CN103207064B - Aircraft handling system load mechanism in-situ test system - Google Patents
Aircraft handling system load mechanism in-situ test system Download PDFInfo
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- CN103207064B CN103207064B CN201210517624.1A CN201210517624A CN103207064B CN 103207064 B CN103207064 B CN 103207064B CN 201210517624 A CN201210517624 A CN 201210517624A CN 103207064 B CN103207064 B CN 103207064B
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Abstract
The present invention relates to a kind of aircraft handling system load mechanism in-situ test system, this system comprises Portable Reinforced Computer and test set, test set comprises control stick and jociey stick jig, it is connected with force transducer between control stick and jociey stick jig, being provided with angle sensor device on jociey stick jig, force transducer and angle sensor device are electrically connected with the pci data capture card being plugged on safety fuse reinforcing computer respectively. Present configuration is simple, volume is little, easy to operate, real-time, quick, accurate, the reliable and safe test of jociey stick stick force and bar displacement can be realized, and automatically generate stick force-bar displacement curve by test software, thus realize the performances evaluation to load mechanism, solve the difficult problem that aviation maintenance support unit lacks test set and load mechanism can not carry out in situ detection.
Description
Technical field
What the present invention relates to is a kind of aircraft handling system test system, is specifically related to a kind of aircraft handling system load mechanism in-situ test system.
Background technology
Aircraft handling system is used for for pilot's operating aircraft around the longitudinal axis, transverse axis and vertical shaft rotary, to change or to keep the flight state of aircraft, is aircraft very important system. The maneuvering system of present generation aircraft is to return power maneuvering system substantially, act on the aerodynamic force on aircraft handling rudder face can not anti-pass to jociey stick. Handle jociey stick for making pilot and have truly feels, maneuvering system is provided with load mechanism, be used for producing suitable steering force, and in can automatically returning when pilot unclamps jociey stick. Such as, horizontal tail load mechanism is used for forming longitudinal steering force, and steering force is changed along with the change of the stroke of jociey stick, flight indicated airspeed and height; Aileron load mechanism is used for being formed and laterally handles stick force, and the size of steering force is directly proportional to jociey stick stroke. Load mechanism is the important accessory of aircraft handling system, if the work of load mechanism is abnormal, aircraft handling system can be caused to occur, and bar is heavy, bar is light or bar leather strap fault, stick force gradient is changed, change of flight person handles custom and sensation normally, the performance of In-Flight Performance all can be caused direct impact by these, even jeopardizes flight safety. Therefore, by the vertical and horizontal stick force-bar displacement of jociey stick is carried out periodic detection, it is achieved to the performance test of load mechanism, ensure that its performance is normally, reliably an important and day-to-day work of aviation maintenance support unit.
At present, the testing apparatus that aircraft handling system load mechanism is not detected by aviation maintaining unit, cannot realize the in situ test to load mechanism. Although the detection of offing normal to load mechanism can be realized, but adds the dismounting workload of load mechanism, extend the troubleshooting time, reduce working efficiency, have impact on the serviceability rate of aircraft, seriously constrain carrying out of aviation maintenance support work.
Summary of the invention
It is an object of the invention to for the problems referred to above that the load mechanism in existing aircraft handling system exists in aviation maintenance support works, provide a kind of aircraft handling system load mechanism in-situ test system for the load mechanism performance index integration test in aircraft handling system, this system operation is simple, safe and reliable, can judge whether normal jociey stick is handled according to technological standard, thus whether the performance judging load mechanism meets the requirements, to meet aviation maintenance support unit regular inspection, troubleshooting, the needs that jociey stick stick force and displacement measurement are worked after installing by new product.
The technical scheme of the present invention is: a kind of aircraft handling system load mechanism in-situ test system, this system comprises Portable Reinforced Computer and test set, test set comprises control stick and jociey stick jig, it is connected with force transducer between control stick and jociey stick jig, being provided with angle sensor device on jociey stick jig, force transducer and angle sensor device are electrically connected with the pci data capture card being plugged on safety fuse reinforcing computer respectively.
Preferably, control stick comprises connecting rod and is connected to the handle at connecting rod two ends, and the middle portion of connecting rod is connected with force transducer.
Preferably, jociey stick jig comprises card hoop and the gripping unit for control card hoop clamping degree, and card hoop is connected with support, and force transducer is connected with support; Being provided with fixed block on support, angle sensor device is arranged on support by fixed block.
Preferably, force transducer adopts and draws/pressure transmitter.
Preferably, Portable Reinforced Computer adopts 220V ac power supply, or uses machine load 27V DC power supply by inversion power supply.
The useful effect of the present invention is: (1) present configuration is simple, volume is little, easy to operate, real-time, quick, accurate, the reliable and safe test of jociey stick stick force and bar displacement can be realized, and automatically generate stick force-bar displacement curve by test software, thus realize the performances evaluation to load mechanism, solve the difficult problem that aviation maintenance support unit lacks test set and load mechanism can not carry out in situ detection. (2) the present invention adopts Portable Reinforced Computer to realize the functions such as the real-time display of data, storage, printing, inquiry, is convenient to carry, it is possible to use under various severe environment; And the force data of whole test process and the real-time collection of displacement data and storage is completed by the pci data capture card being plugged in Portable Reinforced Computer, it is achieved the automatization of data gathering. (3) Portable Reinforced Computer of the present invention adopts 220V ac power supply, it is also possible to uses machine load 27V DC power supply by inversion power supply, makes in Site Detection process without the need to 220V AC power guarantee. (4) the present invention adopts angle sensor device and drawing/pressure transmitter to detect the stick force and displacement data handling jociey stick, and directly it is sent to pci data capture card, the data of sensor collection precision in transport process is not lost, test precision height, angular travel measuring accuracy can reach 0.1 degree, and power measuring accuracy can reach 0.02%FS. (5) the present invention can the performance of load mechanism in situ test aircraft handling system, highly versatile, means of testing advanced person, precision height, reliable operation, easy to operate and be convenient to care and maintenance, to raising airplane readiness, it is ensured that flight safety is all by significant.
Accompanying drawing explanation
Fig. 1 is the test set structural representation of the specific embodiment of the invention.
Fig. 2 is the Controlling System block diagram of the specific embodiment of the invention.
Embodiment
Below in conjunction with accompanying drawing, the invention will be further described.
Embodiment: a kind of aircraft handling system load mechanism in-situ test system, this system comprises Portable Reinforced Computer and test set, test set comprises control stick and jociey stick jig, force transducer 1 it is connected with between control stick and jociey stick jig, being provided with angle sensor device 2 on jociey stick jig, force transducer 1 and angle sensor device 2 are electrically connected with the pci data capture card being plugged in Portable Reinforced Computer respectively.
For the ease of the operation to control stick, above-mentioned control stick comprises connecting rod 3 and is connected to the handle 4 at connecting rod 3 two ends, and the middle portion of connecting rod 3 is connected with force transducer 1.
For the ease of being arranged on jociey stick by test set of the present invention, above-mentioned jociey stick jig comprises card hoop 5 and the gripping unit 6 for control card hoop 5 clamping degree, and card hoop 5 is connected with support 7, and force transducer 1 is connected with support 7; Being provided with fixed block 8 on support 7, angle sensor device 2 is arranged on support by fixed block 8.
In order to meet the test precision of force data, above-mentioned force transducer 1 adopts and draws/pressure transmitter, and its precision reaches 0.02%FS.
Portable Reinforced Computer adopts 220V ac power supply, or uses machine load 27V DC power supply by inversion power supply.
The in situ test of aircraft handling system load mechanism by testing and the stick force-bar displacement curve drawing jociey stick realize. During test, jociey stick jig is arranged on jociey stick, by joystick manipulation jociey stick, complete jociey stick stick force-bar displacement when the aircraft big arm of force of horizontal tail maneuvering system, the middle arm of force, little arm of force state, and the detection of Aileron control system jociey stick stick force-bar displacement data. By in joystick manipulation jociey stick working process, pci data capture card gathers in real time and preserves the power and displacement data that measure by force transducer and angle sensor device, Portable Reinforced Computer reads in pci data capture card the power and displacement data that store, and draw out corresponding stick force-bar displacement curve, judge whether jociey stick stick force-bar displacement curve meets the requirements according to technological standard, thus judge that load mechanism performance is whether normal, and the storage of test data and stick force-bar displacement curve, inquiry and printing can be realized.
Claims (4)
1. an aircraft handling system load mechanism in-situ test system, it is characterized in that: this system comprises Portable Reinforced Computer and test set, test set comprises control stick and jociey stick jig, it is connected with force transducer between control stick and jociey stick jig, being provided with angle sensor device on jociey stick jig, force transducer and angle sensor device are electrically connected with the pci data capture card being plugged in Portable Reinforced Computer respectively; Jociey stick jig comprises card hoop and the gripping unit for control card hoop clamping degree, and card hoop is connected with support, and force transducer is connected with support; Being provided with fixed block on support, angle sensor device is arranged on support by fixed block.
2. as claimed in claim 1 aircraft handling system load mechanism in-situ test system, it is characterised in that: control stick comprises connecting rod and is connected to the handle at connecting rod two ends, and the middle portion of connecting rod is connected with force transducer.
3. aircraft handling system load mechanism in-situ test system as described in claim 1 to 2 any one, it is characterised in that: force transducer adopts and draws/pressure transmitter.
4. aircraft handling system load mechanism in-situ test system as described in claim 1 to 2 any one, it is characterised in that: Portable Reinforced Computer adopts 220V ac power supply, or uses machine load 27V DC power supply by inversion power supply.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210517624.1A CN103207064B (en) | 2012-12-06 | 2012-12-06 | Aircraft handling system load mechanism in-situ test system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210517624.1A CN103207064B (en) | 2012-12-06 | 2012-12-06 | Aircraft handling system load mechanism in-situ test system |
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| CN103207064A CN103207064A (en) | 2013-07-17 |
| CN103207064B true CN103207064B (en) | 2016-06-01 |
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| CN105716838A (en) * | 2014-12-03 | 2016-06-29 | 中国飞机强度研究所 | Single-point double force control actuator cylinder servo loading method |
| CN105511258B (en) * | 2015-11-27 | 2019-03-22 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of boarding gate operator reliability test autocontrol method and device |
| CN106768582B (en) * | 2016-11-30 | 2019-08-16 | 江西洪都航空工业集团有限责任公司 | A kind of tandem cockpit pilot manipulation force measuring device |
| CN107192549B (en) * | 2017-07-13 | 2020-04-28 | 江西洪都航空工业集团有限责任公司 | Aircraft steering column static characteristic measuring device |
| CN111751039A (en) * | 2019-03-27 | 2020-10-09 | 天津莱特兄弟科技有限公司 | QTG test tool and test method thereof |
| CN111003206B (en) * | 2019-12-06 | 2021-11-09 | 江西洪都航空工业集团有限责任公司 | Airplane steering column starting force and operating force detection equipment and detection method |
| CN110979640B (en) * | 2019-12-25 | 2023-03-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Method and circuit for cutting off autopilot by lever force sensor |
| CN112798271B (en) * | 2020-12-25 | 2023-03-28 | 兰州飞行控制有限责任公司 | Test equipment and test method for pitching operation of main flight control cockpit device |
| CN112798272B (en) * | 2020-12-25 | 2023-07-21 | 兰州飞行控制有限责任公司 | Testing equipment and testing method for rolling operation of main flight control cockpit device |
| CN114061976B (en) * | 2021-11-15 | 2024-05-17 | 一汽红塔云南汽车制造有限公司 | Evaluation method for speed change operation of manual transmission automobile |
| CN114104333B (en) * | 2021-11-22 | 2024-06-04 | 中国商用飞机有限责任公司 | Steering wheel measuring device |
| CN114228978A (en) * | 2021-12-27 | 2022-03-25 | 中国航空工业集团公司西安飞机设计研究所 | Airplane control system with balancing mechanism |
| CN114295272A (en) * | 2022-01-11 | 2022-04-08 | 中国人民解放军空军工程大学航空机务士官学校 | Steering column force rod displacement tester |
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| JP2002022615A (en) * | 2000-07-13 | 2002-01-23 | Sumitomo Wiring Syst Ltd | Method for evaluating spring characteristics at part subjected to bending and jig for measuring evaluation data |
| JP2006010324A (en) * | 2004-06-22 | 2006-01-12 | Nec Access Technica Ltd | Operation lever durability test machine |
| CN200979674Y (en) * | 2006-12-15 | 2007-11-21 | 山东超越数控电子有限公司 | A portable reinforced computer with double-display |
| CN201336010Y (en) * | 2009-02-05 | 2009-10-28 | 济南腾越电子有限公司 | Upturned portable-type ruggedized computer |
| CN201607670U (en) * | 2010-03-25 | 2010-10-13 | 山东超越数控电子有限公司 | Downward-turning portable ruggedized computer based on CPCI bus |
| CN102175378B (en) * | 2010-12-29 | 2013-06-12 | 中国商用飞机有限责任公司 | Measuring jigs for steering column and steering wheel |
| CN202033692U (en) * | 2011-01-21 | 2011-11-09 | 上海爱瑞科技发展有限公司 | Portable and high-performance three-dimensional display device with multiple slot positions |
| CN102645325A (en) * | 2011-02-22 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Airplane operation torque and operation angular displacement simulating method |
| CN102269636A (en) * | 2011-04-22 | 2011-12-07 | 支怡 | Airplane control wheel multi-dimensional force and displacement measuring device and method |
| CN102252796A (en) * | 2011-04-22 | 2011-11-23 | 支怡 | Aircraft control stick force and displacement measuring device and measuring method thereof |
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Inventor after: Wang Zhanyong Inventor after: Liu Zhengang Inventor after: Tang Yuanheng Inventor after: Zou Gang Inventor after: Zhang Ding Inventor after: Tang Youcai Inventor after: Guo Gang Inventor before: Zhou Kai Inventor before: Tang Youcai Inventor before: Zou Gang Inventor before: Wang Zhanyong Inventor before: Liu Zhengang Inventor before: Guo Gang |
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