CN103822741A - Wireless dynamic balance test bench hinge torque measurement method - Google Patents
Wireless dynamic balance test bench hinge torque measurement method Download PDFInfo
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- CN103822741A CN103822741A CN201210464541.0A CN201210464541A CN103822741A CN 103822741 A CN103822741 A CN 103822741A CN 201210464541 A CN201210464541 A CN 201210464541A CN 103822741 A CN103822741 A CN 103822741A
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Abstract
The invention belongs to the technical field of helicopter test, and particularly relates to a blade dynamic balance test bench hinge torque measurement method. According to the method, data measured by a force sensor is transmitted by a transmitting device in a wireless signal mode, and then a receiving device receives the data measured by the force sensor and transfers the data to data acquisition equipment for recording and storing. Namely, when a rotor head drives helicopter blades to rotate on a dynamic balance test bench, the force sensor generates a signal, and the signal is transmitted by the transmitting device above the rotor head in a wireless signal mode, received by the receiving device and transferred to signal acquisition equipment so as to complete data acquisition and recording.
Description
Technical field
The invention belongs to helicopter experimental technique field, particularly relate to a kind of blade dynamic balance test stand hinge moment measuring method.
Background technology
In blade dynamic balance running, the hinge moment measurement of blade is the committed step of dynamic balance running.These data are that power sensor and the signal collecting device by being arranged on testing table rotor head measured.When measurement, rotor head rotates, and the electric signal of sensor is transferred to the data acquisition equipment between control by slip ring system.Slip ring system is mainly made up of synthetic carbon brush and turning axle, the ring-type conducting ring of the mutual insulating that distributing on turning axle, synthetic carbon brush be fix and be pressed on these conducting rings with certain pressure, when measurement, keep and the contacting of the conducting ring of these rotations.Like this, sensor signal is transferred in signal collecting device by conducting ring, synthetic carbon brush.But this cover system exists some shortcomings, need to often safeguard.Because contacting of carbon brush and rotary conducting ring is contact, in the situation that carbon brush pressure is lighter, when rotor head rotation, carbon brush and conducting ring often have the situation of disengagement, cause data transmission to interrupt.In the time that pressure is larger, carbon brush abrasion is serious, easily causes conducting ring short circuit.Meanwhile, slip ring system is subject to the oil pollution of seepage on dynamic balance test stand, causes carbon brush and conducting ring loose contact, makes DATA REASONING inaccurate.
Summary of the invention
Object of the present invention:
Thoroughly solve the inaccurate problem of hinge moment measuring system data causing due to slip ring system loose contact, reduce the maintenance cost of equipment, shorten the maintenance period of measuring system, improve test efficiency.
Technical scheme of the present invention:
Technical conceive of the present invention is: the data by force sensor measuring are launched in the mode of wireless signal by emitter, then the data that received and power sensor lock is measured by receiving trap pass to data acquisition equipment and record and preserve.When driving helicopter blade, rotates on dynamic balance running stage body rotor head, power sensor has just produced signal and has been launched with wireless form by the emitter of rotor head top, received by receiving trap, and pass to signal collecting device data acquisition record.
Dynamic balance test stand hinge moment wireless measurement method, system in this method comprises power sensor, emitter, receiving trap and signal collecting device, wherein, rotor head is arranged on blade dynamic balance running stage body, helicopter blade is arranged on rotor head, and power installation of sensors is on rotor head, and emitter is arranged on center, rotor head upper end, power sensor is connected with emitter by wire, and receiving trap is connected with signal collecting device by wire.
This method comprises the steps:
The first step: energising, system is carried out to preheating.
Second step: start dynamic balance test stand, make blade reach rotating speed, while making blade cutting air by changing pitch, the suffered power of blade leading edge is installed in the force sensor measuring on propeller hub.
The 3rd step: power sensor passes to the signal collecting the wireless signal transmitting device being arranged on rotor head.
The 4th step: wireless signal transmitting device converts the electrical signal to wireless signal the form transmitting with wireless signal.
The 5th step: radio receiver receives signal and also signal passed to computing machine, computing machine, and shows with digital form signal-obtaining by software, completes data recording by computer operator.
Technique effect of the present invention:
The invention effect of this Helicopter Blade Dynamic Balance Test table-hinges chain torgue measurement system is: the slip ring system that has solved original system existence easily comes in contact bad problem, simulating signal has just been carried out digital signal conversion at front end, in signals transmission, antijamming capability is strong, reliable and stable after the data demodulates receiving, reduce the maintenance cost of equipment, the maintenance period of shortening system, has improved test efficiency.
Accompanying drawing explanation
Fig. 1 is system scheme of installation of the present invention.Wherein, 1. blade dynamic balance running stage body 2. rotor head 3. power sensor 4. helicopter blade 5. emitter 6. receiving trap 7. signal collecting devices.
Embodiment
(1) system connects
(2) system operating process
The first step switches on power, open wireless measuring system.
Second step starts dynamic balance test stand, and rotor head drives helicopter blade rotation, produces signal.
The 3rd step to the signal receiving by wireless device analyze, record, complete measurement.
The 4th step powered-down.
Claims (1)
1. dynamic balance test stand hinge moment wireless measurement method, system in this method comprises power sensor, emitter, receiving trap and signal collecting device, wherein, rotor head is arranged on blade dynamic balance running stage body, helicopter blade is arranged on rotor head, and power installation of sensors is on rotor head, and emitter is arranged on center, rotor head upper end, power sensor is connected with emitter by wire, and receiving trap is connected with signal collecting device by wire; This method comprises the steps:
The first step: energising, system is carried out to preheating;
Second step: start dynamic balance test stand, make blade reach rotating speed, while making blade cutting air by changing pitch, the suffered power of blade leading edge is installed in the force sensor measuring on propeller hub;
The 3rd step: power sensor passes to the signal collecting the wireless signal transmitting device being arranged on rotor head;
The 4th step: wireless signal transmitting device converts the electrical signal to wireless signal the form transmitting with wireless signal;
The 5th step: radio receiver receives signal and also signal passed to computing machine, computing machine, and shows with digital form signal-obtaining by software, completes data recording by computer operator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210464541.0A CN103822741B (en) | 2012-11-16 | 2012-11-16 | Dynamic balance test stand hinge moment wireless measurement method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210464541.0A CN103822741B (en) | 2012-11-16 | 2012-11-16 | Dynamic balance test stand hinge moment wireless measurement method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103822741A true CN103822741A (en) | 2014-05-28 |
| CN103822741B CN103822741B (en) | 2016-06-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210464541.0A Expired - Fee Related CN103822741B (en) | 2012-11-16 | 2012-11-16 | Dynamic balance test stand hinge moment wireless measurement method |
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| CN (1) | CN103822741B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104122017A (en) * | 2013-04-24 | 2014-10-29 | 哈尔滨飞机工业集团有限责任公司 | Hinge moment measurement system of helicopter main blade dynamic balance testing bench |
| CN105277314A (en) * | 2014-07-08 | 2016-01-27 | 哈尔滨飞机工业集团有限责任公司 | Helicopter blade dynamic balance experiment platform hinge moment parameter correction method |
| CN106394931A (en) * | 2016-11-28 | 2017-02-15 | 中国科学院长春光学精密机械与物理研究所 | Multifunctional electric detecting platform for propeller of unmanned aerial vehicle |
| CN110132455A (en) * | 2019-05-17 | 2019-08-16 | 浙江大学 | A kind of circle spool bottom surface unbalanced moments measuring device and measuring method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1844872A (en) * | 2005-12-29 | 2006-10-11 | 南京航空航天大学 | Optical fiber grating sensing system for measuring distribution load on rotating wings |
| CN101811566A (en) * | 2010-03-03 | 2010-08-25 | 上海交通大学 | Underwater servo propeller |
| US20110246095A1 (en) * | 2010-04-05 | 2011-10-06 | Km Digitech Co., Ltd. | Apparatus for detecting erroneous cable stripping |
| CN102288338A (en) * | 2011-07-08 | 2011-12-21 | 哈尔滨飞机工业集团有限责任公司 | Method for measuring load of rotor wing |
-
2012
- 2012-11-16 CN CN201210464541.0A patent/CN103822741B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1844872A (en) * | 2005-12-29 | 2006-10-11 | 南京航空航天大学 | Optical fiber grating sensing system for measuring distribution load on rotating wings |
| CN101811566A (en) * | 2010-03-03 | 2010-08-25 | 上海交通大学 | Underwater servo propeller |
| US20110246095A1 (en) * | 2010-04-05 | 2011-10-06 | Km Digitech Co., Ltd. | Apparatus for detecting erroneous cable stripping |
| CN102288338A (en) * | 2011-07-08 | 2011-12-21 | 哈尔滨飞机工业集团有限责任公司 | Method for measuring load of rotor wing |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104122017A (en) * | 2013-04-24 | 2014-10-29 | 哈尔滨飞机工业集团有限责任公司 | Hinge moment measurement system of helicopter main blade dynamic balance testing bench |
| CN105277314A (en) * | 2014-07-08 | 2016-01-27 | 哈尔滨飞机工业集团有限责任公司 | Helicopter blade dynamic balance experiment platform hinge moment parameter correction method |
| CN105277314B (en) * | 2014-07-08 | 2018-03-02 | 哈尔滨飞机工业集团有限责任公司 | A kind of Helicopter Blade Dynamic Balance Test platform hinge moment parameter correction method |
| CN106394931A (en) * | 2016-11-28 | 2017-02-15 | 中国科学院长春光学精密机械与物理研究所 | Multifunctional electric detecting platform for propeller of unmanned aerial vehicle |
| CN110132455A (en) * | 2019-05-17 | 2019-08-16 | 浙江大学 | A kind of circle spool bottom surface unbalanced moments measuring device and measuring method |
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| Publication number | Publication date |
|---|---|
| CN103822741B (en) | 2016-06-22 |
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Granted publication date: 20160622 Termination date: 20171116 |
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