CN103600836A - Plane gust lock anti-misoperation structure - Google Patents
Plane gust lock anti-misoperation structure Download PDFInfo
- Publication number
- CN103600836A CN103600836A CN201310556970.5A CN201310556970A CN103600836A CN 103600836 A CN103600836 A CN 103600836A CN 201310556970 A CN201310556970 A CN 201310556970A CN 103600836 A CN103600836 A CN 103600836A
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- Prior art keywords
- rod
- locking
- lock
- handle
- wind
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- Granted
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- 230000035515 penetration Effects 0.000 claims description 5
- 238000010586 diagram Methods 0.000 description 2
- IWEDIXLBFLAXBO-UHFFFAOYSA-N dicamba Chemical compound COC1=C(Cl)C=CC(Cl)=C1C(O)=O IWEDIXLBFLAXBO-UHFFFAOYSA-N 0.000 description 2
- 239000010705 motor oil Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
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- Traffic Control Systems (AREA)
Abstract
The invention provides a gust lock operating structure which is easy and reliable to operate and can indicate the state of the gust lock and send out a correct alarming message without additionally adding an operation step so as to effectively prevent the misoperation of the gust lock in the sky. The structure comprises an operating handle, a rod body, a guiding rail, a locking structure and a position sensor, wherein the operating handle and the rod body are fixedly connected, the guiding rail is arranged on the rod body, the locking structure is arranged on the rod body for locking and unlocking the gust lock; the rod body is separated away from and contacts the position sensor when unlocking and locking the gust lock, so as to transmit different state information messages of the gust lock to an alarming system of the plane.
Description
Technical field
The present invention relates to aircraft manufacturing technical field, particularly a kind of prominent wind latching operation structure that can stop maloperation hidden danger.
Background technology
The purposes of prominent wind lock be for prevent aircraft on ground or during the water surface because being subject to prominent wind impact to damage the device of controlsurface (comprising tab) and maneuvering system.If lock and can bring serious harm to aircraft safety but maloperation makes prominent wind be locked in aerial generation by mistake.
For this reason, in the documents such as various airplane design standards, airworthiness regulation, all explicitly call for and should have counter-measure to this problem, regulation in airplane in transportation category airworthiness standard § 25.679: the device that prevents aircraft on ground or damage controlsurface (comprising tab) and maneuvering system during the water surface because of the wind impact that is subject to dash forward must be set.This prominent wind lock can limit the operation of aircraft, makes chaufeur when starting to take off, just obtain the warning of unlikely misunderstanding.Prominent wind locking device must have its measure of possibility inadvertent engagement awing that prevents.For meeting these requirements, conventional method of designing is to increase fool proof safety screen on the operating mechanism of prominent wind lock at present, to lock and must first open safety screen, set up the extra program of unblanking, increase the weight of the burden of aircraft, greatly increased the possibility that aviator's error operations causes occurring aircraft safety accident.
Summary of the invention
In order to address the above problem, the object of the present invention is to provide that a kind of operation is simple and reliable, without increasing control step, just can show prominent wind lock status and send correct warning message, the wind that effectively prevents from dashing forward is locked the prominent wind of aerial maloperation and is locked handle structure.
A kind of Airplane Penetration wind is locked anti-error handle structure, comprise bar handle, the body of rod, guide rail, locking mechanism, position transduser, alarm system, bar handle with the body of rod for being fixedly connected with, on the body of rod, be provided with guide rail, locking mechanism is just arranged on the body of rod, is used for locking and the prominent wind lock of release, the body of rod can leave and touch position sensor when prominent wind lock release and locking, thereby the different conditions information of prominent wind lock is sent to the alarm system of aircraft.
And locking mechanism includes clamp handle, slide block, locating dowel pin and retracing spring, one end of retracing spring is connected on the termination of the body of rod away from bar handle, the other end is connected with locating dowel pin, locating dowel pin passes and is embedded in the position-limited trough of offering on guide rail, and be connected by attaching parts with slide block, slide block is embedded in and on orbit of guide rail, slides and be fixedly connected with clamp handle, handles clamp handle and makes the prominent wind lock release of locating dowel pin mobile realization in position-limited trough and locking.
Beneficial effect of the present invention shows the operation function of existing prominent wind lock restriction aircraft in a set of prominent wind lock steering unit, prevents that it from may accidentally pin rudder face awing, has again the alarm function that can effectively prevent aerial maloperation simultaneously.
Below in conjunction with embodiment accompanying drawing, this invention is described in further detail.
Accompanying drawing explanation
The prominent wind lock of Fig. 1 handle structure schematic diagram
Fig. 2 slide block and guide rail structure schematic diagram
Number description: 1 bar handle, 2 bodies of rod, 3 clamp handles, 4 throttle killers, 5 guide rails, 6 position transdusers, 7 retracing springs, 8 prominent wind lock driving systems, 9 position-limited troughs, 10 locating dowel pins, 11 slide blocks
The specific embodiment
The anti-error handle structure of Airplane Penetration wind lock of the present invention is shown in accompanying drawing 1, and in this structure, bar handle 1 is fixed on the body of rod 2, is designed with dovetail furrow guide rail 5 on the body of rod 2, in guide rail 5 grooves, packs slide block 11(into as shown in Figure 2), slide block 11 tops connect clamp handle 3.Slide block 11 connects respectively retracing spring 7 and locating dowel pin 10 by attaching parts, and locating dowel pin 10 is stuck in the position-limited trough 9 of opening on guide rail 5.The other end of retracing spring 7 is connected on the body of rod 2, and retracing spring 7 is always in extended state, guarantees locking and lockset position of coupler locating dowel pin 10 can be stuck in position-limited trough by failure-freies.By pulling clamp handle 3 can be with movable slider 11 motion, make locating dowel pin 10 lock and lockset position of coupler between move.While handling prominent wind lock, must first mention clamp handle 3, pull prominent wind locking bar body 2.The throttle killer 4 of connecting engine on the body of rod 2, when operated lock locking structure makes prominent wind lock in locking-in state, restriction throttle lever is at ground idle speed state.Simultaneously the body of rod 2 touches position transduser 6, and position transduser 6 detects locks, and the information of locking is sent to alarm system, engine oil door restrictor 4 by throttle restriction built in little throttle.Operated lock locking structure is locked into while reaching unlocked position prominent wind, by prominent wind lock driving system 8, prominent wind lock lock pin on rudder face is discharged, the body of rod 2 leaves position transduser 6 simultaneously, position transduser 6 detects release, release information is sent to alarm system, the releasing alarm of locking, engine oil door restrictor 4 no longer limits throttle lever motion.By the combination of mechanical position limitation and alarm system, realize the anti-misoperation of prominent wind lock.By locking installation site sensor 6 at prominent wind, after powering on, aircraft can gather prominent wind lock position information, when sensor 6 detects location information, information will be sent to alarm system, sound and point out and drive warning light alarm.Aircraft is before skidding off, if prominent wind lock is not opened, the prominent wind lock of warning light flash for prompting of alarm system pins, and prominent wind lock is opened in voice message.During aerial normal flight, if the prominent wind lock of flight error operations handle 1, alarm system also can be sounded and be pointed out and drive warning light alarm.
This invention lamps structure is simple, and principle is reliable, and function is easy to guarantee; Volume is little, lightweight, handles comfortablely, harmony is installed good; This prominent wind lock handle structure has mechanical anti-misoperation actuating mechanism and auto-alarming function concurrently; Because this prominent wind lock handle structure has position indication and auto-alarming function, effectively alleviated aviator's burden, avoid the prominent wind lock of error operations to cause aircraft possibility out of control, improved the safety and reliability of flight control.
Claims (2)
1. an Airplane Penetration wind is locked anti-error handle structure, comprise bar handle, the body of rod, guide rail, locking mechanism, position transduser, alarm system, it is characterized in that described bar handle is fixedly connected with the described body of rod, the described body of rod is provided with described guide rail, described locking mechanism is arranged on the described body of rod, the described body of rod leaves and contacts described position transduser when described locking mechanism release and the prominent wind lock of locking, dash forward wind lock release and locking information is sent to the alarm system of aircraft.
2. a kind of Airplane Penetration wind is locked anti-error handle structure according to claim 1, it is characterized in that described locking mechanism comprises clamp handle, slide block, locating dowel pin and retracing spring, described retracing spring one end is connected on the termination of the described body of rod away from described bar handle, the other end is connected with described locating dowel pin, described locating dowel pin passes and is embedded in the position-limited trough of offering on guide rail, and be connected by attaching parts with described slide block, described slide block is embedded in and on described orbit of guide rail, slides and be fixedly connected with described clamp handle, handling described clamp handle makes described locating dowel pin mobile wind of dashing forward of realizing in described position-limited trough lock release and locking.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310556970.5A CN103600836B (en) | 2013-11-08 | 2013-11-08 | A kind of plane gust lock anti-misoperation structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310556970.5A CN103600836B (en) | 2013-11-08 | 2013-11-08 | A kind of plane gust lock anti-misoperation structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103600836A true CN103600836A (en) | 2014-02-26 |
| CN103600836B CN103600836B (en) | 2015-08-05 |
Family
ID=50119129
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310556970.5A Active CN103600836B (en) | 2013-11-08 | 2013-11-08 | A kind of plane gust lock anti-misoperation structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN103600836B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109521750A (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of parking brake steerable system |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2459143A (en) * | 1945-11-26 | 1949-01-18 | John C Beirise | Emergency control lock |
| US2584038A (en) * | 1948-03-09 | 1952-01-29 | Boeing Co | Aircraft control lock |
| US4012014A (en) * | 1975-09-11 | 1977-03-15 | Mcdonnell Douglas Corporation | Aircraft flight controller |
| US20090266940A1 (en) * | 2008-04-25 | 2009-10-29 | David George Miller | Precision adjust split detent for a vehicle |
| CN102343977A (en) * | 2010-07-28 | 2012-02-08 | 伍德沃德Mpc股份有限公司 | Active control column with manually activated reversion to passive control column |
| CN102343976A (en) * | 2010-07-28 | 2012-02-08 | 伍德沃德Mpc股份有限公司 | Position control system for cross coupled operation of fly-by-wire control columns |
| CN103328326A (en) * | 2011-01-24 | 2013-09-25 | 萨甘安全防护公司 | Device for actuating an item of equipment that can be controlled automatically or manually, with detection of take-up of manual control |
-
2013
- 2013-11-08 CN CN201310556970.5A patent/CN103600836B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2459143A (en) * | 1945-11-26 | 1949-01-18 | John C Beirise | Emergency control lock |
| US2584038A (en) * | 1948-03-09 | 1952-01-29 | Boeing Co | Aircraft control lock |
| US4012014A (en) * | 1975-09-11 | 1977-03-15 | Mcdonnell Douglas Corporation | Aircraft flight controller |
| US20090266940A1 (en) * | 2008-04-25 | 2009-10-29 | David George Miller | Precision adjust split detent for a vehicle |
| CN102343977A (en) * | 2010-07-28 | 2012-02-08 | 伍德沃德Mpc股份有限公司 | Active control column with manually activated reversion to passive control column |
| CN102343976A (en) * | 2010-07-28 | 2012-02-08 | 伍德沃德Mpc股份有限公司 | Position control system for cross coupled operation of fly-by-wire control columns |
| CN103328326A (en) * | 2011-01-24 | 2013-09-25 | 萨甘安全防护公司 | Device for actuating an item of equipment that can be controlled automatically or manually, with detection of take-up of manual control |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109521750A (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of parking brake steerable system |
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| Publication number | Publication date |
|---|---|
| CN103600836B (en) | 2015-08-05 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: No. 710089 in Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC Xi'an Aircraft Industry Group Co.,Ltd. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: AVIC AIRCRAFT Corp. |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210610 Address after: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC AIRCRAFT Corp. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: XI'AN AIRCRAFT BRANCH OF XI'AN AIRCRAFT INTERNATIONAL Corp. |