CN102069918A - Method for fast mounting and dismounting aircraft control panel and fast mounting-dismounting screw lock - Google Patents
Method for fast mounting and dismounting aircraft control panel and fast mounting-dismounting screw lock Download PDFInfo
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- CN102069918A CN102069918A CN2010105768476A CN201010576847A CN102069918A CN 102069918 A CN102069918 A CN 102069918A CN 2010105768476 A CN2010105768476 A CN 2010105768476A CN 201010576847 A CN201010576847 A CN 201010576847A CN 102069918 A CN102069918 A CN 102069918A
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Abstract
The invention discloses a method for fast mounting and dismounting an aircraft control panel and a fast mounting-dismounting screw lock. In the invention, a lock base with more than two lock cylinder holes is pre-fixed on an aircraft framework for mounting the aircraft control panel and a locking steel is arranged in each lock cylinder hole of the lock base; then more than two fast mounting-dismounting screw locks are fixed on the aircraft control panel; the lock screws of the fast mounting-dismounting screw locks can be buckled on the locking steels of the lock cylinder holes only after being fixed in the lock cylinder hole of the lock base on the aircraft framework and rotating by 90 degrees so as to fast mount the aircraft control panel on the aircraft framework; and the lock screws of the fast mounting-dismounting screw locks can break away from the locking steels in the lock cylinder holes after rotating by 90 degrees towards the opposite direction so as to fast dismount the aircraft control panel from the aircraft framework. The invention has strong fatigue resistance, a small volume and a light weight, is simple and convenient to use and maintain, is fast to mount and dismount and the like.
Description
Technical field
The present invention relates to a kind of quick handling method of aircraft control surface plate and load and unload the spiral lock fast, belong to the aircraft control surface plate and install and fix technical field.
Background technology
At present, in the prior art, when the system panel with the aircraft control is fixed on the fuselage ring of aircraft, generally all be to adopt the screw ways of connecting, though it is reliable that this employing screw ways of connecting connects, exist the problem that installation effectiveness is low, dismounting is inconvenient.Because the existence of these problems, this maintenance and maintenance to aircraft is all unfavorable.Therefore, the handling mode of existing aircraft control surface plate still is not ideal enough.
Summary of the invention
The objective of the invention is to, a kind of quick handling method of aircraft control surface plate is provided and loads and unloads the spiral lock fast, open use needs with quick closedown fast to satisfy the aircraft control surface plate, and can make things convenient for the maintenance of aircraft, improve the maintenance efficiency of aircraft, shorten the time of the quick opening and closing of aircraft cabin flap panel, thereby overcome the deficiencies in the prior art.
Technical scheme of the present invention is achieved in that the quick handling method of a kind of aircraft control surface plate of the present invention is, on predetermined fixed on the fuselage ring that the aircraft control surface plate is installed, be manufactured with the lock of two above lock core holes, and in each lock core hole of lock, the locking steel wire is set all, on the aircraft control surface plate, fix plural quick loading and unloading spiral lock then, when being installed in the aircraft control surface plate on the fuselage ring, the pinning that only needs to load and unload fast the spiral lock injects in the lock core hole that is fixed on the lock on the fuselage ring and after the angle of half-twist, pinning is buckled on the locking steel wire in the lock core hole, so just can is installed in the aircraft control surface plate on the fuselage ring apace; When the aircraft control surface plate is dismantled following time from fuselage ring, only need rotation in the opposite direction fast after the angle of 90 ° of the pinnings of loading and unloading spiral lock, can make the locking steel wire in the pinning disengaging lock core hole, so just can be apace down from the fuselage ring dismounting with the aircraft control surface plate.
A kind of quick loading and unloading spiral lock that is used for the inventive method is, this quick loading and unloading spiral lock comprises and being used for and aircraft control surface plate bonded assembly housing, pinning is installed in housing, on the bar footpath of pinning, be with spring, and pinning is stabilized in the housing by spring, upper end at pinning is provided with tack, is provided with flat recess on tack, is provided with the locking steel wire bonded assembly plug helix that is used for the lock core hole of lock in the bottom in pinning bar footpath; Be provided with the bottle opener hole at the top of housing.
On lock, be provided with plural lock core hole, and the internal diameter of lock core hole can pack into the bar footpath of pinning, on the sidewall of each lock core hole, all be provided with threaded hole of steel, and the locking steel wire is housed in threaded hole of steel.
The center, hole of the lock core hole on the lock all is arranged on the same straight line and by equidistantly distributing, all on same line of centers, the locking steel wire is installed in the threaded hole of steel and runs through all lock core holes at the center, hole of the threaded hole of steel on each lock core hole sidewall.
On lock, be provided with fuselage ring bonded assembly mounting hole with aircraft.
Owing to adopted technique scheme, when dismounting aircraft control surface plate, only need by the bottle opener hole on the housing pinning be revolved to turn 90 degrees and can finish release with bottle opener, just control panel can be opened then; When closing, only pinning need be pressed and revolve in the opposite direction and turn 90 degrees, can make the locking steel wire in the lock core hole rotate and enter in the plug helix like this, thereby control panel is locked along spiral fluted.After testing and proof of actual use, adopt the present invention can satisfy the aircraft control surface plate fully and open requirement with quick closedown fast.After tested, technical index of the present invention is as follows: after closing, the moment of unblanking is 0.141 N.m～0.27 N.m; After opening, locking torque is 0.28 N.m～0.9 N.m.Locking stop intensity is 3.39 N.m, and the locking steel wire breakout force is 661.5N, and specified tensile load is 882N, and specified shearing resistance load is 882N.The antivibration ability meets the 5th class standard of national military standard GJB150.16.Durability of the present invention can reach 5000 times.Fast the material of loading and unloading spiral lock all adopts the material of resisting salt fog corrosion, and its salt spray resistance experiment of loading and unloading the spiral lock fast reaches the standard 100 hours of national military standard GJB715.1.Therefore, the present invention compared with prior art, the present invention not only has and can satisfy the aircraft control surface plate and open with the operating needs of quick closedown fast, make things convenient for aircraft maintenance, improve aircraft maintenance efficient, shorten aircraft cabin flap panel opening and the advantage of shut, but also has advantages such as fatigue resistance height, volume is little, in light weight, working service is easy, dismounting is fast.
Description of drawings
Fig. 1 is the structural representation of the present invention when using;
Fig. 2 is the pinning structural representation that the present invention loads and unloads the spiral lock fast;
Being labeled as in the accompanying drawing: 1-housing, 2-lock, 3-pinning, 4-tack, 5-flat recess, 6-plug helix, 7-spring, 8-aircraft control surface plate, 9-mounting hole, 10-lock core hole, 11-threaded hole of steel, the 12-steel wire that locks.
The specific embodiment
The present invention is described in further detail below in conjunction with drawings and Examples.
Embodiments of the invention: the quick handling method that adopts a kind of aircraft control surface plate of the present invention, carry out the loading and unloading of aircraft control surface plate, promptly on predetermined fixed on the fuselage ring that the aircraft control surface plate is installed, be manufactured with the lock of two above lock core holes, and in each lock core hole of lock, the locking steel wire is set all, on the aircraft control surface plate, fix plural quick loading and unloading spiral lock then, when being installed in the aircraft control surface plate on the fuselage ring, the pinning that only needs to load and unload fast the spiral lock injects in the lock core hole that is fixed on the lock on the fuselage ring and after the angle of half-twist, pinning is buckled on the locking steel wire in the lock core hole, so just can is installed in the aircraft control surface plate on the fuselage ring apace; When the aircraft control surface plate is dismantled following time from fuselage ring, only need rotation in the opposite direction fast after the angle of 90 ° of the pinnings of loading and unloading spiral lock, can make the locking steel wire in the pinning disengaging lock core hole, so just can be apace down from the fuselage ring dismounting with the aircraft control surface plate.
When implementing method of the present invention, adopt a kind of quick loading and unloading spiral lock of the present invention to implement, the structure of loading and unloading spiral lock as shown in Figure 1 fast, comprise and being used for and aircraft control surface plate 8 bonded assembly housings 1, during making, a pinning 3 is installed in housing 1, cover upper spring 7 on the bar footpath of pinning 3, pinning 3 is stabilized in the housing 1 by spring 7, produce tack 4 in the upper end of pinning 3, and on tack 4, produce flat recess 5, produce in the bottom in pinning 3 bars footpath be used for the locking steel wire 12 bonded assembly plug helix 6(of the lock core hole 10 of lock 2 as shown in Figure 2); Produce the bottle opener hole at the top of housing 1; Producing simultaneously the quantity of plural lock core hole 10(lock core hole 10 on lock 2 can determine according to the size and the existing operating needs of aircraft control surface plate 8), make the internal diameter of lock core hole 10 can pack into the bar footpath of pinning 3, on the sidewall of each lock core hole 10, all produce threaded hole of steel 11, and in threaded hole of steel 11, load onto locking steel wire 12; In order to install and easy to make and simplified structure, during making, the center, hole of the lock core hole on the lock 2 10 all can be arranged on the same straight line and by equidistantly distributing, all on same line of centers, the steel wire 12 that will lock then is installed in the threaded hole of steel 11 and makes it run through all lock core holes 10 at the center, hole that makes the threaded hole of steel 11 on each lock core hole 10 sidewall; On lock 2, produce simultaneously and be used for the fuselage ring bonded assembly mounting hole 9 of aircraft.
Working process of the present invention and principle are described as follows again:
The housing 1 of quick loading and unloading spiral lock of the present invention is mounted in around the flap of aircraft control surface plate 8 of aircraft, and lock 2 is mounted on the fuselage ring of aircraft, and during installation, the position of housing 1 is corresponding with lock 2.When the control panel 8 of aircraft is installed, housing around the flap 1 is aimed at the lock core hole 10 of the lock 2 on the aircraft, pinning 3 in each housing 1 is all inserted in the lock core hole 10 of cooresponding lock 2, insert in the flat recess of pinning 3 with bottle opener then, revolve and turn 90 degrees, hand of rotation is by the plug helix decision of pinning; Pinning of the present invention turn 90 degrees so can only revolve because plug helix has only the scope of 90 degree; When rotated, pinning 3 rotates along plug helix, and pinning 3 is slipped in the locking steel wire 12, and pinning 3 is under spring 7 and spiral fluted effect, makes pinning be buckled in firmly on the locking steel wire 12 and can not deviate from from locking steel wire 12 voluntarily.
When needs are opened aircraft control surface plate 8, with bottle opener opposite spin pinning 3, at this moment pinning 3 elastic force that overcomes spring 7 is deviate from from locking steel wire 12, and the steel wire 12 that locks simultaneously skids off and separates with pinning 3 along plug helix 6, and aircraft control surface plate 8 can separate with lock and be opened like this.
Claims (5)
1. the quick handling method of an aircraft control surface plate, it is characterized in that: the lock that on predetermined fixed on the fuselage ring that the aircraft control surface plate is installed, is manufactured with two above lock core holes, and in each lock core hole of lock, the locking steel wire is set all, on the aircraft control surface plate, fix plural quick loading and unloading spiral lock then, when being installed in the aircraft control surface plate on the fuselage ring, the pinning that only needs to load and unload fast the spiral lock injects in the lock core hole that is fixed on the lock on the fuselage ring and after the angle of half-twist, pinning is buckled on the locking steel wire in the lock core hole, so just can is installed in the aircraft control surface plate on the fuselage ring apace; When the aircraft control surface plate is dismantled following time from fuselage ring, only need rotation in the opposite direction fast after the angle of 90 ° of the pinnings of loading and unloading spiral lock, can make the locking steel wire in the pinning disengaging lock core hole, so just can be apace down from the fuselage ring dismounting with the aircraft control surface plate.
2. a quick loading and unloading spiral that is used for the described method of claim 1 is locked, comprise and being used for and aircraft control surface plate (8) bonded assembly housing (1), it is characterized in that: pinning (3) is installed in housing (1), on the bar footpath of pinning (3), be with spring (7), and pinning (3) is stabilized in the housing (1) by spring (7), be provided with tack (4) in the upper end of pinning (3), on tack (4), be provided with flat recess (5), be provided with locking steel wire (12) the bonded assembly plug helix (6) that is used for the lock core hole (10) of lock (2) in the bottom in pinning (3) bar footpath; Top at housing (1) is provided with the bottle opener hole.
3. quick loading and unloading spiral lock according to claim 2, it is characterized in that: on lock (2), be provided with plural lock core hole (10), and the internal diameter of lock core hole (10) can pack into the bar footpath of pinning (3), on the sidewall of each lock core hole (10), all be provided with threaded hole of steel (11), and locking steel wire (12) is housed in threaded hole of steel (11).
4. quick loading and unloading spiral lock according to claim 3, it is characterized in that: the center, hole of the lock core hole (10) on the lock (2) all is arranged on the same straight line and by equidistantly distributing, all on same line of centers, locking steel wire (12) is installed in the threaded hole of steel (11) and runs through all lock core holes (10) at the center, hole of the threaded hole of steel (11) on each lock core hole (10) sidewall.
5. quick loading and unloading spiral lock according to claim 4 is characterized in that: be provided with the fuselage ring bonded assembly mounting hole (9) with aircraft on lock (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105768476A CN102069918A (en) | 2010-12-07 | 2010-12-07 | Method for fast mounting and dismounting aircraft control panel and fast mounting-dismounting screw lock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105768476A CN102069918A (en) | 2010-12-07 | 2010-12-07 | Method for fast mounting and dismounting aircraft control panel and fast mounting-dismounting screw lock |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102069918A true CN102069918A (en) | 2011-05-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010105768476A Pending CN102069918A (en) | 2010-12-07 | 2010-12-07 | Method for fast mounting and dismounting aircraft control panel and fast mounting-dismounting screw lock |
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| CN (1) | CN102069918A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102865278A (en) * | 2012-09-17 | 2013-01-09 | 李理 | Self-locking bolt for furniture |
| CN105083560A (en) * | 2015-09-18 | 2015-11-25 | 航宇救生装备有限公司 | Quick disassembly device |
| CN109185301A (en) * | 2018-10-17 | 2019-01-11 | 贵州航太精密制造有限公司 | A kind of light-duty locking device of unidirectional installation and opening and closing |
| CN114233734A (en) * | 2021-12-22 | 2022-03-25 | 成都成维精密机械制造有限公司 | Rotary fastener and fastening structure |
| CN115199882A (en) * | 2022-06-23 | 2022-10-18 | 中航光电科技股份有限公司 | Bracket with adjustable depth |
| CN115605116A (en) * | 2020-06-22 | 2023-01-13 | 易希提卫生与保健公司（Se） | Dispenser and lock assembly thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4039219A (en) * | 1976-06-23 | 1977-08-02 | Chicago Pneumatic Tool Company | Automatic safety latch lift hook unit |
| DE3703786A1 (en) * | 1987-02-07 | 1988-08-18 | Philips Patentverwaltung | Connecting device with a quick-fastening screw |
| CN200988555Y (en) * | 2006-10-24 | 2007-12-12 | 韩德玮 | Connector |
| CN201162752Y (en) * | 2007-08-14 | 2008-12-10 | 贵州航天精工制造有限公司 | Helical locking device |
| CN201386714Y (en) * | 2009-04-13 | 2010-01-20 | 王鼎瑞 | Locking fixing component |
| CN201471371U (en) * | 2009-06-29 | 2010-05-19 | 中国航空工业集团公司洛阳电光设备研究所 | Closure tool for assembling spiral pinning and tool for assembling spiral pinning |
-
2010
- 2010-12-07 CN CN2010105768476A patent/CN102069918A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4039219A (en) * | 1976-06-23 | 1977-08-02 | Chicago Pneumatic Tool Company | Automatic safety latch lift hook unit |
| DE3703786A1 (en) * | 1987-02-07 | 1988-08-18 | Philips Patentverwaltung | Connecting device with a quick-fastening screw |
| CN200988555Y (en) * | 2006-10-24 | 2007-12-12 | 韩德玮 | Connector |
| CN201162752Y (en) * | 2007-08-14 | 2008-12-10 | 贵州航天精工制造有限公司 | Helical locking device |
| CN201386714Y (en) * | 2009-04-13 | 2010-01-20 | 王鼎瑞 | Locking fixing component |
| CN201471371U (en) * | 2009-06-29 | 2010-05-19 | 中国航空工业集团公司洛阳电光设备研究所 | Closure tool for assembling spiral pinning and tool for assembling spiral pinning |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102865278A (en) * | 2012-09-17 | 2013-01-09 | 李理 | Self-locking bolt for furniture |
| CN105083560A (en) * | 2015-09-18 | 2015-11-25 | 航宇救生装备有限公司 | Quick disassembly device |
| CN109185301A (en) * | 2018-10-17 | 2019-01-11 | 贵州航太精密制造有限公司 | A kind of light-duty locking device of unidirectional installation and opening and closing |
| CN115605116A (en) * | 2020-06-22 | 2023-01-13 | 易希提卫生与保健公司（Se） | Dispenser and lock assembly thereof |
| CN114233734A (en) * | 2021-12-22 | 2022-03-25 | 成都成维精密机械制造有限公司 | Rotary fastener and fastening structure |
| CN115199882A (en) * | 2022-06-23 | 2022-10-18 | 中航光电科技股份有限公司 | Bracket with adjustable depth |
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Application publication date: 20110525 |