CN106705806B - Device for detecting position of hanging point of airplane - Google Patents
Device for detecting position of hanging point of airplane Download PDFInfo
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- CN106705806B CN106705806B CN201710046588.8A CN201710046588A CN106705806B CN 106705806 B CN106705806 B CN 106705806B CN 201710046588 A CN201710046588 A CN 201710046588A CN 106705806 B CN106705806 B CN 106705806B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/14—Measuring arrangements characterised by the use of mechanical techniques for measuring distance or clearance between spaced objects or spaced apertures
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/24—Measuring arrangements characterised by the use of mechanical techniques for measuring angles or tapers; for testing the alignment of axes
- G01B5/25—Measuring arrangements characterised by the use of mechanical techniques for measuring angles or tapers; for testing the alignment of axes for testing the alignment of axes
- G01B5/252—Measuring arrangements characterised by the use of mechanical techniques for measuring angles or tapers; for testing the alignment of axes for testing the alignment of axes for measuring eccentricity, i.e. lateral shift between two parallel axes
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- A Measuring Device Byusing Mechanical Method (AREA)
Abstract
The invention discloses a device for detecting the position of a hanging point of an airplane, and belongs to the field of test measurement design. Comprises a transverse shaft component, a long shaft, a sliding sleeve component and a short shaft component. The transverse distance measurement of the hanging points is realized by respectively inserting one end of each of two long shafts into a left hanging point and a right hanging point, respectively inserting the other end of each of the two long shafts into transverse adjusting shafts on two sides of a transverse adjusting shaft assembly, reading the distance between the left hanging point and the right hanging point by using scales on the transverse adjusting shafts, and adjusting the depth of the long shafts inserted into the hanging points to avoid obstacles between the hanging points. The method for measuring the coaxiality of the hoisting points comprises the steps of inserting a long shaft into a front hoisting point, inserting a short shaft into a rear hoisting point, and connecting a sliding sleeve assembly with the two shafts. In the measurement process, the top end of the short shaft is attached to the sliding sleeve, the position of the sliding block with the groove of the sliding sleeve assembly on the sliding sleeve and the angle between the sliding sleeve assembly and the long shaft are adjusted, the attachment of the semicircular surface of the lower part of the sliding block with the groove and the short shaft is guaranteed, and the data of the coaxiality deviation of the front hoisting point and the rear hoisting point are read by utilizing the scales. The invention has lower requirements on objective conditions such as operation space, measurement environment and the like, is simple to operate and can obtain measurement data in real time.
Description
Technical Field
The invention belongs to the field of test measurement design, and particularly relates to a device for detecting the position of a hanging point of an airplane.
Background
The reverse thrust device is connected with the airplane through an airplane hanger hanging point, and therefore the accuracy of the hanger hanging point needs to be measured and verified. The detection of the position of the aircraft hanging point generally refers to the coaxiality measurement of the aircraft hanging point on the same side and the distance measurement of the different-measurement hanging points, the traditional method for detecting the position of the aircraft hanging point is generally completed by using laser tracker electronic equipment, the laser tracker is expensive in manufacturing cost and complex to operate, the requirement of the instrument on a test environment is high, and the data processing is time-consuming. Due to the particularity of the operation environment of the aircraft hanger, a measuring device which is convenient and simple to operate and meets the measuring precision is needed, and rapid and accurate detection can be carried out anytime and anywhere.
Disclosure of Invention
In order to solve the problems, the invention provides a detection device capable of measuring the hanging points of an airplane hanger, which can accurately measure the distance and the coaxiality of the hanging points in a space range.
The invention relates to a position detection device for an airplane hanging point, which is used for detecting the coaxiality of hanging points on the same side and the distance between hanging points on different sides, and comprises:
the transverse shaft assembly comprises two transverse adjusting shafts with distance scales, one ends of the two transverse adjusting shafts are mutually connected in a sliding manner, and the other ends of the two transverse adjusting shafts are respectively detachably connected with a long shaft;
the two long shafts respectively penetrate through the first hoisting points on different sides, the first ends of the two long shafts are connected with the transverse adjusting shaft, and the second ends of the two long shafts extend to the second hoisting points on the same side;
the sliding sleeve assembly comprises a sleeve, a sliding sleeve fixedly connected with the sleeve and a sliding block sliding on the sliding sleeve, the sleeve is sleeved at the second end of the long shaft, the sleeve and/or the second end are/is provided with angle scales, the sliding direction of the sliding block is vertical to the axial direction of the sleeve, the sliding block and/or the sliding sleeve are/is provided with distance scales, and one end of the sliding block is provided with a semicircular groove;
and the short shaft assembly comprises a short shaft capable of penetrating through the second hoisting point, and one end of the short shaft is in contact with the groove intrados of the sliding block.
The measuring of the transverse distance between the lifting points is realized by respectively inserting one end of each of two long shafts into a left lifting point and a right lifting point, respectively inserting the other end of each of the two long shafts into transverse adjusting shafts on two sides of a transverse adjusting shaft assembly, ensuring the connection and fixation of the long shafts by adjusting the depth of the transverse adjusting shaft on one side inserted into an adjusting rod, reading the distance between the left lifting point and the right lifting point by using scales on the transverse adjusting shafts, and adjusting the depth of the long shafts inserted into the lifting points.
The method for measuring the coaxiality of the lifting points is characterized in that a long shaft is inserted into a front lifting point, a short shaft is inserted into a rear lifting point, and a sliding sleeve assembly is connected with the two shafts. In the measurement process, with the laminating of minor axis top and sliding sleeve, through the position of the trough of belt slider of adjustment sliding sleeve subassembly on the sliding sleeve and the angle of sliding sleeve subassembly and major axis, guarantee trough of belt slider lower part semicircle face and the laminating of minor axis, utilize the scale to read front and back hoisting point axiality deviation data, including deviation angle and displacement in this orientation.
Preferably, the long shaft is provided with a ring groove along the circumferential direction at one end extending into the sleeve, the sleeve is provided with a round hole, and the pin passes through the round hole and extends into the ring groove to limit the axial movement of the sleeve relative to the long shaft.
Preferably, one end of the sliding groove of the sliding sleeve is provided with a limiting pin, so that the sliding block sliding in the sliding groove is prevented from sliding out of the end.
Preferably, the horizontal shaft assembly includes a first horizontal adjustment shaft, a second horizontal adjustment shaft and an adjustment rod, wherein the first horizontal adjustment shaft and the second horizontal adjustment shaft are butted with each other, an external thread is provided at one butted end, and the adjustment rod is provided with an internal thread.
Preferably, the fixing device further comprises a fixing bracket, wherein the fixing bracket is arranged at the first hanging point, extends towards the second hanging point, and forms a mounting end, and the mounting end is used for keeping the long shaft in an axial horizontal state.
Preferably, the short shaft assembly further comprises a nut which is adapted to be mounted on the cylinder, a hole is formed in the middle of the nut, an annular protrusion is arranged on the short shaft of the short shaft assembly, the first part of the short shaft, which is divided by the annular protrusion, and the annular protrusion are limited by the nut to move in the cylinder and extend through the cylinder continuously.
Preferably, the stub shaft assembly further comprises a split pin, a second portion of the stub shaft divided by the annular protrusion is provided with a through hole, and the split pin passes through the through hole so that the second portion is restricted by the nut from moving outside the cylinder.
The device for detecting the position of the hanging point of the aircraft hanger is a measuring device which is convenient and fast, is easy to operate and meets the measuring precision of the hanging point of the aircraft hanger, can carry out rapid and accurate detection at any time, and compared with the prior art, the device has the advantages of lower processing and manufacturing cost, lower requirements on objective conditions such as operating space, measuring environment and the like, and is easy to operate and capable of obtaining measuring data in real time.
The invention adopts a novel measuring structure to simultaneously measure the left-right distance and the front-back coaxiality of the hanging points of the aircraft hanger and can achieve the purpose of avoiding obstacles between the left hanging point and the right hanging point. The structure, the principle and the operation mode of the measuring tool can provide certain reference and help for the design of subsequent related measuring tools, and the detection of space hole distance and hole coaxiality can be realized under the conditions of different use purposes and use occasions by adjusting the sizes of partial structures or parts.
Drawings
Fig. 1 is a schematic structural diagram of a detection device according to a preferred embodiment of the device for detecting the position of an aircraft hanging point.
FIG. 2 is a cross-axis component structure of the embodiment of FIG. 1.
FIG. 3 is a schematic structural view of the sliding sleeve assembly of the embodiment of FIG. 1.
FIG. 4 is a schematic view of the stub shaft assembly of the embodiment of FIG. 1 according to the present invention.
FIG. 5 is a cross-sectional view of the stub shaft assembly and tab connection of the embodiment of FIG. 1 according to the present invention.
Wherein, 1 is a transverse shaft component, 2 is a long shaft, 3 is a sliding sleeve component, 4 is a short shaft, 5 is a pin, 6 is a lug, and 7 is a fixed bracket;
101 is a first horizontal adjusting shaft, 102 is a second horizontal adjusting shaft, 103 is an adjusting rod, and 104 is a bolt;
301 is a sleeve, 302 is a sliding sleeve, 303 is a sliding block, 304 is a limit pin, and 305 is a round hole;
401 is a short shaft, 402 is a nut, 403 is a cotter pin, 404 is an annular protrusion;
61 is a cylinder, 71 is a cylindrical structure, and 7 is a bracket.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
The invention provides a position detection device for an airplane hanging point, which is used for detecting the coaxiality of hanging points on the same side and the distance between hanging points on different sides, as shown in figure 1, a structure A represents a hanging point obstacle, the periphery of the structure A comprises four hanging points, A1-A4, wherein A1 and A2 are respectively a front hanging point and a rear hanging point on the same side, A3 and A4 are respectively a front hanging point and a rear hanging point on the other side, and the hanging points are provided with hanging point holes, the position detection device for the airplane hanging point takes a single-lug structure as an example, and referring to figure 1, the position detection device for the airplane hanging point comprises:
the transverse shaft assembly 1, refer to fig. 2, comprises two transverse adjusting shafts 101,102 with distance scales, wherein one ends of the two transverse adjusting shafts 101,102 are connected with each other in a sliding way, and the other ends are respectively detachably connected with a long shaft 2;
the two long shafts 2 respectively penetrate through first lifting points A1 and A3 on different sides, the first ends of the long shafts are connected with the transverse adjusting shaft, and the second ends of the long shafts extend to second lifting points A2 and A4 on the same side;
the sliding sleeve assembly 3, referring to fig. 3, includes a sleeve 301, a sliding sleeve 302 fixedly connected to the sleeve 301, and a sliding block 303 sliding on the sliding sleeve 302, wherein the sleeve 301 is sleeved on the second end of the long shaft 2, the sleeve 301 and/or the second end has an angle scale, the sliding direction of the sliding block 303 is perpendicular to the axial direction of the sleeve 301, the sliding block 303 and/or the sliding sleeve 302 has a distance scale, and one end of the sliding block 303 is provided with a semicircular groove;
the stub shaft assembly 4, referring to fig. 4, includes a stub shaft 401 capable of passing through the second suspension point, and one end of the stub shaft 401 is in contact with the groove intrados of the slider 303.
Homonymy hoisting point axiality and heteronymy hoisting point interval can be carried out through above-mentioned structure, specifically as follows:
distance between hoisting points on different sides: the transverse shaft assembly is used for measuring the distance between opposite side hanging points A1 and A3, the distance value is read through scales on the transverse adjusting shafts 101 and 102, the lengths of the two transverse adjusting shafts are given in advance, the end parts of the two transverse adjusting shafts are respectively fixed on the long shaft, the long shaft penetrates through the hanging points, the length of the transverse adjusting shafts is equivalent to that the end parts of the transverse adjusting shafts are fixed on the two hanging points on the opposite side, the other ends of the transverse adjusting shafts are in contact adjustment, and the distance between the opposite side hanging points can be measured according to the distance scale degrees on the transverse adjusting shafts in the adjustment process.
Coaxiality of hoisting points on the same side: taking two suspension points A3 and a4 as an example, A3 is the first suspension point, a4 is the second suspension point, the long axis 2 passes through the first suspension point A3, the short axis 401 passes through the second suspension point a4, the long axis 2 and the short axis 401 are connected with each other through a sliding sleeve assembly 3, specifically, referring to fig. 3, the sliding sleeve assembly 3 defines a connecting end, which is a sleeve 301 connecting the long axis 2 and a sliding block 303 connecting the short axis 401, the sleeve 301 and the sliding block 303 are connected through a sliding sleeve 302, and the measurement principle is as follows:
the end arc of the short shaft 401 passing through a4 fits closely in the end semicircular groove of the slider 303, so that, assuming the short shaft 401 is eccentric (here, assuming that the two suspension points A3 and a4 are originally coaxial, and the a4 is not coaxial any more), the short shaft 401 will drive the slider 303 to move, either up/down, left/right, or oblique, and the oblique movement can be decomposed into up/down movement and left/right movement, so that the two cases will be described separately below. For convenience of explanation, it is stated in fig. 3 that the up/down direction is the up/down direction along the movement direction of the slider, the vertical direction is the up/down direction, and the left/right direction is the vertical direction along the axial direction of the sleeve.
When moving up/down, the short shaft 401 only drives the sliding block 303 to move up/down, the sliding sleeve 302 is not moved, and therefore, the sleeve 301 is not moved, at this time, the eccentric degree of the two suspension points A3 and a4 can be read according to the moving distance of the sliding block 303 relative to the sliding sleeve 302, and the eccentric direction is also fixed up or down.
When moving leftwards/rightwards, as can be seen from the prior art fig. 3, the side wall of the sliding sleeve 302 will restrict the movement of the short shaft 401, and at this time, the sliding sleeve 302 in fig. 3 will be deflected 90 ° clockwise/anticlockwise around the bottom, and then the sliding block 303 is pushed to move. When the sliding sleeve 302 deflects 90 °, the sleeve 301 is driven to deflect, and at this time, the eccentricity of the two suspension points A3 and a4 can be read according to the deflection angle of the sleeve and the sliding distance of the sliding block.
It should be noted that the above-mentioned explanation is a hypothetical method, and only for the convenience of those skilled in the art to understand the measurement principle, in practice, whether the two suspension points are eccentric and the eccentric degree are determined after the test piece is processed, and there is no movement process, so the above description of the short shaft deflecting the sliding sleeve by 90 ° is not in accordance with the mechanical principle, in the actual measurement engineering, the short shaft and the long shaft are both motionless, and what is moved is the sliding sleeve assembly, which artificially swings the sliding sleeve 302 and the sliding block 303, so that the sleeve 301 and the sliding block 303 are adapted to connect the long shaft and the short shaft, and further, the eccentric degree of the suspension points can be measured.
It should be noted that, the design of the scale described in this embodiment belongs to a conventional design, and the scale is designed on two structures that change with each other, without limitation, based on the convenient implementation of the skilled in the art, for example, for the angle scale, a reference object may be arranged on the long axis, and the angle scale (the sleeve is a cylindrical structure, and exactly corresponds to an angle of 360 degrees) is arranged on the sleeve 301 connected with the long axis along the circumferential direction; a reference object can be arranged on the sleeve, and angle scales are arranged on the long shaft; it is also possible to provide both with angular scales, with any angle of a certain structure as a reference, etc.
In an alternative embodiment, referring to fig. 3, the long shaft 2 is provided with an annular groove along the circumferential direction at one end extending into the sleeve 301, the sleeve 301 is provided with a round hole 305, and the pin 5 passes through the round hole 305 and extends into the annular groove to limit the axial movement of the sleeve 301 relative to the long shaft 2, so as to ensure that the two can only rotate mutually.
In an alternative embodiment, referring to fig. 3, the sliding sleeve 302 defines a sliding slot, and a limit pin 304 is disposed at the bottom end of the sliding slot, so that the sliding block 303 can only slide into the sliding slot from the upper end of the sliding sleeve 302, and cannot slide out from the lower side of the sliding slot due to the fact that the short shaft is not installed yet during installation. In another alternative embodiment, both ends of the sliding groove can be provided with outlets, namely, the sliding block is limited in the sliding groove of the sliding sleeve in the machining process, and the sliding block and the sliding groove can not be separated.
In this embodiment, the transverse shaft assembly 1 measures the distance between the opposite-side hanging points A3 and a1 through two transverse adjustment shafts, and the specific structure thereof may be, for example: the adjusting device comprises a first horizontal adjusting shaft 101, a second horizontal adjusting shaft 102, an adjusting rod 103 and a bolt 104, wherein the lengths of the first horizontal adjusting shaft 101 and the second horizontal adjusting shaft 102 are known, at least one end part of the first horizontal adjusting shaft is provided with a length scale, one end with the length scale is provided with an external thread, the adjusting rod 103 is provided with an internal thread, the adjusting rod 103 is rotated to enable the ends with the scales of the first horizontal adjusting shaft 101 and the second horizontal adjusting shaft 102 to be close to each other or far away from each other, and it can be understood that the design has requirements on the screwing direction of the threads, and the design belongs to the technology known by a person skilled in the art. In this embodiment, in order to fix the rotated adjusting lever 103 relative to the two lateral adjusting shafts, a threaded hole is formed in the adjusting lever 103, and a bolt is inserted through the threaded hole and pressed against the lateral adjusting shaft disposed in the adjusting lever 103, so that the structure is relatively stable.
Referring to fig. 1, the device for detecting the position of an aircraft hanging point further includes a fixing bracket 7, where the fixing bracket 7 is disposed at the first hanging point, extends toward the second hanging point, and forms a hanging end, and the hanging end is used for keeping the long shaft in an axial horizontal state.
It can be understood that after the long shaft 2 passes through the first hanging point A3, in the process of extending to the second hanging point a4, in order to bend due to gravity and the like, and further generate measurement error, in order to solve this problem, the present embodiment adds a fixing bracket 7, one end of the fixing bracket 7 is fixed at the first hanging point, and it can extend a section of cylindrical structure 71 at the first hanging point, and the cylindrical structure 71 is coaxial with the hanging point hole of the hanging point, and as the extension of the hanging point, it can ensure that the long shaft 2 passing through it keeps a certain level. The fixing bracket may extend toward the second hanging point a4 through the high-strength bracket 72, and a mounting end may be formed near the end of the long shaft, and the mounting end may be in the form of a cylinder, a tray, a clip, or the like, and fig. 1 shows an embodiment of the clip, and the long shaft is held in an axially horizontal state by holding the end of the long shaft with the clip. The term "the long axis is kept axially horizontal" means that the long axis is axially straight and the straight line coincides with the axis of the suspension point hole of the suspension point.
The device for detecting the position of the hanging point of the airplane further comprises a tab 6, referring to fig. 1, the tab 6 is loaded at the second hanging point a4, a cylinder 61 extends along the axial direction of the hanging point hole of the second hanging point a4, the cylinder 61 is provided with an external thread, and the short shaft of the short shaft assembly 4 passes through the cylinder 61 and then contacts the semicircular groove described above.
Referring to fig. 4 and 5, the stub shaft assembly 4 further includes a nut 402 adapted to be mounted on the cylinder 61, the nut having a hole formed therein, an annular protrusion 404 is disposed on the stub shaft 401 of the stub shaft assembly 4, and a first portion (a left portion in fig. 5) of the stub shaft 401 divided by the annular protrusion 404 and the annular protrusion 404 are both limited by the nut 402 to move within the cylinder 61 and continue to extend through the cylinder. It will be appreciated that the right side of the stub shaft in fig. 5 is a second portion divided by an annular protrusion 404, and the aperture size of the central opening of the nut is the same as the outer diameter of the second portion, but smaller than the outer diameter of the protrusion, so that, referring to fig. 5, the stub shaft 401 can be pushed to the left by turning the nut 402, thereby enabling the second portion to be precisely pressed against the sliding sleeve assembly 3.
In this embodiment, the stub shaft assembly 4 further comprises a cotter pin 403, the second part of the stub shaft being provided with a through hole through which the cotter pin 403 passes, such that the second part is restricted from movement outside the cylinder by the nut, i.e. the stub shaft 401 does not slip out from the left in fig. 5.
The device for detecting the hanging point position of the aircraft hanger can be used as a measuring device which is convenient and fast, is simple to operate, meets the requirements of measuring precision and measuring environment, and can be used for quickly and accurately detecting at any time and any place.
In the aspect of cost: the cost of machining a set of detection device is far lower than that of a laser tracker;
the technical aspect is as follows: the method is not limited by environment, the measurement result is not influenced in different environments, the requirement on the measurement space is low, the obstacle of the space can be overcome through self structure adjustment, and the method accords with the environment specificity of the detection of the hanging point of the aircraft hanger;
in the aspect of efficiency: the measurement operation is simple, and the measurement data can be obtained immediately.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (7)
1. The utility model provides an aircraft hangs hoisting point position detection device for detect the axiality of homonymy hoisting point and the interval of heteronymy hoisting point, its characterized in that, aircraft hangs hoisting point position detection device includes:
the transverse shaft assembly (1) comprises two transverse adjusting shafts with distance scales, one ends of the two transverse adjusting shafts are mutually connected in a sliding manner, and the other ends of the two transverse adjusting shafts are respectively detachably connected with a long shaft (2);
the two long shafts (2) respectively penetrate through the first hoisting points on the different sides, the first ends of the two long shafts are connected with the transverse adjusting shaft, and the second ends of the two long shafts extend to the second hoisting points on the same side;
the sliding sleeve assembly (3) comprises a sleeve (301), a sliding sleeve (302) fixedly connected with the sleeve and a sliding block (303) sliding on the sliding sleeve, the sleeve is sleeved at the second end of the long shaft (2), the sleeve and/or the second end is/are provided with angle scales, the sliding direction of the sliding block is vertical to the axial direction of the sleeve, the sliding block and/or the sliding sleeve are/is provided with distance scales, and one end of the sliding block is provided with a semicircular groove;
a stub shaft assembly (4) comprising a stub shaft (401) capable of passing through the second suspension point, one end of the stub shaft being in contact with the groove intrados of the slider;
the eccentric measuring device comprises a sliding sleeve assembly (3), a sleeve (301) is connected with a long shaft (2), a semicircular groove of a sliding block (303) is in contact with a short shaft (401), the sleeve (301) is connected with the sliding block (303) through a sliding sleeve (302), when the coaxiality of a first hanging point and a second hanging point on the same side is measured, the long shaft penetrates through the first hanging point, the short shaft penetrates through the second hanging point, the sliding sleeve (302) and the sliding block (303) are swung, so that the sleeve (301) and the sliding block (303) are respectively in adaptive connection with the long shaft and the short shaft, the eccentric degree of the hanging point can be measured, the eccentric direction is determined through the deflection angle of the sliding sleeve (302), and the eccentric degree is determined through the sliding.
2. An aircraft hanging point position detection device according to claim 1, wherein the long shaft is provided with a circumferential groove at one end extending into the sleeve, the sleeve is provided with a circular hole, and a pin (5) passes through the circular hole and extends into the circumferential groove for limiting axial movement of the sleeve relative to the long shaft.
3. An aircraft hanging position detecting device according to claim 1, wherein a stopper pin is provided at one end of the slide groove of the slide sleeve to prevent the slider sliding in the slide groove from sliding out of the end.
4. The device for detecting the position of an aircraft hanging point according to claim 1, wherein the cross shaft assembly comprises a first cross adjustment shaft, a second cross adjustment shaft and an adjustment rod, wherein the first cross adjustment shaft and the second cross adjustment shaft are butted with each other, an external thread is provided at one butted end, and the adjustment rod is provided with an internal thread.
5. The aircraft hang point position detection device of claim 1, further comprising a fixing bracket (7), wherein the fixing bracket (7) is arranged at the first hang point, extends towards the second hang point, and forms a mounting end, and the mounting end is used for keeping the long shaft in an axial horizontal state.
6. The aircraft hang-point position detection device as claimed in claim 1, further comprising a tab (6), wherein the tab (6) is loaded at the second hang point, and a cylinder (61) extends along the axial direction of the hang point hole of the second hang point, the cylinder (61) is provided with an external thread, the stub shaft assembly (4) further comprises a nut adapted to be mounted on the cylinder (61), the nut is provided with a middle opening, an annular protrusion is provided on the stub shaft of the stub shaft assembly (4), and the first part of the stub shaft divided by the annular protrusion and the annular protrusion are limited by the nut to move in the cylinder (61) and extend continuously through the cylinder.
7. An aircraft hang point position detection apparatus as claimed in claim 6, wherein the stub shaft assembly (4) further comprises a split pin, a second part of the stub shaft divided by the annular protrusion is provided with a through hole, and the split pin passes through the through hole so that the second part is restricted by the nut from moving outside the cylinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201710046588.8A CN106705806B (en) | 2017-01-19 | 2017-01-19 | Device for detecting position of hanging point of airplane |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710046588.8A CN106705806B (en) | 2017-01-19 | 2017-01-19 | Device for detecting position of hanging point of airplane |
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| CN106705806A CN106705806A (en) | 2017-05-24 |
| CN106705806B true CN106705806B (en) | 2019-12-20 |
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| CN107717367B (en) * | 2017-08-28 | 2019-02-19 | 浙江大学 | A kind of positioning inspection tooling of aircraft engine hanging joint |
| CN108896030A (en) * | 2018-08-15 | 2018-11-27 | 深圳市闪龙科技有限公司 | Space positioning apparatus |
| CN113483640B (en) * | 2021-06-25 | 2022-06-14 | 成都飞机工业（集团）有限责任公司 | Device and method for adjusting and detecting limit angle of lug of screw sleeve of pull rod of cartridge receiver |
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