CN2525472Y - Three way displacement test device for aeroplane landing gear landing vibration test - Google Patents
Three way displacement test device for aeroplane landing gear landing vibration test Download PDFInfo
- Publication number
- CN2525472Y CN2525472Y CN 02203084 CN02203084U CN2525472Y CN 2525472 Y CN2525472 Y CN 2525472Y CN 02203084 CN02203084 CN 02203084 CN 02203084 U CN02203084 U CN 02203084U CN 2525472 Y CN2525472 Y CN 2525472Y
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- landing
- aeroplane
- test device
- landing gear
- undercarriage
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Abstract
The utility model relates to a three way displacement test device for aeroplane landing gear landing vibration test; a four degree of freedom space position test device which consists of a space orientation, a rotary-angle sensor and a support bracket can freely rotate along each direction in a three-dimensional space. The front end of the device is provided with magnetic absorption elements. The utility model has the advantages that a manipulator of the three way displacement test device can flexibly move in the three-dimensional space; in the moment when an aeroplane landing gear landing, coordinates values of moving track of the front end of the manipulator in the three-dimensional space can be calculated by a computer in a measuring range of the device through the angle change of the rotary-angle sensor, and furthermore, the dynamic changing process of three way impact displacement of aeroplane wheels can be achieved in the aeroplane landing gear landing vibration tests.
Description
Technical field
The utility model relates to a kind of undercarriage landing shock three direction displacement proving installation, is used at landing gear drop test, undercarriage landing instant wheel three directions is impacted the dynamic trajectory of displacement and tests.
Background technology
Aircraft impacts landing instant, and its undercarriage wheel dynamic variable quantity that three directions are impacted displacement in the space is the be hit key parameter of load and the absorption of merit amount of research aircraft undercarriage.Measure and record aircraft landing instant, wheel three directions are impacted the work of the dynamic changing process of displacement, for the Safety Design of aircraft very important engineering significance are arranged.
Because the impact that lands of undercarriage occurs in very short moment, impulsive force reaches the peaked time only several seconds at zero point, strong collision can cause the high vibration of undercarriage wheel, and the displacement of elastic impact on a large scale that three directions produce tens millimeters even hundreds of millimeter in the space, want on high speed rotating and the undercarriage wheel with strong elastic impact vibration, it is very difficult that wide range space displacement test record device is installed.Therefore, at present domesticly also can't in the drop-test process, undercarriage landing instant wheel three directions be impacted the dynamic changing process of displacement and effectively measure and record.
Summary of the invention
The purpose of this utility model provides a kind of undercarriage drop-test three direction displacement proving installation, measure and write down in the drop-test process, three in space directions of aircraft landing instant undercarriage wheel are impacted the dynamic variable quantity of displacement, for the Safety Design and the use of undercarriage provides reliable test data.
For achieving the above object, the utility model is taked following technical measures: comprise space orientation mechanical arm, rotary angle transmitter, web member, magnetic attracting element, bearing and computing machine, forming one by three space orientation mechanical arms, four rotary angle transmitters and bearing can be at the four-degree-of-freedom space positioning apparatus that the space all directions are freely rotated.Each rotary angle transmitter is connected with computing machine by lead.The front end of this device is equipped with the magnetic attracting element, and when undercarriage wheel landing instant, the mechanical arm of three direction displacement proving installation is connected mobile with undercarriage.
The utility model has the advantages that: the three direction displacement proving installation can freely rotate in three dimensions neatly, and the angle variation by rotary angle transmitter is gone out in this device range ability by COMPUTER CALCULATION, and the mechanical arm front end is at the coordinate figure of three dimensions arbitrfary point.When using this measurement device three direction displacement, therefore the installation testing sensor that need not punch on the undercarriage wheel, does not destroy the structure and the intensity of undercarriage, and expensive undercarriage also can normally use after impulse test finished.
Below in conjunction with drawings and Examples the utility model is further described.
Description of drawings
Fig. 1 is the structural representation of present embodiment;
Undercarriage wheel three directions that Fig. 2 is to use the utility model to record are impacted displacement changing curve figure.
Embodiment
As seen from Figure 1, the utility model is made up of with computing machine 8 three space orientation mechanical arms 1, four rotary angle transmitters 2, bearing 3, magnetic attracting element 4, web members 5.1 series connection of three mechanical arms is hinged, with vertical connection of stile of L shaped web member 5, magnetic attracting element 4 is set on its horizontal sides in the top.Rotary angle transmitter 2 of vertical connection on bearing 3, its upper end is hinged with the lower end of the mechanical arm 1 of connecting, and three above-mentioned jointed shafts are rotary angle transmitter 2, and each rotary angle transmitter 2 is connected with computing machine 8 by lead 7.
The web member 6 that connects a square frame shape at the axle head of the undercarriage wheel 9 of testing usefulness, like this, when undercarriage wheel 9 high speed impact ground, be installed in web member 6 and the magnetic attracting element 4 automatic adhesives that are installed in the utility model mechanical arm 1 front end on 9 of the undercarriage wheels, undercarriage wheel 9 is connected as a single entity with the utility model, mechanical arm 1 of the present utility model is being with same moved further by wheel 6, rotary angle transmitter 2 produces angle to be changed, and be electric signal with the angle change transitions, send into computing machine 8 through lead 7 and store the calculating of carrying out space three-dimensional value of moving, obtain undercarriage wheel 9 at x, y, three directions of z are impacted the dynamic changing curve 10 of displacement, 11,12 (see figure 2)s.
Claims (1)
1, a kind of undercarriage drop-test three direction displacement proving installation, it is characterized in that: comprise space orientation mechanical arm, rotary angle transmitter, web member, magnetic attracting element, bearing, computing machine, three mechanical arm series connection are hinged, be connected with web member in the top, the magnetic attracting element is set on this web member, rotary angle transmitter of vertical connection on bearing, its upper end is hinged with the lower end of the mechanical arm of connecting, three above-mentioned jointed shafts are rotary angle transmitter, and each rotary angle transmitter is connected with computing machine by lead.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 02203084 CN2525472Y (en) | 2002-02-09 | 2002-02-09 | Three way displacement test device for aeroplane landing gear landing vibration test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 02203084 CN2525472Y (en) | 2002-02-09 | 2002-02-09 | Three way displacement test device for aeroplane landing gear landing vibration test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2525472Y true CN2525472Y (en) | 2002-12-11 |
Family
ID=33685412
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 02203084 Expired - Fee Related CN2525472Y (en) | 2002-02-09 | 2002-02-09 | Three way displacement test device for aeroplane landing gear landing vibration test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2525472Y (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102053002A (en) * | 2010-12-09 | 2011-05-11 | 南京航空航天大学 | Drop test bed with speed controllable rotation driving mechanism |
| 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 |
| CN104142231A (en) * | 2014-04-17 | 2014-11-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Landing gear lock service life test designing method |
| CN105333848A (en) * | 2015-11-23 | 2016-02-17 | 西安航空制动科技有限公司 | Device and method for measuring aircraft tire compression amount |
| CN105466371A (en) * | 2015-11-23 | 2016-04-06 | 西安航空制动科技有限公司 | Apparatus of measuring aircraft landing gear wheel shaft end position and measurement method thereof |
| CN108387170A (en) * | 2017-02-03 | 2018-08-10 | 赛峰起落架***公司 | magnetic measurement target |
-
2002
- 2002-02-09 CN CN 02203084 patent/CN2525472Y/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102053002A (en) * | 2010-12-09 | 2011-05-11 | 南京航空航天大学 | Drop test bed with speed controllable rotation driving mechanism |
| 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 |
| CN104142231A (en) * | 2014-04-17 | 2014-11-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Landing gear lock service life test designing method |
| CN104142231B (en) * | 2014-04-17 | 2016-11-02 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of undercarriage lock life test method for designing |
| CN105333848A (en) * | 2015-11-23 | 2016-02-17 | 西安航空制动科技有限公司 | Device and method for measuring aircraft tire compression amount |
| CN105466371A (en) * | 2015-11-23 | 2016-04-06 | 西安航空制动科技有限公司 | Apparatus of measuring aircraft landing gear wheel shaft end position and measurement method thereof |
| CN105466371B (en) * | 2015-11-23 | 2018-06-01 | 西安航空制动科技有限公司 | The device and measuring method of survey aircraft undercarriage wheel shaft end position |
| CN108387170A (en) * | 2017-02-03 | 2018-08-10 | 赛峰起落架***公司 | magnetic measurement target |
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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 |