RU2470833C1 - Method and appliance for mounting aircraft tail unit front shutter - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to assembling aircraft components, namely to attachment of tail unit to fuselage. On fitting tail unit front shutter in gap between fuselage and tail unit end face, tail unit is set to 0° relative to fuselage to remove panels from end face and to set shutter into said gap. Beforehand, shutter mounts are secured on outer shutter. Rod keys are fitted via through holes and turned through 90° to fit in mount part-through slot to strain the shutter to operating sizes. Thereafter, tail unit detachable panels are mounted along strained shutter to remove rod keys. Proposed appliance comprises mounts and rod keys with articulated spherical surfaces. Note here that said mounts have cruciform openings with one through cutout and one part-through cutout. Rod keys are composed of threaded rods on one end and, on opposite end, of plates with flanges shaped to match through cutouts and spherical surfaces of mounts.

EFFECT: ruled out mechanical damages.

2 cl, 5 dwg

Description

The invention relates to aircraft, in particular to the assembly of structures and assemblies of the aircraft.

The shutters close the structural cutout in the aircraft fuselage under the stabilizer, are made of composite material and operate on the principle of a Belleville spring.

An invention is known in which the fixed edges of the curtain are located on the stabilizer, and the free ones rest on the surface of the fuselage of the aircraft (see patent EP 1834873 A1). When the angle of the stabilizer is changed, the curtains move together with the stabilizer along the surface of the fuselage.

There is a method of installing the front curtain of an airplane stabilizer, in which the elastic properties of the curtain and successive movements of the stabilizer toe up and down are used, fixing the intermediate positions of the curtain relative to the stabilizer using wooden supports, while the curtain gap is gradually filled between the fuselage and the stabilizer end and the curtain is installed in working position. The disadvantages of this method are mechanical damage along the perimeter of the curtain and the end part of the stabilizer toe that occurs when it is installed, low-tech assembly, high labor costs.

The invention is known (see US Pat. No. 6,199,798 B1) for attaching panels to the supporting structure of aircraft, with one fastener being used to absorb the compressive force and the other made in such a way that allows you to remove the mount without the use of additional tools.

The closest solution to the proposed invention is a connecting device (see patent RU 2373107 - prototype) for mounting shields or panels on the supporting structure of the aircraft. The device comprises a latch fixed to a shield or panel, which holds the plug-in pin adjustable to a limited extent. In this case, the receiving device on the supporting structure is made of elastically deformable soft material.

The disadvantage of these solutions is a slight deformation of the elastic panels with little effort. The position of the panels can be adjusted to a limited extent, at least vertically with respect to the surface of the panel. A significant drawback of analogues and prototype are the stringent requirements for a mutually agreed arrangement of the reciprocal parts on the frame and mounted panel.

The main objective of the invention is to propose a method that will allow the installation and dismantling of the front curtain of the aircraft stabilizer and the control of these operations with the exception of mechanical damage to the curtain and the end part of the stabilizer toe, to improve the quality of installation of parts, to reduce labor costs.

Another objective of the invention is to propose a device that allows for significant elastic deformation of the stabilizer curtain by changing the direction of action of the force during compression.

The tasks are solved in that the stabilizer is first set to 0 ° with respect to the fuselage, the panels are removed from the end part of the stabilizer toe and the front curtain in the free state is installed in the gap. Further, using the proposed device, consisting of brackets pre-fixed on the outer surface of the curtain, and the tie rods, each of which is inserted through the through holes in the outer surface of the fuselage, in the blind, through the cross-shaped hole of the bracket, set the tie rod by 90 ° into the blind slot of the bracket and deform the curtain to the working size, then install the removable stabilizer panels and remove the tie rods.

The device for installing the aircraft stabilizer curtain consists of brackets and a thrust key. The bracket has a cross-shaped hole, where one slot is through and the other is not through with the stop surface for the shoulder of the key rod, while the joint surface with the key rod is made in the form of a sphere, and for the possibility of manipulating the rod keys and changing the direction of the force during compression The shutter outlet is made in the form of a truncated cone. The key rod is made at one end in the form of a threaded rod, and at the other end, in the form of a plate with beads having geometric dimensions corresponding to the through slot of the bracket and its spherical surface.

The device and method for installing the front curtain stabilizer is illustrated by the drawings:

figure 1 is a General view of the stabilizer of the aircraft;

figure 2 - front curtain with brackets installed on its surface;

figure 3 is a schematic diagram of the installation of the front curtain using the device (section BB of figure 2);

figure 4 - the design of the device, consisting of an arm and rod-keys and their relative position (node B of figure 2);

5 is a section GG of the device.

The device for installing the front curtain of the airplane stabilizer consists of an arm 6 and a tie rod 7, which have articulated spherical surfaces 12. At the same time, the arm has a cross-shaped hole on one side, in which one slot 9 is through and the other slot 11 is continuous, forming a stop surface for the shoulders 10 of the thrust key 7. On the opposite side, the outlet 13 is made in the form of a truncated cone, and the thrust key 7 is made at one end in the form of a threaded rod, at the other end, in the form of a plate with beads 10 and has geometric dimensions corresponding to the through slot 9 of the bracket and its spherical surface 12.

The installation method of the front curtain stabilizer of the aircraft is carried out using the proposed device as follows:

a) the stabilizer 1 is set at an angle of 0 ° with respect to the fuselage 2;

b) remove the panels 3, 4 from the end part of the toe of the stabilizer 1;

c) install the front curtain 5 in the free state in the gap between the fuselage 2 and the end face of the stabilizer 1;

d) the shutter 5 is elastically deformed using the proposed device, consisting of brackets 6, mounted on the outer surface of the shutter 5 in the area of the internal theoretical contour of the stabilizer 1, and rod keys 7, which are inserted through the through holes 8 in the outer surface of the fuselage 2, in the shutter 5 and through crosswise through slots 9 of the brackets 6;

e) fix the connection using the collars 10 of the tie rod 7 in non-through slots 11 of the brackets 6 by turning the tie rod 7 by 90 °.

It should be borne in mind that the deformation of the front curtain 5 begins with the help of the thunder 14 attached to the threaded part of the tie rods 7, alternately and gradually increasing the load on the tie rods 7 within 10-20 kgf to a maximum (total) force of 500 kgf. After crimping the shutter 5 to the operating state, removable stabilizer panels 1 are installed, which are freely positioned along the contour of the deformed shutter 5, and the tie rods 7 are removed.

Thus, through the use of the present invention, the control and installation quality of the front curtain of the airplane stabilizer is improved, since the possibilities of significant elastic deformation of the curtain of the airplane stabilizer are expanded by changing the direction of the force during compression. This reduces the risk of mechanical damage to the front curtain and the end of the nose of the stabilizer of the aircraft, as well as the opportunity to repeatedly mount and dismantle the front curtain of the stabilizer of the aircraft.

Claims (2)

1. A device for installing the front curtain of the aircraft stabilizer in the gap between the fuselage and the end part of the stabilizer toe, containing brackets and tie rods having articulated spherical surfaces, characterized in that the bracket has a cross-shaped hole on one side, one slot through and the other non-through, forming the stop surface for the collars of the thrust key, while on the opposite side the outlet is made in the form of a truncated cone, and the thrust key is made at one end in the form of a rod with thread, and on the other in the form of a plate with shoulders, and has geometric dimensions corresponding to the through slot of the bracket and its spherical surface. 2. The method of installing the front curtain of the airplane stabilizer, including its elastic compression, characterized in that the stabilizer is first set to 0 ° with respect to the fuselage, the panels are removed from the end part of the stabilizer toe, the front curtain is installed in the free state in the gap and, having previously been fixed to the external curtain, the brackets of the device according to claim 1, by inserting the tie rods through the through holes in the outer surface of the fuselage, as well as the curtain and the cruciform aperture of the bracket, set the tie rod by 90 ° to through the slot of the bracket and deform (compress) the curtain to the working size, then install the stabilizer removable panels, placing them along the contour of the deformed curtain, and remove the key rods.

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