CN2393822Y - Apparatus for testing instantaneous rpm of landing vibration test of landing gears - Google Patents
Apparatus for testing instantaneous rpm of landing vibration test of landing gears Download PDFInfo
- Publication number
- CN2393822Y CN2393822Y CN 99244035 CN99244035U CN2393822Y CN 2393822 Y CN2393822 Y CN 2393822Y CN 99244035 CN99244035 CN 99244035 CN 99244035 U CN99244035 U CN 99244035U CN 2393822 Y CN2393822 Y CN 2393822Y
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- CN
- China
- Prior art keywords
- landing
- wheel
- infrared
- landing gear
- grating
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 28
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 23
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 23
- 230000001052 transient effect Effects 0.000 claims description 9
- 238000009434 installation Methods 0.000 claims description 8
- 239000004593 Epoxy Substances 0.000 claims description 4
- 238000000034 method Methods 0.000 abstract description 21
- 238000006073 displacement reaction Methods 0.000 abstract description 6
- 239000004411 aluminium Substances 0.000 abstract 4
- 229920006335 epoxy glue Polymers 0.000 abstract 1
- 238000013461 design Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000004080 punching Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model relates to a momentary speed variation test unit of a landing gear drop test, which is characterized in that a grating aluminium disc, an infrared emitter and an infrared receiver are all arranged on a landing gear. The grating aluminium disc is fixed to an airplane wheel disc by a connecting seat. The infrared emitter and the infrared receiver are fixed to a main shaft of an airplane wheel by a connecting seat. The connecting seats can be bonded to the outer side of airplane wheels by high-strength epoxy glue. The chisel-shaped grating aluminium disc can be fixed to a sensor connecting seat. The momentary speed variation test unit of a landing gear drop test can ensure the structure and the strength of landing gear airplane wheels can not be damaged. The utility model has the advantages that except relative displacement generated by rotation, the infrared emitter, the infrared receiver and the grating aluminium disc basically have no radial displacement and axial displacement. Therefore, the infrared receiver can exactly measure rotary pulse data, and can calculate the dynamic variation process of the momentary speed variation of airplane wheels landing in the process of landing gear impact.
Description
The utility model belongs to landing gear drop test transient rotative speed proving installation, particularly in the drop-test process, and the device that can test the dynamic changing process of the wheel rotating speed of alighting gear landing instant.
Alighting gear is the be hit key parameter of load and the absorption of merit amount of research alighting gear impacting its wheel rotation speed change of landing instant.The work of actual measurement alighting gear landing instant wheel rotation speed change process has very important engineering significance for the safe design of aircraft.Because the landing to impact of alighting gear occurs in moment, only there are several seconds at zero point the time, and in this course the rotation of wheel less than half cycle.Want to be implemented in several seconds at zero point, rotate the measurement less than the impact moment alighting gear wheel speed dynamic change procedure of half cycle, its difficulty is bigger.
In the drop-test process, the sudden rotation speed change scope of wheel landing instant is very big, the wheel rotating speed can reduce to per minute tens commentaries on classics from per minute several thousand commentaries on classics in less than 0.2 second time, also will write down the dynamic changing process of landing instant wheel rotating speed simultaneously.Because alighting gear is subjected to high speed impact power at landing instant, can cause alighting gear three directions produce tens millimeters even hundreds of millimeter in the space displacement of elastic impact on a large scale and vibration, test environment is abominable, is difficult at high speed revolution and is mixed with the recording device of laying the test rotating speed on the alighting gear wheel of intense impact vibration.Therefore, at present domestic also can't be in the drop-test process, the dynamic changing process of alighting gear landing instant wheel rotating speed carries out actv. and measures and record.
The purpose of this utility model is, design and produce a kind of landing gear drop test transient rotative speed proving installation, measure and write down in the drop-test, the alighting gear wheel is under the high speed revolution state, in the dynamic changing process that impacts landing instant wheel rotating speed, for the safe design and the use of alighting gear provides authentic data.
The utility model landing gear drop test transient impact device for testing rotating speed, by the scalpriform grating aluminum pan, infrared transmitter, infrared remote receiver, sensor Connection Block and computing machine are formed, it is characterized in that: in order to overcome owing to the violent shake and the data interpretation mistake that causes of bounce-back of wheel in the impact process of whereabouts, with grating aluminum pan and infrared transmitter, infrared receiver all is installed on the alighting gear, grating aluminum pan connects bearing by sensor and is fixed on the wheel dish, infrared transmitter and infrared remote receiver are fixed on the wheel main shaft by Connection Block, and infrared remote receiver is connected with computing machine by lead, form an organic whole, guaranteed that in impact process infrared remote receiver can collect the true rotation speed change of wheel.Damage alighting gear in order in test process, tachogen not to be installed because of punching, with high strength epoxy the sensor Connection Block is bonded to the wheel outside, again the scalpriform grating aluminum pan is fixed on the sensor Connection Block, to guarantee not destroy the structure and the wheel intensity of alighting gear.After test finishes bonding Connection Block that gets on and grating dish are taken off from wheel, expensive alighting gear also can normally use.
Working process of the present utility model is as follows: when the rotating speed that changes with per minute several thousand when alighting gear falls, and the relative swing offset of generation between the grating aluminum pan on being installed in infrared transmitter, the receptor on the alighting gear main shaft and being installed in wheel.Utilize the light transmission of grating aluminum pan, make infrared remote receiver can receive the light pulse signal that changes with the rotating speed speed, infrared remote receiver becomes light pulse into electric pulse, at the same time the time gap between two adjacent pulses is noted.Because the scalpriform loop hole on the grating aluminum pan is equal angular, corner between two grating open-works is constant constant, so can be, and then provide the rotation speed change curve of wheel in the impact process by rotating speed and the situation of change thereof of COMPUTER CALCULATION and each moment of writing down wheel in impact process.
The utility model has the advantages that: infrared transmitter, receptor and open-work scalpriform grating dish that the measurement rotating speed is used all are installed on the alighting gear by Connection Block, form an organic whole structure, make between infrared transmitter, receptor and the grating dish except the relative displacement that produces by rotation essentially no radial displacement and longitudinal travel.Therefore infrared remote receiver can accurately record rotary pulsed data, calculate alighting gear in impact process wheel at the dynamic changing process of landing instant rotating speed.In order to impact in the process of rotating speed in test, do not damage expensive alighting gear wheel, survey rotating speed grating aluminum pan of using and the method that does not adopt punching to install being connected of wheel, and fix grating aluminum pan with the bonding transition piece of high strength epoxy, expensive wheel can also normally be used after finishing test.
Below in conjunction with drawings and Examples, the utility model will be further described:
Fig. 1 is the organigram of landing gear drop test transient rotative speed proving installation;
Fig. 2 is the lateral plan of landing gear drop test transient rotative speed proving installation;
The wheel that Fig. 3 is to use this landing gear drop test transient rotative speed proving installation to record impacts the rotation speed change diagram of curves;
As seen from the figure, the utility model landing gear drop test transient rotative speed proving installation, by scalpriform grating aluminum pan 3, infrared transmitter 5, infrared remote receiver 6, sensor Connection Block 1 and computing machine 10 are formed.Sensor Connection Block 1 usefulness high strength epoxy bonds to the outside of wheel 2.Be fixed on sensor with key screw scalpriform grating aluminum pan 3 and connect on the bearing 1, grating aluminum pan 3 can be with wheel 2 rotations.Have on the grating aluminum pan 3 and become radial equal angles scalpriform open-work 4 with the center of circle.Infrared transmitter 5 is installed on the wheel axle 8 by attaching parts 7 with infrared remote receiver 6.
Like this, when the rotating speed that changes with per minute several thousand when alighting gear falls, the sensor that is installed in infrared transmitter 6, the receptor 5 on the alighting gear wheel axle 8 and is installed in wheel 2 connects between the grating aluminum pan 3 on the bearing 1 and produces relative swing offset, utilize the light transmission on the grating aluminum pan 3, make infrared remote receiver 5 can receive the light pulse signal that changes with the rotating speed speed, and send into computing machine 10 through lead 9 and store and revolution speed calculating.Obtain wheel by test and impact rotation speed change curve 11 (see figure 3)s.
Claims (1)
1, a kind of landing gear drop test transient rotative speed proving installation, by the scalpriform grating aluminum pan, infrared transmitter, infrared remote receiver, sensor Connection Block and computing machine are formed, it is characterized in that, with grating aluminum pan and infrared transmitter, infrared receiver all is installed on the alighting gear, described grating aluminum pan is fixed on the wheel dish by the sensor Connection Block, infrared transmitter and infrared remote receiver are fixed on the wheel main shaft by Connection Block, wherein Connection Block is bonded to the wheel outside with high strength epoxy, the scalpriform grating aluminum pan is fixed on the sensor Connection Block, and computing machine is connected with infrared remote receiver by lead.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 99244035 CN2393822Y (en) | 1999-09-02 | 1999-09-02 | Apparatus for testing instantaneous rpm of landing vibration test of landing gears |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 99244035 CN2393822Y (en) | 1999-09-02 | 1999-09-02 | Apparatus for testing instantaneous rpm of landing vibration test of landing gears |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2393822Y true CN2393822Y (en) | 2000-08-30 |
Family
ID=34030214
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 99244035 Expired - Fee Related CN2393822Y (en) | 1999-09-02 | 1999-09-02 | Apparatus for testing instantaneous rpm of landing vibration test of landing gears |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2393822Y (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102141573A (en) * | 2010-12-23 | 2011-08-03 | 江西洪都航空工业集团有限责任公司 | Rotational speed image measurement technology of landing gear drop test aircraft wheel |
| 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 |
| CN106787445A (en) * | 2017-03-03 | 2017-05-31 | 浙江永发机电有限公司 | Threephase asynchronous machine |
-
1999
- 1999-09-02 CN CN 99244035 patent/CN2393822Y/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102141573A (en) * | 2010-12-23 | 2011-08-03 | 江西洪都航空工业集团有限责任公司 | Rotational speed image measurement technology of landing gear drop test aircraft wheel |
| CN102141573B (en) * | 2010-12-23 | 2013-08-07 | 江西洪都航空工业集团有限责任公司 | Rotational speed image measurement technology of landing gear drop test aircraft wheel |
| 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 |
| CN106787445A (en) * | 2017-03-03 | 2017-05-31 | 浙江永发机电有限公司 | Threephase asynchronous machine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C53 | Correction of patent for invention or patent application | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: PATENTEE; FROM: WU DAFANG TO: BEIJING UNIV. OF AERONAUTICS + ASTRONAUTICS |
|
| CP01 | Change in the name or title of a patent holder |
Patentee after: Beihang University Patentee before: Wu Dafang |
|
| 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 |