RU-2861456-C2 - AIRCRAFT WING WITH INTERNAL TANK CONSISTING OF SYSTEM OF INTERCONNECTED PIPES

Abstract

FIELD: unmanned aerial vehicles. SUBSTANCE: straight-planform aircraft wing consists of wing consoles comprising a front spar (3) and a rear spar (4), attachment points to the fuselage, a set of ribs, foam inserts (10) filling the space between the ribs (11, 12, 13, 14, 15, 16, 17), a rigid skin made of fibreglass. The fuel tank is a closed sealed system of interconnected rigid pipes (7, 8, 9). EFFECT: simplifying wing manufacture. 1 cl, 2 dwg

Inventors

• Brezgin Georgii Dmitrievich

Dates

Publication Date

20260505

Application Date

20240831

Claims (1)

1. A straight-plan aircraft wing consisting of left and right wing consoles constructed using a spar design, each of which contains front and rear spars, attachment points to the fuselage, a set of ribs, foam inserts filling the space between the ribs, a rigid skin made of fiberglass, a flap, an aileron, while each of the consoles contains an internal tank, characterized in that the tank is a closed, sealed system of rigid pipes connected to each other.

Description

Field of technology to which the invention relates The invention relates to the field of aircraft engineering, namely to the design of unmanned aerial vehicles of the aircraft type and can be used in the design of the wing of an unmanned aircraft for aerial chemical work (aerochemical work). State of the art The prior art discloses a swept-back aircraft wing comprising a center section, integral and detachable cantilever wing sections (see M.N. Shulzhenko's book "Aircraft Design," Mashinostroenie, Moscow, 1971, pp. 78-81), comprising a power frame with load-bearing spars and ribs that together form a torsion box with thin stringerless skins (see ibid., p. 80, Fig. 2.23). The disadvantages of the technical solutions for such a wing and its power parts include the increased material and labor intensity of manufacturing the structural components, the low inherent rigidity of the wing skins, which is fraught with increased damage in the form of local dents during operation, and increased difficulties in servicing the aircraft wing during repair operations. The prior art includes a known aircraft wing design comprising a box-shaped frame with sets of load-bearing elements and skin panels, consisting of a root and tip section, the latter of which are made of a laminated composite material (see patent RU 2191137, B64C, published October 20, 2002). The disadvantages of this technical solution include the wing's poor technical, economic, and operational performance. The closest analogue of the claimed invention is a high-speed swept wing device, see the publication of the Russian Federation patent for invention No. 2384472, IPCB64C39/00, B64C 3/10, B64D 37/04, published 20.03.2010. The known device consists of a center section, right and left wing consoles, each of which is made up of six parts and formed as a single spatial system based on a non-planar median surface, wherein the wing contains fuel tanks located in the center section and the wing consoles, made with a positive angle of the transverse V and including front and rear spars provided with cutouts and walls located in the center section parallel to the spars, a skin with its upper and lower parts, ribs of the wing consoles, some of which are made sealed, while in the center section there is a central fuel tank, limited by the front and rear spars and side ribs and divided by the walls of the center section into compartments, and two groups of fuel tanks located in the wing consoles, limited by the front and rear spars, lower and upper skins and separated from each other by sealed ribs, wherein each group of tanks includes a first fuel tank separated from the central fuel tank by an onboard rib, a second fuel tank located on the periphery of the wing consoles, a third fuel tank located between the first and second fuel tanks and divided into a main compartment and a service compartment, wherein one of the walls of the service compartment is combined with a rib separating the third fuel tank from the first fuel tank, the second wall of the service compartment is combined with the wall of the rear spar, and in the upper parts of the walls separating the service compartments from the main compartments of the third fuel tanks, and in the upper parts of the ribs separating the main compartments of the third tanks from the second, slots are made, wherein a stringer of a closed U-shaped cross-section is included in the longitudinal power set of each console, hermetically connected to the upper part of the wing skin, and the internal cavity of the said stringer is connected to the internal cavities of the first and second fuel tanks, in addition, each group of fuel tanks is equipped with Overflow channels that allow fuel to flow from the primary fuel tanks to the central fuel tank. The disadvantages of the closest analogue to the proposed invention include poor technical, economic, and operational performance. The essence of the invention The problem solved by the claimed invention is to develop and improve the design of a wing containing various tanks for unmanned aircraft, to reduce its weight, to improve the manufacturability of the wing and to simplify its assembly using semi-industrial technology. The technical result of the claimed invention consists in lightening the wing structure and simplifying its manufacture in semi-industrial pilot production conditions. The technical result of the claimed invention is achieved due to the fact that the straight-in-plan wing of the aircraft, consisting of the left and right wing consoles, made according to the spar scheme, each of which contains the front and rear spars, attachment points to the fuselage, a set of ribs, foam inserts filling the space between the ribs, a rigid skin made of two layers of fiberglass impregnated with epoxy resin, with the orientation of the fibers along the wing span and at 45 degrees with respect to the chord of the wing, a flap and an aileron, contains reservoirs with liquid, which are