CN103207042B - Test device for detecting brake moment of helicopter - Google Patents
Test device for detecting brake moment of helicopter Download PDFInfo
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- CN103207042B CN103207042B CN201310146070.3A CN201310146070A CN103207042B CN 103207042 B CN103207042 B CN 103207042B CN 201310146070 A CN201310146070 A CN 201310146070A CN 103207042 B CN103207042 B CN 103207042B
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Abstract
The invention relates to a test device for detecting the brake moment of a helicopter. By the test device, the problems of instability and non-stationarity of the brake moment of helicopters, fixed wing aircrafts and automobiles in the brake process are solved. The test device comprises a draw bar mechanism, a clamping mechanism and a counter weight balance mechanism. The test device is low in cost, simple in structure, good in using effect, convenient to operate and high in measuring accuracy, and can meet the requirement of the stability and stationarity of the brake moment of the helicopter in the brake process. According to the test device, each parameter can be adjusted randomly by using a parameterized design scheme according to requirements on the brake moment of different helicopter types, so that design of different demands can be obtained. Therefore, the test device has high generality and practicality.
Description
Technical field
The present invention relates to a kind of helicopter brake torque detection experiment device.Especially the problem of helicopter, fixed wing aircraft and automobile brake torque unstability and non-stationarity in brake process can be solved.
Background technology
Helicopter anti-skid brake system (ABS) is the important plant equipment of helicopter, takes off and safe landing plays an important role to helicopter.The quality of anti-skid brake system (ABS) performance directly has influence on the safety of helicopter and airborne personnel, breaks down and cause the paralysis of whole system in order to avoid some device of anti-skid brake system (ABS).Just must the brake torque in helicopter anti-skid brake system (ABS) be detected, to guarantee safety, backward being not easy to of the Comparison between detecting methods of traditional helicopter wheel braking moment analog quantity controls and observes, cost is high again, lead time is long again, add the amount of calculation of designer, labor strength is large, there is wheel tire by major defects such as brake locking, wheel skidding, brake torque instability in brake process.
Summary of the invention
The object of the invention is to solve helicopter brake torque in brake process unstable and cause wheel and ground to produce excessive sliding phenomenon, and a kind of brake torque detection experiment device is provided.To eliminate currently used technical defect.Technical scheme of the present invention is, detection experiment device comprises drag link mechanism 1, clamping device 2, counterweight balancing mechanism 3, drag link mechanism 1 is by drag link sleeve, pull bar, packing ring, split pin, bearing pin, bearing, holding screw, connecting pin, hook, screw rod, locking nut, backing plate forms, wherein connected by connecting pin between pull bar and bearing, and fix with holding screw, bearing pin is passed through between hook and pull bar, packing ring, split pin is connected together, bearing passes through bolt, nut, packing ring is fixed on the left semi-ring of clamping device, hook on the right-hand member screw rod of clamping device is hooked on clamping device left end hook, and lock with locking nut, screw rod passes through bearing pin, packing ring, split pin is connected with the torsion bar of clamping device right-hand member, clamping device 2 is by left semi-ring, right semi-ring, torsion bar, left brake block, right brake block, bearing pin, packing ring, split pin forms, wherein left semi-ring is positioned at the lower-left end of drag link mechanism, left semi-ring is by left semi-ring pipe, left semi-ring holding piece, left half ring web plate, left half ring flat-plate, left semi-ring connecting axle is welded, the lower right that right semi-ring is positioned at drag link mechanism is by right semi-ring pipe, right semi-ring holding piece, right semi-ring connecting axle is welded, torsion bar is by torsion bar pipe, torsion bar gusset, torsion bar plate, V-block, baffle plate is welded, one end of right semi-ring and torsion bar is linked together by welding manner, left and right brake block glue is separately fixed on right semi-ring holding piece and left semi-ring holding piece, V-block is fixed on the other end of torsion bar, counterweight balancing mechanism hanging is on the V-block of torsion bar.Counterweight balancing mechanism 3 is made up of suspension hook, balancing weight, handle, bobbin,
The suspension hook of described counterweight balancing mechanism is through balancing weight center and hangs on the V-block of torsion bar.
Advantage of the present invention and beneficial effect are: this experimental rig cost is low, structure is simple, result of use is good, easy to operate, certainty of measurement is high, meet the requirement of helicopter brake torque stability and stationarity in brake process, the present invention adopts parameterized design, random adjustment can be carried out according to the requirement of different type of machines brake torque to parameters, thus draw the design of different demand, so this experimental rig has higher versatility and practicality.This experimental rig cost is low, structure is simple, and result of use is good, easy to operate, certainty of measurement is high, meet the requirement of helicopter brake torque stability and stationarity in brake process, and this experimental rig has higher versatility and practicality.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is the top view of Fig. 1 of the present invention.
Fig. 3 is drag link mechanism schematic diagram of the present invention.
Fig. 4 is clamping device schematic diagram of the present invention.
Fig. 5 is counterweight balancing mechanism schematic diagram of the present invention.
Detailed description of the invention
Below the present invention is described in further details.Detection experiment device comprises drag link mechanism 1, clamping device 2, counterweight balancing mechanism 3, is characterized in that drag link mechanism 1 is by drag link sleeve 101, pull bar 102, packing ring 103, split pin 104, bearing pin 105, bearing 106, holding screw 107, connecting pin 108, hook 109, screw rod 110, locking nut 111, backing plate 112 forms, and is wherein connected by connecting pin between pull bar and bearing, and fixing with holding screw, is by bearing pin between hook and pull bar, packing ring, split pin is connected together, and bearing passes through bolt, nut, packing ring is fixed on left semi-ring, the hook on right-hand member screw rod is hooked on left end hook, and locks with locking nut, and screw rod passes through bearing pin, packing ring, split pin is connected with the torsion bar of right-hand member, and clamping device 2 is by left semi-ring 201, right semi-ring 202, torsion bar 203, left brake block 204, right brake block 205, bearing pin 206, packing ring 207, split pin 208 forms, and wherein left semi-ring is positioned at the lower-left end of drag link mechanism, is by pipe, holding piece, gusset, plate, connecting axle is welded, and the lower right that right semi-ring is positioned at drag link mechanism is by pipe, holding piece, connecting axle is welded, and torsion bar is by pipe, gusset, plate, V-block, baffle plate is welded, and the torsion bar of right semi-ring and right-hand member is linked together by welding manner, and left and right brake block is separately fixed at glue on the holding piece on the semi-ring of left and right, and counterweight balancing mechanism 3 is by suspension hook 301, balancing weight 302, handle 303, bobbin 304 forms, wherein balancing weight is placed on inside bobbin, and suspension hook is through balancing weight center, and handle is welded in outside bobbin, and counterweight balancing mechanism 3 hangs on the torsion bar V-block of right side.
Structural representation of the present invention see Fig. 1.Fig. 2 is the top view of Fig. 1 of the present invention.Be made up of drag link mechanism 1, clamping device 2 and counterweight balancing mechanism 3.Fig. 3 is drag link mechanism schematic diagram of the present invention.It is made up of drag link sleeve 101, pull bar 102, packing ring 103, split pin 104, bearing pin 105, bearing 106, holding screw 107, connecting pin 108, hook 109, screw rod 110, locking nut 111, backing plate 112, and Fig. 4 is clamping device schematic diagram of the present invention.It is made up of left semi-ring 201, right semi-ring 202, torsion bar 203, left brake block 204, right brake block 205, bearing pin 206, packing ring 207, split pin 208.Fig. 5 is counterweight balancing mechanism schematic diagram of the present invention.It is made up of suspension hook 301, pouring weight 302, handle 303, bobbin 304.The scope of the brake torque value specified for helicopter standard, choosing helicopter wheel test brake torque be value is 650 ± 2Nm.Adopt parameterized design, CATIA software is utilized to carry out solid modelling to this experimental rig, after removing counterweight balancing mechanism, position of centre of gravity and the weight of this experimental rig is measured by CATIA software, equal to remove counterweight balancing mechanism utilizing helicopter wheel braking moment values after, around the moment values that wheel center rotating produces, this experimental rig adds that counterweight balancing mechanism hangs on torsion bar around the moment values sum that wheel center rotating produces due to weight itself, and calculate the weight of required balancing weight, counterweight balancing mechanism is hung on torsion bar and sees that whether counterweight balancing mechanism is around wheel center rotating, regulate the parameter of brake disc in anti-skid brake system (ABS) to reach brake torque value required when this experimental rig balances motionless again.And design a kind of helicopter wheel braking moment inspecting experimental rig.
Claims (1)
1. a helicopter brake torque detection experiment device, it is characterized in that, detection experiment device comprises drag link mechanism, clamping device, counterweight balancing mechanism, drag link mechanism is by drag link sleeve, pull bar, packing ring, split pin, bearing pin, bearing, holding screw, connecting pin, hook, screw rod, locking nut, backing plate forms, wherein connected by connecting pin between pull bar and bearing, and fix with holding screw, bearing pin is passed through between hook and pull bar, packing ring, split pin is connected together, bearing passes through bolt, nut, packing ring is fixed on the left semi-ring of clamping device, hook on the right-hand member screw rod of clamping device is hooked on clamping device left end hook, and lock with locking nut, screw rod passes through bearing pin, packing ring, split pin is connected with the torsion bar of clamping device right-hand member, clamping device is by left semi-ring, right semi-ring, torsion bar, left brake block, right brake block, bearing pin, packing ring, split pin forms, wherein left semi-ring is positioned at the lower-left end of drag link mechanism, left semi-ring is by left semi-ring pipe, left semi-ring holding piece, left half ring web plate, left half ring flat-plate, left semi-ring connecting axle is welded, the lower right that right semi-ring is positioned at drag link mechanism is by right semi-ring pipe, right semi-ring holding piece, right semi-ring connecting axle is welded, torsion bar is by torsion bar pipe, torsion bar gusset, torsion bar plate, V-block, baffle plate is welded, one end of right semi-ring and torsion bar is linked together by welding manner, left and right brake block is separately fixed on the holding piece on the semi-ring of left and right, V-block is fixed on the other end of torsion bar, counterweight balancing mechanism hanging is on the V-block of torsion bar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310146070.3A CN103207042B (en) | 2013-04-24 | 2013-04-24 | Test device for detecting brake moment of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310146070.3A CN103207042B (en) | 2013-04-24 | 2013-04-24 | Test device for detecting brake moment of helicopter |
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| Publication Number | Publication Date |
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| CN103207042A CN103207042A (en) | 2013-07-17 |
| CN103207042B true CN103207042B (en) | 2015-04-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310146070.3A Active CN103207042B (en) | 2013-04-24 | 2013-04-24 | Test device for detecting brake moment of helicopter |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103785874B (en) * | 2013-10-29 | 2016-02-24 | 中航沈飞民用飞机有限责任公司 | A kind of method using numerical control device to process aircraft engine suspending assembly bolt hole |
| CN103604555B (en) * | 2013-12-04 | 2015-12-02 | 中国飞机强度研究所 | Five-degree-of-freedom follow-up brake moment measurement device |
| CN110803300B (en) * | 2019-11-22 | 2021-05-25 | 航天时代飞鸿技术有限公司 | Testing method of unmanned aerial vehicle wheel braking moment testing tool |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201152818Y (en) * | 2008-02-20 | 2008-11-19 | 杨文俊 | Automobile braking efficiency detection device |
| CN201173837Y (en) * | 2008-03-05 | 2008-12-31 | 中南大学 | Aeroplane wheel braking pair structure strength detection device |
| CN202693185U (en) * | 2012-07-13 | 2013-01-23 | 哈尔滨飞机工业集团有限责任公司 | Equipment for measuring braking torque of aircraft wheel |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06317488A (en) * | 1993-05-07 | 1994-11-15 | Hitachi Chem Co Ltd | Roller driven brake tester |
| KR100224264B1 (en) * | 1997-08-30 | 1999-10-15 | 정몽규 | Brake dynamo system |
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2013
- 2013-04-24 CN CN201310146070.3A patent/CN103207042B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201152818Y (en) * | 2008-02-20 | 2008-11-19 | 杨文俊 | Automobile braking efficiency detection device |
| CN201173837Y (en) * | 2008-03-05 | 2008-12-31 | 中南大学 | Aeroplane wheel braking pair structure strength detection device |
| CN202693185U (en) * | 2012-07-13 | 2013-01-23 | 哈尔滨飞机工业集团有限责任公司 | Equipment for measuring braking torque of aircraft wheel |
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| CN103207042A (en) | 2013-07-17 |
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Effective date of registration: 20160122 Address after: The northeast side of loop 150066 Heilongjiang province Harbin City Hanan Industrial Park Road two, south of the Yangtze River in Nancheng Patentee after: Harbin Hafei Aviation Industry Co. Ltd. Address before: 150066 Heilongjiang Province, Harbin city Youxie Street Pingfang District No. 15 Patentee before: Harbin Aircraft Industrial (Group) Co., Ltd. |