CN204128480U - A kind of aircraft horizontal tail angular displacement sensor detecting device - Google Patents
A kind of aircraft horizontal tail angular displacement sensor detecting device Download PDFInfo
- Publication number
- CN204128480U CN204128480U CN201420629217.4U CN201420629217U CN204128480U CN 204128480 U CN204128480 U CN 204128480U CN 201420629217 U CN201420629217 U CN 201420629217U CN 204128480 U CN204128480 U CN 204128480U
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- bevel protractor
- horizontal tail
- rotating shaft
- web member
- holder
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- 238000006073 displacement reaction Methods 0.000 title claims abstract description 19
- 238000005259 measurement Methods 0.000 abstract description 7
- 230000000875 corresponding Effects 0.000 description 4
- 238000001514 detection method Methods 0.000 description 4
- 238000009987 spinning Methods 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 1
- 230000001808 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Abstract
A kind of aircraft horizontal tail angular displacement sensor detecting device, belong to measurement, technical field of measurement and test, comprise vernier universal bevel protractor, bevel protractor holder, pressing plate, web member and base, described vernier universal bevel protractor is arranged on bevel protractor holder, and fixing by pressing plate location, the rotating shaft of described web member one end and horizontal tail degree of bias signal mechanism is assembled, and the other end and vernier universal bevel protractor are equipped with, described bevel protractor holder is arranged on base, described base horizontal positioned.The utility model has that structure is simple, easy to operate, testing result feature accurately, improves the work quality of aircraft maintenance maintenance.
Description
Technical field
The utility model relates to a kind of pick-up unit, and especially a kind of aircraft horizontal tail angular displacement sensor detecting device, belongs to measurement, technical field of measurement and test.
Background technology
The horizontal tail angular displacement (i.e. the horizontal tail degree of bias) of aircraft is the important parameter controlling its flight attitude, the horizontal tail degree of bias transmitted by rotating shaft is converted to inductance value and exports by the signal mechanism of aircraft, when the horizontal tail degree of bias changes, there is corresponding change in the inductance value that signal mechanism exports, pilot can give corresponding adjustment according to this changing value to equipment, to control the flight attitude of aircraft.Therefore, need to detect (namely detecting aircraft horizontal tail angular displacement sensor performance) variation relation between the aircraft horizontal tail degree of bias and sensing signal inductance value when aircraft maintenance maintenance, current testing process has been estimated by maintenance personal mostly, there is the defect that testing result accuracy is difficult to ensure, have a strong impact on aircraft maintenance maintenance work quality.
Utility model content
The purpose of this utility model is the drawback for prior art, provides a kind of aircraft horizontal tail angular displacement sensor detecting device, and it has, and structure is simple, easy to operate, testing result feature accurately, fully can ensure the work quality of aircraft maintenance maintenance.
Problem described in the utility model solves by with following technical proposals:
A kind of aircraft horizontal tail angular displacement sensor detecting device, comprise vernier universal bevel protractor, bevel protractor holder, pressing plate, web member and base, described vernier universal bevel protractor is arranged on bevel protractor holder, and it is fixing by pressing plate location, the rotating shaft of described web member one end and horizontal tail degree of bias signal mechanism is assembled, the other end and vernier universal bevel protractor are equipped with, and described bevel protractor holder is arranged on base, described base horizontal positioned.
Above-mentioned aircraft horizontal tail angular displacement sensor detecting device, described web member is inverted " L " type structure, its horizontal arm end face arranges the threaded hole assembled with vernier universal bevel protractor, its vertical arm is offered the rotating shaft connecting hole with elongated slot and clamping and positioning hole, the elongated slot of described rotating shaft connecting hole runs through rotating shaft connecting hole and extends to web member vertical arm lower surface, described clamping and positioning hole comprises the two parts being positioned at elongated slot left and right sides, its central axis and rotating shaft connecting hole central axis upright, they are positioned at the below of rotating shaft connecting hole.
Above-mentioned aircraft horizontal tail angular displacement sensor detecting device, described vernier universal bevel protractor comprises main scale and secondary chi, described main scale is fixed on base, described secondary chi and main scale are equipped with, secondary chi is provided with push pedal, described push pedal is provided with web member pilot hole, and secondary chi passes through web member pilot hole and bolt assembly and web member and assembles.
Above-mentioned aircraft horizontal tail angular displacement sensor detecting device, described bevel protractor holder is provided with the pilot hole coordinated with the rotating shaft of horizontal tail degree of bias signal mechanism, and described pilot hole center overlaps with the main scale datum mark of vernier universal bevel protractor.
The utility model is realize a kind of special detection device that aircraft horizontal tail angular displacement sensor Performance Detection designs.This special detection device passes through web member, the spinning movement of horizontal tail degree of bias signal mechanism rotating shaft to be converted on vernier universal bevel protractor secondary chi relative to the movement of main scale, by the measurement to horizontal tail degree of bias signal mechanism rotating shaft four position of rotation (as 0o, 5o, 10o, 20o) angles, read horizontal tail degree of bias changing value each time, be the horizontal tail angular displacement of aircraft, it is corresponding with the inductance value that horizontal tail degree of bias signal mechanism exports, draw variation relation between the aircraft horizontal tail degree of bias and sensing signal inductance value.The utility model is provided with the pilot hole of coupling horizontal tail degree of bias signal mechanism rotating shaft on bevel protractor holder, and pilot hole center is overlapped with the datum mark of the main scale of general-purpose angle, thus achieve the consistance of vernier universal bevel protractor reading and horizontal tail degree of bias signal mechanism shaft rotary corner, ensure that the accuracy of measurement result.In a word, the utility model has that structure is simple, easy to operate, testing result feature accurately, improves the work quality of aircraft maintenance maintenance.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, the utility model is described in further detail.
Fig. 1 is structural representation of the present utility model;
Fig. 2 is the right side view of Fig. 1;
Fig. 3 is vernier universal bevel protractor structural representation;
Fig. 4 is web member front view;
Fig. 5 is the right side view of Fig. 4;
Fig. 6 is the side view of bevel protractor holder;
Fig. 7 is utility model works view.
In figure, each list of reference numerals is: 1, base, 2, bevel protractor holder, and 2-1, pilot hole, 3, pressing plate, 4, vernier universal bevel protractor, 4-1, main scale, 4-2, secondary chi, 4-3, push pedal, 4-4, web member pilot hole, 5, web member, 5-1, clamping and positioning hole, 5-2, threaded hole, 5-3, rotating shaft connecting hole, 5-4, elongated slot, 6, horizontal tail degree of bias signal mechanism, 6-1, rotating shaft, 7, bolt assembly.
Embodiment
Referring to Fig. 1, Fig. 2, the utility model comprises vernier universal bevel protractor 4, bevel protractor holder 2, pressing plate 3, web member 5 and base 1, described vernier universal bevel protractor 4 is arranged on bevel protractor holder 2, and located fixing by pressing plate 3, the rotating shaft 6-1 of described web member 5 one end and horizontal tail degree of bias signal mechanism 6 assembles, the other end and vernier universal bevel protractor 4 are equipped with, and described bevel protractor holder 2 is arranged on base 1, described base 1 horizontal positioned.
Referring to Fig. 1, Fig. 4, Fig. 5, web member 5 of the present utility model is inverted " L " type structure, its horizontal arm end face arranges the threaded hole 5-2 assembled with vernier universal bevel protractor 4, its vertical arm is offered the rotating shaft connecting hole 5-3 with elongated slot 5-4 and clamping and positioning hole 5-1, the elongated slot 5-4 of described rotating shaft connecting hole 5-3 runs through rotating shaft connecting hole 5-3 and extends to the vertical arm lower surface of web member 5, described clamping and positioning hole 5-1 comprises the two parts being positioned at elongated slot 5-4 left and right sides, its central axis and rotating shaft connecting hole 5-3 central axis upright, they are positioned at the below of rotating shaft connecting hole 5-3.
Referring to Fig. 1, Fig. 3, vernier universal bevel protractor 4 of the present utility model comprises main scale 4-1 and secondary chi 4-2, described main scale 4-1 is fixed on base 1, described secondary chi 4-2 and main scale 4-1 is equipped with, secondary chi 4-2 is provided with push pedal 4-3, described push pedal 4-3 is provided with web member pilot hole 4-4, and secondary chi 4-2 is assembled with web member 5 by web member pilot hole 4-4 and bolt assembly 7.
Referring to Fig. 1, Fig. 2, Fig. 6, bevel protractor holder 2 of the present utility model is provided with the pilot hole 2-1 coordinated with the rotating shaft 6-1 of horizontal tail degree of bias signal mechanism 6, and described pilot hole 2-1 center overlaps with the datum mark of vernier universal bevel protractor 4 main scale 4-1.
Referring to Fig. 1, Fig. 7, the spinning movement of horizontal tail degree of bias signal mechanism 6 rotating shaft 6-1 to be converted on vernier universal bevel protractor 4 secondary chi 4-2 relative to the movement of main scale 4-1 by web member 5 by the utility model, by to horizontal tail degree of bias signal mechanism 6 rotating shaft 6-1 tetra-position of rotation (as 0o, 5o, 10o, 20o) the measurement of angle, read horizontal tail degree of bias changing value each time, be the horizontal tail angular displacement of aircraft, it is corresponding with the inductance value that horizontal tail degree of bias signal mechanism 6 exports, draw variation relation between the aircraft horizontal tail degree of bias and sensing signal inductance value, complete the detection to aircraft horizontal tail angular displacement sensor performance.
Claims (4)
1. an aircraft horizontal tail angular displacement sensor detecting device, it is characterized in that: comprise vernier universal bevel protractor (4), bevel protractor holder (2), pressing plate (3), web member (5) and base (1), described vernier universal bevel protractor (4) is arranged on bevel protractor holder (2), and it is fixing by pressing plate (3) location, the rotating shaft (6-1) of described web member (5) one end and horizontal tail degree of bias signal mechanism (6) is assembled, the other end and vernier universal bevel protractor (4) are equipped with, described bevel protractor holder (2) is arranged on base (1), described base (1) horizontal positioned.
2. a kind of aircraft horizontal tail angular displacement sensor detecting device according to claim 1, it is characterized in that, described web member (5) is inverted " L " type structure, its horizontal arm end face arranges the threaded hole (5-2) assembled with vernier universal bevel protractor (4), its vertical arm is offered the rotating shaft connecting hole (5-3) with elongated slot (5-4) and clamping and positioning hole (5-1), the elongated slot (5-4) of described rotating shaft connecting hole (5-3) runs through rotating shaft connecting hole (5-3) and extends to the vertical arm lower surface of web member (5), described clamping and positioning hole (5-1) comprises the two parts being positioned at elongated slot (5-4) left and right sides, its central axis and rotating shaft connecting hole (5-3) central axis upright, they are positioned at the below of rotating shaft connecting hole (5-3).
3. a kind of aircraft horizontal tail angular displacement sensor detecting device according to claim 2, it is characterized in that, described vernier universal bevel protractor (4) comprises main scale (4-1) and secondary chi (4-2), described main scale (4-1) is fixed on base (1), described secondary chi (4-2) is equipped with main scale (4-1), secondary chi (4-2) is provided with push pedal (4-3), described push pedal (4-3) is provided with web member pilot hole (4-4), and secondary chi (4-2) is assembled with web member (5) by web member pilot hole (4-4) and bolt assembly (7).
4. a kind of aircraft horizontal tail angular displacement sensor detecting device according to claim 3, it is characterized in that, described bevel protractor holder (2) is provided with the pilot hole (2-1) coordinated with the rotating shaft (6-1) of horizontal tail degree of bias signal mechanism (6), and described pilot hole (2-1) center overlaps with the datum mark of vernier universal bevel protractor (4) main scale (4-1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420629217.4U CN204128480U (en) | 2014-10-24 | 2014-10-24 | A kind of aircraft horizontal tail angular displacement sensor detecting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420629217.4U CN204128480U (en) | 2014-10-24 | 2014-10-24 | A kind of aircraft horizontal tail angular displacement sensor detecting device |
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| Publication Number | Publication Date |
|---|---|
| CN204128480U true CN204128480U (en) | 2015-01-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420629217.4U Active CN204128480U (en) | 2014-10-24 | 2014-10-24 | A kind of aircraft horizontal tail angular displacement sensor detecting device |
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| CN (1) | CN204128480U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105509618A (en) * | 2015-11-25 | 2016-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Deflection angle measurer of flap aileron |
| CN110530328A (en) * | 2019-08-13 | 2019-12-03 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of angle of attack sensor setter |
| CN110803298A (en) * | 2019-10-18 | 2020-02-18 | 中航通飞华南飞机工业有限公司 | Device and method for determining neutral position of control surface of airplane |
| CN112960140A (en) * | 2021-03-15 | 2021-06-15 | 中国商用飞机有限责任公司 | Horizontal tail trim angle adjusting device |
-
2014
- 2014-10-24 CN CN201420629217.4U patent/CN204128480U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105509618A (en) * | 2015-11-25 | 2016-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Deflection angle measurer of flap aileron |
| CN110530328A (en) * | 2019-08-13 | 2019-12-03 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of angle of attack sensor setter |
| CN110530328B (en) * | 2019-08-13 | 2021-11-02 | 中国航空工业集团公司西安飞行自动控制研究所 | Angle of attack sensor gives device |
| CN110803298A (en) * | 2019-10-18 | 2020-02-18 | 中航通飞华南飞机工业有限公司 | Device and method for determining neutral position of control surface of airplane |
| CN112960140A (en) * | 2021-03-15 | 2021-06-15 | 中国商用飞机有限责任公司 | Horizontal tail trim angle adjusting device |
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