CN101788355A - Landing gear load field calibration method and special device thereof - Google Patents
Landing gear load field calibration method and special device thereof Download PDFInfo
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- CN101788355A CN101788355A CN201010102559A CN201010102559A CN101788355A CN 101788355 A CN101788355 A CN 101788355A CN 201010102559 A CN201010102559 A CN 201010102559A CN 201010102559 A CN201010102559 A CN 201010102559A CN 101788355 A CN101788355 A CN 101788355A
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Abstract
The invention discloses a landing gear load field calibration method and a special device thereof, which are used for performing the field calibration on the airplane landing gear load. In the landing gear load field calibration method, each landing gear of an airplane is placed on a top plate of the special device and the heading friction force or side friction force of the landing gear is directly calibrated. Because the heading or side friction force is directly measured by using a sensor, the influence of the rolling friction force between a roller plate and a roller post on a measuring result is avoided, and the measurement accuracy is improved. A side rolling roller post (11) is arranged between a fixed bottom plate (5) and a middle lower plate (4) of the device; a heading rolling roller post (10) is arranged between the middle lower plate (4) and a middle upper plate (3); a spacial 90-degree angle is formed between the heading rolling roller post (10) and the side rolling roller post (11); and a sensor (2) is arranged between the middle upper plate (3) and a top plate (1). Due to the adoption of roller posts for bearing, after the loading direction is inclined, the direction of the friction force generated by the landing gear is in the heading or side direction, and the measurement accuracy is improved.
Description
Technical field
The present invention relates to a kind of scaling method, particularly a kind of landing gear load field calibration method; Also relate to this landing gear load field calibration method isolated plant.
Background technology
With reference to Figure 16,17, document " Granted publication number be the Chinese invention patent of CN1273814C " discloses a kind of landing gear load field calibration test method and device thereof.Adopt this device that landing-gear load is carried out on-site proving, solved undercarriage under situation about not dismantling, carry out the problem that on-the-spot load applies and demarcates, guaranteed the safety of aircraft effectively, protected the authenticity of stand under load and the precision of load calibration again.This patent utilizes the jin end that do not fall to link to each other with undercarriage ears or side handles of a utensil on measuring method, and the other end links to each other with sensor, turnbuckle and another ears or side handles of a utensil, and two undercarriages are formed drawing; Perhaps utilize connected systems such as jin does not fall, sensor, wire rope, counterweight respectively two undercarriages to be carried out outer drawing.In drawing process, produce relative motion between ball and the rolling plate, finally measure plus load by sensor and electronic scales, plus load is equal to course friction force or side-friction force under the gear tyre.This measuring method has been ignored the force of rolling friction between rolling plate and the ball.Under big loading, big elastic deformation can take place in ball, has increased the coefficient of rolling friction between rolling plate and the ball, and the force of rolling friction between rolling plate and the ball can not be ignored at this moment.
Device in this patent is by the clamp that the undercarriage wheel subcard is tight, two two ears that draw that draw ear or two undercarriage wheel shaft centers at clamp ground connection place, and jin does not fall, sensor, turnbuckle, wire rope, and individual layer ball rolling plate is formed.In measuring process, make to produce relative motion between ball and the rolling plate to drawing or drawing outward by undercarriage is carried out, and then measure course or side-friction force under the gear tyre.Because contact by point between ball and the rolling plate, loaded area is less, under loading greatly, the contact stress of ball can cause ball load-bearing capacity deficiency above the allowable contact stress of ball.In addition, adopt individual layer ball rolling plate in device, after the direction deflection of reinforcing, the friction force direction under the gear tyre is not along the course or lateral, thereby has reduced the load calibration precision.
Summary of the invention
To adopt prior-art devices that landing-gear load is carried out the deficiency that there is error in on-site proving in order overcoming, to the invention provides a kind of landing gear load field calibration method, can carry out the scene to landing-gear load and accurately demarcate.
The present invention also provides this landing gear load field calibration method isolated plant.
The technical solution adopted for the present invention to solve the technical problems: a kind of landing gear load field calibration method is characterized in comprising the steps:
(a) each undercarriage with aircraft is placed on the isolated plant top board, regulates the pillar decrement of each undercarriage, keeps the aircraft horizontal positioned.
When (b) measuring the course friction force of undercarriage, be divided into drawing and drawing two states to carry out load calibration outward.
To tension state, on the middle upper plate of the isolated plant of nose-gear, apply the course power of contrary vector, apply course power on the middle upper plate to the isolated plant of left and right undercarriage, reach stress balance, then the course load of aircraft is demarcated along vector.
Outer tension state, on the middle upper plate of the isolated plant of nose-gear, apply course power along vector, apply the course power of contrary vector on the middle upper plate to the isolated plant of left and right undercarriage, reach stress balance, and then the course load of aircraft is demarcated.
To each undercarriage, course load is applied on the middle upper plate, power transmission block in course will make fixed base plate and middle lower plate keep relative static, produce force of rolling friction between upper plate and its lower floor's course rolling roller in the middle of this moment, to produce course friction force between top board and the tire, by the sensor measurement course friction force between top board and the middle upper plate.
When (c) measuring the side-friction force of undercarriage, be divided into drawing and drawing two states to carry out load calibration outward.
Measure left and right undercarriage side load to tension state the time, after the aircraft sideward directed aircraft inboard, middle lower plate upper edge of the isolated plant of left and right undercarriage applies side force, reaches stress balance, the side load of left and right undercarriage is demarcated.
When measuring the outer tension state of left and right undercarriage side load, after the aircraft sideward directed aircraft outside, middle lower plate upper edge of the isolated plant of left and right undercarriage applies side force, reaches stress balance, the side load of left and right undercarriage is demarcated.
Measure the nose-gear side force to tension state the time, on the middle upper plate of the isolated plant of nose-gear, apply the course power of contrary vector, on middle lower plate, apply along the side force in aircraft sideward directed aircraft left side, on the middle upper plate of left undercarriage isolated plant, apply course power along vector, on middle lower plate, apply along the side force of aircraft sideward directed aircraft inboard, after reaching stress balance, the side load of nose-gear is demarcated.
Measure the nose-gear side force to tension state the time, on the middle upper plate of the isolated plant of nose-gear, apply course power along vector, on middle lower plate, apply along the side force on aircraft sideward directed aircraft right side, on the middle upper plate of left undercarriage isolated plant, apply the course power of contrary vector, on middle lower plate, apply along the side force in the aircraft sideward directed aircraft outside, after reaching stress balance, the side force of aircraft nose-gear is demarcated.
When measuring the side force on each undercarriage, side load is applied on the middle lower plate, at this moment, upper plate kept relative static with middle lower plate in the middle of side force power transmission block made, produce force of rolling friction between lower plate and its lower floor's side rolling roller in the middle of this moment, to produce friction force between top board and the tire, can directly side-friction force be measured by the sensor between top board and the middle upper plate.
When (d) applying proof load, on the middle upper plate of the isolated plant of nose-gear, apply load along the course, on middle the upper plate of the isolated plant of left and right undercarriage, apply simultaneously course load respectively, on the middle lower plate of the isolated plant of left and right undercarriage, apply respectively along the load of aircraft sideward directed inboard against vector.Course power and side force by each undercarriage of sensor measurement between top board and the middle upper plate.
When (e) measuring vertical load, add suspending weight on airframe, suspending weight should symmetry load aboard, to keep overall aircraft level, not run-off the straight.Aircraft is carried out the loading of the load of different operating modes by the quality that changes suspending weight.Directly measure vertical load by the sensor between top board and the middle upper plate.
A kind of above-mentioned landing gear load field calibration method isolated plant, comprise top board 1, sensor 2 and fixed base plate 5, upper plate 3, middle lower plate 4, side force power transmission block 6, side force positive stop 7, course positive stop 8, course power power transmission block 9, course rolling roller 10 and side rolling roller 11 in the middle of being characterized in also comprising, arrange side rolling roller 11 between fixed base plate 5 and the middle lower plate 4, side rolling roller 11 is totally eight rows, each 15 row of every row; Arrange course rolling roller 10 between middle lower plate 4 and the middle upper plate 3, course rolling roller 10 is totally eight rows, each 15 row of every row, become space 90 degree on course rolling roller 10 and side rolling roller 11 directions, between middle upper plate 3 and top board 1, be furnished with four sensors 2 on four angles of upper plate 3 in the middle of being positioned at, two course positive stops 8 are set on fixed base plate 5, pass through bolt between two course positive stops 8 and the fixed base plate 5, fixed base plate 5 be provided with middle lower plate 4 near course power power transmission block 9, two side direction positive stops 7, pass through bolt between two side direction positive stops 7 and the fixed base plate 5, middle lower plate 4 be provided with middle upper plate 3 near side force power transmission block 6, when applying side force, upper plate 3 in the middle of the power of middle lower plate 4 being passed to, and then by sensor 2 dynamometry between middle upper plate 3 and the top board 1; Described sensor 2 is three-dimensional strength measurement sensors, and there is strain fancy foil gauge inside.
Described strain fancy foil gauge, its foil gauge B measures along vertical load, and foil gauge A and foil gauge C measure course friction force or side-friction force respectively.
The present invention has following beneficial effect:
(1) on measuring method, utilize built-in sensors directly to measure course or side-friction force, avoid between rolling plate and the roller force of rolling friction to the influence of measurement result, thereby improved measuring accuracy.
(2) on measurement mechanism, adopt the roller carrying, owing to be that line contacts between roller and the rolling plate, and the friction factor between roller and the rolling plate is very little, thus improved the load-bearing capacity of measurement mechanism.
(3) on measurement mechanism, adopt the roller carrying, after the loading direction deflection, the friction force direction that still can guarantee generation gear tyre under is along the course or side direction, thereby improved measuring accuracy.
Below in conjunction with drawings and Examples the present invention is elaborated.
Description of drawings
Fig. 1 is that the inventive method is measured the loading synoptic diagram of the course load of undercarriage to tension state.
Fig. 2 is the loading synoptic diagram that the inventive method is measured the outer tension state of course load of undercarriage.
Fig. 3 is that the inventive method is measured the loading synoptic diagram of left and right undercarriage side load to tension state.
Fig. 4 is the loading synoptic diagram that the inventive method is measured the outer tension state of left and right undercarriage side load.
Fig. 5 is that the inventive method is measured the loading synoptic diagram of the side load of nose-gear to tension state.
Fig. 6 is the loading synoptic diagram that the inventive method is measured the outer tension state of side load of nose-gear.
Fig. 7 is the loading synoptic diagram that the inventive method measurement undercarriage course load and side load apply proof load simultaneously.
Fig. 8 is the front view of isolated plant of the present invention.
Fig. 9 is the left view of isolated plant of the present invention.
Figure 10 is the vertical view of isolated plant of the present invention.
Figure 11 is the enlarged drawing of three-dimensional strength measurement sensor among Fig. 8.
Figure 12 is the vertical view of Figure 11.
Figure 13 is the strain fancy foil gauge of used sensor in the isolated plant of the present invention.
Figure 14 is the force analysis synoptic diagram that the inventive method applies course load.
Figure 15 is the force analysis synoptic diagram that the inventive method applies side load.
Figure 16 is the measurement mechanism synoptic diagram of prior art undercarriage course load and side load.
Figure 17 is the measurement mechanism synoptic diagram of prior art undercarriage vertical load.
Among the figure, the 1-top board; The 2-sensor; Upper plate in the middle of the 3-; Lower plate in the middle of the 4-; The 5-fixed base plate; 6-side force power transmission block; 7-side direction positive stop; 8-course positive stop; 9-course power power transmission block; 10-course rolling roller; 11-side rolling roller.
Embodiment
With reference to Fig. 1～15.
Embodiment 1: isolated plant of the present invention is made up of top board 1, sensor 2, middle upper plate 3, middle lower plate 4, fixed base plate 5, side force power transmission block 6, side force positive stop 7, course positive stop 8, course power power transmission block 9, course rolling roller 10 and side rolling roller 11.Course rolling roller 10 and side rolling roller 11 each eight row, each 15 row of every row.Arrange between fixed base plate 5 and the middle lower plate 4 that one deck can be along the roller 11 of aircraft side rolling, arrange between middle lower plate 4 and the middle upper plate 3 that one deck becomes space 90 degree can be along the roller 10 of vector rolling with above-mentioned arranged direction.Be furnished with three-dimension sensor 2 between middle upper plate 3 and the top board 1, wherein the center section of top board 1 needs thickening, to strengthen the strength and stiffness of top board 1.Middle upper plate 3 is for applying the plate of course load, and middle lower plate 4 is for applying the plate of side load.When applying course load,, pass through Bolt Connection being equipped with on the fixed base plate 5 between 8, two course positive stops 8 of two course positive stops and the fixed base plate 5 for the displacement of upper plate 3 in the middle of limiting.Be equipped with on the fixed base plate 5 one with middle lower plate 4 near course power power transmission block 9, with so that fixed base plate 5 keeps relative static with middle lower plate 4, promptly be not subjected to the friction force effect between the side rolling roller 11 of centre lower plate 4 and its lower floor.When applying side force,, pass through Bolt Connection being equipped with on the fixed base plate 5 between 7, two side direction positive stops 7 of two side direction positive stops and the fixed base plate 5 for the displacement of lower plate 4 in the middle of limiting.On middle lower plate 4, be equipped with one with middle upper plate 3 near side force power transmission block 6, when applying side force, upper plate 3 in the middle of the power of middle lower plate 4 being passed to.Sensor 2 is three-dimensional strength measurement sensors, the inner strain fancy foil gauge that adopts.Foil gauge B measures along vertical load, and foil gauge A and foil gauge C measure course friction force or side-friction force.
Embodiment 2: the concrete implementation step of landing gear load field calibration method of the present invention is as follows:
(a) each undercarriage with aircraft is placed on the above-mentioned isolated plant, regulates the pillar decrement of each undercarriage, keeps the aircraft horizontal positioned.
(b) measure course load.
When measuring the course friction force of undercarriage, be divided into drawing and drawing two states to carry out load calibration outward.Tension state is carried out as follows, on the middle upper plate 3 of the isolated plant of nose-gear, apply the course power of contrary vector, apply course power on the middle upper plate 3 to the isolated plant of left and right undercarriage respectively along vector, reach stress balance, then the course load of aircraft is demarcated.
Outer tension state carries out as follows, on the middle upper plate 3 of the isolated plant of nose-gear, apply course power along vector, apply the course power of contrary vector on the middle upper plate 3 to the isolated plant of left and right undercarriage respectively, reach stress balance, and then the course load of aircraft is demarcated.Course power scaling method to each undercarriage is as follows:
With course load F
xOn the upper plate 3, course power transmission block 9 will make fixed base plate 5 keep relative static with middle lower plate 4, produce force of rolling friction E in the middle of this moment between upper plate 3 and its lower floor's course rolling roller 10 in the middle of being applied to
f, will produce course friction force F between top board 1 and the tire
i, choose top board 1 and middle upper plate 3 and analyze as a whole, F is then arranged
x=F
i+ F
f, measure course friction force F by A foil gauge among the Y1 in the sensor 2 between top board 1 and the middle upper plate 3 and C foil gauge
i
(c) measure side load.
When measuring the side-friction force of undercarriage, be divided into drawing and drawing two states to carry out load calibration outward.What left and right undercarriage side force was demarcated is undertaken by following method tension state, on the middle lower plate 4 of the isolated plant of left and right undercarriage, apply side force along aircraft sideward directed aircraft inboard respectively, reach stress balance, then the side load of left and right undercarriage is demarcated.
The outer tension state that left and right undercarriage side force is demarcated carries out as follows, on the middle lower plate 4 of the isolated plant of left and right undercarriage, apply side force along the aircraft sideward directed aircraft outside respectively, reach stress balance, then the side load of left and right undercarriage is demarcated.
What the nose-gear side force was demarcated is undertaken by following method tension state, on the middle upper plate 3 of the isolated plant of nose-gear, apply the course power of contrary vector, on middle lower plate 4, apply along the side force in aircraft sideward directed aircraft left side, on the middle upper plate 3 of left undercarriage isolated plant, apply course power along vector, on middle lower plate 4, apply along the side force of aircraft sideward directed aircraft inboard, reach stress balance, then the side load of nose-gear is demarcated.
The outer tension state that the nose-gear side force is demarcated carries out as follows, on the middle upper plate 3 of the isolated plant of nose-gear, apply course power along vector, on middle lower plate 4, apply along the side force on aircraft sideward directed aircraft right side, on the middle upper plate 3 of left undercarriage isolated plant, apply the course power of contrary vector, on middle lower plate 4, apply along the side force in the aircraft sideward directed aircraft outside, after reaching stress balance, the side force of aircraft nose-gear is demarcated.Lateral force on each undercarriage is analyzed as follows:
With side load F
zOn the lower plate 4, at this moment, upper plate 3 kept relative static with middle lower plate 4 in the middle of side force power transmission block 6 made, and produced force of rolling friction F in the middle of this moment between lower plate 4 and its lower floor's side rolling roller 11 in the middle of being applied to
f, will produce friction force F between top board 1 and the tire
a, choose top board 1, middle upper plate 3, middle lower plate 4 and side force power transmission block 6 and analyze as a whole, F is then arranged
z=F
a+ F
fCan be by A foil gauge among the Y2 in the sensor 2 between top board 1 and the middle upper plate 3 and C foil gauge directly with side-friction force F
aMeasure.
(d) apply proof load.On the middle upper plate 3 of the isolated plant of nose-gear, apply load along the course, on middle the upper plate 3 of the isolated plant of left and right undercarriage, apply simultaneously course load respectively, on the middle lower plate 4 of the isolated plant of left and right undercarriage, apply respectively along the load of aircraft sideward directed inboard against vector.By the foil gauge A in the sensor 2 between top board 1 and the middle upper plate 3 and foil gauge C course power and the side force to undercarriage respectively demarcated.Can what apply that proof load is used to detect undercarriage satisfy work requirements under the composite condition condition.
(e) measure vertical load.Add suspending weight on airframe, suspending weight should symmetry load aboard, to keep overall aircraft level, not run-off the straight.Can carry out the loading of the load of different operating modes to aircraft by the quality that changes suspending weight.The vertical load of measuring will directly be measured by the foil gauge B in the sensor 2 between top board 1 and the middle upper plate 3.
Claims (3)
1. a landing gear load field calibration method is characterized in that comprising the steps:
(a) each undercarriage with aircraft is placed on the isolated plant top board, regulates the pillar decrement of each undercarriage, keeps the aircraft horizontal positioned;
When (b) measuring the course friction force of undercarriage, be divided into drawing and drawing two states to carry out load calibration outward;
To tension state, on the middle upper plate of the isolated plant of nose-gear, apply the course power of contrary vector, apply course power on the middle upper plate to the isolated plant of left and right undercarriage, reach stress balance, then the course load of aircraft is demarcated along vector;
Outer tension state, on the middle upper plate of the isolated plant of nose-gear, apply course power along vector, apply the course power of contrary vector on the middle upper plate to the isolated plant of left and right undercarriage, reach stress balance, and then the course load of aircraft is demarcated;
To each undercarriage, course load is applied on the middle upper plate, power transmission block in course will make fixed base plate and middle lower plate keep relative static, produce force of rolling friction between upper plate and its lower floor's course rolling roller in the middle of this moment, to produce course friction force between top board and the tire, by the sensor measurement course friction force between top board and the middle upper plate;
When (c) measuring the side-friction force of undercarriage, be divided into drawing and drawing two states to carry out load calibration outward;
Measure left and right undercarriage side load to tension state the time, after the aircraft sideward directed aircraft inboard, middle lower plate upper edge of the isolated plant of left and right undercarriage applies side force, reaches stress balance, the side load of left and right undercarriage is demarcated;
When measuring the outer tension state of left and right undercarriage side load, after the aircraft sideward directed aircraft outside, middle lower plate upper edge of the isolated plant of left and right undercarriage applies side force, reaches stress balance, the side load of left and right undercarriage is demarcated;
Measure the nose-gear side force to tension state the time, on the middle upper plate of the isolated plant of nose-gear, apply the course power of contrary vector, on middle lower plate, apply along the side force in aircraft sideward directed aircraft left side, on the middle upper plate of left undercarriage isolated plant, apply course power along vector, on middle lower plate, apply along the side force of aircraft sideward directed aircraft inboard, after reaching stress balance, the side load of nose-gear is demarcated;
Measure the nose-gear side force to tension state the time, on the middle upper plate of the isolated plant of nose-gear, apply course power along vector, on middle lower plate, apply along the side force on aircraft sideward directed aircraft right side, on the middle upper plate of left undercarriage isolated plant, apply the course power of contrary vector, on middle lower plate, apply along the side force in the aircraft sideward directed aircraft outside, after reaching stress balance, the side force of aircraft nose-gear is demarcated;
When measuring the side force on each undercarriage, side load is applied on the middle lower plate, at this moment, upper plate kept relative static with middle lower plate in the middle of side force power transmission block made, produce force of rolling friction between lower plate and its lower floor's side rolling roller in the middle of this moment, to produce friction force between top board and the tire, can directly side-friction force be measured by the sensor between top board and the middle upper plate;
When (d) applying proof load, on the middle upper plate of the isolated plant of nose-gear, apply load along the course, on middle the upper plate of the isolated plant of left and right undercarriage, apply simultaneously course load respectively, on the middle lower plate of the isolated plant of left and right undercarriage, apply respectively along the load of aircraft sideward directed inboard against vector; Course power and side force by each undercarriage of sensor measurement between top board and the middle upper plate;
When (e) measuring vertical load, add suspending weight on airframe, suspending weight should symmetry load aboard, to keep overall aircraft level, not run-off the straight; Aircraft is carried out the loading of the load of different operating modes by the quality that changes suspending weight; Directly measure vertical load by the sensor between top board and the middle upper plate.
2. claims 1 described landing gear load field calibration method isolated plant, comprise top board (1), sensor (2) and fixed base plate (5), it is characterized in that: upper plate (3), middle lower plate (4), side force power transmission block (6), side force positive stop (7), course positive stop (8), course power power transmission block (9), course rolling roller (10) and side rolling roller (11) in the middle of also comprising, arrange side rolling roller (11) between fixed base plate (5) and the middle lower plate (4), side rolling roller (11) is totally eight rows, each 15 row of every row; Arrange course rolling roller (10) between middle lower plate (4) and the middle upper plate (3), course rolling roller (10) is totally eight rows, each 15 row of every row, become space 90 degree on course rolling roller (10) and side rolling roller (11) direction, between middle upper plate (3) and top board (1), be furnished with four sensors (2) on four angles of upper plate (3) in the middle of being positioned at, two course positive stops (8) are set on fixed base plate (5), pass through bolt between two course positive stops (8) and the fixed base plate (5), fixed base plate (5) be provided with middle lower plate (4) near course power power transmission block (9), two side direction positive stops (7), pass through bolt between two side direction positive stops (7) and the fixed base plate (5), middle lower plate (4) be provided with middle upper plate (3) near side force power transmission block (6), when applying side force, upper plate (3) in the middle of the power of middle lower plate (4) being passed to, and then by sensor (2) dynamometry between middle upper plate (3) and the top board (1); Described sensor (2) is the three-dimensional strength measurement sensor, and there is strain fancy foil gauge inside.
3. landing gear load field calibration method isolated plant according to claim 2 is characterized in that: described strain fancy foil gauge, and its foil gauge B measures along vertical load, and foil gauge A and foil gauge C measure course friction force or side-friction force respectively.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2010101025597A CN101788355B (en) | 2010-01-28 | 2010-01-28 | Landing gear load field calibration method and special device thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101025597A CN101788355B (en) | 2010-01-28 | 2010-01-28 | Landing gear load field calibration method and special device thereof |
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| CN101788355A true CN101788355A (en) | 2010-07-28 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102135461A (en) * | 2010-12-14 | 2011-07-27 | 西北工业大学 | Undercarriage load calibration device and method for calibrating load of undercarriage by using device |
| 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 |
| CN105716886A (en) * | 2014-12-03 | 2016-06-29 | 中国飞行试验研究院 | Aircraft landing gear load calibration method and test fake wheel structure |
| CN106546365A (en) * | 2016-09-22 | 2017-03-29 | 北京空间飞行器总体设计部 | A kind of sun blanket pressure calibration method of flexible solar wing |
| CN107884108A (en) * | 2017-11-30 | 2018-04-06 | 江西洪都航空工业集团有限责任公司 | A kind of triaxial residual stresses based on uniaxially pull pressure sensor |
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| DE676732C (en) * | 1935-07-10 | 1939-06-10 | Vomag Maschinenfabrik A G | Wheel pressure compensator |
| SU1164572A2 (en) * | 1984-01-27 | 1985-06-30 | Харьковский Автомобильно-Дорожный Институт Им.Комсомола Украины | Test bed for testing metalworks for working equipment of earth-moving machines |
| CN1273814C (en) * | 2002-12-31 | 2006-09-06 | 中国农业机械化科学研究院 | On-site calibrating test method and its device for landing gear load |
| CN201607314U (en) * | 2010-01-28 | 2010-10-13 | 西北工业大学 | Special device for scene marking method for undercarriage load |
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| CN102135461A (en) * | 2010-12-14 | 2011-07-27 | 西北工业大学 | Undercarriage load calibration device and method for calibrating load of undercarriage by using device |
| CN102135461B (en) * | 2010-12-14 | 2012-12-19 | 西北工业大学 | Undercarriage load calibration device and method for calibrating load of undercarriage by using device |
| CN105716886A (en) * | 2014-12-03 | 2016-06-29 | 中国飞行试验研究院 | Aircraft landing gear load calibration method and test fake wheel structure |
| CN105716886B (en) * | 2014-12-03 | 2018-01-19 | 中国飞行试验研究院 | A kind of undercarriage load calibration method and the false wheel construction of experiment |
| 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 |
| CN106546365A (en) * | 2016-09-22 | 2017-03-29 | 北京空间飞行器总体设计部 | A kind of sun blanket pressure calibration method of flexible solar wing |
| CN106546365B (en) * | 2016-09-22 | 2019-03-12 | 北京空间飞行器总体设计部 | A kind of sun blanket pressure calibration method of flexibility solar wing |
| CN107884108A (en) * | 2017-11-30 | 2018-04-06 | 江西洪都航空工业集团有限责任公司 | A kind of triaxial residual stresses based on uniaxially pull pressure sensor |
| CN107884108B (en) * | 2017-11-30 | 2020-01-31 | 江西洪都航空工业集团有限责任公司 | three-dimensional force measuring platform based on single axial tension pressure sensor |
| CN114088275A (en) * | 2021-11-22 | 2022-02-25 | 中航飞机起落架有限责任公司 | Main wheel friction force measuring device and method |
| CN114088275B (en) * | 2021-11-22 | 2024-04-05 | 中航飞机起落架有限责任公司 | Main wheel friction force measuring device and measuring method |
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| CN101788355B (en) | 2011-12-14 |
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