CN201908925U

CN201908925U - Quick release lock used on airplane hatch cover

Info

Publication number: CN201908925U
Application number: CN 201020638087
Authority: CN
Inventors: 唐伟
Original assignee: Guizhou Hangtai Precision Manufacturing Co Ltd
Current assignee: Guizhou Hangtai Precision Manufacturing Co Ltd
Priority date: 2010-12-02
Filing date: 2010-12-02
Publication date: 2011-07-27
Anticipated expiration: 2020-12-02

Abstract

The utility model discloses a quick release lock used on an airplane hatch cover, which comprises an upper lock body and a lower lock body. For the quick release lock, the upper lock body with a pin is installed on the hatch cover, the lower lock body with a clamping groove is installed on an airplane body frame; when the lock is locked, the upper lock body is inserted inside the lower lock body and the pin is stuck inside the clamping groove under the effect of a spring, people rotates a bolt connected with the pin through a screw driver to unlock the lock and the pin overcomes the spring force and comes off from the groove, so that the upper lock body can be separated from the lower lock body to quickly release the hatch cover. The quick release lock is installed on the airplane to fulfill the requirements on quickly opening and closing of the airplane hatch cover, facilitate the maintenance of the airplane, improve the maintenance efficiency of the airplane, and reduce the time of quickly opening and reliably closing of the airplane hatch cover. The quick release lock is utilized so as to prevent the outer liquids from seeping into the hatch cover and avoid the damages on crucial equipments of the airplane caused by the influence of the outer liquids.

Description

The quick-release lock that uses on a kind of aircraft flap

Technical field

The utility model relates to the quick-release lock that uses on a kind of aircraft flap.

Background technique

The connection of aircraft flap at present now is mainly the quick-release lock, it can guarantee that flap opens or closes fast, but the quick-release that uses at present lock does not possess sealing function, when rainwater or fluid drips drain on the flap, liquid runs down quick-release lock is infiltered in the flap cabin, major part is the aircraft visual plant in the flap cabin, if cause visual plant to corrode fast easily after in rainwater or the fluid seepage access cover cabin, influences the normal operation and the working life of visual plant.Maintenance and maintenance to aircraft increase difficulty, for country causes heavy economic losses.

The model utility content

The technical problems to be solved in the utility model provides the sealing quick-release lock that uses on a kind of aircraft flap.

The quick-release lock that uses on a kind of aircraft flap comprises upper lock body and the down lock body that is provided with draw-in groove; Upper lock body comprises bolt, and the bolt upper end is provided with tack, and tack is provided with cross recess, the bottom of bolt is provided with pin-and-hole, is fixed with pin in the pin-and-hole, is with the lock cover on the bolt of pin top, between lock cover and tack, be provided with spring, be with the stopper ring of band internal tooth on the lock cover; Down lock body is provided with the core hole, and core hole internal diameter matches with lock cover external diameter, and bottom, core hole internal diameter matches with the bolt external diameter; The length of pin is less than the internal diameter in core hole; The external cylindrical surface of down lock body is provided with seal closure.

The both sides, core hole of down lock body bottom are provided with the draw-in groove of two symmetries, and a side of two draw-in grooves is respectively equipped with helicoid, and two helicoids are symmetrical arranged.The angle of swing of helicoid is 90 °.

Open and lock conveniently after adopting structure of the present utility model, and the band sealing function.Only need the lock core in the upper lock body be revolved to turn 90 degrees and finish release, just flap can be opened then with screw-driver; When closing, only the bolt in the upper lock body need be pressed and revolved in the opposite direction and turn 90 degrees, pin in the upper lock body is entered in the down lock body draw-in groove along the down lock body helicoid, hatch cover is pinned, and simultaneously, lock pin is under the effect of spring, lock pin is stuck in the draw-in groove of down lock body, play safety effect, make lock pin can not withdraw from the draw-in groove of down lock body automatically, hatch cover is locked.After this sealing quick-release lock is installed on the aircraft, can satisfies the aircraft cabin flap and open requirement with quick closedown fast, and can prevent that outside liquid from infiltering in the flap cabin.This quick-release lock also has the fatigue strength height, characteristics such as volume is little, in light weight, working service is easy, dismounting is fast, sealing.

Description of drawings

Fig. 1 is the structural representation of the open mode of the utility model quick-release lock;

Fig. 2 is the structural representation of the locking state of the utility model quick-release lock;

Embodiment

As shown in Figure 1, the quick-release lock that uses on a kind of aircraft flap comprises upper lock body 1 and the down lock body 4 that is provided with draw-in groove 6; Down lock body 4 is provided with core hole 8, and core hole 8 top internal diameters are corresponding with lock cover 15 external diameters, and core hole 8 bottom internal diameters are corresponding with bolt 12 external diameters.The side that 8 both sides, core hole of down lock body 4 bottoms are provided with 6, two draw-in grooves 6 of draw-in groove of two symmetries is respectively equipped with 7, two helicoids 7 of helicoid and is symmetrical arranged.The angle of swing of helicoid 7 is 90 °, is with seal closure 5 on down lock body 4 outer cylinder.Upper lock body 1 comprises bolt 12, and bolt 12 upper ends are provided with tack 13, and tack 13 is provided with cross recess 14.Be with the stopper ring 11 of band internal tooth on the lock cover 15.The bottom of bolt 12 is provided with pin-and-hole 3, is fixed with pin 9 in the pin-and-hole 3, and the length of pin 9 is less than core hole 8 top internal diameters.Be with lock cover 15 on the bolt 12 of pin 9 tops, between lock cover 15 and tack 13, be provided with spring 2.Down lock body 4 is provided with the mounting hole 10 that is connected with aircraft.

Working procedure of the present utility model and principle

Fig. 2 is the locking state of quick-release lock.This quick-release lock comprises upper lock body 1 and down lock body 4, upper lock body 1 is mounted in around the flap of aircraft, and down lock body 4 is mounted on the framework of aircraft, during installation, the position of upper lock body 1 is corresponding with down lock body 4, and down lock body 4 should be consistent with the Normal direction of fuselage lock point.When the flap of aircraft is installed, upper lock body around the flap 1 is aimed at the core hole 8 of down lock body 4 on the aircraft, each upper lock body 1 is all inserted in the corresponding down lock body 4, then with in the cross recess 14 on the bolt of screw-driver insertion upper lock body 1, revolve and turn 90 degrees, sense of rotation is determined by the helicoid on the down lock body 4.Because the helicoid of down lock body 4 has only the scope of 90 degree, turn 90 degrees so can only revolve.When rotated, the pin 9 on the upper lock body 1 slides along helicoid, and pin 9 is slipped in the draw-in groove 6 of down lock body 4, under the effect of spring 2, makes pin 9 not deviate from from draw-in groove 6 voluntarily, and at this moment bolt 12 just flushes with airframe.

Fig. 1 is a quick-release lock open mode.During release, with the release respectively of the lock of the quick-release around the flap, release is with screw-driver opposite spin bolt 12, and so-called opposite direction is meant that the sense of rotation when locking is opposite.Pin 9 overcomes spring force, deviates from from draw-in groove 6, skids off along helicoid, can see that bolt 12 ejects, and at this moment bolt 12 exceeds the airframe surface, and bolt 12 is ejection states as can be seen.With pulling the upper lock body 1 that ejects, flap is opened then.

In order to prevent that upper lock body 1 assembly from coming off and prevent that upper lock body 1 assembly from rotating from flap.On lock cover 15 stopper ring 11 is installed, the internal tooth of stopper ring 11 has elasticity, can tightly be stuck on the lock cover 15.

In order to prevent that outside liquid from infiltrating in the flap cabin, on down lock body 4 external diameters, be with seal closure 5, seal closure 5 and down lock body 4 are connected by cold rolling, reach sealing effect.

Technical order of the present utility model is as follows: initial lowest pull 35.5N; Locking back flap and body impacting force are 890N; After closing, the moment of unblanking is 0.112N.m～1.4N.m; After opening, locking torque is 0.112N.m～1.25N.m.The shear strength of pin 9 has determined the tensile strength of sealing quick-release lock greater than 890N, and the shear strength of lock cover 10 is greater than 890N, and the antivibration ability meets the 5th class standard of national military standard GJB150.16A-2009.Durability of the present utility model can reach 5000 times.The material of lock adopts the material of resisting salt fog corrosion, makes the salt spray resistance experiment of sealing quick-release lock reach the standard 200 hours of national military standard GJB715.1-1989.

Adopt the utility model can satisfy when aircraft cabin flap panel is opened with quick closedown fast and can seal, 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, can prevent from simultaneously in the outside liquid infiltration flap cabin visual plant to be impacted.

Claims

1. the quick-release lock that uses on the aircraft flap comprises upper lock body (1) and is provided with the down lock body (4) of draw-in groove (6); Upper lock body (1) comprises bolt (12), bolt (12) upper end is provided with tack (13), tack (13) is provided with cross recess (14), the bottom of bolt (12) is provided with pin-and-hole (3), be fixed with pin (9) in the pin-and-hole (3), be with lock cover (15) on the bolt (12) of pin (9) top, between lock cover (15) and tack (13), be provided with spring (2), be with the stopper ring (11) of band internal tooth on the lock cover (15); Described down lock body (4) is provided with core hole (8), and core hole (8) internal diameter matches with lock cover (15) external diameter, and bottom, core hole (8) internal diameter matches with bolt (12) external diameter; The length of pin (9) is characterized in that less than the internal diameter of core hole (8): the external cylindrical surface of described down lock body (4) is provided with seal closure (5).

2. the quick-release lock of aircraft flap according to claim 1, it is characterized in that: the both sides, core hole (8) of described down lock body (4) bottom are provided with the draw-in groove (6) of two symmetries, one side of two draw-in grooves (6) is respectively equipped with helicoid (7), and two helicoids (7) are symmetrical arranged.

3. the quick-release lock of aircraft flap according to claim 2, it is characterized in that: the angle of swing of described helicoid (7) is 90 °.