CN210338276U - Landing gear control handle assembly - Google Patents
Landing gear control handle assembly Download PDFInfo
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- CN210338276U CN210338276U CN201921303084.0U CN201921303084U CN210338276U CN 210338276 U CN210338276 U CN 210338276U CN 201921303084 U CN201921303084 U CN 201921303084U CN 210338276 U CN210338276 U CN 210338276U
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- landing gear
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- undercarriage
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Abstract
The utility model relates to an undercarriage control handle subassembly. The undercarriage control handle assembly comprises an undercarriage handle, an undercarriage handle lowering lock and an undercarriage handle lowering lock electromagnet, wherein when the flight speed of an airplane on the ground or the airplane is higher than the maximum allowable flight speed of the undercarriage, the undercarriage handle lowering lock electromagnet is powered off, and the undercarriage handle is locked at the lowering position by the undercarriage handle lowering lock; when the aircraft is in the air and the flight speed of the aircraft is not higher than the maximum allowable flight speed of the landing gear, the electromagnet of the landing gear handle lowering lock is electrified, the landing gear handle lowering lock is unlocked through mechanical driving, and the landing gear handle can move from the lowering position to the retrieving position. According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: the landing gear can be prevented from being accidentally operated by the landing gear handle when the flying speed is higher than the maximum allowable flying speed of the landing gear.
Description
Technical Field
The utility model relates to an undercarriage control handle subassembly belongs to undercarriage control field, and more wideer belongs to aircraft design and manufacturing field.
Background
Currently, the landing gear control handle assembly for preventing accidental operation is mainly composed of a landing gear handle, a landing gear handle lock and a handle lock electromagnet. When the air ground signal indicates that the airplane is on the ground, the electromagnet of the handle lock is powered off, the handle lock is locked, and the handle is locked at a Down (DN) position; when the air ground signal indicates that the airplane is in the air, the handle lock electromagnet is electrified, the handle lock is unlocked, and the handle can move from a put-down position (DN) to a put-UP Position (UP).
The main disadvantages of current landing gear control handle assemblies are: the accidental retraction of the landing gear when the aircraft flight speed exceeds the maximum allowable flight speed for the retraction of the landing gear cannot be prevented.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an undercarriage control handle subassembly, at least some problems that prior art exists can be solved to it, and the undercarriage is received to unexpected operation undercarriage handle when can preventing that the airspeed is higher than the maximum allowable airspeed of receiving the undercarriage.
The above object of the present invention is achieved by an undercarriage control handle assembly comprising an undercarriage handle, an undercarriage handle lowering lock and an undercarriage handle lowering lock electromagnet, wherein when the flight speed of the aircraft on the ground or the aircraft is higher than the maximum allowable flight speed for winding up the undercarriage, the undercarriage handle lowering lock electromagnet is de-energized, and the undercarriage handle lowering lock locks the undercarriage handle in the lowering position; when the aircraft is in the air and the flight speed of the aircraft is not higher than the maximum allowable flight speed of the landing gear, the electromagnet of the landing gear handle lowering lock is electrified, the landing gear handle lowering lock is unlocked through mechanical driving, and the landing gear handle can move from the lowering position to the retrieving position.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: the landing gear can be prevented from being accidentally operated by the landing gear handle when the flying speed is higher than the maximum allowable flying speed of the landing gear.
Specifically speaking, when the aircraft flying speed is higher than the maximum allowable flying speed of the landing gear, the electromagnet of the undercarriage handle lowering lock is powered off, the undercarriage handle lowering lock locks the undercarriage handle in the lowering position, the landing gear handle is prevented from being operated accidentally, and potential safety hazards caused by the fact that the landing gear is retracted when the aircraft flies at a high speed are avoided.
Preferably, the landing gear control handle assembly further comprises a landing gear handle stow-up lock and a landing gear handle stow-up lock electromagnet, wherein,
when the flight speed of the aircraft is higher than the maximum allowable flight speed of the landing gear, the electromagnet of the landing gear handle retraction uplock is powered off, and the landing gear handle retraction uplock locks the landing gear handle in a retraction uplock;
when the flight speed of the aircraft is not higher than the maximum allowable flight speed of the landing gear, the electromagnet of the landing gear handle retraction uplock is electrified, the landing gear handle retraction uplock is unlocked through mechanical driving, and the landing gear handle can move to the lowering position from the retraction uplock.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: accidental operation of the landing gear handle to lower the landing gear at speeds above the maximum allowable landing gear speed is prevented.
Preferably, the undercarriage control handle assembly further comprises an undercarriage handle lowering lock unlocking switch, and when the undercarriage handle lock electromagnet cannot be normally unlocked due to a fault, the undercarriage handle lowering lock unlocking switch is manually pressed, so that the undercarriage handle lowering lock is manually and mechanically released.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: when the electromagnet of the undercarriage handle lock can not be normally unlocked due to faults, the undercarriage handle lowering lock can be manually and mechanically released.
Preferably, the undercarriage control handle assembly further comprises an undercarriage handle uplock unlocking switch, and when the undercarriage handle uplock electromagnet cannot be normally unlocked due to a fault, the undercarriage handle uplock unlocking switch is manually pressed, so that the undercarriage handle uplock is manually and mechanically released.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: when the electromagnet of the undercarriage handle lock can not be normally unlocked due to faults, the undercarriage handle retraction up lock can be manually and mechanically released.
Preferably, the landing gear control handle assembly further comprises a landing gear handle position switch for sensing the position of the landing gear handle to send an electrical signal indicative of the landing gear handle position to a landing gear control unit.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: the landing gear control unit can be sent the landing gear handle position command in a suitable manner.
Preferably, the maximum allowable flight speed of the landing gear is no higher than the maximum allowable flight speed of the landing gear.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: the maximum allowable flight speed for landing gear retraction and landing gear retraction can be set within a suitable range.
Preferably, the maximum allowable flight speed of the landing gear is 220 and 270 sections.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: the maximum allowable flight speed of the retractable landing gear can be set within a proper range, so that the landing gear can be prevented from being accidentally operated by the landing gear handle when the flight speed is higher than the maximum allowable flight speed of the retractable landing gear.
Preferably, the maximum allowable flight speed of the landing gear is 250 and 270 sections.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: the maximum allowable flight speed of the landing gear can be set within a suitable range, so that accidental operation of the landing gear handle to the landing gear when the flight speed is higher than the maximum allowable flight speed of the landing gear is better prevented.
Drawings
Fig. 1 is a schematic structural view of a landing gear control handle assembly according to an embodiment of the present invention.
List of reference numerals
10. Landing gear handle
11. Landing gear handle lowering lock
12. Electromagnet for lowering gear handle lock
13. Unlocking switch for undercarriage handle lowering lock
20. Undercarriage handle position switch
21. Landing gear handle upper lock
22. Electromagnet for landing gear handle upper lock
23. Unlocking switch for landing gear handle upper lock
Detailed Description
In the following description of the embodiments of the present invention, it is noted that in the detailed description of the embodiments, all the features of the actual embodiments may not be described in detail in order to make the description concise and concise. It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions are made to achieve the developers' specific goals, such as compliance with system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be further appreciated that such a development effort might be complex and tedious, but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure, and it should be understood that such a development effort might be complex and tedious.
Unless otherwise defined, technical or scientific terms used in the claims and the specification should have the ordinary meaning as understood by those having ordinary skill in the art to which the present invention belongs. The use of "first," "second," and similar terms in the description and in the claims does not indicate any order, quantity, or importance, but rather is used to distinguish one element from another. The terms "a" or "an," and the like, do not denote a limitation of quantity, but rather denote the presence of at least one. The word "comprise" or "comprises", and the like, means that the element or item listed before "comprises" or "comprising" covers the element or item listed after "comprising" or "comprises" and its equivalent, and does not exclude other elements or items. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, nor are they restricted to direct or indirect connections.
Fig. 1 is a schematic structural view of a landing gear control handle assembly according to an embodiment of the present invention.
Note: the broken-line arrows between the respective blocks in the drawing indicate mechanical connections, and the solid-line arrows between the respective blocks in the drawing indicate electrical connections.
As shown in fig. 1, according to an embodiment of the present invention, the landing gear control handle assembly includes a landing gear handle 10, a landing gear handle lowering lock 11, and a landing gear handle lowering lock electromagnet 12, wherein,
when the airplane is on the ground or the airplane flying speed is higher than the maximum allowable flying speed for taking up the undercarriage, the electromagnet 12 of the undercarriage handle lowering lock is powered off, and the undercarriage handle lowering lock 11 locks the undercarriage handle 10 in the lowering position;
when the aircraft is in the air and the aircraft flight speed is not higher than the maximum allowable flight speed for landing gear retraction, the landing gear handle lowering lock electromagnet 12 is energized to mechanically actuate the landing gear handle lowering lock 11 (e.g. by movement of a plunger) to unlock and the landing gear handle 10 can be moved from the down position to the up position.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: the landing gear can be prevented from being accidentally operated by the landing gear handle when the flying speed is higher than the maximum allowable flying speed of the landing gear.
Specifically speaking, when the aircraft flying speed is higher than the maximum allowable flying speed of the landing gear, the electromagnet of the undercarriage handle lowering lock is powered off, the undercarriage handle lowering lock locks the undercarriage handle in the lowering position, the landing gear handle is prevented from being operated accidentally, and potential safety hazards caused by the fact that the landing gear is retracted when the aircraft flies at a high speed are avoided.
Preferably, the landing gear control handle assembly further comprises a landing gear handle stow-up lock 21 and a landing gear handle stow-up lock electromagnet 22, wherein,
when the flight speed of the aircraft is higher than the maximum allowable flight speed of the landing gear, the electromagnet 22 of the landing gear handle retraction uplock is powered off, and the landing gear handle retraction uplock 21 locks the landing gear handle 10 in the retraction uplock;
when the aircraft flight speed is not higher than the maximum allowable landing gear flight speed, the landing gear handle retraction uplock electromagnet 22 is energized (e.g. by movement of a plunger) to mechanically actuate the landing gear handle retraction uplock unlocking 21, and the landing gear handle 10 can be moved from the retracted to the lowered position.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: accidental operation of the landing gear handle to lower the landing gear at speeds above the maximum allowable landing gear speed is prevented.
Preferably, as shown in figure 1, the landing gear control handle assembly further comprises a landing gear handle hold down lock unlock switch 13, and when the landing gear handle lock electromagnet 12 fails to unlock normally due to a fault, the landing gear handle hold down lock unlock switch 13 is manually pressed, and the landing gear handle hold down lock 11 is manually and mechanically released.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: when the electromagnet of the undercarriage handle lock cannot be normally unlocked due to a fault, the undercarriage handle lowering lock can be manually and mechanically released.
Preferably, as shown in figure 1, the landing gear control handle assembly further comprises a landing gear handle stow up lock unlock switch 23, and when the landing gear handle lock electromagnet 22 fails to unlock normally due to a fault, the landing gear handle stow up lock unlock switch 23 is manually pressed, and the landing gear handle stow up lock 21 is manually mechanically released.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: when the electromagnet of the undercarriage handle lock cannot be normally unlocked due to a fault, the undercarriage handle retraction up lock can be manually and mechanically released.
Preferably, as shown in figure 1, the landing gear control handle assembly further comprises a landing gear handle position switch 20, the landing gear handle position switch 20 being arranged to sense the position of the landing gear handle 10 so as to send a position command for the landing gear handle 10 to the landing gear control unit as an electrical signal.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: the landing gear control unit can be sent the landing gear handle position command in a suitable manner.
Preferably, the maximum allowable flight speed for landing gear retraction is no higher than the maximum allowable flight speed for landing gear retraction.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: the maximum allowable flight speed for landing gear retraction and landing gear retraction can be set within a suitable range.
Preferably, the maximum allowable flight speed for the landing gear is 220-.
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: the maximum allowable flight speed of the retractable landing gear can be set within a proper range, so that the landing gear can be prevented from being accidentally operated by the landing gear handle when the flight speed is higher than the maximum allowable flight speed of the retractable landing gear.
More preferably, the maximum allowable flight speed for the landing gear is 220 knots (407 km/h).
Preferably, the maximum allowable airspeed for the landing gear is 250 + 270 knots (at 463 + 500 km/h).
According to the technical scheme, the utility model discloses an undercarriage control handle subassembly can play following beneficial technological effect: the maximum allowable flight speed of the landing gear can be set within a suitable range, so that accidental operation of the landing gear handle to the landing gear when the flight speed is higher than the maximum allowable flight speed of the landing gear is better prevented.
More preferably, the maximum allowable flight speed for the landing gear is 250 knots (463 km/h).
Of course, the above maximum allowable flying speed for retractable landing gear is only a preferred range or value for the maximum allowable flying speed for retractable landing gear of the landing gear control handle assembly of the present invention, and those skilled in the art can understand on the basis of the present disclosure that other suitable ranges or values can be adopted without departing from the scope of the present invention.
While particular embodiments of the present invention have been described above, it will be understood by those skilled in the art that the above embodiments do not constitute limitations on the present invention, and that various modifications may be made by those skilled in the art based on the above disclosure without departing from the scope of the present invention.
Claims (8)
1. A landing gear control handle assembly, characterized in that the landing gear control handle assembly comprises a landing gear handle, a landing gear handle lowering lock and a landing gear handle lowering lock electromagnet, wherein,
when the airplane is on the ground or the airplane flying speed is higher than the maximum allowable flying speed for taking up the undercarriage, the electromagnet of the undercarriage handle lowering lock is powered off, and the undercarriage handle lowering lock locks the undercarriage handle in the lowering position;
when the aircraft is in the air and the flight speed of the aircraft is not higher than the maximum allowable flight speed of the landing gear, the electromagnet of the landing gear handle lowering lock is electrified, the landing gear handle lowering lock is unlocked through mechanical driving, and the landing gear handle can move from the lowering position to the retrieving position.
2. The landing gear control handle assembly of claim 1, further comprising a landing gear handle stow-up lock and a landing gear handle stow-up lock electromagnet, wherein,
when the flight speed of the aircraft is higher than the maximum allowable flight speed of the landing gear, the electromagnet of the landing gear handle retraction uplock is powered off, and the landing gear handle retraction uplock locks the landing gear handle in a retraction uplock;
when the flight speed of the aircraft is not higher than the maximum allowable flight speed of the landing gear, the electromagnet of the landing gear handle retraction uplock is electrified, the landing gear handle retraction uplock is unlocked through mechanical driving, and the landing gear handle can move to the lowering position from the retraction uplock.
3. The landing gear control handle assembly of claim 1, further comprising a landing gear handle hold down lock unlock switch that is manually depressed to manually mechanically disengage the landing gear handle hold down lock when the landing gear handle lock electromagnet fails to normally unlock due to a fault.
4. The landing gear control handle assembly of claim 2, further comprising a landing gear handle stow up lock unlock switch that is manually depressed to manually mechanically unlock the landing gear handle stow up lock when the landing gear handle lock electromagnet fails to normally unlock due to a fault.
5. A landing gear control handle assembly according to claim 1 or claim 2, further comprising a landing gear handle position switch for sensing the position of the landing gear handle to send a position command for the landing gear handle as an electrical signal to a landing gear control unit.
6. The landing gear control handle assembly according to claim 2, wherein the maximum allowable flight speed for the landing gear on the nose is no higher than the maximum allowable flight speed for the landing gear on the nose.
7. The landing gear control handle assembly according to claim 1, wherein the maximum allowable airspeed for the landing gear is 220 plus 270 knots.
8. The landing gear control handle assembly of claim 2, wherein the maximum allowable airspeed of the landing gear is 250 and 270 knots.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921303084.0U CN210338276U (en) | 2019-08-09 | 2019-08-09 | Landing gear control handle assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921303084.0U CN210338276U (en) | 2019-08-09 | 2019-08-09 | Landing gear control handle assembly |
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| Publication Number | Publication Date |
|---|---|
| CN210338276U true CN210338276U (en) | 2020-04-17 |
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| CN201921303084.0U Active CN210338276U (en) | 2019-08-09 | 2019-08-09 | Landing gear control handle assembly |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114446112A (en) * | 2022-02-09 | 2022-05-06 | 安胜（天津）飞行模拟系统有限公司 | Undercarriage handle fault simulation method and locking device |
| CN116176832A (en) * | 2023-05-04 | 2023-05-30 | 成都凯天电子股份有限公司 | Method for controlling retraction, extension and extension based on complex undercarriage configuration |
-
2019
- 2019-08-09 CN CN201921303084.0U patent/CN210338276U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114446112A (en) * | 2022-02-09 | 2022-05-06 | 安胜（天津）飞行模拟系统有限公司 | Undercarriage handle fault simulation method and locking device |
| CN114446112B (en) * | 2022-02-09 | 2024-01-23 | 安胜（天津）飞行模拟系统有限公司 | Landing gear handle fault simulation method and locking device |
| CN116176832A (en) * | 2023-05-04 | 2023-05-30 | 成都凯天电子股份有限公司 | Method for controlling retraction, extension and extension based on complex undercarriage configuration |
| CN116176832B (en) * | 2023-05-04 | 2023-10-24 | 成都凯天电子股份有限公司 | Method for controlling retraction, extension and extension based on complex undercarriage configuration |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220928 Address after: No.25, Zhangyang Road, China (Shanghai) pilot Free Trade Zone, Pudong New Area, Shanghai, 201210 Patentee after: COMMERCIAL AIRCRAFT CORPORATION OF CHINA, Ltd. Patentee after: Shanghai Aircraft Design Research Institute Co.,Ltd. Address before: No.25 Zhangyang Road, Pudong New Area, Shanghai 201210 Patentee before: COMMERCIAL AIRCRAFT CORPORATION OF CHINA, Ltd. Patentee before: COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD SHANGHAI AIRCRAFT DESIGN AND Research Institute |
|
| TR01 | Transfer of patent right |