CN103207042A - Test device for detecting brake moment of helicopter - Google Patents
Test device for detecting brake moment of helicopter Download PDFInfo
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- CN103207042A CN103207042A CN2013101460703A CN201310146070A CN103207042A CN 103207042 A CN103207042 A CN 103207042A CN 2013101460703 A CN2013101460703 A CN 2013101460703A CN 201310146070 A CN201310146070 A CN 201310146070A CN 103207042 A CN103207042 A CN 103207042A
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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 and detect test unit.Especially can solve the problem of helicopter, fixed wing aircraft and automobile brake torque instability and non-stationarity in brake process.
Background technology
The helicopter anti-skid brake system (ABS) is the important plant equipment of helicopter, and helicopter is taken off to play an important role with safe landing.The quality of anti-skid brake system (ABS) performance directly has influence on helicopter and airborne personnel's safety, breaks down for fear of some device of anti-skid brake system (ABS) and causes the paralysis of total system.Just must the brake torque in the helicopter anti-skid brake system (ABS) be detected, to guarantee safety, relatively backward being not easy to of the detection method of traditional helicopter wheel braking moment analog quantity controlled and observed, cost is high again, lead time is long again, increased designer's amount of calculation, labor strength is big, in brake process, exist the wheel tire by brake locking, wheel skid, major defect such as brake torque instability.
Summary of the invention
It is unstable and cause wheel and ground to produce excessive sliding phenomenon to the objective of the invention is to solve helicopter brake torque in brake process, and a kind of brake torque detection test unit is provided.To eliminate currently used technical defective.Technical scheme of the present invention is, detect test unit and comprise drag link mechanism 1, clamping device 2, counterweigh 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, set nut, backing plate is formed, wherein connect by connecting pin between pull bar and the bearing, and fix with holding screw, pass through bearing pin between hook and the pull bar, packing ring, split pin is connected together, bearing is to pass 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 the clamping device left end hook, and lock with set nut, screw rod is to pass 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 side brake block, right brake block, bearing pin, packing ring, split pin is formed, wherein left semi-ring is positioned at the lower-left end of drag link mechanism, left side semi-ring is by left semi-ring pipe, left side semi-ring holding piece, left side semi-ring gusset, left side semi-ring plate, left side semi-ring coupling shaft 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 coupling shaft is welded, torsion bar is by the torsion bar pipe, the torsion bar gusset, the torsion bar plate, V-block, baffle plate is welded, one end of right semi-ring and torsion bar links together by welding manner, left and right sides brake block is separately fixed on right semi-ring holding piece and the left semi-ring holding piece with glue, V-block is fixed on the other end of torsion bar, and counterweigh mechanism hangs on the V-block of torsion bar.Counterweigh mechanism 3 is made up of suspension hook, balancing weight, handle, bobbin,
The suspension hook of described counterweigh mechanism is to pass on the V-block that the balancing weight center hangs over torsion bar.
Advantage of the present invention and beneficial effect are: this test unit cost is low, simple in structure, result of use is good, easy to operate, measuring accuracy is high, satisfy the requirement of helicopter brake torque stability and stationarity in brake process, the present invention adopts parameterized design proposal, can carry out random adjustment according to the requirement of different type of machines brake torque to each parameter, thereby draw the design of different demands, so this test unit has high generality and practicality.This test unit cost is low, simple in structure, result of use is good, and is easy to operate, measuring accuracy is high, satisfied the requirement of helicopter brake torque stability and stationarity in brake process, and this test unit has high generality and practicality.
Description of drawings
Fig. 1 is structural representation of the present invention.
Fig. 2 is the vertical view of Fig. 1 of the present invention.
Fig. 3 is drag link mechanism synoptic diagram of the present invention.
Fig. 4 is clamping device synoptic diagram of the present invention.
Fig. 5 is counterweigh structural scheme of mechanism of the present invention.
Embodiment
Below the present invention is described in further details.Detect test unit and comprise drag link mechanism 1, clamping device 2, counterweigh mechanism 3, it 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, set nut 111, backing plate 112 is formed, wherein connect by connecting pin between pull bar and the bearing, and fix with holding screw, be to pass through bearing pin between hook and the pull bar, packing ring, split pin is connected together, bearing is to pass through bolt, nut, packing ring is fixed on the left semi-ring, hook on the right-hand member screw rod is hooked on the left end hook, and lock with set nut, screw rod is to pass through bearing pin, packing ring, split pin is connected with the torsion bar of right-hand member, clamping device 2 is by left semi-ring 201, right semi-ring 202, torsion bar 203, left side brake block 204, right brake block 205, bearing pin 206, packing ring 207, split pin 208 is formed, wherein left semi-ring is positioned at the lower-left end of drag link mechanism, be by pipe, holding piece, gusset, plate, coupling shaft is welded, the lower right that right semi-ring is positioned at drag link mechanism is by pipe, holding piece, coupling shaft is welded, torsion bar is by pipe, gusset, plate, V-block, baffle plate is welded, the torsion bar of right semi-ring and right-hand member links together by welding manner, left and right sides brake block is to be separately fixed on the holding piece on the semi-ring of the left and right sides with glue, counterweigh mechanism 3 is by suspension hook 301, balancing weight 302, handle 303, bobbin 304 is formed, wherein balancing weight is placed on the bobbin the inside, suspension hook passes the balancing weight center, handle is welded in the bobbin outside, and counterweigh mechanism 3 hangs on the torsion bar V-block of right side.
Be structural representation of the present invention referring to Fig. 1.Fig. 2 is the vertical view of Fig. 1 of the present invention.Formed by drag link mechanism 1, clamping device 2 and counterweigh mechanism 3.Fig. 3 is drag link mechanism synoptic 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, set nut 111, backing plate 112, and Fig. 4 is clamping device synoptic 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 counterweigh structural scheme of mechanism of the present invention.It is made up of suspension hook 301, pouring weight 302, handle 303, bobbin 304.Scope with the brake torque value of helicopter standard code is example, and choosing helicopter wheel test brake torque is 650 ± 2Nm for value.Adopt parameterized design proposal, utilize CATIA software that this test unit is carried out solid modelling, after removing counterweigh mechanism, measure centre of gravity place and the weight of this test unit by CATIA software, after utilizing helicopter wheel braking moment values to equal to remove counterweigh mechanism, this test unit adds that counterweigh mechanism hangs over the moment values sum that produces around the rotation of wheel center on the torsion bar because the weight of itself is rotated the moment values that produces around the wheel center, and calculate the weight of needed balancing weight, counterweigh mechanism hung over see on the torsion bar that whether counterweigh mechanism rotates around the wheel center, regulate in the anti-skid brake system (ABS) parameter of brake flange again and reach this test unit balance needed brake torque value when motionless.Detect test unit and design a kind of helicopter wheel braking moment.
Claims (2)
1. a helicopter brake torque detects test unit, it is characterized in that, detect test unit and comprise drag link mechanism, clamping device, counterweigh 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, set nut, backing plate is formed, wherein connect by connecting pin between pull bar and the bearing, and fix with holding screw, pass through bearing pin between hook and the pull bar, packing ring, split pin is connected together, bearing is to pass 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 the clamping device left end hook, and lock with set nut, screw rod is to pass 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 side brake block, right brake block, bearing pin, packing ring, split pin is formed, wherein left semi-ring is positioned at the lower-left end of drag link mechanism, left side semi-ring is by left semi-ring pipe, left side semi-ring holding piece, left side semi-ring gusset, left side semi-ring plate, left side semi-ring coupling shaft 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 coupling shaft is welded, torsion bar is by the torsion bar pipe, the torsion bar gusset, the torsion bar plate, V-block, baffle plate is welded, one end of right semi-ring and torsion bar links together by welding manner, left and right sides brake block is separately fixed on right semi-ring holding piece and the left semi-ring holding piece with glue, V-block is fixed on the other end of torsion bar, and counterweigh mechanism hangs on the V-block of torsion bar.
2. a helicopter brake torque detects test unit, it is characterized in that, the suspension hook of described counterweigh mechanism is to pass on the V-block that the balancing weight center hangs over 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 true CN103207042A (en) | 2013-07-17 |
| CN103207042B 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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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103604555A (en) * | 2013-12-04 | 2014-02-26 | 中国飞机强度研究所 | Five-degree-of-freedom follow-up brake moment measurement device |
| CN103785874A (en) * | 2013-10-29 | 2014-05-14 | 中航沈飞民用飞机有限责任公司 | Method for machining bolt holes in hanging subassembly of aircraft engine by using numerical control equipment |
| CN110803300A (en) * | 2019-11-22 | 2020-02-18 | 航天时代飞鸿技术有限公司 | Tool and method for testing braking moment of airplane wheel of unmanned aerial vehicle |
Citations (5)
| 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 |
| 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 |
-
2013
- 2013-04-24 CN CN201310146070.3A patent/CN103207042B/en active Active
Patent Citations (5)
| 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 |
| 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 |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103785874A (en) * | 2013-10-29 | 2014-05-14 | 中航沈飞民用飞机有限责任公司 | Method for machining bolt holes in hanging subassembly of aircraft engine by using numerical control equipment |
| 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 |
| CN103604555A (en) * | 2013-12-04 | 2014-02-26 | 中国飞机强度研究所 | Five-degree-of-freedom follow-up brake moment measurement device |
| CN110803300A (en) * | 2019-11-22 | 2020-02-18 | 航天时代飞鸿技术有限公司 | Tool and method for testing braking moment of airplane wheel of unmanned aerial vehicle |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103207042B (en) | 2015-04-29 |
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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. |