CN209396064U - A kind of aircraft front-wheel deflection angle measuring device - Google Patents
A kind of aircraft front-wheel deflection angle measuring device Download PDFInfo
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- CN209396064U CN209396064U CN201821883201.0U CN201821883201U CN209396064U CN 209396064 U CN209396064 U CN 209396064U CN 201821883201 U CN201821883201 U CN 201821883201U CN 209396064 U CN209396064 U CN 209396064U
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- deflection angle
- pedestal
- aircraft front
- bearing
- measuring device
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Abstract
A kind of aircraft front-wheel deflection angle measuring device, belongs to test, field of measuring technique.The aircraft front-wheel deflection angle measuring device includes pedestal, shaft, bearing, rotary bracket, pointer and angle board；The pedestal is placed on level ground, and bearing mounting groove is arranged in pedestal one end setting angle plate, and in the centre of pedestal；The bearing is placed in bearing mounting groove；The shaft is mounted on the base by bearing, installs rotary bracket in the upper end of shaft；The rotary bracket is equipped with the cavity for accommodating aircraft front-wheel, installs pointer on the outer wall of rotary bracket one end.The utility model provides exact value by the measurement to aircraft front-wheel actual deflection angle, to compare with manipulation instruction deflection angle, has achieved the purpose that make aircraft front-wheel deflection executing agency's Reliability of Microprocessor and accurately judge.
Description
Technical field
The utility model relates to a kind of angle measurement unit, especially a kind of aircraft front-wheel deflection angle measuring device,
Belong to test, field of measuring technique.
Background technique
In aircraft lands, it need to guarantee aircraft taxiing turn and the sliding race of amendment by controlling the deflection angle of front-wheel
Direction, especially on unpiloted aircraft, front-wheel deflection angle is to utilize radio robot and the program provided for oneself
Control device manipulation is realized by the mechanical action of executing agency, due to existing in executing agency's mechanical action conductive process
Accumulated error causes manipulation instruction and actual deflection angle inconsistent, thus in the technical standard of unmanned vehicle, sternly
The lattice specification difference range of manipulation instruction and actual deflection angle.
Unmanned vehicle manufacture and maintenance process in, in order to aircraft front-wheel deflection executing agency movement can
Accurate judge is made by property, front-wheel actual deflection angle number value need to be measured, and be compared with manipulation instruction deflection angle,
It determines whether the requirement for meeting technical standard, therefore designs a kind of aircraft front-wheel deflection angle measuring device gesture must
Row.
Utility model content
The utility model provides a kind of aircraft front-wheel deflection angle measuring device, it is intended to by practical to aircraft front-wheel
The measurement of deflection angle provides exact value to compare with manipulation instruction deflection angle, reaches and deflect execution to aircraft front-wheel
Mechanism action reliability makes the purpose accurately judged.
To achieve the above objectives, the present invention adopts the following technical solutions:
A kind of aircraft front-wheel deflection angle measuring device, including pedestal, shaft, bearing, rotary bracket, pointer and angle
Plate；The pedestal is placed on level ground, is pacified in pedestal one end setting angle plate, and in the centre of pedestal setting bearing
Tankage；The bearing is placed in bearing mounting groove；The shaft is mounted on the base by bearing, installs rotation in the upper end of shaft
Ask frame；The rotary bracket is equipped with the cavity for accommodating aircraft front-wheel, installs pointer on the outer wall of rotary bracket one end.
Above-mentioned aircraft front-wheel deflection angle measuring device, the rotary bracket include the left clamp being arranged symmetrically and right folder
Plate, the left clamp and right clamping plate pass through bindiny mechanism's fixing assembling；The bindiny mechanism is equipped with left ear muff, auris dextra set, left set
Pipe, right casing and bolt assembly, the left ear muff and left Socket welding are on the outer wall of left clamp both ends, the auris dextra set and right set
Pipe is welded on the outer wall of right clamping plate both ends, after bolt passes through auris dextra set, right casing, left casing, left ear muff in the bolt assembly
It is assembled with lock-nut.
Above-mentioned aircraft front-wheel deflection angle measuring device, the bearing are tapered roller bearing, are arranged outside bearing
Protective case.
Above-mentioned aircraft front-wheel deflection angle measuring device is bonded rubber mat in the bottom surface of the pedestal.
Above-mentioned aircraft front-wheel deflection angle measuring device, further includes locking nail, and the locking nail setting is in pedestal and turns
Locking at axis cooperation, to off working state.
The utility model is a kind of aircraft front-wheel deflection angle measuring device, and angle board is arranged in pedestal one end in it,
The middle of the base assembles shaft by bearing, and rotary bracket is mounted on shaft upper end, corresponding with angle board in rotary bracket
The pointer of mounting end orientation angle plate scale on the outer wall of one end.When carrying out the measurement of aircraft front-wheel deflection angle, will fly
Device front-wheel is placed in the cavity of rotary bracket, makes aircraft front-wheel that rotary bracket be driven to turn an angle by manipulation instruction,
It after the actual deflection angle value of reading pointer instruction, is compared with manipulation instruction deflection angle, determines whether the two difference is full
The requirement of sufficient technical standard.It can be seen that the utility model is and behaviour by the measurement to aircraft front-wheel actual deflection angle
It controls throw of pointer angle and offer exact value is provided, reached and standard is made to aircraft front-wheel deflection executing agency's Reliability of Microprocessor
The purpose really judged.
Detailed description of the invention
Fig. 1 is the utility model structure diagram；
Fig. 2 is the A direction view of Fig. 1；
Fig. 3 is the top view of Fig. 1；
Fig. 4 is utility model works status diagram；
Fig. 5 is the top view of Fig. 4.
Each list of reference numerals in figure are as follows: 1, pedestal, 2, angle board, 3, pointer, 4, rotary bracket, 4-1, left clamp, 4-2, the right side
Clamping plate, 5, protective case, 6, bearing, 7, shaft, 8, rubber mat, 9, bindiny mechanism, 9-1, bolt assembly, 9-2, left ear muff, 9-3, a left side
Casing, 9-4, right casing, 9-5, auris dextra set, 10, locking nail, 11, aircraft front-wheel.
Specific embodiment
With reference to the accompanying drawing and specific embodiment the utility model is described in further detail.
Referring to Fig. 1, Fig. 2, Fig. 3, the utility model is a kind of aircraft front-wheel deflection angle measuring device, it includes bottom
Seat 1, shaft 7, bearing 6, rotary bracket 4, pointer 3 and angle board 2；The pedestal 1 is placed on level ground, in the pedestal
1 bottom surface is bonded rubber mat 8, and in 1 one end setting angle plate 2 of pedestal, bearing mounting groove is arranged in the centre of pedestal；The axis
6 are held as tapered roller bearing, is placed in bearing mounting groove, protective case 5 is set outside bearing 6；The shaft 7 passes through bearing 6
It is mounted on pedestal 1, rotary bracket 4 is installed in the upper end of shaft 7；The rotary bracket 4 includes the left clamp 4-1 being arranged symmetrically
With right clamping plate 4-2, the left clamp 4-1 and right clamping plate 4-2 by 9 fixing assembling of bindiny mechanism, by left clamp 4-1 and right clamping plate
4-2 forms the cavity for accommodating aircraft front-wheel, and pointer 3 is installed on 4 one end outer wall of rotary bracket；The utility model also wraps
Include locking nail 10, locking of the setting of locking nail 10 at pedestal 1 and 7 cooperation of shaft, to off working state.
Left ear muff 9-2 is equipped with referring to Fig. 1, Fig. 2, the bindiny mechanism 9, auris dextra covers 9-5, left casing 9-3, right casing 9-4
It is welded on the outer wall of the both ends left clamp 4-1 with bolt assembly 9-1, the left ear muff 9-2 and left casing 9-3, the auris dextra covers 9-5
It is welded on the outer wall of the both ends right clamping plate 4-2 with right casing 9-4, bolt passes through auris dextra set 9-5, right set in the bolt assembly 9-1
It is assembled after pipe 9-4, left casing 9-3, left ear muff 9-2 with lock-nut.
Referring to Fig. 4, Fig. 5, when carrying out the measurement of aircraft front-wheel deflection angle using the utility model, by aircraft front-wheel 11
It is placed in the cavity of rotary bracket 4, makes aircraft front-wheel 11 that rotary bracket 4 be driven to turn an angle by manipulation instruction, read
It after the actual deflection angle value that fetching needle 3 indicates, is compared with manipulation instruction deflection angle, determines whether the two difference meets
The requirement of technical standard.
Claims (5)
1. a kind of aircraft front-wheel deflection angle measuring device, characterized in that the aircraft front-wheel deflection angle measuring device
Including pedestal (1), shaft (7), bearing (6), rotary bracket (4), pointer (3) and angle board (2)；The pedestal (1) is placed on
On level ground, bearing mounting groove is set in pedestal (1) one end setting angle plate (2), and in the centre of pedestal；The axis
(6) are held to be placed in bearing mounting groove；The shaft (7) is mounted on pedestal (1) by bearing (6), is pacified in the upper end of shaft (7)
It fills rotary bracket (4)；The rotary bracket (4) is equipped with the cavity for accommodating aircraft front-wheel, outside rotary bracket (4) one end
Pointer (3) are installed on wall.
2. aircraft front-wheel deflection angle measuring device according to claim 1, characterized in that the rotary bracket (4)
Including the left clamp (4-1) being arranged symmetrically and right clamping plate (4-2), the left clamp (4-1) and right clamping plate (4-2) pass through connection machine
Structure (9) fixing assembling；The bindiny mechanism (9) is equipped with left ear muff (9-2), auris dextra set (9-5), left casing (9-3), right casing
(9-4) and bolt assembly (9-1), the left ear muff (9-2) and left casing (9-3) are welded on the outer wall of the both ends left clamp (4-1),
The auris dextra set (9-5) and right casing (9-4) are welded on the outer wall of the both ends right clamping plate (4-2), spiral shell in the bolt assembly (9-1)
Bolt passes through auris dextra set (9-5), right casing (9-4), left casing (9-3), left ear muff (9-2) and assembles afterwards with lock-nut.
3. aircraft front-wheel deflection angle measuring device according to claim 1 or 2, characterized in that the bearing (6) is
Protective case (5) are arranged outside bearing (6) in tapered roller bearing.
4. aircraft front-wheel deflection angle measuring device according to claim 3, characterized in that in the pedestal (1)
Bottom surface is bonded rubber mat (8).
5. aircraft front-wheel deflection angle measuring device according to claim 1, characterized in that further include locking nail
(10), locking of locking nail (10) setting at pedestal (1) and shaft (7) cooperation, to off working state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821883201.0U CN209396064U (en) | 2018-11-15 | 2018-11-15 | A kind of aircraft front-wheel deflection angle measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821883201.0U CN209396064U (en) | 2018-11-15 | 2018-11-15 | A kind of aircraft front-wheel deflection angle measuring device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209396064U true CN209396064U (en) | 2019-09-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821883201.0U Active CN209396064U (en) | 2018-11-15 | 2018-11-15 | A kind of aircraft front-wheel deflection angle measuring device |
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| Country | Link |
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| CN (1) | CN209396064U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111891381A (en) * | 2020-06-17 | 2020-11-06 | 成都飞机工业（集团）有限责任公司 | Aircraft front wheel deflection angle measuring mechanism |
-
2018
- 2018-11-15 CN CN201821883201.0U patent/CN209396064U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111891381A (en) * | 2020-06-17 | 2020-11-06 | 成都飞机工业（集团）有限责任公司 | Aircraft front wheel deflection angle measuring mechanism |
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