CN109708554B - Stroke measuring clamp for performance detection of aircraft hydraulic booster - Google Patents
Stroke measuring clamp for performance detection of aircraft hydraulic booster Download PDFInfo
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- CN109708554B CN109708554B CN201811623208.3A CN201811623208A CN109708554B CN 109708554 B CN109708554 B CN 109708554B CN 201811623208 A CN201811623208 A CN 201811623208A CN 109708554 B CN109708554 B CN 109708554B
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- mounting seat
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- stroke measuring
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Abstract
The invention discloses a stroke measuring clamp for detecting the performance of an aircraft hydraulic booster, which comprises a U-shaped mounting seat, a support arm, a movable connecting piece and a joint bearing, wherein the movable connecting piece comprises a connecting part and a rod part which are mutually connected, a convex block is arranged at the upper end of the U-shaped mounting seat, a bearing hole for mounting the joint bearing is arranged on the convex block, a bushing is arranged on the joint bearing in a penetrating way, the rod part is movably arranged in the bushing in a penetrating way, a positioning arc surface is arranged at one end of the rod part, which extends out of the bushing, the support arm is arranged on the U-shaped mounting seat, a dial indicator is arranged on the support arm, and the dial indicator is opposite to the.
Description
Technical Field
The invention relates to performance detection equipment of an aircraft hydraulic booster, in particular to a stroke measuring clamp for performance detection of the aircraft hydraulic booster.
Background
Because the aircraft is of various types, the working performance of the booster required by different aircraft is different, so that the booster is of various types, and not only are various performances different, but also the appearance structures of the boosters are different. Aiming at the boosters with different models, a plurality of technical parameters need to be detected in the repair process, if the special test equipment for designing and manufacturing each type of airplane booster can cause unnecessary waste, a simple and practical device is necessary to be developed, a working site does not need to be additionally increased, and the detection requirement can be realized by accessing a general hydraulic device.
The booster can not make the current situation of rectilinear motion under the fixed piston rod state in the test process. The main disadvantages existing in the prior booster test are: in the prior booster test process, a shell or a machine body is fixed on a test type frame, an input rocker arm is operated to enable an output piston rod to do reciprocating motion, and the piston rod can do linear motion in the state. When the piston rod is fixed on the test fixture, the bearing of the piston rod connecting lug has the characteristic of flexible movement direction, so that the shell or the machine body can not move linearly when the rocker arm is operated to make the shell or the machine body move linearly. The movement of the shell is an arc rather than a pure linear movement. Due to the movement mode, certain performances of the booster cannot be accurately measured, the measurement error is increased, and the reliability of the product is reduced.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a stroke measuring clamp with high measuring accuracy for detecting the performance of a hydraulic booster of an airplane.
In order to solve the technical problems, the invention adopts the following technical scheme:
the utility model provides a stroke measurement anchor clamps for aircraft hydraulic booster performance detects, stroke measurement anchor clamps include U-shaped mount pad, support arm, swing joint spare and joint bearing, swing joint spare includes interconnect's connecting portion and pole portion, U-shaped mount pad upper end is equipped with a lug, be equipped with the dead eye that is used for installing joint bearing on the lug, wear to locate a bush on the joint bearing, the pole portion is mobilizable to be worn to locate in the bush, and the one end that the bush was stretched out in pole portion is equipped with the location arc surface, the support arm is installed on the U-shaped mount pad, be equipped with the percentage table on the support arm, the percentage table is just to the location arc surface.
As a further improvement of the above technical solution, preferably, a tightening component is arranged on a side wall of the U-shaped groove of the U-shaped mounting seat, the tightening component includes a jacking block and a stud, the stud is arranged on one side wall of the U-shaped groove in a penetrating manner, and the jacking block points to the other side wall of the U-shaped groove.
As a further improvement of the above technical solution, preferably, the connecting portion is a movable fork, and the movable fork is connected to an input rocker arm of the aircraft hydraulic booster through a pin.
As a further improvement of the above technical solution, preferably, a joint screw is provided at an end face of one end of the rod portion, and the positioning arc surface is provided on a nut of the joint screw.
As a further improvement of the above technical solution, preferably, the bushing has a limit step at one end of the joint bearing, the other end of the bushing is provided with an anti-drop nut, the rod portion is sleeved with the limit nut, and the limit nut is in threaded fit with the rod portion and can abut against the limit step.
As a further improvement of the above technical solution, preferably, the support arm includes L shape portion and U-shaped portion, the U-shaped portion is fixed on the U-shaped mount pad, L shape portion is equipped with two relative splint, be equipped with the half slot on the splint, two half slots are used for installing the percentage table, are equipped with the clamping screw who presss from both sides two half slots on two splint.
As a further improvement of the above technical solution, preferably, the U-shaped portion is connected to the U-shaped mounting seat by a screw, the U-shaped portion is provided with a through hole, the U-shaped mounting seat is provided with a threaded hole, and the screw passes through the through hole and is connected to the threaded hole. .
Compared with the prior art, the invention has the advantages that:
according to the stroke measuring clamp for detecting the performance of the hydraulic booster of the airplane, disclosed by the invention, the distance between the dial indicator and the positioning arc surface on the rod part is constant, so that the measuring accuracy is greatly improved, the measuring error is reduced, and the measuring reliability is improved.
Drawings
Fig. 1 is a front view schematically showing the structure of the stroke measuring jig of the present invention.
Fig. 2 is a side view of the stroke measuring jig of the present invention.
Fig. 3 is a schematic structural view of a U-shaped mounting base in the present invention.
FIG. 4 is a schematic view of a support arm according to the present invention
FIG. 5 is a side view of the arm of the present invention.
Fig. 6 is a schematic structural view of a test fixture used with the stroke measuring jig of the present invention in front elevation.
FIG. 7 is a schematic top view of a test fixture for use with the travel measurement fixture of the present invention.
Fig. 8 is a schematic structural view of an upper support frame of a test fixture used with the stroke measuring fixture of the present invention.
The reference numerals in the figures denote:
1. the device comprises a base plate, 11, a guide plate, 2, a fixed support, 21, a fixed fork-shaped part, 22, a support leg, 23, a pin shaft, 24, an adjusting nut, 3, a movable support, 301, a circular arc groove, 31, an upper support frame, 32, a lower moving frame, 33, a rolling piece, 34, a connecting bolt, 4, a U-shaped mounting seat, 41, a bump, 42, a U-shaped groove, 5, a support arm, 51, L-shaped parts, 511, a clamping plate, 512, a semicircular groove, 513, a clamping screw, 52, a U-shaped part, 53, a screw, 6, a movable connecting piece, 61, a connecting part, 62, a rod part, 621, a positioning circular arc surface, 622, a joint screw, 63, a limiting nut, 7, a joint bearing, 71, a bushing, 711, a limiting step, 72, an anti-falling nut, 8, a jacking component, 81, a jacking block.
Detailed Description
The invention is described in further detail below with reference to the figures and specific examples of the specification.
The invention relates to an aircraft hydraulic booster, which is an existing product and mainly comprises a shell, a piston rod monaural component, an input rocker arm and the like, wherein the shell is of an upper-lower semicircular structure. The stroke measuring clamp for detecting the performance of the aircraft hydraulic booster is matched with a test tool for mobile use, as shown in fig. 6-8, the test tool comprises a bottom plate 1, a fixed support 2 and a movable support 3, the fixed support 2 is fixed on the bottom plate 1, the movable support 3 is movably arranged on the bottom plate 1 relative to the fixed support 2, and the movable support 3 is provided with an arc groove 301 matched with the semicircular outer wall of the aircraft hydraulic booster. The movable support 3 comprises an upper support frame 31 and a lower support frame 32, the guide plate 11 is arranged on the bottom plate 1, the lower support frame 32 is provided with rolling parts 33 capable of moving along two sides of the guide plate 11, and the arc groove 301 is arranged on the upper support frame 31. The rolling members 33 are bearing rollers, the lower moving frame 32 is two bearing frames, each bearing frame is provided with one bearing roller, and two ends of the upper supporting frame 31 are connected with the two bearing frames through connecting bolts 34. Circular arc recess 301 is used for placing the booster, and the booster is placed steadily to laminating outer wall circular arc, assurance booster. The fixed support 2 comprises a fixed fork part 21 and a supporting leg 22, the supporting leg 22 is fixedly connected with the bottom plate 1, and the fixed fork part 21 is connected with a piston rod monaural component of the airplane hydraulic booster through a pin shaft 23. The fixing fork part 21 is of a conventional fork structure, the supporting leg 22 is in threaded connection with the bottom plate 1, the supporting leg 22 is provided with an adjusting nut 24, and the adjusting nut 24 is used for adjusting the direction and the supporting height of the fixing fork part 21 and adjusting the booster to be kept in a horizontal position and a proper length during a test.
As shown in fig. 1 to 5, the stroke measuring fixture for detecting performance of an aircraft hydraulic booster of the present embodiment includes a U-shaped mounting seat 4, a support arm 5, a movable connecting member 6 and a knuckle bearing 7, the movable connecting member 6 includes a connecting portion 61 and a rod portion 62 that are connected to each other, a protruding block 41 is disposed at an upper end of the U-shaped mounting seat 4, a bearing hole for mounting the knuckle bearing 7 is disposed on the protruding block 41, a bushing 71 is disposed on the knuckle bearing 7, the rod portion 62 is movably disposed in the bushing 71, and one end of the rod portion 62 extending out of the bushing 71 is provided with a positioning arc surface 621, the support arm 5 is mounted on the U-shaped mounting seat 4, a dial indicator (not shown in the figure) is disposed on the support arm 5, the dial indicator is directly opposite to the positioning arc surface 621.
When the device is used, a semi-circle body of the lower half part of a shell of the airplane hydraulic booster is arranged on the arc groove 301, a piston rod single lug assembly at one end of the semi-circle body is connected with the fixed support 2, the stroke measuring clamp is clamped on a square body of the upper half part of the shell through the U-shaped mounting seat 4, a connecting part 61 of the movable connecting part 6 is connected with an input rocker arm of the airplane hydraulic booster and is fixed through a pin shaft 23, the operation input rocker arm drives the movable connecting part 6 to drive the shell of the airplane hydraulic booster to move relative to the fixed support 2 through hydraulic pressure force, the operation input rocker arm drives the movable connecting part 6 to move, meanwhile, the shell of the airplane hydraulic booster is driven to move relative to the fixed support 2 through hydraulic pressure. Because the input rocker arm moves in an arc shape, the rod part 62 moves linearly in the bushing 71 and moves slightly in an arc shape around the center of the joint bearing 7, because of the arrangement of the positioning arc surface 621, the distance between any point on the positioning arc surface 621 and the center of the joint bearing 7 is equal, the distance between the dial indicator and the positioning arc surface 621 is constant, the thimble of the dial indicator is always in contact with the positioning arc surface 621, the reading of the dial indicator is changed along with the movement of the positioning arc surface 621, and therefore the dial indicator can accurately read the movement stroke of the input rocker arm, and the performance parameter of the hydraulic booster of the airplane is obtained. The invention changes the traditional test mode, tests the performance of the booster in a mode that the piston rod is fixed and the shell moves, ensures that the shell of the hydraulic booster of the airplane moves in a pure straight line by arranging the movable support 3, and simultaneously ensures that the distance between the dial indicator and the positioning circular arc surface 621 on the rod part 62 is constant, thereby greatly improving the measurement accuracy, reducing the measurement error and improving the measurement reliability.
In this embodiment, a jacking assembly 8 is arranged on a side wall of the U-shaped groove 42 of the U-shaped mounting seat 4, the jacking assembly 8 includes a jacking block 81 and a stud 82, the stud 82 is arranged on one side wall of the U-shaped groove 42 in a penetrating manner, and the jacking block 81 points to the other side wall of the U-shaped groove 42. The U-shaped groove 42 of the U-shaped mounting seat 4 is clamped on the square outer wall of the aircraft hydraulic booster, and the ejector block 81 is adjusted to enable the U-shaped mounting seat 4 to be tightly abutted against the square outer wall of the aircraft hydraulic booster, so that the U-shaped mounting seat 4 is clamped on the square outer wall.
In this embodiment, the connecting portion 61 of the movable connecting member 6 is a movable fork, and the movable fork is connected with the input rocker arm of the aircraft hydraulic booster through a pin 23. The end face of one end of the rod part 62 is provided with a joint screw 622, the joint screw 622 is in threaded connection with the rod part 62, and the positioning arc 621 is arranged on a nut of the joint screw 622. The rod part 62 is actually a screw, the bushing 71 has a limit step 711 at one end of the joint bearing 7, the other end is provided with a retaining nut 72, the rod part 62 is sleeved with the limit nut 63, and the limit nut 63 is in threaded fit with the rod part 62 and can abut against the limit step 711. The retaining nut 72 and the stop step 711 are used to clamp the bushing 71, and the stop nut 63 is used to limit the moving distance of the rod 62. The spherical plain bearing 7 is a standard component.
In this embodiment, the support arm 5 includes L-shaped portion 51 and U-shaped portion 52, the U-shaped portion 52 is fixed on the U-shaped mounting base 4, two opposite clamping plates 511 are arranged on the L-shaped portion 51, a semicircular groove 512 is arranged on the clamping plate 511, the two semicircular grooves 512 are used for mounting a dial indicator, a clamping screw 513 for clamping the two semicircular grooves 512 is arranged on the two clamping plates 511, a mounting hole of the clamping screw 513 is perpendicular to the two semicircular grooves 512, the U-shaped portion 52 is connected with the U-shaped mounting base 4 through a screw 53, a through hole is arranged on the U-shaped portion 52, a threaded hole is arranged on the U-shaped mounting base 4, and the screw 53 penetrates through the through hole.
The working principle is as follows:
because the U-shaped mounting seat 4 is clamped on the square body on the upper part of the aircraft hydraulic booster, theoretically, the U-shaped mounting seat 4 and the square body are fixedly and rigidly connected.
When the input rocker arm is operated to move, the movable connecting piece 6 does slight circular arc motion around the joint bearing 7 under the driving of the motion of the input rocker arm, and the shell of the booster does not move.
When the input rocker arm is operated under the loading hydraulic pressure, the U-shaped mounting seat 4 is rigidly connected with the square body of the booster, the U-shaped mounting seat 4 does not move relative to the shell, the relative fixing support 2 moves along with the shell of the booster, the input rocker arm moves relative to the shell at the moment, the shell moves relative to the fixing support 2, the input rocker arm moves relative to the fixing support 2, and the movement direction of the input rocker arm is consistent with the direction of the shell. The movable connecting piece 6 moves linearly relative to the bushing 71 under the driving of the movement of the input rocker arm and moves slightly in an arc around the knuckle bearing 7, the thimble of the dial indicator is always in contact with the positioning arc surface 621, and the reading of the dial indicator is changed along with the movement of the positioning arc surface 621, so that the dial indicator can accurately read the movement stroke of the input rocker arm, and the performance parameter of the hydraulic booster of the airplane is obtained.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to be limited thereto. Those skilled in the art can make numerous possible variations and modifications to the present invention, or modify equivalent embodiments to equivalent variations, without departing from the scope of the invention, using the teachings disclosed above. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical spirit of the present invention should fall within the protection scope of the technical scheme of the present invention, unless the technical spirit of the present invention departs from the content of the technical scheme of the present invention.
Claims (7)
1. The utility model provides a stroke measurement anchor clamps for aircraft hydraulic booster performance detects which characterized in that: the stroke measuring clamp comprises a U-shaped mounting seat (4), a support arm (5), a movable connecting piece (6) and a joint bearing (7), the movable connecting piece (6) comprises a connecting part (61) and a rod part (62) which are connected with each other, a convex block (41) is arranged at the upper end of the U-shaped mounting seat (4), a bearing hole for mounting the joint bearing (7) is arranged on the convex block (41), a lining (71) is arranged on the joint bearing (7) in a penetrating way, the rod part (62) is movably arranged in the lining (71) in a penetrating way, and one end of the rod part (62) extending out of the bush (71) is provided with a positioning arc surface (621), the support arm (5) is arranged on the U-shaped mounting seat (4), the support arm (5) is provided with a dial indicator, the dial indicator is opposite to the positioning arc surface (621), and a thimble of the dial indicator is always in contact with the positioning arc surface (621).
2. The stroke measuring clamp for detecting the performance of an aircraft hydraulic booster of claim 1, wherein: the U-shaped groove (42) side wall of the U-shaped mounting seat (4) is provided with a jacking component (8), the jacking component (8) comprises a jacking block (81) and a stud (82), the stud (82) penetrates through one side wall of the U-shaped groove (42), and the jacking block (81) points to the other side wall of the U-shaped groove (42).
3. The stroke measuring clamp for detecting the performance of the hydraulic booster of the aircraft according to claim 1 or 2, wherein: the connecting part (61) is a movable fork-shaped part, and the movable fork-shaped part is connected with an input rocker arm of the airplane hydraulic booster through a pin shaft (23).
4. The stroke measuring clamp for detecting the performance of the hydraulic booster of the aircraft according to claim 1 or 2, wherein: the one end terminal surface of pole portion (62) is equipped with joint screw (622), location arc surface (621) are located on the nut of joint screw (622).
5. The stroke measuring clamp for detecting the performance of the hydraulic booster of the aircraft according to claim 1 or 2, wherein: the bush (71) is provided with a limiting step (711) at one end of the joint bearing (7), the other end of the bush is provided with an anti-falling nut (72), the rod part (62) is sleeved with the limiting nut (63), and the limiting nut (63) is in threaded fit with the rod part (62) and can abut against the limiting step (711).
6. The stroke measuring clamp for detecting the performance of the hydraulic booster of the airplane as claimed in claim 1 or 2 is characterized in that the supporting arm (5) comprises an L-shaped part (51) and a U-shaped part (52), the U-shaped part (52) is fixed on the U-shaped mounting seat (4), two opposite clamping plates (511) are arranged on the L-shaped part (51), a semicircular groove (512) is formed in each clamping plate (511), the two semicircular grooves (512) are used for mounting a dial indicator, and a clamping screw (513) for clamping the two semicircular grooves (512) is arranged on each clamping plate (511).
7. The stroke measuring fixture for detecting the performance of an aircraft hydraulic booster of claim 6, wherein: the U-shaped portion (52) is connected with the U-shaped mounting seat (4) through a screw (53), a through hole is formed in the U-shaped portion (52), a threaded hole is formed in the U-shaped mounting seat (4), and the screw (53) penetrates through the through hole and is connected with the threaded hole.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811623208.3A CN109708554B (en) | 2018-12-28 | 2018-12-28 | Stroke measuring clamp for performance detection of aircraft hydraulic booster |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811623208.3A CN109708554B (en) | 2018-12-28 | 2018-12-28 | Stroke measuring clamp for performance detection of aircraft hydraulic booster |
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| CN109708554A CN109708554A (en) | 2019-05-03 |
| CN109708554B true CN109708554B (en) | 2020-07-21 |
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| CN201811623208.3A Active CN109708554B (en) | 2018-12-28 | 2018-12-28 | Stroke measuring clamp for performance detection of aircraft hydraulic booster |
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| CN110044233B (en) * | 2019-05-16 | 2024-03-08 | 沈阳飞机工业（集团）有限公司 | Non-contact rocker arm part free travel checking measuring instrument and use method thereof |
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| CN109703782A (en) * | 2018-12-28 | 2019-05-03 | 长沙五七一二飞机工业有限责任公司 | A kind of Hydraulic Servo Mechanism for Plane device for detecting performance |
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| KR100819978B1 (en) * | 2006-08-01 | 2008-04-07 | 현대자동차주식회사 | Brake system for hybrid and electric vehicle and control method thereof |
| CN202126231U (en) * | 2011-06-24 | 2012-01-25 | 柳州长虹机器制造公司 | Idle stroke detection table of car brake master cylinder and vacuum booster assembly |
| CN102642624B (en) * | 2012-05-11 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Load simulator of plane booster dummy assembly |
| CN102818709B (en) * | 2012-07-25 | 2014-08-27 | 杭州沃镭科技有限公司 | Testing device of comprehensive performance of automotive clutch booster |
| CN105043232A (en) * | 2015-06-23 | 2015-11-11 | 哈尔滨工程大学 | Device and method for calibrating dragged LVDT displacement sensor |
| CN105606369B (en) * | 2015-09-08 | 2018-05-11 | 宁波拓普智能刹车系统有限公司 | A kind of motorcar electric machinery booster is performance test bed |
| CN206362285U (en) * | 2016-12-27 | 2017-07-28 | 浙江正泰电器股份有限公司 | Circuit breaker tripping device for detecting distance of travel |
| CN107941525B (en) * | 2017-11-22 | 2023-09-01 | 温州瑞立科密汽车电子有限公司 | Vacuum booster with brake master cylinder performance detection device and detection method thereof |
| CN108801106B (en) * | 2018-07-28 | 2020-07-03 | 国营芜湖机械厂 | Device and method for measuring dead-point-free stroke of interlocking mechanism |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109703782A (en) * | 2018-12-28 | 2019-05-03 | 长沙五七一二飞机工业有限责任公司 | A kind of Hydraulic Servo Mechanism for Plane device for detecting performance |
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