RU191016U1 - CONSTRUCTION LONGERONA - Google Patents

Abstract

The utility model (PM) is related to aviation and can be used as the main structural elements of the power skeleton of the wing and tail unit, especially in small aircraft and in the design of unmanned aerial vehicles. GMH). The technical result is achieved by creating a new form of the spar in the form of a dumbbell in cross section and manufacturing on the basis of polymer composite materials als. 3 il.

Description

The utility model (PM) is related to aviation and can be used as the main structural elements of the power skeleton of the wing and tail unit, especially in small aircraft and in the design of unmanned aerial vehicles.

A common problem of creating elements of the power frame of aircraft (LA) are somewhat contradictory requirements: strength, low specific weight, low cost of the material used, manufacturability and articulation of the side members with other power elements: ribs, stringers, as well as the strength and durability of the structure.

Spar designs are widely known, used in modern aircraft in the form of G, T, P, H and other figurative forms (in cross sections) of which are wood (at the dawn of aviation), steel, duralumin and various alloys.

The power frame of the aircraft is a significant part of its total weight and therefore the reduction in weight is: reduction in fuel consumption, increase in payload, etc.

The technical task of PM is to increase the strength characteristics with a simultaneous decrease in the overall mass characteristics (HMH).

The technical result is achieved by creating a new shape of the spar in the form of a dumbbell in cross section and manufacturing based on polymer composite materials.

To solve this task, a spar design is proposed, characterized in that it has a dumbbell-shaped form in cross section, both ends of which - rods - have a geometric shape of circles interconnected by a coupler, determining the shape of the structure, with the rods made of pultruded glass armature, the partition wall is made of polystyrene foam , and the outer shell is covered with fiberglass.

In the drawing (Fig. 1) shows the design of the spar in isometric with a cut, made by the method of computer graphics, which shows:

1 - spar

2 - spherical endings - longitudinal rods

3 - rods in section

4 - a coupler between the rods in the section

5 - tie between the rods in the longitudinal form

6 - outer shell

The spar is completely made of polymer composite materials on a binder of epoxy resin. It is made by molding (impregnation of individual components with epoxy resin) in a special snap-in (matrices), followed by curing under pressure.

Bending forces in the vertical and horizontal planes assume the rods of fiberglass reinforcement, as well as the outer shell of fiberglass, polystyrene foam serves to fill the free space between the rods and shape the structure. Advantages of the proposed design:

- the design is not afraid of exposure to the external environment (light \ water \ air \ chemistry);

- similar weight with aluminum;

- significantly less than the steel weight;

- sigma is 2-3 times higher than aluminum D16 (maximum permissible bending stress);

- many times greater (as compared with aluminum grade D16) resistance to bending forces (the number of bending cycles is five times greater);

- no need for fasteners to assemble the wing spar.

The proposed design of the spar was developed specifically for the design of the wing of a promising UAV with improved GMH, and most importantly with high aerodynamic quality. The wing blowing in the wind tunnel and the flight tests of the UAV with the new design of the spar and wing showed good results and, as a consequence, the possibility of its use in other UAV designs and in small aircraft.

FIG. 3, a general view of a half-wing without a top plating, as an example of the execution of the power frame of the wing. It shows that the spars are located between the lower and upper profile of the wing along its entire length or part between the ribs, and the wing skins are attached to the top and bottom of the side members and ribs, and the wing console spar is single, and the side members 10 and 11 are double.

The spar 9 is attached to the ribs 18, 19, 20, 21, and the spars 16 and 17 are attached to the ribs 22 and 23.

FIG. 3 shows:

7 - center section;

8 - console;

9 - console flap;

10 - center section flap;

11 - aileron;

12 - console flap diffuser;

13 - center wing flap diffuser;

14 - the rear wall of the console;

15 - console spar;

16-17-spar of the center section;

18-22 - the ribs;

23 - wingtip (winglet);

24 - servos;

25 - flap drive;

26 - tail balkaf.

Thus, the proposed design of the spar, and therefore the wing of the UAV is fully consistent with the economic postulate "cost - efficiency."

Claims (1)

The design of the spar, characterized by the fact that in cross section is a dumbbell shape, both ends of which - rods - have the shape of a geometric circle, interconnected by a coupler, defining the final shape of the structure, and the rods are made of pultruded reinforcement, the coupler is made of expanded polystyrene, and the outer the shell of the spar is covered with fiberglass.

Images