CN201607314U - Special device for scene marking method for undercarriage load - Google Patents
Special device for scene marking method for undercarriage load Download PDFInfo
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- CN201607314U CN201607314U CN2010201033599U CN201020103359U CN201607314U CN 201607314 U CN201607314 U CN 201607314U CN 2010201033599 U CN2010201033599 U CN 2010201033599U CN 201020103359 U CN201020103359 U CN 201020103359U CN 201607314 U CN201607314 U CN 201607314U
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Abstract
The utility model discloses a special device for a scene marking method in an undercarriage load, which is used for marking an airplane undercarriage load in scene. The technical scheme of the special device includes that a lateral rotary rolling post (11) is arranged between a fixed bottom plate (5) and a middle lower plate (4); a heading rotary rolling post (10) is arranged between the middle lower plate (4) and a middle upper plate (3); an included angle of space 90 degrees is formed by the heading rotary rolling post (10) and the lateral rotary rolling post (11) in direction; and a sensor is arranged between the middle upper plate (3) and a top plate (1). When in marking, undercarriages of an airplane are placed on the top plate of the special device, and a user directly marks heading friction force or lateral friction force of the undercarriages. As rolling posts are adopted for bearing, the special device ensures that the direction of the friction force generated by the undercarriages is along the heading or the lateral direction after an upload direction is inclined, avoids effect on measuring results of the rotary friction force between a rotary plate and the rotary posts, and improves measuring accuracy.
Description
Technical field
The utility model relates to a kind of measurement mechanism, particularly a kind of 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
Adopt prior-art devices that landing-gear load is carried out the deficiency that there is error in on-site proving in order to overcome, the utility model provides a kind of landing gear load field calibration method isolated plant, can carry out the scene to landing-gear load and accurately demarcate.
The technical scheme that its technical matters that solves the utility model adopts: a kind of 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 utlity model has following beneficial effect: owing to adopt the roller carrying, be that line contacts between roller and the rolling plate, and the friction factor between roller and the rolling plate is very little, thereby has improved the load-bearing capacity of measurement mechanism; After the loading direction deflection, still can guarantee under the gear tyre friction force direction that produces along the course or side direction, thereby improve measuring accuracy.
Below in conjunction with drawings and Examples the utility model is elaborated.
Description of drawings
Fig. 1 is that the utility model is at the loading synoptic diagram of the course load of measuring undercarriage to tension state.
Fig. 2 is the loading synoptic diagram of the utility model tension state outside the course load of measuring undercarriage.
Fig. 3 is that the utility model is being measured the loading synoptic diagram of left and right undercarriage side load to tension state.
Fig. 4 is the loading synoptic diagram of the utility model tension state outside measuring left and right undercarriage side load.
Fig. 5 is that the utility model is at the loading synoptic diagram of the side load of measuring nose-gear to tension state.
Fig. 6 is the loading synoptic diagram of the utility model tension state outside the side load of measuring nose-gear.
Fig. 7 is that the utility model is being measured the loading synoptic diagram that undercarriage course load and side load apply proof load simultaneously.
Fig. 8 is the front view of the utility model isolated plant.
Fig. 9 is the left view of the utility model isolated plant.
Figure 10 is the vertical view of the utility model isolated plant.
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 utility model isolated plant.
Figure 14 is that the utility model is applying the force analysis synoptic diagram of course load.
Figure 15 is that the utility model is applying the force analysis synoptic diagram of 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.Isolated plant of the present utility model 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.
The utility model landing gear load field calibration method isolated plant is performed such on-site proving:
(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 F 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 (2)
1. 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.
2. landing gear load field calibration method isolated plant according to claim 1 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201033599U CN201607314U (en) | 2010-01-28 | 2010-01-28 | Special device for scene marking method for undercarriage load |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201033599U CN201607314U (en) | 2010-01-28 | 2010-01-28 | Special device for scene marking method for undercarriage load |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201607314U true CN201607314U (en) | 2010-10-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010201033599U Expired - Fee Related CN201607314U (en) | 2010-01-28 | 2010-01-28 | Special device for scene marking method for undercarriage load |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201607314U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101788355B (en) * | 2010-01-28 | 2011-12-14 | 西北工业大学 | Landing gear load field calibration method and special device thereof |
-
2010
- 2010-01-28 CN CN2010201033599U patent/CN201607314U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101788355B (en) * | 2010-01-28 | 2011-12-14 | 西北工业大学 | Landing gear load field calibration method and special device thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20101013 Termination date: 20120128 |