CN103308272B - A kind of non-planar DCB Specimen aeroperformance dynamic checkout unit - Google Patents

A kind of non-planar DCB Specimen aeroperformance dynamic checkout unit Download PDF

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Publication number
CN103308272B
CN103308272B CN201310207066.3A CN201310207066A CN103308272B CN 103308272 B CN103308272 B CN 103308272B CN 201310207066 A CN201310207066 A CN 201310207066A CN 103308272 B CN103308272 B CN 103308272B
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rotor
aeroperformance
planar
drive motor
dcb specimen
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CN103308272A (en
Inventor
白越
雷瑶
高庆嘉
赵常均
宫勋
孙强
续志军
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Changchun Institute of Optics Fine Mechanics and Physics of CAS
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Changchun Institute of Optics Fine Mechanics and Physics of CAS
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Abstract

The invention discloses a kind of non-planar DCB Specimen aeroperformance proving installation, by full-automatic parameter adjustment part, microprocessor unit, wireless communication module and computer system composition, by steering wheel make rotor complete adjustment that Arbitrary Rotation realizes rotor state and tilt angle, sway brace in axial direction movement is made to realize the adjustment of rotor spacing by linear electric motors, lift signal is converted to voltage signal by force snesor, after microprocessor unit and wireless communication module, computer system is transferred to together with the electric current of rotor drive motor and voltage signal, carry out real-time lift and power consumption display, achieve wireless two-way link transmission.This proving installation can carry out rapid adjustment to the multiple parameter of DCB Specimen under remote-wireless operation, has convenience, safety, accurately advantage.

Description

A kind of non-planar DCB Specimen aeroperformance dynamic checkout unit
Technical field
The invention belongs to small aircraft rotor aerodynamics field, relate to a kind of non-planar DCB Specimen 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 rotor tilt angle, define by horizontal positioned by the tilt angle be rotated counterclockwise as just, then by tilt angle, the state of verting of adjacent two rotors can be divided into face-to-face state with back-to-back state .The rotor unit placed compared to conventional flat due to the aeroperformance of the rotor unit of non-planar configuration improves a lot, and the test of its aeroperformance needs to take multiple measurements the multiple aerodynamic parameters related to (comprising rotor location mode, rotor tilt angle, rotor spacing, gyroplane rotate speed etc.).And in existing rotor aeroperformance test macro, major part is all test for single rotor, fraction can complete the test of coaxial double-rotary wing aeroperformance.The test of on-plane surface DCB Specimen aeroperformance relates to multiple aerodynamic parameter, and existing rotor Pneumatic test system cannot complete the test to on-plane surface DCB Specimen aeroperformance.And existing rotor aeroperformance test macro physical construction is comparatively complicated, failure rate is high, has more testing efficiency low, and with personal damage during fault.In existing test macro, the proving installation for on-plane surface DCB Specimen aeroperformance there is not yet open.
Summary of the invention
In order to overcome the deficiency of conventional planar DCB Specimen Performance Test System, the present invention proposes a kind of non-planar DCB Specimen aeroperformance dynamic checkout unit, it can regulate nonplanar two gyroplane rotate speeds, rotor tilt angle and rotor spacing automatically according to input instruction, can at a distance, noncontact completes the collection of drive motor voltage, electric current and force sensor data under different rotor state, rotor tilt angle and rotor spacing condition, automatically completes the treatment and analysis of DCB Specimen aeroperformance; Both ensure that the high-level efficiency that multivariate is tested and high reliability, and can remote-controlled operation have been realized again, improve security.
The present invention takes following technical scheme for achieving the above object:
A kind of non-planar DCB Specimen aeroperformance dynamic checkout unit, forms primarily of full-automatic parameter adjustment part, microprocessor unit, wireless communication module and computer system;
Described full-automatic parameter adjustment part forms primarily of base, column, mounting bracket, drive motor, rotor, force snesor, sway brace, linear electric motors and steering wheel;
Described microprocessor unit can send instruction to drive motor and steering wheel, can send instruction to linear electric motors and receive the voltage and current information of drive motor, be gathered the information of force snesor by A/D;
Described wireless communication module comprises transmitter module and receiver module, transmitter module and receiver module support duplex mode of operation, when transmitter module is operated in emission mode, receiver module is operated in receiving mode, when receiver module is operated in emission mode, transmitter module is operated in receiving mode, completes the wireless receiving and dispatching of instruction and information; Transmitter module and microprocessor unit both-way communication, receiver module is with computer system both-way communication;
Described computer system completes Initial parameter sets and test data post-processing function.
In technique scheme, described microprocessor unit is single-chip microcomputer, ARM or DSP.
In technique scheme, described microprocessor unit sends instruction by PWM to steering wheel; Instruction is sent to linear electric motors by I2C; Instruction is sent to drive motor by CAN.
In technique scheme, described microprocessor unit receives the voltage and current information of drive motor by CAN.
In technique scheme, described transmitter module is by 232 or 485 and microprocessor unit both-way communication.
In technique scheme, described receiver module passes through 232 or 485 with computer system both-way communication.
In technique scheme, rotor is connected in the rotating shaft of drive motor, and drive motor is fixed on force snesor, and force snesor is fixed on sway brace one end, the sway brace other end connects the motion parts of linear electric motors, by the rectilinear motion adjustment rotor spacing 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, regulated the tilt angle of rotor by the rotary motion of steering wheel, it is face-to-face state or back-to-back state that the tilt angle simultaneously by adjusting two rotors arranges rotor state.
In technique scheme, base and column, and the connected mode between column and mounting bracket is that bolt connects or welding.
In technique scheme, two sway brace angular range, for being more than or equal to 60 °, are less than or equal to 180 °.
In technique scheme, the tilt angle of rotor scope for being greater than 0 °, be less than 90 °.
Beneficial effect of the present invention and advantage are:
A kind of non-planar DCB Specimen aeroperformance dynamic checkout unit that the present invention provides, can remote-wireless parameters, the rotor state of automatic adjustment on-plane surface DCB Specimen, gyroplane rotate speed, rotor tilt angle and rotor spacing, the output of the voltage of automatic collection drive motor, current data and force snesor, automatically complete lift and the power consumption calculation of on-plane surface DCB Specimen, test result can select the mode of data file, form and curve.Achieve the far distance automatic adjustment of multiparameter of on-plane surface DCB Specimen aeroperformance test, height of support it also avoid ground effect, the on-plane surface DCB Specimen aeroperformance proving installation that the present invention provides has conveniently, safety, accurately outstanding advantages, meets the test needs of non-planar DCB Specimen aeroperformance completely.
Accompanying drawing explanation
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.
Fig. 1 is non-planar DCB Specimen aeroperformance dynamic checkout unit schematic diagram;
Fig. 2 is full-automatic parameter adjustment part-structure schematic diagram;
Fig. 3 is the automatic adjustment member communication of microprocessor unit and full-automatic parameter and interface diagram;
Fig. 4 is wireless transmission unit and microprocessor unit and computer system communication and interface 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 in figure is expressed as:
The full-automatic parameter adjustment part of 1-; 2-microprocessor unit; 3-wireless communication module; 4-computer system;
101-base; 102-column; 103-mounting bracket; 104-drive motor; 105-rotor; 106-force snesor; 107-sway brace; 108-linear electric motors; 109-steering wheel;
301-transmitter module; 302-receiver module.
Embodiment
Invention thought of the present invention is: non-planar DCB Specimen performance testing device of the present invention is made up of full-automatic parameter adjustment part, microprocessor unit, wireless communication module and computer system.Described full-automatic parameter adjustment part is made up of base, column, mounting bracket, drive motor, rotor, force snesor, sway brace, linear electric motors and steering wheel.Rotor is connected on drive motor and realizes lift size variation by the change of drive motor rotating speed, and this lift size is tested by force snesor and gathered by microprocessor unit, then is sent to computer system by wireless transport module; The adjustment of two on-plane surface rotor spacing is realized by the rectilinear motion being connected to the linear electric motors on two sway braces; Realized the adjustment of two on-plane surface rotor spacing by the anglec of rotation change of steering wheel, it is face-to-face state and back-to-back state that the tilt angle simultaneously by adjusting two rotors arranges rotor state.Base bottom surface is greater than 1.5 meters to avoid ground effect to the distance of mounting bracket upper surface.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, is sent the voltage and current information of instruction and reception drive motor, gather force snesor information by A/D by I2C or CAN to linear electric motors.By wireless transport module, parameter is by computer system settings and be sent to microprocessor unit, then sends to full-automatic parameter adjustment part to complete the automatic adjustment of parameter by microprocessor unit.By wireless transport module, the information of microprocessor unit collection is sent to computer system, and calculating and system complete the treatment and analysis of Information Monitoring, complete record and the aftertreatment of rotor system lift and power consumption.
The present invention can also take following technical measures:
Rotor is arranged on sway brace front end by force snesor and is driven by drive motor, sway brace is connected with mounting bracket by steering wheel, linear electric motors are arranged on sway brace rear end and are fixed on mounting bracket by steering wheel, rotor lift adjustment is realized by drive motor rotation speed change, the adjustment of rotor tilt angle and rotor state is realized by the anglec of rotation change of steering wheel, sway brace can be made to move linearly vertically by the linear electric motors be connected on sway brace to realize the adjustment of rotor spacing, can lift signal be converted to voltage signal by force snesor.
The hinge that described microprocessor unit transmits as information between full-automatic parameter adjustment portion and computer system, it is mutual and transform mainly to carry out data-signal.And the work that the data collected are further analyzed and process has been come by described computer system; Communication between described microprocessor unit and computer system is realized by the wireless transport module of diplex operation.
Described microprocessor unit sends instruction by PWM, I2C or CAN to drive motor and steering wheel, is sent the voltage and current information of instruction and reception drive motor, gather force snesor information by A/D by I2C or CAN to linear electric motors.By wireless transport module, parameter is by computer system settings and be sent to microprocessor unit, then sends to full-automatic parameter adjustment part to complete the automatic adjustment of parameter by microprocessor unit.Described microprocessor unit can control drive motor, linear electric motors and steering wheel to realize the adjustment of gyroplane rotate speed, rotor spacing and rotor tilt angle.
Described computer system given parameters adjustment instruction, comprising: rotor label, rotor spacing, gyroplane rotate speed, rotor state; Rotor tilt angle represents the angle of rotor wing rotation plane and body plane, and definition rotor tilt angle is tilt angle scope be 0 degree (not containing 0 degree) to 90 degree (not comprising 90 degree), regulation rotor is rotated counterclockwise as just, and tilt angle corresponding to face-to-face state is tilt angle corresponding to back-to-back state 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, by the rectilinear motion adjustment rotor spacing of linear electric motors.
On the static part connection support of described steering wheel, regulated the tilt angle of rotor by the rotary motion of steering wheel, it is face-to-face state and back-to-back state that the tilt angle simultaneously by adjusting two rotors arranges rotor state.
Described force snesor test rotor lift, can select as required one dimension force sensor, 2 D force sensor ..., until six-dimension force sensor.
The voltage transitions that the Data Post of computer system comprises force snesor becomes lift, the electric current of drive motor becomes 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 described in detail.
As shown in Figure 1, a kind of non-planar DCB Specimen aeroperformance dynamic checkout unit that the present invention provides, is made up of full-automatic parameter adjustment part 1, microprocessor unit 2, wireless communication module 3 and computer system 4.Computer system 4 given parameters design load and test initial value, microprocessor unit 2 is sent at a distance by wireless communication module 3, parameter designing value and test initial value signal by microprocessor unit 2 input to full-automatic parameter adjustment part 1 carry out initialization and test, test result is again carried out signal conversion by microprocessor unit 2 and is 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 made up of base 101, column 102, mounting bracket 103, drive motor 104, rotor 105, force snesor 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 force snesor 106, force snesor 106 is fixed on sway brace 107 one end, and sway brace 107 other end connects the motion parts of linear electric motors, by rectilinear motion adjustment rotor 105 spacing 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, regulated the tilt angle of rotor 105 by the rotary motion of steering wheel 109, it is face-to-face state and back-to-back state that the tilt angle simultaneously by adjusting two rotors 105 arranges rotor 105 state; Base 101 and column 102 and the connection between column 102 and mounting bracket 103 can the modes such as with bolts, welding but be not limited to aforesaid way, and 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 the microprocessor unit such as single-chip microcomputer, ARM or DSP as required but be not limited to above-mentioned three kinds, instruction is sent to drive motor 104, steering wheel 109 by PWM, I2C or CAN, sent the voltage and current information of instruction and reception drive motor 104 to linear electric motors 108 by I2C or CAN, force snesor 106 information is gathered by A/D, force snesor 106 tests rotor 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 support duplex mode of operation, when transmitter module 301 is operated in emission mode, receiver module 302 is operated in receiving mode, when receiver module 302 is operated in emission mode, transmitter module 301 is operated in receiving mode, completes the wireless receiving and dispatching of instruction and information; Transmitter module is by 232 or 485 and microprocessor unit both-way communication, and receiver module 302 passes through 485 or 232 with computer system 4 both-way communication.Computer system 4 completes Initial parameter sets and test data post-processing function.The voltage transitions that the Data Post of computer system 4 comprises force snesor 106 becomes lift, the electric current of drive motor 104 becomes power consumption with voltage transitions, and result can select data text, form and curve mode to show.
As shown in Figure 5, need rotor 105 to be adjusted to face-to-face state according to test, tilt angle corresponding to face-to-face state is tilt angle need to be arranged to 0 degree of arbitrarily angled within the scope of 90 degree according to test, but do not comprise 0 degree, also do not comprise 90 degree.
As shown in Figure 6, need rotor 105 to be adjusted to back-to-back state according to test, tilt angle corresponding to back-to-back state is tilt angle need to be arranged to 0 degree of arbitrarily angled within the scope of 90 degree according to test, but do not comprise 0 degree, also do not comprise 90 degree.
Obviously, above-described embodiment is only for clearly example being described, and the restriction not 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 exhaustive without the need to also giving all embodiments.And thus the apparent change of extending out or variation be still among the protection domain of the invention.

Claims (8)

1. a non-planar DCB Specimen aeroperformance dynamic checkout unit, is characterized in that: primarily of full-automatic parameter adjustment part (1), microprocessor unit (2), wireless communication module (3) and computer system (4) composition;
Described full-automatic parameter adjustment part (1) forms primarily of base (101), column (102), mounting bracket (103), drive motor (104), rotor (105), force snesor (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 instruction be sent to linear electric motors (108) and receive the voltage and current information of drive motor (104), be gathered the information of force snesor (106) by A/D;
Described wireless communication module (3) comprises transmitter module (301) and receiver module (302), transmitter module (301) and receiver module (302) support duplex mode of operation, when transmitter module (301) is operated in emission mode, receiver module (302) is operated in receiving mode, when receiver module (302) is operated in emission mode, transmitter module (301) is operated in receiving mode, completes the wireless receiving and dispatching of instruction and information; Transmitter module (301) and microprocessor unit (2) both-way communication, receiver module (302) same to computer system (4) both-way communication;
Described computer system (4) completes Initial parameter sets and test data post-processing function;
Rotor (105) is connected in the rotating shaft of drive motor (104), drive motor (104) is fixed on force snesor (106), force snesor is fixed on sway brace (107) one end, sway brace (107) other end connects the motion parts of linear electric motors (108), by rectilinear motion adjustment rotor (105) spacing 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), regulated the tilt angle of rotor (105) by the rotary motion of steering wheel (109), arrange rotor (105) state by the tilt angle of adjustment two rotors (105) is face-to-face state or back-to-back state simultaneously;
The tilt angle of rotor (105) scope for being greater than 0 °, be less than 90 °.
2. a kind of non-planar DCB Specimen aeroperformance dynamic checkout unit according to claim 1, is characterized in that: described microprocessor unit (2) is single-chip microcomputer, ARM or DSP.
3. a kind of non-planar DCB Specimen aeroperformance dynamic checkout unit according to claim 2, is characterized in that: described microprocessor unit (2) sends instruction by PWM to steering wheel (109); Instruction is sent to linear electric motors (108) by I2C; Instruction is sent to drive motor (104) by CAN.
4. a kind of non-planar DCB Specimen 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 DCB Specimen 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 DCB Specimen 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. according to a kind of non-planar DCB Specimen aeroperformance dynamic checkout unit in claim 1-6 described in any one, it is characterized in that: base (101) and column (102), and the connected mode between column (102) and mounting bracket (103) is that bolt connects or welding.
8. according to a kind of non-planar DCB Specimen aeroperformance dynamic checkout unit in claim 1-6 described in any one, it is characterized in that: two sway brace (107) angular range, for being more than or equal to 60 °, are less than or equal to 180 °.
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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
CN106347705A (en) * 2016-10-31 2017-01-25 安徽理工大学 Rotor lift force testing system for unmanned aerial vehicle
CN107167329B (en) * 2017-06-07 2020-03-03 北京航空航天大学 Aerodynamic loading test device for control surface of asymmetric aircraft
CN108482708B (en) * 2018-03-15 2020-09-01 华南农业大学 Longitudinal double-rotor pneumatic performance 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
CN111216922B (en) * 2020-04-22 2020-07-17 北京清航紫荆装备科技有限公司 Lifting force testing device of cross dual-rotor 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

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CN102180270A (en) * 2011-03-10 2011-09-14 北京航空航天大学 Microminiature rotorcraft experiment platform and application thereof
CN102426458A (en) * 2011-11-28 2012-04-25 北京航空航天大学 Ground control system applicable to rotor-wing unmanned aerial vehicle

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