-mentioned deficiencies of the prior art, the utility model provides coaxial tilting type rotor aeroperformance test
Platform.
The device can to automatically adjust, the spacing of rotor, rotor incline up and down in coaxial double-rotary wing according to default parameter
Angle, rotor rotating speed and rotor spacing, automatic data collection rotor under different conditions the voltage of the data of force snesor and motor,
Current information, computer system are automatically performed the processing of institute's gathered data, obtain the real-time pulling force of rotor and power, to analyze altogether
The aeroperformance of axle tilting type rotor provides foundation.The device not only ensure that the high reliability and high efficiency of multivariable test,
And automation mechanized operation improves security.
The utility model uses following technical scheme：A kind of coaxial tilting type rotor aeroperformance test platform, its feature
It is：Including parameter automatic regulation system, microprocessor, wireless communication module and the computer system being sequentially connected；The ginseng
Number automatic regulating systems include base, T-shaped support, rotor, motor, electric pushrod, force snesor, support arm, steering wheel and
Linear electric motors；The T-shaped support is fixedly connected with base；The static part of steering wheel is arranged on T-shaped support；The motion portion of steering wheel
Divide and be connected with the static part of linear electric motors；One end of the motion parts of linear electric motors and support arm connects, support arm it is another
End is fixed with electric pushrod；Force snesor is installed in the both sides of support arm；One end of motor is fixed with force snesor, another
Rotor is installed, motor drives rotor wing rotation by rotating shaft in the rotating shaft at end；The microprocessor respectively with electric pushrod, rudder
Machine, linear electric motors, motor, force snesor are electrically connected with；The rotor is coaxial double-rotary wing；Electric pushrod changes coaxial double
The interval S of rotor above and below in rotor.
In the embodiment of the utility model one, the wireless communication module supports double-channel data transmission.
Compared with prior art, the utility model has advantages below：The device can carry out wireless remote to parameter and set
Put, realize to the adjustment of rotor spacing, rotor inclination angle, rotor rotating speed, rotor spacing, while according to institute up and down in coaxial double-rotary wing
Gather the data of force snesor and voltage, the electric current of motor are worth to the pulling force and power of coaxial tilting type rotor, institute
There is measured value to be summarized in computer system to be post-processed, foundation is provided to analyze the aeroperformance of coaxial tilting type rotor.No
It is safe only in this way, the measurement device is accurate, easy to use, compared with the advantage of conventional planar rotor aeroperformance measurement apparatus
Significantly.
Brief description of the drawings
Fig. 1 is coaxial tilting type rotor aeroperformance test device schematic diagram；
Fig. 2 is parameter automatic regulation system structural representation；
Fig. 3 is surface-to-surface rotor to structure chart；
Fig. 4 is the back of the body-back of the body rotor to structure chart；
Fig. 5 is that microprocessor exchanges schematic diagram with the information of parameter automatic regulation system.
Embodiment
Explanation is further explained to the utility model with specific embodiment below in conjunction with the accompanying drawings.
A kind of coaxial tilting type rotor aeroperformance test platform, its parameter automatic regulation system for including being sequentially connected,
Microprocessor, wireless communication module and computer system；The parameter automatic regulation system include base, T-shaped support, rotor,
Motor, electric pushrod, force snesor, support arm, steering wheel and linear electric motors；The T-shaped support is fixedly connected with base；Rudder
The static part of machine is arranged on T-shaped support；The motion parts of steering wheel and the static part of linear electric motors connect；Linear electric motors
One end of motion parts and support arm is connected, and the other end and the electric pushrod of support arm are fixed；In the both sides installing force of support arm
Sensor；One end of motor is fixed with force snesor, and rotor is installed in the rotating shaft of the other end, and motor passes through rotating shaft band
Dynamic rotor wing rotation；The microprocessor electrically connects with electric pushrod, steering wheel, linear electric motors, motor, force snesor respectively
Connect；The rotor is coaxial double-rotary wing；Electric pushrod changes the interval S of rotor above and below in coaxial double-rotary wing.
In the embodiment of the utility model one, the wireless communication module supports double-channel data transmission.
As shown in Fig. 1, the utility model is by parameter automatic regulation system 1, microprocessor 2, wireless communication module 3 and meter
Calculation machine system 4 forms.Computer system 4 gives test parameters, and relevant parameter is sent into microprocessor by wireless communication module 3
Device 2, parameter value are transferred to parameter automatic regulation system 1 by microprocessor 2, and parameter automatic regulation system 1 is carried out according to parameter value
Adjust and tested, test result carries out signal conversion by microprocessor 2 and is transferred to department of computer science by wireless communication module 3
System 4 carries out data processing.
As shown in Fig. 2 parameter automatic regulation system 1 mainly includes base 101, T-shaped support 102, rotor 103, driving electricity
Machine 104, electric pushrod 105, force snesor 106, support arm 107, steering wheel 108 and linear electric motors 109.T-shaped support 102 passes through weldering
The mode connect is connected with base 101, and the static part of steering wheel 108 is arranged on T-shaped support 102, and steering wheel 108 is used for adjusting rotor
103 inclination angle makes rotor to being arranged to surface-to-surface and the back of the body-back of the body rotor pair.The motion parts connection linear electric motors 109 of steering wheel 108
Static part, linear electric motors 109 can change the spacing of rotor pair.The motion parts connection support arm 107 of linear electric motors 109
One end, electric pushrod 105 is fixed in the other end of support arm 107, electric pushrod 105 is used for changing upper backspin in coaxial double-rotary wing
The spacing of the wing.Force snesor 106 is installed in the both sides of support arm 107, force snesor 106 is used for measuring the pulling force of rotor 103, driven
One end of dynamic motor 104 is fixed with force snesor 106, rotor 103 is installed in the rotating shaft of the other end, motor 104 is by turning
Axle drives rotor 103 to rotate.
Rotor 103 as shown in Figure 3 is surface-to-surface state, and corresponding inclination angle is（- α, α）, the excursion at inclination angle is（0,
90°）, rotor 103 as shown in Figure 4 is the back of the body-back of the body state, and corresponding inclination angle is（α ,-α）, the excursion at inclination angle is（0,
90°）, the spacing of rotor is S up and down in coaxial double-rotary wing, and rotor spacing is H, and T-shaped support can be carried out apart from the height of base
Adjust to avoid producing ground effect.
As shown in Fig. 5, tach signal is sent to motor 104 by microprocessor 2, and motor 104 is revolved by controlling
The rotating speed of the wing 103 changes pulling force, and pulling force, which is measured by force snesor 106, to carry out analog-to-digital conversion via ADC and obtain rotor really drawing
Power numerical value.The measurement gained value of thrust of rotor and voltage, the current information of motor 104 are acquired by microprocessor 2, root
The power of rotor 103 is can obtain according to formula P=UI.Meanwhile microprocessor 2 is to electric pushrod 105, motor 104, straight-line electric
Machine 109 and steering wheel 108 assign command adapted thereto respectively, are changed by electric pushrod 105 above and below in coaxial double-rotary wing between rotor 103
The rotating speed of rotor 103 is controlled away from S, by motor 104, by between the linear motion change rotor pair of linear electric motors 109
The inclination angle of rotor 103 is adjusted away from H and by the rotary motion of steering wheel 108.
Above is preferred embodiment of the present utility model, all changes made according to technical solutions of the utility model are produced
Function without departing from technical solutions of the utility model scope when, belong to the scope of protection of the utility model.
Claims (2)
- A kind of 1. coaxial tilting type rotor aeroperformance test platform, it is characterised in that：Parameter including being sequentially connected is adjusted automatically Section system, microprocessor, wireless communication module and computer system；The parameter automatic regulation system includes base, T-shaped branch Frame, rotor, motor, electric pushrod, force snesor, support arm, steering wheel and linear electric motors；The T-shaped support is consolidated with base Fixed connection；The static part of steering wheel is arranged on T-shaped support；The motion parts of steering wheel and the static part of linear electric motors connect； The motion parts of linear electric motors and one end of support arm are connected, and the other end and the electric pushrod of support arm are fixed；In support arm Both sides are installed by force snesor；One end of motor is fixed with force snesor, and rotor, motor are installed in the rotating shaft of the other end Rotor wing rotation is driven by rotating shaft；The microprocessor senses with electric pushrod, steering wheel, linear electric motors, motor, power respectively Device is electrically connected with；The rotor is coaxial double-rotary wing；Electric pushrod changes the interval S of rotor above and below in coaxial double-rotary wing.
- 2. coaxial tilting type rotor aeroperformance test platform according to claim 1, it is characterised in that：The channel radio Believe that module supports double-channel data transmission.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720321816.3U CN207197776U (en) | 2017-03-30 | 2017-03-30 | Coaxial tilting type rotor aeroperformance test platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720321816.3U CN207197776U (en) | 2017-03-30 | 2017-03-30 | Coaxial tilting type rotor aeroperformance test platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207197776U true CN207197776U (en) | 2018-04-06 |
Family
ID=61792944
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720321816.3U Expired - Fee Related CN207197776U (en) | 2017-03-30 | 2017-03-30 | Coaxial tilting type rotor aeroperformance test platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207197776U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108482708A (en) * | 2018-03-15 | 2018-09-04 | 华南农业大学 | A kind of lap siding DCB Specimen aeroperformance detection device and detection method |
| CN110254703A (en) * | 2019-06-28 | 2019-09-20 | 福州大学 | One kind DCB Specimen that verts hovers T-type UAV system automatically |
| CN112345197A (en) * | 2020-10-23 | 2021-02-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Transmission, tilting and vibration reduction system of icing wind tunnel helicopter test device |
| CN112630649A (en) * | 2019-10-08 | 2021-04-09 | 北京京东尚科信息技术有限公司 | Motor testing device |
-
2017
- 2017-03-30 CN CN201720321816.3U patent/CN207197776U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108482708A (en) * | 2018-03-15 | 2018-09-04 | 华南农业大学 | A kind of lap siding DCB Specimen aeroperformance detection device and detection method |
| CN110254703A (en) * | 2019-06-28 | 2019-09-20 | 福州大学 | One kind DCB Specimen that verts hovers T-type UAV system automatically |
| CN110254703B (en) * | 2019-06-28 | 2023-09-12 | 福州大学 | Tilting double-rotor wing automatic hovering T-shaped unmanned aerial vehicle system |
| CN112630649A (en) * | 2019-10-08 | 2021-04-09 | 北京京东尚科信息技术有限公司 | Motor testing device |
| CN112630649B (en) * | 2019-10-08 | 2024-01-12 | 北京京东尚科信息技术有限公司 | Motor testing device |
| CN112345197A (en) * | 2020-10-23 | 2021-02-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Transmission, tilting and vibration reduction system of icing wind tunnel helicopter test device |
| CN112345197B (en) * | 2020-10-23 | 2022-05-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Transmission, tilting and vibration damping system of icing wind tunnel helicopter test device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207197776U (en) | Coaxial tilting type rotor aeroperformance test platform | |
| CN109612681A (en) | A kind of aerodynamic interference measurement method of the coaxial rigid rotor model of helicopter | |
| CN103364755B (en) | A kind of electric energy meter power frequency magnetic field automatically scanning pilot system and test method | |
| CN206311975U (en) | A kind of Radar IF simulation device | |
| CN107063622A (en) | Coaxial tilting type rotor aeroperformance test platform and its method | |
| CN101329218A (en) | Automatic calibration and automatic measurement device of fluid flow test probe | |
| CN102680892A (en) | Universal test bench for detecting performance of permanent magnet generator | |
| CN102360027A (en) | Differential pressure type airspeed sensor testing system | |
| CN104018996A (en) | Wind turbine blade with automatic windward area adjustment function | |
| CN205497523U (en) | Robot joint flexible drive ware | |
| CN105181307A (en) | Double-blade model wind driven generator experimental table and experimental method | |
| CN205898345U (en) | Plant protection unmanned aerial vehicle's power detecting system | |
| CN101762260A (en) | Large-scale turning axle verticality detection device and method | |
| CN202939020U (en) | Vehicle retarder test bed with inertia load | |
| CN107387316B (en) | Independent variable pitch control system of fan based on pressure transmitter | |
| CN209209059U (en) | A kind of unmanned plane power performance test macro | |
| CN208498774U (en) | A kind of energy-saving automatic wind facing sail ship navaid | |
| CN202383260U (en) | Universal test bench for performance testing of permanent magnet generator | |
| CN106560685A (en) | Airfoil-shaped dynamic aerodynamic characteristic test bench for horizontal-axis wind turbine | |
| CN206255212U (en) | A kind of remote-controlled test device of rotor lift parameter | |
| CN112857719B (en) | Fixed airfoil flutter ground test device and method | |
| CN104731090A (en) | Experiment device for verifying automatic control methods by using pitch angle as control object | |
| CN205027513U (en) | Double -bladed model aerogenerator laboratory bench | |
| CN106872085A (en) | A kind of unmanned plane horn kinetic energy efficiency automatic test device | |
| CN202451359U (en) | Closed-loop control device for simulating waves |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180406 Termination date: 20200330 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |