CN112857184A - Undercarriage wheel corner measuring device - Google Patents
Undercarriage wheel corner measuring device Download PDFInfo
- Publication number
- CN112857184A CN112857184A CN201911195803.6A CN201911195803A CN112857184A CN 112857184 A CN112857184 A CN 112857184A CN 201911195803 A CN201911195803 A CN 201911195803A CN 112857184 A CN112857184 A CN 112857184A
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- China
- Prior art keywords
- scale
- measuring device
- landing gear
- wheel
- protrusion
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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
Abstract
The invention relates to the technical field of airplane debugging and discloses a measuring device for the rotation angle of an undercarriage wheel. Undercarriage wheel corner measuring device for measure the corner of a barrel subassembly in the undercarriage, the barrel subassembly includes urceolus and rotates the inner tube of being connected with the urceolus, and the urceolus is connected in the aircraft fuselage, and the inner tube is connected in the aircraft wheel, and undercarriage wheel corner measuring device includes: the scale is wound on the outer cylinder; the pointer is used for indicating the scales on the scale and is detachably arranged on the inner barrel. The undercarriage wheel rotation angle measuring device can be arranged on an airplane nose undercarriage, firstly, the scale indicated by the pointer when the airplane nose wheel is straightened is observed, then, the scale indicated by the pointer when the airplane turning hand wheel is straightened is observed, and the deflection angle of the airplane nose wheel when the turning hand wheel is straightened is obtained through the scale difference of the two scales, so that whether the deflection angle meets the requirement or not is judged. After the front wheel of the airplane is debugged, the pointer arranged on the inner cylinder can be detached so as not to influence the normal flight and sliding of the airplane.
Description
Technical Field
The invention relates to the technical field of airplane debugging, in particular to a device for measuring the rotation angle of an undercarriage wheel.
Background
One way to steer the aircraft in a turn on the ground is to steer the wheels on the nose landing gear of the aircraft, i.e. to steer the nose wheels of the aircraft to turn. The steering of the airplane during the taxiing on the ground is generally controlled by operating a turning hand wheel in an airplane cab, namely, an airplane driver operates the turning hand wheel to adjust the deflection angle of a front wheel of the airplane, so that the airplane is steered.
If the airplane needs to slide along a straight line towards the front, the turning hand wheel needs to be straightened so that the front wheel of the airplane rolls towards the front. However, if the front wheel of the airplane is not properly assembled or the equipment is aged, the front wheel of the airplane is not completely aligned when the turning hand wheel is aligned; once this occurs, a flight accident is highly likely to occur.
Disclosure of Invention
In view of the above, an object of the present invention is to provide a landing gear wheel turning angle measuring device capable of measuring a deflection angle of a front wheel of an aircraft when a turning hand wheel is turned, and determining whether the deflection angle of the front wheel is within a predetermined range to avoid a flight accident.
In order to achieve the purpose, the invention adopts the following technical scheme:
the utility model provides an undercarriage wheel corner measuring device for measure the corner of barrel subassembly in the undercarriage, the barrel subassembly include the urceolus and with the urceolus rotates the inner tube of connecting, the urceolus is connected in the aircraft fuselage, the inner tube is connected in the aircraft wheel, undercarriage wheel corner measuring device includes:
the scale is wound on the outer cylinder;
and the pointer is used for indicating the scale marks on the scale and is detachably arranged on the inner barrel.
Preferably, the device for measuring the wheel rotation angle of the landing gear further comprises a mounting seat, a clamping groove is formed in the mounting seat, a protrusion is arranged on the inner barrel, and the protrusion is clamped in the clamping groove.
Preferably, one side of the mounting seat, which is far away from the clamping groove, is provided with a crack, and the pointer is clamped in the crack.
Preferably, the protrusion comprises a first protrusion and a second protrusion, a clamping shaft is erected between the first protrusion and the second protrusion, and the clamping shaft is clamped in the clamping groove.
Preferably, the number of the clamping shafts is two, a set screw is screwed on the first side wall of the clamping groove, and the set screw abuts against one clamping shaft, so that the other clamping shaft abuts against the second side wall of the clamping groove.
Preferably, the second side wall is inclined toward the inner side of the card slot from the bottom wall of the card slot to the opening of the card slot.
Preferably, one end of the scale is connected to the other end of the scale by a tension spring.
Preferably, one end of the scale is connected to the other end of the scale by a stud.
Preferably, both ends of the scale are provided with bending parts, the two bending parts are opposite to each other, and the stud penetrates through the two bending parts.
Preferably, the stud is sleeved with a protective sleeve.
The invention has the beneficial effects that:
the undercarriage wheel rotation angle measuring device can be arranged on an airplane nose undercarriage, firstly, the scale indicated by the pointer when the airplane nose wheel is straightened is observed, then, the scale indicated by the pointer when the airplane turning hand wheel is straightened is observed, and the deflection angle of the airplane nose wheel when the turning hand wheel is straightened is obtained through the scale difference of the two scales, so that whether the deflection angle meets the requirement or not is judged. After the front wheel of the airplane is debugged, the pointer arranged on the inner cylinder can be detached so as not to influence the normal flight and sliding of the airplane.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the description of the embodiments of the present invention will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the contents of the embodiments of the present invention and the drawings without creative efforts.
FIG. 1 is a schematic view of a portion of the structure of a landing gear;
FIG. 2 is an enlarged view of area A of FIG. 1;
FIG. 3 is a three-dimensional view one of the mount;
FIG. 4 is a second three-dimensional view of the mount;
FIG. 5 is a three-dimensional view of a pointer;
FIG. 6 is a top view of a scale according to one embodiment;
FIG. 7 is an enlarged view of area B of FIG. 6;
FIG. 8 is a plan view of a scale in the second embodiment;
fig. 9 is an enlarged view of the region C in fig. 8.
In the figure:
100-a drum assembly; 101-an outer cylinder; 102-an inner cylinder; 103-a bump; 1031-first projection; 1032-a second bump; 104-a chuck shaft;
1-a scale; 10-bending part; 11-scale marks; 111-a first mounting hole; 112-a second mounting hole; 12-a tension spring;
2-a pointer; 21-clamping plate;
3-mounting a base; 30-crack; 31-a card slot; 311-a first side wall; 312-a second sidewall; 32-set screw.
Detailed Description
In order to make the technical problems solved, technical solutions adopted and technical effects achieved by the present invention clearer, the technical solutions of the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. 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.
Example one
Referring to fig. 1 and 2, the present embodiment provides a landing gear wheel rotation angle measuring device for measuring the rotation angle of a drum assembly 100 in a landing gear, wherein the drum assembly 100 comprises an outer cylinder 101 and an inner cylinder 102 rotationally connected with the outer cylinder 101, the outer cylinder 101 is connected to the aircraft fuselage, and the inner cylinder 102 is connected to the aircraft wheels. The undercarriage in this embodiment is an aircraft nose undercarriage, and the wheels on the undercarriage are aircraft nose wheels.
Still referring to fig. 1 and 2, the landing gear wheel angle measurement device includes: a scale 1 wound around the outer cylinder 101; the pointer 2 is used for indicating the scale marks 11 on the scale 1 and is detachably arranged on the inner cylinder 102; the mounting base 3 is provided with a clamping groove 31 on the mounting base 3, the inner cylinder 102 is provided with a protrusion 103, and the protrusion 103 is clamped in the clamping groove 31. The protrusion 103 may be an original structure on the inner cylinder 102, or may be specially processed on the inner cylinder 102.
Specifically, the scale indicated by the pointer 2 when the front wheel of the airplane is straightened is observed, then the scale indicated by the pointer 2 when the turning hand wheel of the airplane is straightened is observed, and the deflection angle of the front wheel of the airplane when the turning hand wheel is straightened is obtained through the scale difference between the two scales, so that whether the deflection angle meets the requirement is judged. The engagement of the slot 31 and the protrusion 103 enables the pointer 2 to be stably mounted on the inner cylinder 102, and facilitates the detachment of the pointer 2; after the front wheel of the aircraft is debugged, the pointer 2 mounted on the inner barrel 102 can be removed so as not to affect the normal flight and taxiing of the aircraft.
In this embodiment, the protrusion 103 includes a first protrusion 1031 and a second protrusion 1032, a clamping shaft 104 is erected between the first protrusion 1031 and the second protrusion 1032, and the clamping shaft 104 is clamped in the clamping slot 31. The first protrusions 1031, the second protrusions 1032 and the two clamping shafts 104 are respectively provided with two protrusions, and the two clamping shafts 104 are respectively in one-to-one correspondence with the two first protrusions 1031 and the two second protrusions 1032. The clamping shaft 104 may be a stud bolt screwed to the first and second protrusions 1031 and 1032; the shaft 104 may also be a bolt, which is inserted through the first protrusion 1031 and the second protrusion 1032, and one end of the shaft 104, which extends out of the first protrusion 1031 or the second protrusion 1032, is fastened by a nut; the shaft 104 may also be a pin shaft, and is inserted into the first protrusion 1031 and the second protrusion 1032 by interference fit.
Referring to fig. 2 and 3, a set screw 32 is screwed on a first side wall 311 of the card slot 31, and the set screw 32 abuts against one of the card shafts 104, so that the other card shaft 104 abuts against a second side wall 312 of the card slot 31. During assembly, the two clamping shafts 104 can extend into the clamping groove 31 from the direction opposite to the bottom wall of the clamping groove 31.
Specifically, the first side wall 311 is perpendicular to the bottom wall of the card slot 31; from the bottom wall of the card slot 31 to the opening of the card slot 31, the second side wall 312 is inclined toward the inner side of the card slot 31, that is, compared with the edge of the second side wall 312 departing from the bottom wall of the card slot 31, the connection between the second side wall 312 and the bottom wall of the card slot 31 is farther away from the first side wall 311, so that the card shaft 104 is firmly abutted against the second side wall 312.
When the mount 3 is detached from the inner cylinder 102, the card shaft 104 can be detached together with the mount 3 by detaching the card shaft 104 from the first projections 1031 and the second projections 1032; the set screw 32 on the first side wall 311 may also be loosened to disengage the latch shaft 104 from the latch slot 31. In this embodiment, one of the dismounting manners may be selected according to the actual dismounting space, the structure and the mounting form of the clamping shaft 104, and other specific factors.
Referring to fig. 3, 4 and 5, a slit 30 is formed in a side of the mounting base 3 away from the clamping groove 31, and the clamping plate 21 on the pointer 2 is clamped in the slit 30, so that the pointer 2 and the mounting base 3 can be conveniently detached and assembled, and the clamping position of the pointer 2 can be conveniently adjusted. Two set screws 32 are screwed to the side walls of the slit 30, and the set screws 32 abut against the clamp plate 21.
Referring to fig. 6 and 7, one end of the scale 1 is connected to the other end of the scale 1 by a stud. Two ends of the scale 1 are both provided with bending parts 10, and the two bending parts 10 are opposite to each other and are both provided with first mounting holes 111; the studs respectively penetrate through the two first mounting holes 111, and nuts for axially positioning the studs on the scale 1 are respectively screwed at two ends of the studs. The two bending parts 10 are arranged to facilitate installation of the stud; in order to prevent the thread on the stud from scratching the outer surface of the outer cylinder 101, a protective sleeve is sleeved outside the stud.
The assembly process of the scale 1 in this embodiment is as follows:
firstly, the strip-shaped scale 1 is wound on the outer barrel 101, so that the scale 1 is annular, the two bending parts 10 at the two ends of the scale 1 are opposite to each other, the stud is respectively penetrated through the two first mounting holes 111, then the nut is screwed on the two ends of the stud, and the two bending parts 10 are continuously close by screwing the nut until the annular scale 1 is tightly sleeved on the outer barrel 101.
It can be seen that the tightness of the scale 1 sleeved on the outer cylinder 101 can be adjusted by adjusting the pretightening force of the nut, so that the scale 1 and the outer cylinder 101 are stably matched, but the assembling method is not convenient.
Example two
The present embodiment provides another landing gear wheel rotation angle measuring device, which is substantially the same as the landing gear wheel rotation angle measuring device of the first embodiment, with reference to fig. 8 and 9, except that:
one end of the scale 1 is connected to the other end of the scale 1 through a tension spring 12; both ends of the scale 1 are provided with second mounting holes 112; one end of the tension spring 12 is hooked on the second mounting hole 112 at one end of the scale 1, and the other end of the tension spring 12 is hooked on the second mounting hole 112 at the other end of the scale 1.
The assembly process of the scale 1 in this embodiment is as follows:
firstly, the strip-shaped scale 1 is wound on the outer cylinder 101, so that the scale 1 is annular, then one end of the tension spring 12 is hooked at one end of the scale 1, and then the tension spring 12 is stretched to hook the other end of the tension spring 12 at the other end of the scale 1, so that the annular scale 1 is tightly sleeved on the outer cylinder 101 under the action of the tension force of the tension spring 12.
It will be appreciated that this assembly method is very simple and quick, but if the tension spring 12 ages, the scale 1 is easily removed from the outer cylinder 101.
It is to be noted that the foregoing is only illustrative of the preferred embodiments of the present invention and the technical principles employed. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the invention. Therefore, although the present invention has been described in greater detail by the above embodiments, the present invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the spirit of the present invention, and the scope of the present invention is determined by the scope of the appended claims.
Claims (10)
1. A landing gear wheel angle measurement device for measuring the angle of rotation of a drum assembly (100) in a landing gear, the drum assembly (100) comprising an outer drum (101) and an inner drum (102) rotatably connected to the outer drum (101), the outer drum (101) being connected to an aircraft fuselage, the inner drum (102) being connected to an aircraft wheel, the landing gear wheel angle measurement device comprising:
a scale (1) wound around the outer cylinder (101);
and the pointer (2) is used for indicating the scale marks (11) on the scale (1) and is detachably arranged on the inner cylinder (102).
2. The undercarriage wheel angle measuring device of claim 1, further comprising a mounting base (3), wherein the mounting base (3) is provided with a clamping groove (31), the inner cylinder (102) is provided with a protrusion (103), and the protrusion (103) is clamped in the clamping groove (31).
3. The landing gear wheel angle measuring device according to claim 2, characterized in that a side of the mounting seat (3) facing away from the catch groove (31) is provided with a crack (30), and the pointer (2) is clamped in the crack (30).
4. The landing gear wheel angle measuring device according to claim 2, characterized in that the protrusion (103) comprises a first protrusion (1031) and a second protrusion (1032), a clamping shaft (104) is mounted between the first protrusion (1031) and the second protrusion (1032), and the clamping shaft (104) is clamped in the clamping groove (31).
5. The landing gear wheel angle measuring device according to claim 4, wherein two of the clamping shafts (104) are provided, a set screw (32) is screwed on a first side wall (311) of each clamping groove (31), and the set screw (32) abuts against one clamping shaft (104) so that the other clamping shaft (104) abuts against a second side wall (312) of each clamping groove (31).
6. The landing gear wheel rotation angle measuring device according to claim 5, characterized in that the second side wall (312) is inclined inward of the catch groove (31) from a bottom wall of the catch groove (31) to an opening of the catch groove (31).
7. A landing gear wheel angle measuring device according to any one of claims 1 to 6, wherein one end of the scale (1) is connected to the other end of the scale (1) by a tension spring (12).
8. A landing gear wheel angle measuring device according to any one of claims 1 to 6, wherein one end of the scale (1) is connected to the other end of the scale (1) by a stud.
9. The undercarriage wheel angle measuring device according to claim 8, characterized in that both ends of the scale (1) are provided with a bending portion (10), the two bending portions (10) are opposite to each other, and the stud is arranged on the two bending portions (10) in a penetrating manner.
10. The landing gear wheel angle measurement device of claim 8, wherein the stud is sheathed with a protective sleeve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911195803.6A CN112857184A (en) | 2019-11-28 | 2019-11-28 | Undercarriage wheel corner measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911195803.6A CN112857184A (en) | 2019-11-28 | 2019-11-28 | Undercarriage wheel corner measuring device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112857184A true CN112857184A (en) | 2021-05-28 |
Family
ID=75995981
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911195803.6A Pending CN112857184A (en) | 2019-11-28 | 2019-11-28 | Undercarriage wheel corner measuring device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112857184A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103310675A (en) * | 2012-03-14 | 2013-09-18 | 天津奥捷航空科技有限公司 | Turning hand wheel for simulator flight |
| CN106839944A (en) * | 2016-12-28 | 2017-06-13 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft engine drive gear disk V-groove angle on-site measurement method |
| CN107021244A (en) * | 2017-04-21 | 2017-08-08 | 陕西飞机工业（集团）有限公司 | A kind of measurement apparatus for aircraft nose wheel deflection angle |
| CN108225411A (en) * | 2017-12-13 | 2018-06-29 | 中国特种飞行器研究所 | A kind of multifunction test measuring device |
-
2019
- 2019-11-28 CN CN201911195803.6A patent/CN112857184A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103310675A (en) * | 2012-03-14 | 2013-09-18 | 天津奥捷航空科技有限公司 | Turning hand wheel for simulator flight |
| CN106839944A (en) * | 2016-12-28 | 2017-06-13 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft engine drive gear disk V-groove angle on-site measurement method |
| CN107021244A (en) * | 2017-04-21 | 2017-08-08 | 陕西飞机工业（集团）有限公司 | A kind of measurement apparatus for aircraft nose wheel deflection angle |
| CN107021244B (en) * | 2017-04-21 | 2019-08-02 | 陕西飞机工业（集团）有限公司 | A kind of measuring device for aircraft nose wheel deflection angle |
| CN108225411A (en) * | 2017-12-13 | 2018-06-29 | 中国特种飞行器研究所 | A kind of multifunction test measuring device |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210528 |
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| RJ01 | Rejection of invention patent application after publication |