RU2582506C1 - Cantilever folding of aerodynamic surface made of polymer composite material - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to folding aerodynamic surfaces made from composite materials. Cantilever made from polymer composite of folding aerodynamic surface made of black-reinforced plastic or glass fibre and integral circuit, consists from metal bracket and composite box multi-wall structure. Box structure is designed as a monoblock consisting of a closed casing and wall, which is made by vacuum non-autoclave forming within single process stage. Bracket on the side of cantilever attachment is made in the form of a comb with grooves formed by walls connecting mating surfaces of bracket and monoblock extended along the grooves. Arrangement of grooves corresponds to location of walls of the monoblock, which are made to provide free entrance into respective grooves for connection of bracket and monoblock.

EFFECT: higher reliability, accuracy of design, improved aerodynamic characteristics.

1 cl, 2 dwg

Description

The invention relates to the field of aircraft construction, to the folding aerodynamic surfaces of unmanned aerial vehicles (UAVs) or carrier-based aircraft, in particular to aerodynamic surfaces made of composite materials of wings, wing devices and plumage.

The “Integral Wing of Composite Material” is known (patent US 6889937, publication date 05/10/2005, IPC B29C 37/00). The integrated design of the aerodynamic surface, consisting of a casing and spars, which can have different shapes, is obtained due to the joint polymerization of the casing and the spars.

The disadvantage of this analogue is that clumsy wings have large dimensions compared to folding wings, as a result of which an aircraft with clumsy wings requires more space for transportation and storage, and the maneuverability and aerodynamic characteristics of the carrier are impaired.

It is also known "Folding wing of the aircraft" (patent RU No. 2336489, publication date of 12/27/2007, IPC F29B 10/04), which contains a base with a recess, a console and latches. The folding wing is made of metal alloys.

The disadvantage of this technical solution is the large weight of the folding wing of the aircraft, the low manufacturability of the manufacturing process and, therefore, the high complexity.

The closest in technical essence to the claimed technical solution and taken as a prototype is a "folding aerodynamic surface of a polymer composite material" (RU patent for utility model No. 134310, publication date 10.11.2013, IPC F42B 10/14), consisting of a fixed part mounted on the rocket body, the console, the folding mechanism and the fixing means in the unfolded position, and the folding mechanism includes a bracket to which the console is attached using fasteners and plates in the form of plates, installed on the outer surface of the console, while the fairing of the fixed part and the console are made of polymer composite material, the console is made according to the integrated circuit and has a box-shaped multi-wall spar with two power belts and a side rib, and the console is fixed in the folded position by means of a fixing means consisting from a rod molded into the console and a fastener.

The disadvantage of the prototype is the junction of the console and the bracket, which can lead to stress concentrators in the casing due to the fact that there is no fastening of the middle walls with the bracket. As a result of this, destruction of the skin under the heads of the fasteners may occur, which reduces the strength of the connection. In order to strengthen the joint, in this case, fastening is carried out through plates in the form of plates on top of the skin. Obviously, such a solution, in addition to additional details, also creates additional aerodynamic drag. In addition, it is technologically difficult to ensure the repeatability of the specified characteristics of the product, due to changes in the characteristics of the material of the mandrels from temperature and mechanical stress during each technological cycle.

The object of the invention is to increase the reliability of the design and improve aerodynamic characteristics due to the exact execution of the surface profile, excluding stress concentrators and additional aerodynamic drags.

The technical result from the use of the invention is the creation of a reliable, accurate and high-tech console folding aerodynamic surface for aircraft with a large specific load on the wing, with a minimum manufacturing cost and short production cycle, as well as improved aerodynamic characteristics.

The technical result is achieved by the fact that in the console of a folding aerodynamic surface made of a polymer composite material made of carbon fiber or fiberglass and according to an integrated circuit consisting of a metal bracket and a composite box-shaped multi-wall structure, the box-shaped multi-wall structure is made in the form of a monoblock consisting of a closed casing forming contours and perceiving distributed loads and working on transverse and longitudinal bending and torsion, and walls, perceived having cutting force and torsion, which is made by the method of vacuum autoclaveless molding in one technological transition, and the bracket on the side of the console mounting is made in the form of a comb with grooves formed by the walls connecting the elongated surfaces along the grooves of the interface of the bracket with a monoblock, while the location of the grooves corresponds to the location of the walls monoblock, which are made with the possibility of free entry into the corresponding grooves for mounting the bracket with a monoblock, and mounting the monoblock to ronshteynu accomplished by adhesive or kleeklepatelnogo compound monoblock casing with the bracket coupling surfaces, and for load balancing in their connection end surfaces of the walls and grooves monoblock walls are designed as cutouts.

New is:

The proposed technical solution will make it possible to obtain a reliable, high-tech invention by shortening the production cycle, increasing the manufacturability of the manufacturing process and providing a more accurate aerodynamic profile of the console of the folding aerodynamic surface of the polymer composite material by fabricating by vacuum autoclave-free molding in one technological transition, performing the console in the form of a single monoblock parts without expensive equipment.

The present invention will allow the manufacture of a folding aerodynamic surface for aircraft with a large specific load on the wing, with a minimum manufacturing cost and short production cycle, as well as improved aerodynamic characteristics.

The essence of the invention is illustrated by graphic materials:

- in FIG. 1 shows a General view of the console folding aerodynamic surface of a polymer composite material;

- in FIG. 2 shows a longitudinal section of the mounting of the bracket to the monoblock, where:

1 - bracket;

2 - monoblock;

3 - casing;

4 - longitudinal walls;

5 - fasteners.

The folding aerodynamic surface console made of a polymer composite material consists of a bracket 1, a monoblock 2 with a casing 3, longitudinal walls 4 and fasteners 5.

The bracket 1 is part of the folding mechanism of the aircraft and is made on the side of the console mounting in the form of a comb with grooves formed by walls connecting the elongated surfaces along the grooves of the interface between the bracket 1 and the monoblock 2, while the grooves correspond to the location of the walls of the monoblock 2. The mechanism of the folding of the aerodynamic surface on figures not reflected, since in this case it does not matter.

Monoblock 2 made of polymer composite material, carbon fiber reinforced plastic or fiberglass, box-shaped multi-wall construction is made according to the integrated circuit by the method of vacuum autoclave-free molding in one technological transition, which allows it to be performed as a single part without expensive equipment, and consists of closed casing 3, forming contours and receiving distributed load, and working on transverse and longitudinal bending and torsion and walls 4, perceiving shear force and torsion, made with the possibility Iyu free entry into the corresponding grooves for mounting the bracket 1 with a monoblock 2.

The monoblock 2 is mounted on the bracket 1 using fasteners 5 (blind rivets, rivet bolts or bolts). The installation of a monoblock is carried out on a pre-applied adhesive strip on the surface of its interface with the bracket, after it is cured, the connection is made with fasteners 5.

Thus, the proposed technical solution, in comparison with the known analogues, allows you to create a reliable, high-tech console folding aerodynamic surface with a more accurate execution profile, excluding stress concentrators and additional aerodynamic drags. The present invention will allow the manufacture of a folding aerodynamic surface for aircraft with a large specific load on the wing, with a minimum manufacturing cost and short production cycle, as well as improved aerodynamic characteristics.

Claims (1)

Console of a folding aerodynamic surface made of a polymer composite material made of carbon fiber reinforced plastic or fiberglass and integrated circuit consisting of a metal bracket and a composite box-shaped multi-wall structure, characterized in that the box-shaped multi-wall structure is made in the form of a monoblock, consisting of a closed skin forming the contours and receiving distributed loads and working on transverse and longitudinal bending and torsion, and walls perceiving cutting force and torsion, which is made by the method of vacuum autoclaveless molding in one technological transition, and the bracket on the side of the console mounting is made in the form of a comb with grooves formed by walls connecting the elongated along the grooves of the interface surface of the bracket with a monoblock, while the location of the grooves corresponds to the location of the walls of the monoblock, which are made with the possibility of free entry into the corresponding grooves for mounting the bracket with a monoblock, and the monoblock is attached to the bracket with omoschyu adhesive or kleeklepatelnogo compound monoblock casing with the bracket coupling surfaces, and for load balancing in their connection end surfaces of the walls and grooves monoblock walls are designed as cutouts.

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