CN203111497U - Power backup unlocking device of gear uplock - Google Patents
Power backup unlocking device of gear uplock Download PDFInfo
- Publication number
- CN203111497U CN203111497U CN 201220734297 CN201220734297U CN203111497U CN 203111497 U CN203111497 U CN 203111497U CN 201220734297 CN201220734297 CN 201220734297 CN 201220734297 U CN201220734297 U CN 201220734297U CN 203111497 U CN203111497 U CN 203111497U
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- China
- Prior art keywords
- drive motor
- uplock
- controller
- tripper
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- Expired - Lifetime
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Abstract
The utility model relates to a power backup unlocking device of a gear uplock. The power backup unlocking device of the gear uplock comprises a drive motor (11), a speed reducer (14), a screw motion pair (8), a shell (6) and a controller (10), wherein the shell (6) is of a hollow structure; a U-shaped groove is formed in a cavity shell (6) in which the screw motion pair (8) is placed; a guide device (12) of the screw motion pair is arranged in the groove; two bumps are arranged outside the shell and respectively extend out of a position switch (9) and a recovery position switch (13); the screw motion pair (8) is arranged inside the shell (6) and connected with a shaft of the speed reducer (14); and a motor shaft of the drive motor (11) is connected with the shaft of the speed reducer. Unlocking of the gear uplock is achieved through the power backup unlocking device when a hydraulic system has a fault; dual-redundancy control of unlocking of the uplock is achieved; the power backup unlocking device is compact in structure and convenient to achieve; the reliability of receiving and releasing the gear can be increased; and the security of an airplane is also improved.
Description
Technical field
The utility model relates to a kind of tripper, is specifically related to a kind of landing gear uplock electricity backup tripper.
Background technology
General landing gear uplock tripper only is the high-voltage oil liquid by hydraulic efficiency pressure system, opens uplock and makes gear down, in case hydraulic efficiency pressure system breaks down, can't finish the folding and unfolding of alighting gear, causes the safety of aircraft to reduce.So, need increase the backup tripper at original uplock tripper, when hydraulic actuation breaks down, realize electronic release.
The utility model content
The purpose of this utility model: for the landing gear uplock tripper increases remaining control, improve reliability and the aircraft safety of undercarriage control.The utility model provides a kind of electricity backup tripper, when hydraulic efficiency pressure system breaks down, can finish opening and reset function of landing gear uplock, makes alighting gear be able to folding and unfolding.
The technical solution of the utility model is: landing gear uplock electricity backup tripper comprises drive motor (11), retarder (14), guide screw movement pair (8), housing (6), controller (10); Described housing (6) is hollow structure, inside has for offering U-lag on the cavity housing (6) of placing guide screw movement pair (8), the guide piece (12) of guide screw movement pair is installed in the groove, outside has two projectioies, is respectively extended position switch (9) and retrieving position switch (13); Described guide screw movement pair (8) is arranged in the housing (6), links to each other with the axle of retarder (14); The motor shaft of drive motor (11) links to each other with reducer shaft; Controller (10) links to each other with drive motor (11); Controller (10) comprises electric machine control and control signal conditioning module, and this signal condition module links to each other with position transduser on the drive motor (11), constitutes position closed loop.
Described position transduser is Hall element.
The principle of work of landing gear uplock electricity backup tripper is: when hydraulic actuator breaks down, start electric backup unlocking device, drive motor (11) is received the signal output torque of starting working, driving guide screw movement pair (8) rotates, feed screw nut is along the leading screw moving linearly, promotion axle drive shaft (5) (4) around the shaft rotates to an angle, make latch hook (1) landing from control stalk (3), dextrorotation goes to objective body (2) and deviates from, when extended position switch (9) provides high voltage signal, drive motor (11) stops operating, and finishes the process of unblanking.The induction targets body sensor provides " opening " signal, and drive motor (11) is received signal and is inverted to retrieving position switch (13) and stops when providing high voltage signal, and electricity backup tripper resets.
The beneficial effects of the utility model: the landing gear uplock electricity backup tripper that the utility model proposes, when hydraulic efficiency pressure system breaks down, by electricity backup tripper, realization is to the release of landing gear uplock, realized two remaining controls of uplock release, its compact conformation, it is convenient to realize, can increase the reliability of undercarriage control, improve aircraft safety.
Description of drawings
Fig. 1 is the structural representation of the present utility model landing gear uplock electricity backup tripper;
Fig. 2 is the control principle block diagram of direct drive servovalve valve of the present invention;
Wherein, 1-latch hook, 2-objective body, 3-control stalk, 4-rotating shaft, 5-axle drive shaft, 6-housing, 7-piston barrel, 8-guide screw movement pair, 9-extended position switch, 10-controller, 11-drive motor, 12-guide piece, 13-retrieving position switch, 14-retarder, 15-hydraulic actuator, 21-signal condition, 22-position transduser, 23-command signal, 24-feedback signal.
The specific embodiment
The present invention is described in further detail below by the specific embodiment.
See also Fig. 1, it is the structural representation of utility model landing gear uplock electricity backup tripper.
Landing gear uplock electricity backup tripper comprises drive motor 11, retarder 14, guide screw movement pair 8, housing 6, controller 10; Described housing 6 is hollow structure, inside has for offering U-lag on the cavity housing 6 of placing the guide screw movement pair, guiding leading screw kinematic pair 8 crank motions, the guide piece 12 of guide screw movement pair is installed in the groove, outside has two projectioies, be respectively extended position switch 9 and retrieving position switch 13, for detection of the present position of guide screw movement pair, give controller 10 feedback signals; Described guide screw movement pair 8 is arranged in the housing 6, links to each other with the axle of retarder 14, as the output shaft of retarder; The motor shaft of drive motor 11 links to each other with reducer shaft, as the input shaft of drive motor; Controller 10 links to each other with drive motor 11; Controller 10 comprises electric machine control and control signal conditioning module, and this signal condition module links to each other with position transduser on the drive motor 11, constitutes position closed loop.
This utility model integral installation is in hydraulic pressure release pressurized strut 15, and ball screw assembly, is as the output shaft of retarder 14, and input shaft is the main shaft of drive motor 11.In addition, controller 10 is arranged on the drive motor 11, is used for the control drive motor and clockwise rotates or rotate counterclockwise, and described drive motor 11 is DC servo motor, and in the present embodiment, this displacement pickup is Hall element.
See also Fig. 2, it is the control principle block diagram of the utility model landing gear uplock electricity backup tripper.During the real work of the utility model landing gear uplock electricity backup tripper, judge the high low voltage of position 9/13 earlier, entered the controller 10 of drive motor 11 then by computing machine output instruction signal 23, controller sends the driving signal, and control drive motor 11 clockwise rotates or rotates counterclockwise.After giving signal condition 21 modules, embedded position sensor 22 feedback signals 24 of drive motor enter controller 10, form the position closed loop of drive motor, rotatablely moving of drive motor passes to guide screw movement pair 8 by retarder 14, the rotating band movable wire thick stick nut moving linearly of leading screw is realized the control to axle drive shaft 5.
The landing gear uplock electricity backup tripper that utility model proposes, when hydraulic efficiency pressure system breaks down, by electricity backup tripper, realization is to the release of landing gear uplock, realized two remaining controls of uplock release, its compact conformation, it is convenient to realize, can increase the reliability of undercarriage control, improve aircraft safety.
Claims (2)
1. landing gear uplock electricity backup tripper is characterized in that: comprise drive motor (11), retarder (14), guide screw movement pair (8), housing (6), controller (10); Described housing (6) is hollow structure, inside has for offering U-lag on the cavity housing (6) of placing guide screw movement pair (8), the guide piece (12) of guide screw movement pair is installed in the groove, outside has two projectioies, is respectively extended position switch (9) and retrieving position switch (13); Described guide screw movement pair (8) is arranged in the housing (6), links to each other with the axle of retarder (14); The motor shaft of drive motor (11) links to each other with reducer shaft; Controller (10) links to each other with drive motor (11); Controller (10) comprises electric machine control and control signal conditioning module, and this signal condition module links to each other with position transduser on the drive motor (11), constitutes position closed loop.
2. landing gear uplock electricity according to claim 1 backs up tripper, and it is characterized in that: position transduser is Hall element.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220734297 CN203111497U (en) | 2012-12-27 | 2012-12-27 | Power backup unlocking device of gear uplock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220734297 CN203111497U (en) | 2012-12-27 | 2012-12-27 | Power backup unlocking device of gear uplock |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203111497U true CN203111497U (en) | 2013-08-07 |
Family
ID=48891867
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220734297 Expired - Lifetime CN203111497U (en) | 2012-12-27 | 2012-12-27 | Power backup unlocking device of gear uplock |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203111497U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ITUA20162712A1 (en) * | 2016-04-19 | 2017-10-19 | Magnaghi Aeronautica S P A | System Structure Trolley for Aircraft equipped with electromechanical actuation and Aircraft equipped with this Structure |
| CN109823522A (en) * | 2017-11-23 | 2019-05-31 | 成都凯天电子股份有限公司 | Multi-redundant undercarriage electric retractable controller |
| CN112572779A (en) * | 2020-12-04 | 2021-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Electrically driven passive pillar upper lock |
-
2012
- 2012-12-27 CN CN 201220734297 patent/CN203111497U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ITUA20162712A1 (en) * | 2016-04-19 | 2017-10-19 | Magnaghi Aeronautica S P A | System Structure Trolley for Aircraft equipped with electromechanical actuation and Aircraft equipped with this Structure |
| WO2017182955A1 (en) * | 2016-04-19 | 2017-10-26 | Magnaghi Aeronautica S.P.A. | Aircraft landing gear assembly with electromechanical actuation and aircraft provided with such assembly |
| US10894597B2 (en) | 2016-04-19 | 2021-01-19 | Magnaghi Aeronautica S.P.A. | Aircraft landing gear assembly with electromechanical actuation and aircraft provided with such assembly |
| CN109823522A (en) * | 2017-11-23 | 2019-05-31 | 成都凯天电子股份有限公司 | Multi-redundant undercarriage electric retractable controller |
| CN109823522B (en) * | 2017-11-23 | 2024-02-23 | 成都凯天电子股份有限公司 | Multi-redundancy undercarriage electric retraction controller |
| CN112572779A (en) * | 2020-12-04 | 2021-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Electrically driven passive pillar upper lock |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130807 |
|
| CX01 | Expiry of patent term |