CN103822741B - Dynamic balance test stand hinge moment wireless measurement method - Google Patents
Dynamic balance test stand hinge moment wireless measurement method Download PDFInfo
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- CN103822741B CN103822741B CN201210464541.0A CN201210464541A CN103822741B CN 103822741 B CN103822741 B CN 103822741B CN 201210464541 A CN201210464541 A CN 201210464541A CN 103822741 B CN103822741 B CN 103822741B
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- signal
- rotor head
- dynamic balance
- blade
- force transducer
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Abstract
The invention belongs to helicopter experimental technique field, particularly relate to a kind of blade dynamic balance test stand hinge moment measuring method。This method will be launched by discharger by the data of force sensor measuring in the way of wireless signal, then received by receiving device and the data that force transducer lock is measured are passed to data acquisition equipment record and preserved。Namely when rotor head drives helicopter blade to rotate on dynamic balance running stage body, force transducer just creates signal and is launched with wireless form by the discharger above rotor head, is received by receiving device, and passes to signal collecting device data acquisition record。
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 the force transducer by being arranged on testing stand rotor head and signal collecting device measurement。During measurement, rotor head is to rotate, and the signal of telecommunication of sensor is transferred to the data acquisition equipment between control by slip ring system。Slip ring system is mainly made up of synthesis carbon brush and rotating shaft, and rotating shaft is dispersed with the annular conductive ring of mutual insulating, and synthesis carbon brush is fixing and is pressed on these conducting rings with certain pressure, the contact of the conducting ring of maintenance and these rotations during measurement。So, sensor signal is transferred in signal collecting device by conducting ring, synthesis carbon brush。But this cover system there are disadvantages that, it is necessary to often safeguards。Owing to the contact of carbon brush and rotary conducting ring is contact, when carbon brush pressure is lighter, when rotor head rotates, carbon brush and conducting ring often have the situation of disengagement, cause data-transmission interruptions。When pressure is bigger, carbon brush abrasion is serious, it is easy to cause conducting ring short circuit。Meanwhile, the oil pollution that slip ring system is subject on dynamic balance test stand seepage, causes carbon brush and conducting ring loose contact, makes DATA REASONING inaccurate。
Summary of the invention
The purpose of the present invention:
Thoroughly solve the hinge moment owing to slip ring system loose contact causes and measure the inaccurate problem of system data, reduce the maintenance cost of equipment, shorten the maintenance period of measurement system, improve test efficiency。
Technical scheme:
The technology design of the present invention is: will be launched in the way of wireless signal by discharger by the data of force sensor measuring, then is received by receiving device and the data that force transducer lock is measured are passed to data acquisition equipment record and preserved。Namely when rotor head drives helicopter blade to rotate on dynamic balance running stage body, force transducer just creates signal and is launched with wireless form by the discharger above rotor head, is received by receiving device, and passes to signal collecting device data acquisition record。
Dynamic balance test stand hinge moment wireless measurement method, system in this method includes force transducer, discharger, reception device and signal collecting device, wherein, rotor head is arranged on blade dynamic balance running stage body, helicopter blade is arranged on rotor head, and force transducer is arranged on rotor head, and discharger is arranged on rotor head upper end center position, force transducer is connected with discharger by wire, receives device and is connected with signal collecting device by wire。
This method comprises the steps:
The first step: energising, preheats system。
Second step: start dynamic balance test stand, make blade reach rotating speed, the power force sensor measuring that is installed on propeller hub suffered by blade leading edge when making blade cutting air by changing pitch。
3rd step: the signal collected is passed to the wireless signal transmitting device being arranged on rotor head by force transducer。
4th step: wireless signal transmitting device converts the electrical signal to wireless signal and launches with the form of wireless signal。
5th step: radio receiver receives signal and signal passes to computer, computer passes through software by signal-obtaining, and shows in digital form, computer operator complete data record。
The technique effect of the present invention:
This Helicopter Blade Dynamic Balance Test platform hinge moment measures the invention effect of system: solve the problem that the slip ring system of original system existence is susceptible to loose contact, analogue signal has just carried out digital signal conversion in front end, in signals transmission, capacity of resisting disturbance is strong, the data received are reliable and stable after demodulating, decrease the maintenance cost of equipment, the maintenance period of shortening system, improves test efficiency。
Accompanying drawing explanation
Fig. 1 is the system scheme of installation of the present invention。Wherein, 1. blade dynamic balance running stage body 2. rotor head 3. force transducer 4. helicopter blade 5. discharger 6. receives device 7. signal collecting device。
Detailed description of the invention
(1) system connects
Rotor head 2 is arranged on blade dynamic balance running stage body 1, and helicopter blade 4 is arranged on rotor head 2, and force transducer 3 is arranged on rotor head 2, and discharger 5 is arranged on rotor head 2 upper end center position, and force transducer 2 is connected with discharger 5 by wire。Receive device 6 to be connected with signal collecting device 7 by wire。
(2) system operation procedure
The first step switches on power, and opens wireless measuring system。
Second step starts dynamic balance test stand, and rotor head drives helicopter blade to rotate, and produces signal。
The signal received by wireless device is analyzed by the 3rd step, record, completes to measure。
4th step closes power supply。
Claims (1)
1. dynamic balance test stand hinge moment wireless measurement method, system in this method includes force transducer, discharger, reception device and signal collecting device, wherein, rotor head is arranged on blade dynamic balance running stage body, helicopter blade is arranged on rotor head, and force transducer is arranged on rotor head, and discharger is arranged on rotor head upper end center position, force transducer is connected with discharger by wire, receives device and is connected with signal collecting device by wire；It is characterized in that, this method comprises the steps:
The first step: energising, preheats system；
Second step: start dynamic balance test stand, make blade reach rotating speed, the power force sensor measuring that is installed on propeller hub suffered by blade leading edge when making blade cutting air by changing pitch；
3rd step: the signal collected is passed to the wireless signal transmitting device being arranged on rotor head by force transducer；
4th step: wireless signal transmitting device converts the electrical signal to wireless signal and launches with the form of wireless signal；
5th step: radio receiver receives signal and signal passes to computer, computer passes through software by signal-obtaining, and shows in digital form, computer operator complete data record。
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 CN103822741A (en) | 2014-05-28 |
| CN103822741B true CN103822741B (en) | 2016-06-22 |
Family
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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 |
Country Status (1)
| Country | Link |
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| CN (1) | CN103822741B (en) |
Families Citing this family (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 |
| 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 |
| CN110132455B (en) * | 2019-05-17 | 2020-03-17 | 浙江大学 | Device and method for measuring unbalanced moment of bottom surface of circular valve core |
Citations (3)
| 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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8452549B2 (en) * | 2010-04-05 | 2013-05-28 | Km Digitech Co., Ltd. | Apparatus for detecting erroneous cable stripping |
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2012
- 2012-11-16 CN CN201210464541.0A patent/CN103822741B/en not_active Expired - Fee Related
Patent Citations (3)
| 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 |
| 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 |
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| Publication number | Publication date |
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| CN103822741A (en) | 2014-05-28 |
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| C14 | Grant of patent or utility model | ||
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160622 Termination date: 20171116 |