KR100399753B1 - Latch for quick access door of aircraft - Google Patents

Abstract

The latch for a quick access door of an aircraft according to the present invention is easy to install and assemble through a latch structure having a detachable button, can freely adjust the amount of deviation in the field, if necessary, buttons having different shapes to the latch By assembling, it is to maximize the ease and applicability of the manufacturing, the opening and locking button portion (10, 20) and the latch portion 40 to the link section (51, 52, 53) supported on the bracket 30 And then, after fixing the bracket 30 to the mounting portion 60 of the quick access door, by pressing the opening and locking button portion (10, 20) so that the latch portion 40 is locked or released from the door frame, The opening and locking button portions 10 and 20 are provided with through holes 18, and the buttons 11 and 12 having plate-shaped holes 19, 19 'and 19 " , 13, 14) are combined as a detachable means.

Description

LATCH FOR QUICK ACCESS DOOR OF AIRCRAFT}

TECHNICAL FIELD The present invention relates to a latch for a quick access door of an aircraft, and more particularly, to provide a disassembleable assembly structure of a button attached to a latch, so that the contour of the surface of the quick access door can be provided. A latch for a quick access door of an aircraft installed to match the

Typically, a number of quick access doors are installed inside and outside the fuselage of an aircraft. Such a quick access door is hinged to one end of the door frame or configured to be completely separated from the door frame, and typically includes a latch that is one of opening and closing devices.

The latch quickly generates a restraint force between the door frame and the quick access door during the locking operation, and the latch portion of the latch plays a role of quickly releasing from the engagement hole of the door frame according to the opening operation of the user.

Such latches include a sliding type in which the clamp is moved in the axial direction when the handle is pulled out, and a push button type in which the clamp rotates at a finite rotation angle along the hinge axis when the opening and locking button is pressed.

Such pushbutton latches are installed in many places on the aircraft body, such as maintenance panels, canopies, covers for engines and devices, and the like.

However, when a general push button latch is installed on a quick access door surface having a geometric streamline shape such as the outside of an aircraft, the horizontal latch and the buttons do not coincide with the contour of the door surface, thereby causing an assembly tolerance, and thus a quick This results in deterioration of the access door quality.

In addition, the general latch may be structurally deformed due to excessive adjustment, even if the assembly process is delayed when the offset is excessively adjusted in the field to eliminate the assembly tolerance.

In addition, the latches used in the aircraft's quick access doors use rivets to fix the protruding parts, such as buttons, to the link sections, so that even a slight shape change in the field is very difficult and the application is very poor. There is this.

In addition, the latches used in the aircraft's quick access doors depend entirely on imports, so that assembling the aircraft has a lot of difficulty in purchasing the latches by type, and in fact, for foreign aircraft design and assembly companies, The situation where the aircraft body and its local parts (such as a quick access door) are designed using the mounting position and the shape as the design factor values.

Therefore, the present invention has been made to solve the problems of the prior art as described above, through a latch structure having a removable button, easy to install and assemble, can freely adjust the amount of deviation in the field, if necessary It is an object of the present invention to provide a latch for a quick access door of an aircraft that maximizes ease of manufacture and applicability by assembling buttons having different shapes to a latch.

1 is a plan view for explaining the configuration of a latch for a quick access door of an aircraft according to an embodiment of the present invention;

Figure 2 is a side cross-sectional view for explaining the coupling relationship of the buttons in the latch for the quick access door of the aircraft shown in FIG.

3 is a side cross-sectional view for explaining the installation relationship of the latch for a quick access door of the aircraft shown in FIG.

4 and 5 are side views for explaining the shape of the buttons used in the present invention.

<Description of Symbols for Main Parts of Drawings>

10: release button 11, 12, 13, 14: button

18: through hole 19, 19 ', 19 ": dish hole

20: lock button portion 30: bracket

40: clasp 51, 52, 53: link section

The object of the present invention described above is to connect the opening and locking button portion and the clasp with the link section supported by the bracket, and after fixing the bracket to the mounting portion of the quick access door, by pressing the opening and locking button portion, the latch is locked in the door frame or A latch for a quick access door of an aircraft to be released, wherein the opening and locking button portions are formed with through holes, and the plate-shaped holes corresponding to the through holes are respectively combined with detachable means. Achieved by a latch for a quick access door.

In addition, according to the present invention, the button is preferably manufactured by thickness and shape type to correspond to the surface of the quick access door having a geometric streamline shape.

Further, according to the present invention, the detachable means is preferably a bolt and nut insertable into the dish-shaped hole.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings.

1 is a plan view for explaining the configuration of the latch for a quick access door of the aircraft according to an embodiment of the present invention, Figure 2 is a side cross-sectional view for explaining the coupling relationship of the button in the latch for a quick access door. . In addition, Figure 3 is a side cross-sectional view for explaining the installation relationship of the quick access door latch, Figures 4 and 5 are side views for explaining the shape of the buttons used in the present invention.

As shown in FIG. 1, a latch for a quick access door of an aircraft according to the present invention includes an opening button portion 10 having a first button 11 having a circular disk shape, and an inner coupling hole of a rectangular bracket 30. The locking button unit 20 has a second button 12 inserted therein. Here, the bracket 30 has a plurality of installation holes 33 are formed in each corner portion to be mounted to the quick access door, the first hinge 31 of the '' 'cross-section integrally on one side end. Is formed. And the latch of this invention arrange | positions the latch part 40 near the opposite side side of the opening button part 10 so that the quick access door may be engaged with the engagement hole of the door frame (not shown) to which the quick access door hinge-engages.

As shown in FIG. 2, each of the button parts 10 and 20 fixes each of the buttons 11 and 12 by using a plate-shaped bolt such as 'NAS1581', which is a detachable means, and a nut corresponding thereto. Here, through-holes 18 are formed in the shaft centers of the button portions 10 and 20, respectively, and the through-holes 18 include countersinks 19 formed in the shaft centers of the buttons 11 and 12, respectively. In agreement, the plate-shaped bolt and nut are fastened through these holes 18 and 19. Therefore, the operator can freely detach and mount the buttons 11 and 12 from the open and lock button portions 10 and 20 using a tightening mechanism such as a screwdriver.

That is, a cramped first link section 51 is formed on the lower surface of the open button part 10 in which the first button 11 can be detachably freely attached to the bolt. The first link section 51 has a 'c' cross-section, while fixing the wide side portion to the lower surface of the open button portion 10 and at the same time hinged to the first hinge 31 of the bracket 30 It is hinged with one side end of the second link section 52 at the vertically bent portion, the bent end is fixed to the lock button portion (20). In addition, the other side end of the second link section 52 is hinged to the third link section 53 of the clasp 40, the vertically bent end of the third link section 53 is a bracket (30) The second hinge 32 of the hinge is hinged. Here, a coil spring (not shown) is provided on the hinge shaft of the second hinge 32, so that the opening and locking button portions 10 and 20 can be quickly rotated to a finite radius by receiving a restoring force. .

The latch for the quick access door of the aircraft of the present invention thus hinged to the bracket 30 with a plurality of link sections 51, 52, 53 has a hinge mechanism that operates as indicated by the arrows in FIG. 3. That is, when the user presses the open button portion 10 with a finger to open the quick access door (F), the open button portion 10 and the first link section 51 based on the first hinge 31. ) Rotates at a finite angle, so that the open button portion 10 is recessed inward of the mounting portion 60 of the quick access door (a), and the lock button portion 20 protrudes outward (b). At the same time, the second link section 52 pulls the third link section 53 so that the clasp 40 rotates about the second hinge 32 (c). Accordingly, the latch portion 40 exits from the engaging hole of the door frame hinged to the quick access door, so that the quick access door can be opened. In addition, when the user presses the lock button 20 to lock the quick access door, the link clauses 51, 52, and 53 operate in a process opposite to that described above.

The latch for the quick access door of the aircraft according to the present invention operated in this way is installed at a position where two button mounting holes 61 and 62 are formed in the mounting portion 60 of the quick access door, as mentioned in the prior art. Likewise, when the mounting portion 60 has a geometric streamline shape, the contour line T does not coincide with the horizontal plane of the latch. In this case, the operator may interpose a filling, such as a compound, in the adhesive site, or adjust the thickness of the adhesive layer so that the surface of the latch and the mounting site 60 is in close contact.

However, the surfaces of the buttons 11 and 12 of the open and lock button portions 10 and 20 and the surface of the mounting portion 60 do not coincide, so that the buttons 11 and 12 are below the contour line T as shown in the drawing. There is a deviation amount when it is recessed, but in order to prevent this, the operator dismantles the bolts directly coupled to the buttons 11 and 12 in the field, and then the first replacement button having a convex cross-sectional shape as shown in FIG. 4. You can adjust the amount of deviation using (13).

In addition, although not shown, when the latch is installed where the surface of the mounting portion 60 is gently bent upward, as shown in FIG. 5 to prevent the edges of the buttons 11 and 12 from protruding. By using the second replacement button 14 having a thin thickness d, the amount of deviation can be adjusted.

The replacement buttons 13 and 14 shown in FIGS. 4 and 5 form dish-shaped holes 19 'and 19 "at the shaft center and are coupled to the opening and locking button portions 10 and 20 with bolts and nuts. Pre-fabricated by thickness and shape type to correspond to the surface of the quick access door having a geometric streamline shape, that is, the replacement buttons 13 and 14 are formed to have a convex shape or a concave shape and a relatively thin or thick thickness. .

In addition, when the deviation amount is small so that the original buttons 11 and 12 can be used without using the second replacement button 14, the operator sands, files, and grinders the separated buttons 11 and 12. By surface-treating, etc., the thickness is reduced locally or as a whole, and then bolted again to complete the installation of the latch.

As described in detail above, the latch for the quick access door of the aircraft according to the present invention bolts the button and the open and lock button to substantially match the surface of the button to match the mounting portion of the quick access door having a geometric streamline shape. It can be freely disassembled and assembled so that the installation of the latch can be done efficiently by using different replacement buttons according to the thickness and shape of the latch. There are advantages to it.

Thus, the latch for the quick access door of the aircraft according to the present invention can be combined by controlling the amount of deviation in the field without changing the parts specifications, by reusing only the surface of the button to suit the purpose, reuse, assembly and assembly of the latch accordingly This has the advantage of reducing the work time.

The technical idea of the latch for the quick access door of the aircraft according to the present invention has been described above with the accompanying drawings, but this is only illustrative of the best embodiment of the present invention and not intended to limit the present invention. In addition, it is obvious that any person skilled in the art can make various modifications and imitations without departing from the scope of the technical idea of the present invention.

Claims (3)

The link sections 51, 52, and 53 supported by the bracket 30 connect the opening and locking button portions 10, 20 and the clasp 40, and the bracket 30 is mounted to the quick access door ( In the latch for the quick access door of the aircraft in which the latch portion 40 is locked or released from the door frame by pressing the opening and locking button portions 10 and 20 after being fixed to Through-holes 18 are formed in the opening and locking button portions 10 and 20, and the plate 11 having plate-shaped holes 19, 19 ', 19 " , 12, 13, 14 latches for quick access doors of the aircraft, characterized in that coupled to the removable means. The method of claim 1, The button (11, 12, 13, 14) is a latch for a quick access door of an aircraft, characterized in that it is manufactured by thickness and shape type to correspond to the surface of the quick access door having a geometric streamline shape. The method of claim 1, And said detachable means is a bolt and nut insertable into said dish-shaped hole (19, 19 ', 19 ").