CN103308272A - Non-planar dynamic testing device for aerodynamic performances of dual rotors - Google Patents
Non-planar dynamic testing device for aerodynamic performances of dual rotors Download PDFInfo
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- CN103308272A CN103308272A CN2013102070663A CN201310207066A CN103308272A CN 103308272 A CN103308272 A CN 103308272A CN 2013102070663 A CN2013102070663 A CN 2013102070663A CN 201310207066 A CN201310207066 A CN 201310207066A CN 103308272 A CN103308272 A CN 103308272A
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Abstract
The invention discloses a non-planar dynamic testing device for aerodynamic performances of dual rotors. The non-planar dynamic testing device consists of a full-automatic parameter adjusting part, a microprocessor unit, a wireless communication module and a computer system; the rotation of any angle of the rotors is finished and the adjustment of the state and the inclined angles of the rotors is realized by a steering engine; a support arm is enabled to move along the axial direction and the adjustment between the space between the rotors is realized by a liner motor; a lift force signal is converted into a voltage signal by a force sensor; and the voltage signal together with current and voltage signals of a rotor driving motor passes through the microprocessor unit and the wireless communication module and then is transmitted to the computer system for carrying out real-time lift force and power consumption display, so that wireless two-way link transmission is realized. According to the non-planar dynamic testing device, multiple parameters of the dual rotors can be quickly adjusted under the long-distance wireless operation; and the non-planar dynamic testing device has the advantages of convenience, safety and accuracy.
Description
Technical field
The invention belongs to small aircraft rotor aerodynamics field, relate to a kind of non-planar bispin wing aeroperformance dynamic checkout unit in many rotor systems.
Background technology
The configuration of non-planar rotor refers to that rotor wing rotation plane and body plane exist the rotor configuration of certain angle, this angle
In on-plane surface rotor unit, be called the rotor tilt angle, definition by horizontal positioned by the tilt angle that is rotated counterclockwise for just, then can the state of verting of adjacent two rotors be divided into face-to-face state by tilt angle
With back-to-back state
Because the aeroperformance of the rotor unit of non-planar configuration improves a lot than the rotor unit of traditional horizontal positioned, its aeroperformance test need to take multiple measurements a plurality of aerodynamic parameters (comprising rotor location mode, rotor tilt angle, rotor spacing, gyroplane rotate speed etc.) that relate to.And in the existing rotor aeroperformance test macro, major part all is for single rotor test, and fraction can be finished the test of coaxial double-rotary wing aeroperformance.The test of on-plane surface bispin wing aeroperformance relates to a plurality of aerodynamic parameters, and existing rotor Pneumatic test system can't be finished the test to on-plane surface bispin wing aeroperformance.And existing rotor aeroperformance test macro physical construction is comparatively complicated, and failure rate is high, has more testing efficiency low, and the personal damage during with fault.In the existing test macro, there is not yet open for the proving installation of on-plane surface bispin wing aeroperformance.
Summary of the invention
In order to overcome the deficiency of conventional planar formula bispin wing Performance Test System, the present invention proposes a kind of non-planar bispin wing aeroperformance dynamic checkout unit, it can regulate nonplanar two gyroplane rotate speeds, rotor tilt angle and rotor spacing automatically according to the input instruction, can be at a distance, noncontact finishes the collection of drive motor voltage, electric current and force sensor data under different rotor states, rotor tilt angle and the rotor spacing condition, automatically finishes analysis and the processing of bispin wing aeroperformance; Both guarantee high-level efficiency and the high reliability of multivariate test, can realize remote-controlled operation again, improved security.
The present invention takes following technical scheme for achieving the above object:
A kind of non-planar bispin wing aeroperformance dynamic checkout unit mainly is comprised of full-automatic parameter adjustment part, microprocessor unit, wireless communication module and computer system;
Described full-automatic parameter adjustment part mainly is comprised of base, column, mounting bracket, drive motor, rotor, power sensor, sway brace, linear electric motors and steering wheel;
Described microprocessor unit can send instruction to drive motor and steering wheel, can send to linear electric motors the voltage and current information of instruction and reception drive motor, gathers the information of power sensor by A/D;
Described wireless communication module comprises transmitter module and receiver module, transmitter module and receiver module are supported the diplex operation pattern, receiver module was operated in receiving mode when transmitter module was operated in emission mode, transmitter module was operated in receiving mode when receiver module was operated in emission mode, finished the wireless receiving and dispatching of instruction and information; Transmitter module and microprocessor unit both-way communication, receiver module is with the computer system both-way communication;
Described computer system is finished initial parameter and is set and the test data post-processing function.
In the technique scheme, described microprocessor unit is single-chip microcomputer, ARM or DSP.
In the technique scheme, described microprocessor unit sends instruction by PWM to steering wheel; Send instruction by I2C to linear electric motors; Send instruction by CAN to drive motor.
In the technique scheme, described microprocessor unit receives the voltage and current information of drive motor by CAN.
In the technique scheme, described transmitter module is by 232 or 485 and the microprocessor unit both-way communication.
In the technique scheme, described receiver module passes through 232 or 485 with the computer system both-way communication.
In the technique scheme, rotor is connected in the rotating shaft of drive motor, and drive motor is fixed on the power sensor, and the power sensor is fixed on sway brace one end, the sway brace other end connects the motion parts of linear electric motors, adjusts the rotor spacing by the rectilinear motion of linear electric motors; The static part of linear electric motors connects the motion parts of steering wheel, on the static part connection support of steering wheel, regulate the tilt angle of rotor by rotatablely moving of steering wheel, by the tilt angle of adjusting two rotors the rotor state being set simultaneously is face-to-face state or back-to-back state.
In the technique scheme, base and column, and the connected mode between column and the mounting bracket is that bolt connects or welding.
In the technique scheme, two sway brace angular range are more than or equal to 60 °, less than or equal to 180 °.
In the technique scheme, the tilt angle of rotor
Scope be greater than 0 °, less than 90 °.
Beneficial effect of the present invention and advantage are:
A kind of non-planar bispin wing aeroperformance dynamic checkout unit that the present invention provides, can the remote-wireless parameters, automatically adjust rotor state, gyroplane rotate speed, rotor tilt angle and the rotor spacing of the on-plane surface bispin wing, automatically gather the output of voltage, current data and the power sensor of drive motor, automatically finish lift and the power consumption calculation of the on-plane surface bispin wing, test result can be selected the mode of data file, form and curve.Realized the far distance automatic adjustment of multiparameter of on-plane surface bispin wing aeroperformance test, height of support has also been avoided ground effect, the on-plane surface bispin wing aeroperformance proving installation that the present invention provides has conveniently, safety, outstanding advantages accurately, satisfies the test needs of non-planar bispin wing aeroperformance fully.
Description of drawings
Below in conjunction with the drawings and specific embodiments the present invention is described in further detail.
Fig. 1 is non-planar bispin wing aeroperformance dynamic checkout unit schematic diagram;
Fig. 2 is full-automatic parameter adjustment part-structure schematic diagram;
Fig. 3 is microprocessor unit and the full-automatic automatic adjustment member communication of parameter and interface schematic diagram;
Fig. 4 is wireless transmission unit and microprocessor unit and computer system communication and interface schematic diagram;
Fig. 5 is the face-to-face status architecture schematic diagram of twin rotor system;
Fig. 6 is the back-to-back status architecture schematic diagram of twin rotor system.
Reference numeral among the figure is expressed as:
The full-automatic parameter adjustment part of 1-; The 2-microprocessor unit; The 3-wireless communication module; The 4-computer system;
The 101-base; The 102-column; The 103-mounting bracket; The 104-drive motor; The 105-rotor; 106-power sensor; The 107-sway brace; The 108-linear electric motors; The 109-steering wheel;
The 301-transmitter module; The 302-receiver module.
Embodiment
Invention thought of the present invention is: non-planar bispin wing performance testing device of the present invention is comprised of full-automatic parameter adjustment part, microprocessor unit, wireless communication module and computer system.Described full-automatic parameter adjustment part is comprised of base, column, mounting bracket, drive motor, rotor, power sensor, sway brace, linear electric motors and steering wheel.Rotor is connected to the change of passing through the drive motor rotating speed on the drive motor and realizes the lift size variation, and this lift size is sent to computer system by wireless transport module again by the power sensor test and by the microprocessor unit collection; Realize the adjustment of two on-plane surface rotor spacings by the rectilinear motion that is connected to two linear electric motors on the sway brace; The anglec of rotation by steering wheel changes the adjustment that realizes two on-plane surface rotor spacings, and by the tilt angle of adjusting two rotors the rotor state being set simultaneously is face-to-face state and back-to-back state.The base bottom surface to the distance of mounting bracket upper surface greater than 1.5 meters to avoid ground effect.Described two sway brace angular range are that 60 ° (comprising 60 °) are to 180 ° (comprising 180 °).Described microprocessor unit sends instruction by PWM, I2C or CAN to drive motor and steering wheel, and the voltage and current information by I2C or CAN send instruction and reception drive motor to linear electric motors gathers the power sensor information by A/D.By wireless transport module, parameter is by computer system settings and be sent to microprocessor unit, sends to the automatic adjustment that parameter is partly finished in full-automatic parameter adjustment by microprocessor unit again.By wireless transport module, the information of microprocessor unit collection is sent to computer system, and calculating and system finish analysis and the processing of Information Monitoring, finish record and the aftertreatment of rotor system lift and power consumption.
The present invention can also take following technical measures:
Rotor drives at the sway brace front end and by drive motor by the power installation of sensors, sway brace is connected with mounting bracket by steering wheel, linear electric motors are installed in the sway brace rear end and are fixed on the mounting bracket by steering wheel, realize the rotor lift adjustment by the drive motor rotation speed change, the anglec of rotation by steering wheel changes the adjustment that realizes rotor tilt angle and rotor state, by be connected to linear electric motors on the sway brace can make sway brace vertically traveling priority realize the adjustment of rotor spacing can converting the lift signal to voltage signal by the power sensor.
The hinge that information is transmitted between part and the computer system is regulated in described microprocessor unit conduct automatically parameter, mainly carries out data-signal alternately and conversion.And the work that the data that collect are further analyzed and process is finished by described computer system; Communicating by letter between described microprocessor unit and the computer system is to realize by the wireless transport module of diplex operation.
Described microprocessor unit sends instruction by PWM, I2C or CAN to drive motor and steering wheel, and the voltage and current information by I2C or CAN send instruction and reception drive motor to linear electric motors gathers the power sensor information by A/D.By wireless transport module, parameter is by computer system settings and be sent to microprocessor unit, sends to the automatic adjustment that parameter is partly finished in full-automatic parameter adjustment by microprocessor unit again.Described microprocessor unit can be controlled the adjusting that drive motor, linear electric motors and steering wheel are realized gyroplane rotate speed, rotor spacing and rotor tilt angle.
Described computer system given parameters is adjusted instruction, comprising: rotor label, rotor spacing, gyroplane rotate speed, rotor state; The rotor tilt angle represents the angle on rotor wing rotation plane and body plane, and definition rotor tilt angle is
Tilt angle
Scope be 0 degree (do not contain 0 degree) to 90 degree (not comprising 90 degree), the regulation rotor is rotated counterclockwise as just, tilt angle corresponding to state is face-to-face
The tilt angle that back-to-back state is corresponding is
Described linear electric motors motion parts connects sway brace, and the static part of linear electric motors connects the motion parts of steering wheel, adjusts the rotor spacing by the rectilinear motion of linear electric motors.
On the static part connection support of described steering wheel, regulate the tilt angle of rotor by rotatablely moving of steering wheel, by the tilt angle of adjusting two rotors the rotor state being set simultaneously is face-to-face state and back-to-back state.
Described power sensor test rotor lift, can select as required one dimension force sensor, 2 D force sensor ..., until six-dimension force sensor.
The Data Post of computer system comprises that the voltage transitions of power sensor becomes the electric current of lift, drive motor to become power consumption with voltage transitions, and result can select data text, form and curve mode to show.
Below in conjunction with accompanying drawing the present invention is done to describe in detail.
As shown in Figure 1, a kind of non-planar bispin wing aeroperformance dynamic checkout unit that the present invention provides is comprised of full-automatic parameter adjustment part 1, microprocessor unit 2, wireless communication module 3 and computer system 4.Computer system 4 given parameters design loads and test initial value, send at a distance microprocessor unit 2 by wireless communication module 3, parameter designing value and test initial value signal input to full-automatic parameter adjustment part 1 by microprocessor unit 2 to carry out initialization and begins test, and test result is again carried out the signal conversion by microprocessor unit 2 and radioed to computer system 4 via wireless communication module 3 and carry out Data Post.
As shown in Figure 2, full-automatic parameter adjustment part 1 is comprised of base 101, column 102, mounting bracket 103, drive motor 104, rotor 105, power sensor 106, sway brace 107, linear electric motors 108 and steering wheel 109.Rotor 105 is connected in the rotating shaft of drive motor 104, drive motor 104 is fixed on the power sensor 106, power sensor 106 is fixed on sway brace 107 1 ends, and sway brace 107 other ends connect the motion parts of linear electric motors, adjusts rotor 105 spacings by the rectilinear motion of linear electric motors 108; The static part of linear electric motors 108 connects the motion parts of steering wheel 109, on the static part connection support 103 of steering wheel 109, regulate the tilt angle of rotor 105 by rotatablely moving of steering wheel 109, by the tilt angle of adjusting two rotors 105 rotor 105 states being set simultaneously is face-to-face state and back-to-back state; Modes such as the connection between base 101 and column 102 and column 102 and the mounting bracket 103 can be with bolts, welding but be not limited to aforesaid way, two sway brace 107 angular range are that 60 ° (comprising 60 °) are to 180 ° (comprising 180 °).
As shown in Figure 3, microprocessor unit 2 can adopt as required the microprocessor units such as single-chip microcomputer, ARM or DSP but be not limited to above-mentioned three kinds, send instruction by PWM, I2C or CAN to drive motor 104, steering wheel 109, send the voltage and current information of instruction and reception drive motor 104 to linear electric motors 108 by I2C or CAN, gather power sensor 106 information by A/D, power sensor 106 test rotors 105 lift, can select as required one dimension force sensor, 2 D force sensor ..., until six-dimension force sensor.
As shown in Figure 4, wireless communication module 3 comprises transmitter module 301 and receiver module 302, transmitter module 301 and receiver module 302 are supported the diplex operation pattern, receiver module 302 was operated in receiving mode when transmitter module 301 was operated in emission mode, transmitter module 301 was operated in receiving mode when receiver module 302 was operated in emission mode, finished the wireless receiving and dispatching of instruction and information; Transmitter module by 232 or 485 with the microprocessor unit both-way communication, receiver module 302 passes through 485 or 232 with computer system 4 both-way communications.Computer system 4 is finished initial parameter and is set and the test data post-processing function.The Data Post of computer system 4 comprises that the voltage transitions of power sensor 106 becomes the electric current of lift, drive motor 104 to become power consumption with voltage transitions, and result can select data text, form and curve mode to show.
As shown in Figure 5, be adjusted into face-to-face state according to test needs rotor 105, tilt angle corresponding to state is face-to-face
Tilt angle
Can be arranged to arbitrarily angled in the 90 degree scopes of 0 degree according to the test needs, but not comprise 0 degree, also not comprise 90 degree.
As shown in Figure 6, be adjusted into back-to-back state according to test needs rotor 105, the tilt angle that back-to-back state is corresponding is
Tilt angle
Can be arranged to arbitrarily angled in the 90 degree scopes of 0 degree according to the test needs, but not comprise 0 degree, also not comprise 90 degree.
Obviously, above-described embodiment only is for example clearly is described, and is not the restriction to embodiment.For those of ordinary skill in the field, can also make other changes in different forms on the basis of the above description.Here need not also can't give all embodiments exhaustive.And the apparent variation of being extended out thus or change still are among the protection domain of the invention.
Claims (10)
1. a non-planar bispin wing aeroperformance dynamic checkout unit is characterized in that: mainly be comprised of full-automatic parameter adjustment part (1), microprocessor unit (2), wireless communication module (3) and computer system (4);
Described full-automatic parameter adjustment part (1) mainly is comprised of base (101), column (102), mounting bracket (103), drive motor (104), rotor (105), power sensor (106), sway brace (107), linear electric motors (108) and steering wheel (109);
Described microprocessor unit (2) can send instruction to drive motor (104) and steering wheel (109), can send to linear electric motors (108) the voltage and current information of instruction and reception drive motor (104), gather the information of power sensor (106) by A/D;
Described wireless communication module (3) comprises transmitter module (301) and receiver module (302), transmitter module (301) and receiver module (302) are supported the diplex operation pattern, transmitter module (301) when being operated in emission mode receiver module (302) be operated in receiving mode, receiver module (302) when being operated in emission mode transmitter module (301) be operated in receiving mode, finish the wireless receiving and dispatching of instruction and information; Transmitter module (301) and microprocessor unit (2) both-way communication, the same computer system of receiver module (302) (4) both-way communication;
Described computer system (4) is finished initial parameter and is set and the test data post-processing function.
2. a kind of non-planar bispin wing aeroperformance dynamic checkout unit according to claim 1, it is characterized in that: described microprocessor unit (2) is single-chip microcomputer, ARM or DSP.
3. a kind of non-planar bispin wing aeroperformance dynamic checkout unit according to claim 2 is characterized in that: described microprocessor unit (2) sends instruction by PWM to steering wheel (109); Send instruction by I2C to linear electric motors (108); Send instruction by CAN to drive motor (104).
4. a kind of non-planar bispin wing aeroperformance dynamic checkout unit according to claim 2 is characterized in that: described microprocessor unit (2) receives the voltage and current information of drive motor (104) by CAN.
5. a kind of non-planar bispin wing aeroperformance dynamic checkout unit according to claim 1 is characterized in that: described transmitter module (301) is by 232 or 485 and microprocessor unit (2) both-way communication.
6. a kind of non-planar bispin wing aeroperformance dynamic checkout unit according to claim 1 is characterized in that: described receiver module (302) is by 232 or 485 same computer system (4) both-way communications.
7. the described a kind of non-planar bispin wing aeroperformance dynamic checkout unit of any one according to claim 1-6, it is characterized in that: rotor (105) is connected in the rotating shaft of drive motor (104), drive motor (104) is fixed on the power sensor (106), the power sensor is fixed on sway brace (107) one ends, sway brace (107) other end connects the motion parts of linear electric motors (108), adjusts rotor (105) spacing by the rectilinear motion of linear electric motors (108); The static part of linear electric motors (108) connects the motion parts of steering wheel (109), on the static part connection support (103) of steering wheel (109), regulate the tilt angle of rotor (105) by rotatablely moving of steering wheel (109), by the tilt angle of adjusting two rotors (105) rotor (105) state being set simultaneously is face-to-face state or back-to-back state.
8. the described a kind of non-planar bispin wing aeroperformance dynamic checkout unit of any one according to claim 1-6, it is characterized in that: base (101) and column (102), and the connected mode between column (102) and the mounting bracket (103) is that bolt connects or welding.
9. the described a kind of non-planar bispin wing aeroperformance dynamic checkout unit of any one according to claim 1-6 is characterized in that: two sway braces (107) angular range is more than or equal to 60 °, less than or equal to 180 °.
10. the described a kind of non-planar bispin wing aeroperformance dynamic checkout unit of any one is characterized in that: the tilt angle of rotor (105) according to claim 1-6
Scope be greater than 0 °, less than 90 °.
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| CN201310207066.3A CN103308272B (en) | 2013-05-30 | 2013-05-30 | A kind of non-planar DCB Specimen aeroperformance dynamic checkout unit |
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| CN201310207066.3A CN103308272B (en) | 2013-05-30 | 2013-05-30 | A kind of non-planar DCB Specimen aeroperformance dynamic checkout unit |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103954426A (en) * | 2014-03-31 | 2014-07-30 | 南京航空航天大学 | Rotor wing dynamic test device |
| CN106347705A (en) * | 2016-10-31 | 2017-01-25 | 安徽理工大学 | Rotor lift force testing system for unmanned aerial vehicle |
| CN107063622A (en) * | 2017-03-30 | 2017-08-18 | 福州大学 | Coaxial tilting type rotor aeroperformance test platform and its method |
| CN107167329A (en) * | 2017-06-07 | 2017-09-15 | 北京航空航天大学 | A kind of air force load testing machine of unsymmetrical flight device rudder face |
| CN108427432A (en) * | 2018-05-25 | 2018-08-21 | 福州大学 | A kind of three rotor craft of non-planar and control method |
| 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 |
| CN108594840A (en) * | 2018-05-29 | 2018-09-28 | 中山星图航空航天技术有限公司 | It verts control device and its control method |
| CN111207923A (en) * | 2020-04-22 | 2020-05-29 | 北京清航紫荆装备科技有限公司 | Test bed for transmission device of cross dual-rotor unmanned helicopter |
| CN111216922A (en) * | 2020-04-22 | 2020-06-02 | 北京清航紫荆装备科技有限公司 | Lifting force testing device of cross dual-rotor helicopter |
| CN114397084A (en) * | 2022-01-06 | 2022-04-26 | 吉林大学 | Six-rotor unmanned aerial vehicle aerodynamic characteristic test device and test method thereof |
| CN114964715A (en) * | 2022-08-01 | 2022-08-30 | 中国空气动力研究与发展中心空天技术研究所 | Water-air mixed flow field and aircraft rotor coupling effect test device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103954426B (en) * | 2014-03-31 | 2016-08-17 | 南京航空航天大学 | A kind of rotor dynamic testing equipment |
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| CN106347705A (en) * | 2016-10-31 | 2017-01-25 | 安徽理工大学 | Rotor lift force testing system for unmanned aerial vehicle |
| CN107063622B (en) * | 2017-03-30 | 2023-06-16 | 福州大学 | Coaxial tilting rotor wing pneumatic performance test platform and method thereof |
| CN107063622A (en) * | 2017-03-30 | 2017-08-18 | 福州大学 | Coaxial tilting type rotor aeroperformance test platform and its method |
| CN107167329A (en) * | 2017-06-07 | 2017-09-15 | 北京航空航天大学 | A kind of air force load testing machine of unsymmetrical flight device rudder face |
| 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 |
| CN108427432A (en) * | 2018-05-25 | 2018-08-21 | 福州大学 | A kind of three rotor craft of non-planar and control method |
| CN108427432B (en) * | 2018-05-25 | 2023-06-23 | 福州大学 | Non-planar three-rotor aircraft and control method |
| CN108594840A (en) * | 2018-05-29 | 2018-09-28 | 中山星图航空航天技术有限公司 | It verts control device and its control method |
| CN111207923A (en) * | 2020-04-22 | 2020-05-29 | 北京清航紫荆装备科技有限公司 | Test bed for transmission device of cross dual-rotor unmanned helicopter |
| CN111207923B (en) * | 2020-04-22 | 2020-08-21 | 北京清航紫荆装备科技有限公司 | Test bed for transmission device of cross dual-rotor unmanned helicopter |
| CN111216922A (en) * | 2020-04-22 | 2020-06-02 | 北京清航紫荆装备科技有限公司 | Lifting force testing device of cross dual-rotor helicopter |
| CN114397084A (en) * | 2022-01-06 | 2022-04-26 | 吉林大学 | Six-rotor unmanned aerial vehicle aerodynamic characteristic test device and test method thereof |
| CN114964715A (en) * | 2022-08-01 | 2022-08-30 | 中国空气动力研究与发展中心空天技术研究所 | Water-air mixed flow field and aircraft rotor coupling effect test device |
| CN114964715B (en) * | 2022-08-01 | 2022-10-21 | 中国空气动力研究与发展中心空天技术研究所 | Water-air mixed flow field and aircraft rotor coupling effect test device |
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