CN1512149A - On-site calibrating test method and its device for landing gear load - Google Patents

On-site calibrating test method and its device for landing gear load Download PDF

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Publication number
CN1512149A
CN1512149A CNA021589607A CN02158960A CN1512149A CN 1512149 A CN1512149 A CN 1512149A CN A021589607 A CNA021589607 A CN A021589607A CN 02158960 A CN02158960 A CN 02158960A CN 1512149 A CN1512149 A CN 1512149A
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load
landing gear
situation
pillar
undercarriage
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CN1273814C (en
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阎楚良
孟繁沛
张书明
王赞平
何彧
王慧梅
丁亚修
孟祥民
张鑫
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Chinese Academy of Agricultural Mechanization Sciences
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Chinese Academy of Agricultural Mechanization Sciences
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Abstract

The present invention discloses on-site calibrating test method and device for landing gear load and is related to the safety and reliability of landing gear. The present invention features in-situ load application and calibration for landing gear under true and natural no-detachment condition to ensure the truth and precision of load calibration and measurement. The present invention solves the difficult problem of practically measuring and calibrating landing gear load of, especially, large airplane. The measured load spectrum data provides for the research and design of landing gear with important mechanical reference.

Description

Landing gear load field calibration test method and device thereof
Invention field
The present invention relates to a kind of undercarriage load calibration test method, the invention still further relates to the isolated plant that uses this test method.
Background technology
Undercarriage is as the vitals under the state of landing and ground motion, need it should be in light weight, but it is safe in utilization again, therefore, understand that its force-bearing situation and serviceable life are the problems that people are concerned about always, but past when undercarriage is carried out load test carries out after all undercarriage being removed from aircraft, such test had not both guaranteed the authenticity of stand under load, did not guarantee the precision of load measurement and demarcation yet.
The present inventor is at the deficiencies in the prior art; carry out discovering with great concentration, under the condition that undercarriage is not dismantled, carried out on-the-spot load and apply and demarcate, promptly can guarantee the safety of aircraft; can protect the authenticity of stand under load and the precision of load calibration again, so finished the present invention.
Summary of the invention
The test method that the purpose of this invention is to provide a kind of landing gear load field calibration.
A further object of the present invention provides a kind of device of realizing above-mentioned test method.
Specifically, it keeps demarcating under the stopped status at aircraft, it is characterized in that: under the condition that undercarriage is not dismantled, carry out according to following step,
(1) the nose-gear pillar is full of oil, has arranged gas; Fill an amount of inert gas or oil in the left and right main landing gear compression cylinder; Aircraft is weighed, determine centre of gravity place; Add counterweight, transfer centre of gravity place, make centre of gravity place near the aircraft line of symmetry;
(2) record weight, centre of gravity place; Before the record, main landing gear earth point position,
(3) coordinate system is selected, and coordinate origin is the intersection point of fuselage construction horizontal line and O bit line (1.0m behind the head), and X-axis overlaps with the fuselage construction horizontal line, and backward for just, Y-axis makes progress in the aircraft plane of symmetry to just, the Z axle sensing In-particular wing and X, Y-axis formation right-handed system,
(4) according to the undercarriage design load, load is demarcated on the characteristics of determining undercarriage ground as shown in table 1, situation 1-13, by the strain sensing apparatus load is put on wheel shaft center or tire ground connection place, write down load value step by step, and the corresponding pillar decrement of record, the pillar decrement realizes by draining the oil or putting inert gas, when applying situation 1-13 load, must eliminate frictional ground force, situation 14-15 puts on load on the lifting jack by jack device, write down load value step by step, and the corresponding pillar decrement of record.
Load is demarcated on table 1 undercarriage ground
Situation number Load value (kN) Explanation
??1 Selected Being applied to left and right master plays the tire earth point and (demarcates left and right master and play P ZLoad)
??2 Selected Be applied to that lead on a left side, preceding wheel shaft center (left P that led of demarcation XLoad)
??3 Selected Be applied to right lead, (P has been led on the demarcation right side at preceding wheel shaft center XLoad)
??4 Selected Be applied to the moment of torsion M that left and right master rises YBe 8kNm and (demarcate the moment of torsion M that left and right master rises Y)
??5 Selected Be applied to and play tire earth point (the preceding P of rising of demarcation before has led on a left side ZLoad)
??6 Selected Be applied to preceding, the left wheel shaft center of having led; Before rise, the right load of lead the wheel shaft center is 8kN and (demarcates a preceding P XLoad)
??7 Selected Be applied to that lead on a left side, preceding wheel shaft center (left P that led of demarcation XLoad)
??8 Selected Be applied to right lead, (P has been led on the demarcation right side at preceding wheel shaft center XLoad)
??9 Selected Be applied to that lead on a left side, preceding tire earth point (left F that led of demarcation XLoad)
??10 Selected Be applied to right lead, (F has been led on the demarcation right side to preceding tire earth point XLoad)
??11 Selected Be applied to preceding, the left wheel shaft center of having led; Before rise, the right load of lead the wheel shaft center is 6kN and (demarcates a preceding P XLoad)
??12 Selected 1 situation and 9 situations apply (proof load situation) simultaneously
??13 Selected 1 situation and 10 situations apply (proof load situation) simultaneously
??14 Selected The preceding lifting jack that rises adds P Y=10, rise before being applied on the lifting jack and (play P before demarcating YLoad)
??15 Selected Left and right master plays lifting jack and respectively adds P Y=50, be applied to two and led on the lifting jack and (to demarcate and to have led P YLoad)
When applying situation 1-6, the strain sensing apparatus is substantially by the clamp that the undercarriage wheel subcard is tight, two two ears that draw that draw ear or be contained in undercarriage wheel shaft center that clamp ground connection place loads onto, jin does not fall, sensor, turnbuckle are formed, utilize the jin end that do not fall to link to each other with undercarriage ears or side handles of a utensil, the other end conforms to a conventional pattern with sensor, degree of tightness and another undercarriage ears or side handles of a utensil link to each other, and two undercarriages are formed drawing; And the record load value applies situation 7-11, utilize jin not fall, sensor, wire rope, connected systems such as counterweight are respectively with two undercarriages, link to each other by the ears or side handles of a utensil at wheel shaft center or the ears or side handles of a utensil at tire ground connection place, make two undercarriages carry out outer drawing, measure step by step with electronic scale, and the record load value, and the horizontal shift at tire ground connection place, see Table 2.
Load is demarcated on table 2 undercarriage ground
Situation number Load value (kN) Applying method Explanation
? ? ??1 Selected Utilize the tire earth point place ears or side handles of a utensil to drawing Being applied to left and right master plays the tire earth point and (demarcates left and right master and play P ZLoad)
? ? ??2 Selected Utilize the wheel shaft center ears or side handles of a utensil to drawing Be applied to that lead on a left side, preceding wheel shaft center (left P that led of demarcation XLoad)
? ? ??3 Selected Utilize the wheel shaft center ears or side handles of a utensil to drawing Be applied to right lead, (P has been led on the demarcation right side at preceding wheel shaft center XLoad)
??4 Selected To drawing Be applied to the moment of torsion M that left and right master rises YBe 8kNm and (demarcate the moment of torsion M that left and right master rises Y)
? ? ??5 Selected Utilize the tire earth point place ears or side handles of a utensil to drawing Be applied to and play tire earth point (the preceding P of rising of demarcation before has led on a left side ZLoad)
? ? ??6 Selected Utilize the wheel shaft center ears or side handles of a utensil to drawing Be applied to preceding, the left wheel shaft center of having led; Before rise, the right load of lead the wheel shaft center is 8kN and (demarcates a preceding P XLoad)
??7 Selected Utilize wheel Be applied to a left side lead, preceding wheel shaft center
The axle center ears or side handles of a utensil are to drawing (demarcate a left side and led P XLoad)
? ? ????8 Selected Utilize the wheel shaft center ears or side handles of a utensil to draw outward Be applied to right lead, (P has been led on the demarcation right side at preceding wheel shaft center XLoad)
? ? ????9 Selected Utilize the tire earth point place ears or side handles of a utensil to draw outward Be applied to that lead on a left side, preceding tire earth point (left F that led of demarcation XLoad)
? ? ????10 Selected Utilize the tire earth point place ears or side handles of a utensil to draw outward Be applied to right lead, (F has been led on the demarcation right side to preceding tire earth point XLoad)
? ? ????11 Selected Utilize the wheel shaft center ears or side handles of a utensil to draw outward Be applied to preceding, the left wheel shaft center of having led; Before rise, the right load of lead the wheel shaft center is 6kN and (demarcates a preceding P XLoad)
????12 Selected Combination loads 1 situation and 9 situations apply (proof load situation) simultaneously
????13 Selected Combination loads 1 situation and 10 situations apply (proof load situation) simultaneously
????14 Selected Lifting jack The preceding lifting jack that rises adds P Y=10, rise before being applied on the lifting jack and (play P before demarcating YLoad)
????15 Selected Lifting jack Left and right master plays lifting jack and respectively adds P Y=50, be applied to two and led on the lifting jack and (to demarcate and to have led P YLoad)
Demarcate main landing gear Y when load, two masters of usefulness with aircraft play lifting jack with aircraft jack-up, demarcate nose-gear Y when load, with the preceding lifting jack of aircraft with aircraft jack-up, sensor is loaded onto in the lifting jack upper end, each sensor connects an electronic scale, writes down load value step by step, and writes down the pillar decrement under the load at different levels simultaneously.
Demarcate main landing gear P X, F X, P Z, M YDuring load, require pillar decrement branch to carry out, demarcate P YDuring load, when being maximum one-level, the pillar decrement demarcates nose-gear P X, P Y, P ZDuring load, require the pillar compression to carry out with branch; Situation 12, preceding, led pillar first, carry out (as undercarriage decrement branch level Four) during third level decrement; Situation 13, preceding, led pillar second, carry out (as undercarriage decrement branch level Four) during fourth stage decrement.
Preferably, demarcate main landing gear P X, F X, P Z, M YDuring load, require pillar decrement branch to carry out, demarcate P YDuring load, when being maximum one-level, the pillar decrement demarcates nose-gear P X, P Y, P ZDuring load, require the pillar compression to carry out with branch; Situation 12, preceding, led pillar first, carry out (as undercarriage decrement branch level Four) during third level decrement; Situation 13, preceding, led pillar second, carry out (as undercarriage decrement branch level Four) during fourth stage decrement.
Preferably, when carrying out described landing gear load field calibration test method, each undercarriage is placed on the rolling plate that can horizontal direction moves, to eliminate frictional ground force.
During demarcation situation 1-13, in fuselage (7), (31), and left and right sides wing rib (11) locates to add the protection carriage, and fore hold door, back landing gate add the course and support; During demarcation situation 14, in fuselage (7), (31), left and right sides wing rib (11) locates to add the protection carriage, adds block before the nose-gear wheel.
During demarcation situation 4, load(ing) point acts on left and right sides main landing gear respectively on the clamp ears or side handles of a utensil at wheel shaft center, uses moment of torsion M YThe value load(ing) point calculates the load value that applies to the vertical range at wheel shaft center.
In addition, situation 12,13 does not load step by step.
The present invention also provides a kind of isolated plant of realizing in claim 1 or the 2 described load calibration test methods, it is characterized in that: sensor device is substantially by the clamp that the undercarriage wheel subcard is tight, two two ears that draw that draw ear or two undercarriage wheel shaft centers that clamp ground connection place loads onto, jin does not fall, sensor, and turnbuckle and wire rope are formed; When utilizing the jin end that do not fall when drawing, needs two undercarriages link to each other with undercarriage ears or side handles of a utensil, the other end and sensor, turnbuckle and another undercarriage ears or side handles of a utensil link to each other, when drawing outside needs two undercarriages, utilizing this connected system is to load onto sensor in the lifting jack upper end with the ears or side handles of a utensil or the outer ears or side handles of a utensil of the tire ground connection jack device that links to each other of two undercarriages by the wheel shaft center, connects an electronic scales on the sensor and writes down load value and pillar decrement etc.
Because the present invention carries out under the condition that undercarriage is not dismantled, both guaranteed the safety of aircraft, guaranteed the precision of the authenticity load calibration of undercarriage stand under load again, carry rating test by strain transducer and set up load equation, also just can measure aircraft exactly and under the motion state of landing ground, act on external applied load time history on this undercarriage, decide the mechanics basis that longevity and simulated experiment load as fatigue.
Description of drawings
Fig. 1 is to drawing load to apply synoptic diagram.
Fig. 2 draws load to apply synoptic diagram outside being.
Fig. 3 is that main landing gear Y direction is demarcated the loading method signal.
Fig. 4 has led load calibration method synoptic diagram about 1 situation.
Fig. 5 is that 2 situations are demarcated the left P that led XThe loading method synoptic diagram.
Fig. 6 is that left and right master plays moment of torsion M YDemarcate the loading method synoptic diagram.
Fig. 7 plays P before 5 situations are demarcated ZThe loading method synoptic diagram.
Fig. 8 plays P before 6 situations XLoad (contrary course) scaling method synoptic diagram.
Fig. 9 is that 7 situations are demarcated the left P that led XLoading method synoptic diagram (8 situations and 7 situation symmetries).
Figure 10 is that F has been led on 9 a situations left side XLoad calibration method synoptic diagram (10 situations and 9 situation symmetries).
Embodiment
Below in conjunction with drawings and Examples the present invention is described in further detail
1. selected coordinate system, true origin is the intersection point of fuselage construction horizontal line and O bit line (1.0m behind the head), and X-axis overlaps with the fuselage construction horizontal line, and backward for just, Y-axis makes progress in the aircraft plane of symmetry to just, Z axle sensing left wing and X, Y-axis formation right-handed system.
2. undercarriage is demarcated
Before demarcating, plays the landing-gear load calibration request load p X, P Y, P ZWith led load p X, P Y, P z, F x, M yLoad p x, P Y, M yAct on the wheel shaft center; F x, P zAct on the tire earth point, and through the projection of wheel shaft center on ground.
Before the demarcation, must do following work:
1) the nose-gear pillar is full of oil, has arranged gas;
2) fill an amount of nitrogen or oil in the left and right main landing gear compression cylinder;
3) aircraft is weighed, determine centre of gravity place;
4) add counterweight, transfer centre of gravity place, make centre of gravity place near the aircraft line of symmetry;
5) record weight, centre of gravity place;
6) preceding, the main landing gear earth point position of record.
2.1 demarcation load
Undercarriage is demarcated load and is seen Table 3.
Load is demarcated on table 3 undercarriage ground
Situation number Load value (kN) Applying method Explanation
????1 ????28 To drawing Being applied to left and right master plays the tire earth point and (demarcates left and right master and play P ZLoad)
????2 ??29 To drawing Be applied to that lead on a left side, preceding wheel shaft center (left P that led of demarcation XLoad)
????3 ??29 To drawing Be applied to right lead, (P has been led on the demarcation right side at preceding wheel shaft center XLoad)
????4 ??8(kN·m) To drawing Be applied to the moment of torsion M that left and right master rises YBe 8kNm and (demarcate the moment of torsion M that left and right master rises Y)
????5 ??20 To drawing Be applied to and play tire earth point (the preceding P of rising of demarcation before has led on a left side ZLoad)
????6 ??8 To drawing Be applied to preceding, the left wheel shaft center of having led; Before rise, the right load of lead the wheel shaft center is 8kN and (demarcates a preceding P XLoad)
????7 ??29 Draw outward Be applied to that lead on a left side, preceding wheel shaft center (left P that led of demarcation XLoad)
????8 ??29 Draw outward Be applied to right lead, (P has been led on the demarcation right side at preceding wheel shaft center XLoad)
????9 ??29 Draw outward Be applied to that lead on a left side, preceding tire earth point (left F that led of demarcation XLoad)
????10 ??29 Draw outward Be applied to right lead, (F has been led on the demarcation right side to preceding tire earth point XLoad)
????11 ??6 Draw outward Be applied to preceding, the left wheel shaft center of having led; Before rise, the right load of lead the wheel shaft center is 6kN and (demarcates a preceding P XLoad)
????12 Combination loads 1 situation and 9 situations apply (proof load situation) simultaneously
????13 Combination loads 1 situation and 10 situations apply (proof load situation) simultaneously
????14 ??10 Lifting jack The preceding lifting jack that rises adds P Y=10, rise before being applied on the lifting jack and (play P before demarcating YLoad)
????15 ??50 Lifting jack Left and right master plays lifting jack and respectively adds P Y=50, be applied to two and led on the lifting jack and (to demarcate and to have led P YLoad)
Annotate:
1 demarcates main landing gear P X, F X, P Z, M YDuring load, require pillar decrement branch level Four: 30mm, 130mm, 220mm, 240mm.Demarcate P YDuring load, carry out during for 240mm in the pillar decrement.
2 demarcate nose-gear P X, P Y, P ZDuring load, require pillar decrement branch level Four: 20mm, 50mm, 80mm, 100mm.
3 nose-gears pillar decrements at different levels are by the realization of draining the oil.
4 left and right main landing gears pillar decrements at different levels are by putting an amount of nitrogen or draining the oil) realize;
5 situations 12, preceding, led pillar first, carry out during third level decrement.
6 situations 13, preceding, led pillar second, carry out during fourth stage decrement.
7 when applying situation 1-14 load, must eliminate frictional ground force.
8 demarcate P YDuring load, write down the pillar decrement of load correspondences at different levels.
9 timing signals, the horizontal shift of writing down each gear tyre earth point.
2.2 load applies
Load applies situation and sees accompanying drawing 1, accompanying drawing 2.
Annotate:
Be the loading synoptic diagram of 1-3,5-10 situation shown in 1 figure, each situation load applies by wire rope, adds dynamometer on the wire rope.
The torque load of 2 situations 4 realizes that by the load that applies horizontal direction load applies by wire rope, adds dynamometer on the wire rope.
3 situations 12,13 are the proof load situation, not classification.
The load of 4 situations 14,15 realizes loading requirement by the power on aircraft deadweight and the adjustment aircraft lifting jack.
3. undercarriage is demarcated loading method
3.1 aircraft status of support
3.1.1 the aircraft status of support of the situation of demarcation 1-13
Aircraft keeps stopped status, adjusts the pillar decrement by oil extraction for preceding, and main landing gear is adjusted pillar decrement (the pillar decrement near requirement gets final product) by exhaust (or draining the oil).On the rolling plate that the energy horizontal direction that is placed on each undercarriage moves, to eliminate frictional ground force.Add the protection carriage at fuselage 7 frames, 31 frames, left and right sides wing 11 rib places, fore hold door, back landing gate add the course and support.
3.1.2 the aircraft status of support of demarcation situation 14
With the preceding jack stand of aircraft, add dynamometer on the lifting jack, by adjust power on the lifting jack with the Y that obtains nose-gear in the case to load, the main landing gear lifting jack is turned down.Add the protection carriage at fuselage 7 frames, 31 frames, left and right sides wing 11 rib places, add block before preceding the wheel.
3.1.3 the aircraft status of support of demarcation situation 15
Demarcate main landing gear P YDuring load, the aircraft of known weight, center of gravity is played jack stand with 2 masters, adds dynamometer on the lifting jack, by adjust power on the lifting jack with the Y that obtains main landing gear in the case to load, each lifting jack harmony loading.
3.2 undercarriage Y is to the load calibration loading method
After having determined the weight of aircraft, center of gravity, led lifting jack with aircraft jack-up with two of aircraft, sensor is loaded onto in the lifting jack upper end, and each sensor connects an electronic scale.The power of adjusting step by step then on each lifting jack makes it reach P at last Y=50kN is put lifting jack more step by step, writes down load value step by step, writes down the pillar decrement under the load at different levels simultaneously.
Demarcate load value and see Table 3, demarcate loading method and see Fig. 3.
3.3 nose-gear Y is to the loading method of load calibration (situation 14)
With aircraft jack-up, sensor is loaded onto in the lifting jack upper end with the preceding lifting jack of aircraft, and sensor connects an electronic scale.The power of adjusting step by step then on the lifting jack makes it reach P at last Y=10kN is put lifting jack more step by step, writes down load value step by step.Demarcate load and see Table 3.
3.4 undercarriage X, Z are to demarcating loading method
Undercarriage X, Z take self-balance method to demarcate loading, and rise before promptly and two masters rise and promptly do load(ing) point mutually, do support point again, and to drawing or draw imposed load outward, the situation that applies of load is seen Fig. 1, Fig. 2 mutually, and magnitude of load sees Table 3.
A) 1 situation master plays P ZDemarcate loading method
Utilize clamp tight two main gear wheels subcards, clamp ground connection place loads onto two ears that draw, and utilizes a not fall end and led the ears or side handles of a utensil and link to each other of jin, and it is continuous that the other end and sensor, turnbuckle and another have been led the ears or side handles of a utensil.Make two to lead in the Z direction and form drawing, see Fig. 4, load value sees Table 3.Measure step by step with electronic scale, carry out the load record step by step.
Led load calibration method synoptic diagram about Fig. 41 situation.
B) 2 load condition masters play P X(along course) demarcate loading method with jin do not fall, connected systems such as sensor, turnbuckle and wire rope, rise before making and leftly led the wheel shaft center ears or side handles of a utensil and carry out drawing, electronic scale is measured load and record step by step, load value sees Table 3, loading method is seen Fig. 5.
Fig. 52 situations are demarcated a left side and have been led P XLoading method synoptic diagram (3 situations and 2 situation symmetries).
C) the left and right master of 4 situations plays moment of torsion M YDemarcate loading method
Load(ing) point acts on left and right master respectively and rises on the clamp ears or side handles of a utensil at wheel shaft center, uses moment of torsion M YValue and load(ing) point calculate the load value utilization jin that applies to the vertical range at wheel shaft center and do not fall, and sensor, turnbuckle and wire rope play left and right master and couple together, and make two to lead in the Z direction and form drawing.See Fig. 6, load value sees Table 3.Measure step by step with electronic scale, carry out the load record step by step.
D) 5 load conditions, preceding P ZDemarcate loading method
With jin do not fall, connected systems such as sensor, turnbuckle and wire rope, rise before making and a left side has been led the earth point ears or side handles of a utensil and carried out drawing, electronic scale is measured load and record step by step, load value sees Table 3, loading method is seen Fig. 7.
E) play P before 6 load conditions X(contrary course) demarcates loading method
Utilize that jin does not fall, connected systems such as sensor, turnbuckle and wire rope, by two led and preceding clamp on the ears or side handles of a utensil, respectively two led and preceding couple together, connecting line is by preceding and two wheel shaft center of lead, makes preceding to rise with left and right master and all to carry out drawing, two jin harmony loading that do not fall, measure with electronic scale step by step, and record, load value sees Table 3, demarcates loading method and sees Fig. 8.
F) P has been led on 7 a load conditions left side X(contrary course) demarcates loading method
With jin do not fall, sensor, connected systems such as wire rope and counterweight link to each other main an of left side respectively with preceding the ears or side handles of a utensil by the wheel shaft center, rise before making and a left side lead and is carried out outer drawing, the left P that led of demarcation X(contrary course) load loads step by step, measures with electronic scale step by step, and record, load value sees Table 3, demarcates loading method and sees Fig. 9,8 situations and 7 situation symmetries.
G) F has been led on 9 a load conditions left side XDemarcate loading method
Utilize connected systems such as jin does not fall, sensor, wire rope, counterweight, respectively main an of left side is linked to each other with preceding the ears or side handles of a utensil by the tire earth point, rise before making and a left side has been led and drawn the left F that led of demarcation outside carrying out XLoad loads step by step, measures with electronic scale step by step, and record, load value sees Table 3, demarcates loading method and sees Figure 10,10 situations and 9 situation symmetries.
H) play P before 11 load conditions X(along the course) demarcates loading method
Utilize jin not fall, sensor, connected systems such as wire rope and counterweight, left and right master is risen links to each other with preceding the ears or side handles of a utensil by the wheel shaft center respectively rises before making and left and right master rises and all carries out outer drawing, a P before demarcating X(along course) load, two jin are not dropped into capable harmony loading, and loading method is the combination of situation 7 and situation 8, and left and right master plays the ears or side handles of a utensil can not connect that jin does not fall, sensor.Load value sees Table 3.Load step by step and measure, carry out record simultaneously with electronic scale.
I) loading method of 12 combined load situations
1 situation and 9 situations apply (not loading step by step), the line item of going forward side by side simultaneously.
J) loading method of 13 combined load situations
1 situation and 10 situations apply (not loading step by step), the line item of going forward side by side simultaneously.
4. calibrating procedure
Do following work before the demarcation:
A) the nose-gear pillar is full of oil, has arranged gas;
B) fill an amount of nitrogen or oil in the left and right main landing gear compression cylinder;
C) aircraft is weighed, determine centre of gravity place;
D) add counterweight, transfer centre of gravity place, make centre of gravity place near the aircraft line of symmetry;
E) record weight, centre of gravity place;
F) preceding, the main landing gear tire earth point position of record.
Timing signal is undertaken by following program:
1) nose-gear pillar decrement is adjusted to 20mm, the main unit of landing gear decrement is adjusted to 30mm, carries out record simultaneously.
Carry out the demarcation of situation 1-12 and situation 14 by above-mentioned corresponding loading method.
2) nose-gear pillar decrement is adjusted to 50mm, the main unit of landing gear decrement is adjusted to 130mm, carries out record simultaneously.
Carry out the demarcation of situation 1-11 and situation 13-14 by above-mentioned corresponding loading method.
3) nose-gear pillar decrement is adjusted to 80mm, the main unit of landing gear decrement is adjusted to 220mm, carries out record simultaneously.
Carry out the demarcation of situation 1-12 and situation 14 by above-mentioned corresponding loading method.
4) nose-gear pillar decrement is adjusted to 100mm, the main unit of landing gear decrement is adjusted to 240mm, carries out record simultaneously.
Carry out the demarcation of situation 1-11 and situation 13-14 by above-mentioned corresponding demarcation loading method.
5) when the main unit of landing gear decrement is 240mm, presses the 5.1.6.2 loading method and demarcate the Y of main landing gear to load.
In addition, the present invention is not only applicable to undercarriage, for other similar take-off and landing devices, so long as under the condition of not dismantling, with sensor device test take-off and landing device load, all belong to protection scope of the present invention.

Claims (17)

1. the test method of a landing gear load field calibration, it keeps demarcating under the stopped status at aircraft, it is characterized in that: carry out according to following step under the condition that undercarriage is not dismantled:
(1) the nose-gear pillar is full of oil, has arranged gas; Fill an amount of inert gas or oil in the left and right main landing gear compression cylinder; Aircraft is weighed, determine centre of gravity place; Add counterweight, transfer centre of gravity place, make centre of gravity place near the aircraft line of symmetry;
(2) record weight, centre of gravity place; Before the record, main landing gear earth point position,
(3) coordinate system is selected, and coordinate origin is the intersection point of fuselage construction horizontal line and O bit line (1.0m behind the head), and X-axis overlaps with the fuselage construction horizontal line, and backward for just, Y-axis makes progress in the aircraft plane of symmetry to just, the Z axle sensing In-particular wing and X, Y-axis formation right-handed system,
According to the undercarriage design load, determine undercarriage ground demarcation load, situation 1-13, by the strain sensing apparatus load is put on wheel shaft center or tire ground connection place and write down load value step by step, and the corresponding pillar decrement of record, the pillar decrement realizes by draining the oil or putting inert gas, when applying situation 1-13 load, must eliminate frictional ground force, situation 14-15, by jack device load is put on and to write down load value on the lifting jack step by step, and the corresponding pillar decrement of record.
2. landing gear load field calibration test method according to claim 1, it is characterized in that: when applying situation 1-6, the strain sensing apparatus is substantially by the clamp that the undercarriage wheel subcard is tight, two two ears that draw that draw ear or be contained in undercarriage wheel shaft center that clamp ground connection place loads onto, jin does not fall, and sensor, turnbuckle are formed, and utilizes the jin end that do not fall to link to each other with undercarriage ears or side handles of a utensil, the other end conforms to a conventional pattern with sensor, degree of tightness and another undercarriage ears or side handles of a utensil link to each other, and two undercarriages are formed drawing; And the record load value applies situation 7-11, utilize jin not fall, sensor, wire rope, connected systems such as counterweight link to each other by the ears or side handles of a utensil at wheel shaft center or the ears or side handles of a utensil at tire ground connection place respectively with two undercarriages, make two undercarriages carry out outer drawing, measure step by step with electronic scale, and the record load value, and the horizontal shift at tire ground connection place.
3, to show 1 or 2 described landing gear load field calibration test methods according to right, it is characterized in that: demarcate main landing gear Y when load, two masters of usefulness with aircraft play lifting jack with aircraft jack-up, demarcate nose-gear Y when load, with aircraft jack-up, sensor is loaded onto in the lifting jack upper end with the preceding lifting jack of aircraft, and each sensor connects an electronic scale, write down load value step by step, and write down the pillar decrement under the load at different levels simultaneously.
4, landing gear load field calibration test method according to claim 1 and 2 is characterized in that: demarcate main landing gear P X, F X, P Z, M YDuring load, require pillar decrement branch to carry out, demarcate P YDuring load, when being maximum one-level, the pillar decrement demarcates nose-gear P X, P Y, P ZDuring load, require the pillar compression to carry out with branch; Situation 12, preceding, led pillar first, carry out during third level decrement; Situation 13, preceding, led pillar second, carry out during fourth stage decrement.
5, landing gear load field calibration test method according to claim 3 is characterized in that: demarcate main landing gear P X, F X, P Z, M YDuring load, require pillar decrement branch to carry out, demarcate P YDuring load, when being maximum one-level, the pillar decrement carries out; Demarcate nose-gear P X, P Y, P ZDuring load, require the pillar compression to carry out with branch; Situation 12, preceding, led pillar first, carry out during third level decrement; Situation 13, preceding, led pillar second, carry out during fourth stage decrement.
6, landing gear load field calibration test method according to claim 1 and 2 is characterized in that: each undercarriage is placed on the rolling plate that can horizontal direction moves to eliminate frictional ground force.
7, landing gear load field calibration test method according to claim 3 is characterized in that: each undercarriage is placed on the rolling plate that can horizontal direction moves to eliminate frictional ground force.
8, landing gear load field calibration test method according to claim 5 is characterized in that: each undercarriage is placed on the rolling plate that can horizontal direction moves to eliminate frictional ground force.
9, landing gear load field calibration test method according to claim 3 is characterized in that: when demarcating situation 1-13, and in fuselage (7), (31), and left and right sides wing rib (11) locates to add the protection carriage, and fore hold door, back landing gate add the course and support; During demarcation situation 14, in fuselage (7), (31), left and right sides wing rib (11) locates to add the protection carriage, adds block before the nose-gear wheel.
10, landing gear load field calibration test method according to claim 5 is characterized in that: when demarcating situation 1-13, and in fuselage (7), (31), and left and right sides wing rib (11) locates to add the protection carriage, and fore hold door, back landing gate add the course and support; During demarcation situation 14, in fuselage (7), (31), left and right sides wing rib (11) locates to add the protection carriage, adds block before the nose-gear wheel.
11, landing gear load field calibration test method according to claim 6 is characterized in that: when demarcating situation 1-13, and in fuselage (7), (31), and left and right sides wing rib (11) locates to add the protection carriage, and fore hold door, back landing gate add the course and support; During demarcation situation 14, in fuselage (7), (31), left and right sides wing rib (11) locates to add the protection carriage, adds block before the nose-gear wheel.
12, landing gear load field calibration test method according to claim 5 is characterized in that: during demarcation situation 4, load(ing) point acts on left and right sides main landing gear respectively on the clamp ears or side handles of a utensil at wheel shaft center, uses moment of torsion M YThe value load(ing) point calculates the load value that applies to the vertical range at wheel shaft center.
13, landing gear load field calibration test method according to claim 6 is characterized in that: during demarcation situation 4, load(ing) point acts on left and right sides main landing gear respectively on the clamp ears or side handles of a utensil at wheel shaft center, uses moment of torsion M YThe value load(ing) point calculates the load value that applies to the vertical range at wheel shaft center.
14, landing gear load field calibration test method according to claim 9 is characterized in that: during demarcation situation 4, load(ing) point acts on left and right sides main landing gear respectively on the clamp ears or side handles of a utensil at wheel shaft center, uses moment of torsion M YThe value load(ing) point calculates the load value that applies to the vertical range at wheel shaft center.
15, landing gear load field calibration test method according to claim 1 and 2 is characterized in that: situation 12,13 does not load step by step.
16, landing gear load field calibration test method according to claim 5 is characterized in that: situation 12,13 does not load step by step.
17, the isolated plant in realization claim 1 or the 2 described load calibration test methods, it is characterized in that: sensor device is substantially by the clamp that the undercarriage wheel subcard is tight, two two ears that draw that draw ear or two undercarriage wheel shaft centers that clamp ground connection place loads onto, jin does not fall, sensor, and turnbuckle and wire rope are formed; When utilizing the jin end that do not fall when drawing, needs two undercarriages link to each other with undercarriage ears or side handles of a utensil, the other end and sensor, turnbuckle and another undercarriage ears or side handles of a utensil link to each other, when drawing outside needs two undercarriages, utilize this connected system that the ears or side handles of a utensil or the tire ground connection outer ears or side handles of a utensil of two undercarriages by the wheel shaft center are linked to each other; Jack device is to load onto sensor in the lifting jack upper end, connects an electronic scales on the sensor and writes down load value and pillar decrement.
CN 02158960 2002-12-31 2002-12-31 On-site calibrating test method and its device for landing gear load Expired - Fee Related CN1273814C (en)

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