CN2419590Y - Device for testing range of buffer for undercarriage unit landing shocks - Google Patents
Device for testing range of buffer for undercarriage unit landing shocks Download PDFInfo
- Publication number
- CN2419590Y CN2419590Y CN 99249075 CN99249075U CN2419590Y CN 2419590 Y CN2419590 Y CN 2419590Y CN 99249075 CN99249075 CN 99249075 CN 99249075 U CN99249075 U CN 99249075U CN 2419590 Y CN2419590 Y CN 2419590Y
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- displacement
- undercarriage
- photoelectric encoder
- wheel
- test wheel
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Abstract
The utility model relates to a travel test unit of a landing gear drop impact buffer, which is characterized in that a photoelectric encoder is connected with a displacement test wheel. A displacement transmission strip is contacted with the displacement test wheel in a flexible sliding friction mode. A rolling-shaped tension spring is connected with the displacement transmission strip. The upper side and the lower side of the displacement test wheel are respectively provided with a guiding press wheel. The photoelectric encoder, the displacement test wheel, the guiding press wheel and the rolling-shaped tension spring are fixed to a main shaft of a landing gear by a detachable movable connecting component so as to ensure that the structure and the strength of landing gear airplane wheels can not be damaged. The utility model has the advantages that the displacement test wheel is contacted with the displacement transmission strip in a flexible mode, and therefore, the photoelectric encoder can exactly measure rotation pulse data by the rotation angle variation of the displacement test wheel under the condition of strong impact vibration. The dynamic variation process of the momentary landing gear buffer travel of airplane landing can be calculated by a computer.
Description
The utility model belongs to undercarriage landing shock draft gear travel proving installation, particularly in the landing gear drop test process, and the device that the impact dynamic changing process of aircraft landing instant undercarriage draft gear travel is tested.
Aircraft is impacting landing instant, and the dynamic change of its undercarriage draft gear travel is that be hit load and merit of research and analysis undercarriage put the important parameter of absorption.The work of the impact dynamic changing process of survey aircraft landing instant undercarriage draft gear travel has very important engineering significance for aircraft safety landing design.Because the landing to impact of aircraft occurs in very short moment, the undercarriage impact damper only has several seconds at zero point from static to the time that reaches the maximum cushioning displacement, and this in a flash the variation range of undercarriage draft gear travel can reach hundreds of millimeters.Want in several seconds at zero point, to the high speed of aircraft landing instant undercarriage draft gear travel, dynamic changing process is measured on a large scale, its difficulty is very big.
Because undercarriage is subjected to high speed impact power at landing instant, can cause that undercarriage produces the displacement of elastic impact on a large scale and the vibration of hundreds of millimeter, be installed in impact damper on the undercarriage except producing along the linear slide displacement of undercarriage major axes orientation, also can produce strong transverse judder and elasticity swing offset, test environment is abominable.If use existing linear displacement transducer, owing to be that accurate compactness is slidingly matched between the rigidity linear telescopic pull bar of sensor and sensor main body, in test process, can be because the transverse judder and the elasticity swing offset of impact damper, make the linear telescopic pull bar of linear displacement transducer produce distortion, the linear telescopic pull bar often can't be free to slide, and the stuck phenomenon of telescopic lever in the experimentation can occur.Therefore, at present domestic also can't be in the drop-test process, the impact dynamic changing process of undercarriage landing instant draft gear travel is measured and record exactly.
The purpose of this utility model is, design and produce a kind of undercarriage landing shock draft gear travel proving installation, measure with the record drop-test in, the impact dynamic changing process of aircraft landing instant undercarriage draft gear travel is for the Safety Design and the use of undercarriage provides authentic data.
The utility model undercarriage landing shock draft gear travel proving installation is made up of photoelectric encoder, displacement measurement wheel, displacement transmission band, guiding pinch roller, scroll extension spring, web member and computing machine.It is characterized in that: at the aircraft landing instant, the undercarriage buffer generating be out of shape on a large scale and the situation with judder under, measure the transient impact change in displacement of undercarriage impact damper, special the displacement measurement partial design is become flexible structure.The displacement measurement wheel is installed on photoelectric encoder, adopts Flexible Sliding rubbing contact mode between high strength elastic transmission band and the displacement measurement wheel, make the photoelectric encoder that fuses with the displacement measurement wheel accept the displacement signal of impact damper.And the scroll extension spring is installed on undercarriage main shaft top, and is connected with high strength elastic transmission band, by the tension force and the elasticity of scroll extension spring, make displacement transmission band maintenance linear state.For guaranteeing the reliability of rubbing contact between displacement transmission band and the displacement measurement wheel, two surveys up and down at the displacement testing wheel respectively are equipped with a guiding pinch roller, in order to contact area and the friction force between increase transmission band and the displacement measurement wheel, and can isolate the shake that undercarriage impacts elastic displacement transmission band in the process that lands.Damage undercarriage in order in test process, displacement tester not to be installed because of punching, parts such as photoelectric encoder, displacement measurement wheel, guiding pinch roller, scroll extension spring all use detachable active connection to be fixed on undercarriage main shaft and the impact damper, to guarantee not destroy the structure and the intensity of undercarriage.After test finishes active connection and other test component are taken off from undercarriage, expensive undercarriage also can normally use.
The course of work of the present utility model is as follows: when aircraft landing, undercarriage high speed impact ground, in order to absorb impact energy, impact strength when slowing down few aircraft landing, the telescopic moving up and down of impact damper on the undercarriage main shaft, the displacement that is installed on the impact damper is transmitted band also along with the flexible of impact damper moves up and down, simultaneous displacement transmission band drives the rotation of displacement measurement wheel, the displacement measurement wheel that is connected with photoelectric encoder changes straight-line displacement into time dependent corner displacement, photoelectric encoder and displacement measurement wheel rotate synchronously, and corner displacement is become electric impulse signal.Impact the time dependent electric pulse data of time 7 photoelectric coder that land by undercarriage under the computer recording, can calculate in impact process the situation of change of each draft gear travel moment, and then provide the dynamic changing curve of draft gear travel in the impact process.
The utility model has the advantages that: the displacement measurement wheel of this undercarriage landing shock draft gear travel proving installation becomes flexible connection mode with displacement transmission strip design, avoided undercarriage in the process of landing, owing to the high vibration and the swing offset of impact damper, the jammed phenomenon of linear telescopic pull bar of displacement transducer appears.Therefore photoelectric encoder can be under the intense impact vibration condition, and the corner variation of taking turns by displacement measurement provides electric impulse signal, is gone out the dynamic changing process of aircraft landing instant undercarriage buffer offset by COMPUTER CALCULATION.For in process of the test, do not damage expensive undercarriage, parts such as the photoelectric encoder of this undercarriage landing shock draft gear travel proving installation, displacement measurement wheel, guiding pinch roller, scroll extension spring, all use detachable active connection to be fixed on undercarriage main shaft and the impact damper, on undercarriage, do not beat mounting hole, do not destroy the structure of undercarriage.After test finishes active connection and other test component are taken off from undercarriage, expensive undercarriage also can normally use.
Below in conjunction with drawings and Examples, the utility model will be further described:
Fig. 1 is the organigram of undercarriage landing shock draft gear travel proving installation;
Fig. 2 is the side view of undercarriage landing shock draft gear travel proving installation;
Fig. 3 is to use the dynamic changing curve figure of the aircraft landing instant cushion stroke that this undercarriage landing shock draft gear travel proving installation records.
As seen from the figure, the utility model undercarriage landing shock draft gear travel proving installation is made up of with computing machine 7 displacement transmission band 3, guiding pinch roller 4, scroll extension spring 5, web member 6 that photoelectric encoder 1, displacement measurement wheel 2, flexible steel wire are made.Photoelectric encoder 1, displacement measurement wheel 2, guiding pinch roller 4 are fixed on the undercarriage main shaft 11 with scroll extension spring 5 usefulness web members 6.One end of displacement transmission band 3 is fixed on the wheel axle 8, and the other end fuses with scroll extension spring 5 with connecting dop 9.
Like this, when undercarriage high speed impact ground, impact damper 10 is along the telescopic moving about in the of 11 of undercarriage main shaft, displacement transmission band 3 is along with the flexible of impact damper 10 moves up and down, because the scalability of scroll extension spring 5 also has very strong tension force, make displacement transmission band 3 remain linear state in test process, displacement transmission band 3 is made by flexible steel wire, has eliminated the phenomenon that slide unit is stuck in the intense impact vibration.Displacement transmission band 3 drives 2 rotations of displacement measurement wheel with 2 frictions of displacement measurement wheel, and photoelectric encoder 1 and displacement measurement wheel 2 rotation synchronously change straight-line displacement into time dependent corner displacement, and corner displacement is transformed into electric impulse signal.Send into computing machine 7 through lead 12 and store and displacement calculating, obtain dynamic changing curve 13 (see figure 3)s of undercarriage landing shock draft gear travel.
Claims (1)
1, a kind of undercarriage landing shock draft gear travel proving installation, by photoelectric encoder, the displacement measurement wheel, displacement transmission band, the guiding pinch roller, the scroll extension spring, web member and computing machine are formed, it is characterized in that, photoelectric encoder is connected with the displacement measurement wheel, between transmitting band and displacement measurement is taken turns, displacement contacts for sliding friction, the scroll extension spring is connected with displacement transmission band, each installs guiding pinch roller two surveys up and down of displacement measurement wheel, described photoelectric encoder, the displacement measurement wheel, guiding pinch roller and scroll extension spring are fixed on the undercarriage main shaft by web member, and computing machine is connected with photoelectric encoder by lead.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 99249075 CN2419590Y (en) | 1999-10-28 | 1999-10-28 | Device for testing range of buffer for undercarriage unit landing shocks |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 99249075 CN2419590Y (en) | 1999-10-28 | 1999-10-28 | Device for testing range of buffer for undercarriage unit landing shocks |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2419590Y true CN2419590Y (en) | 2001-02-14 |
Family
ID=34034128
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 99249075 Expired - Fee Related CN2419590Y (en) | 1999-10-28 | 1999-10-28 | Device for testing range of buffer for undercarriage unit landing shocks |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2419590Y (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101405589B (en) * | 2006-03-16 | 2011-01-12 | 空中客车英国有限公司 | Testing strut assembly |
| CN102020014A (en) * | 2010-12-09 | 2011-04-20 | 南京航空航天大学 | Airplane landing gear with deflected airplane wheel retraction jack |
| CN102072804A (en) * | 2010-12-21 | 2011-05-25 | 南京航空航天大学 | High-accuracy airplane wheel pre-rotating mechanism for drop test of airplane landing gear |
| CN103308264A (en) * | 2013-01-05 | 2013-09-18 | 中国航空工业集团公司西安飞机设计研究所 | Frequency excitation method for landing gear shimmy test |
| CN103983413A (en) * | 2014-04-17 | 2014-08-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for drop test for verifying buffer performance of undercarriage |
| CN105015788A (en) * | 2014-04-21 | 2015-11-04 | 哈尔滨飞机工业集团有限责任公司 | Landing gear |
| CN105501435A (en) * | 2014-10-11 | 2016-04-20 | 中国航空工业集团公司西安飞机设计研究所 | Method for avoiding excess vibration during landing state of undercarriage |
| CN106428623A (en) * | 2016-08-29 | 2017-02-22 | 中国航空工业集团公司西安飞机设计研究所 | Loading method of variable stroke test for undercarriage |
| CN109781071A (en) * | 2019-01-28 | 2019-05-21 | 北京卫星环境工程研究所 | High frequency photographing measurement method is unfolded in the electric detonation of landing buffer mechanism under hot vacuum environment |
| CN109959491A (en) * | 2018-10-26 | 2019-07-02 | 中国飞行试验研究院 | A kind of landing-gear load is taken a flight test middle buffer principal fault diagnostic method |
| CN114486138A (en) * | 2021-12-30 | 2022-05-13 | 中国飞机强度研究所 | Airplane vibration comfort test device and method in full-airplane state |
-
1999
- 1999-10-28 CN CN 99249075 patent/CN2419590Y/en not_active Expired - Fee Related
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101405589B (en) * | 2006-03-16 | 2011-01-12 | 空中客车英国有限公司 | Testing strut assembly |
| CN102020014A (en) * | 2010-12-09 | 2011-04-20 | 南京航空航天大学 | Airplane landing gear with deflected airplane wheel retraction jack |
| CN102020014B (en) * | 2010-12-09 | 2012-11-21 | 南京航空航天大学 | Airplane landing gear with deflected airplane wheel retraction jack |
| CN102072804A (en) * | 2010-12-21 | 2011-05-25 | 南京航空航天大学 | High-accuracy airplane wheel pre-rotating mechanism for drop test of airplane landing gear |
| CN102072804B (en) * | 2010-12-21 | 2012-07-18 | 南京航空航天大学 | High-accuracy airplane wheel pre-rotating mechanism for drop test of airplane landing gear |
| CN103308264A (en) * | 2013-01-05 | 2013-09-18 | 中国航空工业集团公司西安飞机设计研究所 | Frequency excitation method for landing gear shimmy test |
| CN103308264B (en) * | 2013-01-05 | 2015-08-05 | 中国航空工业集团公司西安飞机设计研究所 | A kind of landing gear shimmy test frequency motivational techniques |
| CN103983413A (en) * | 2014-04-17 | 2014-08-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for drop test for verifying buffer performance of undercarriage |
| CN105015788A (en) * | 2014-04-21 | 2015-11-04 | 哈尔滨飞机工业集团有限责任公司 | Landing gear |
| CN105501435A (en) * | 2014-10-11 | 2016-04-20 | 中国航空工业集团公司西安飞机设计研究所 | Method for avoiding excess vibration during landing state of undercarriage |
| CN106428623A (en) * | 2016-08-29 | 2017-02-22 | 中国航空工业集团公司西安飞机设计研究所 | Loading method of variable stroke test for undercarriage |
| CN109959491A (en) * | 2018-10-26 | 2019-07-02 | 中国飞行试验研究院 | A kind of landing-gear load is taken a flight test middle buffer principal fault diagnostic method |
| CN109959491B (en) * | 2018-10-26 | 2020-12-29 | 中国飞行试验研究院 | Method for diagnosing air leakage fault of buffer in landing gear load test flight |
| CN109781071A (en) * | 2019-01-28 | 2019-05-21 | 北京卫星环境工程研究所 | High frequency photographing measurement method is unfolded in the electric detonation of landing buffer mechanism under hot vacuum environment |
| CN109781071B (en) * | 2019-01-28 | 2021-03-23 | 北京卫星环境工程研究所 | High-speed photogrammetry method for landing buffer mechanism electric explosion deployment in thermal vacuum environment |
| CN114486138A (en) * | 2021-12-30 | 2022-05-13 | 中国飞机强度研究所 | Airplane vibration comfort test device and method in full-airplane state |
| CN114486138B (en) * | 2021-12-30 | 2024-03-19 | 中国飞机强度研究所 | Device and method for testing vibration comfort of aircraft in full-aircraft state |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |