CN203848758U - Fairing of missile wing leading edge - Google Patents

Abstract

The utility model relates to a missile wing leading edge structure, in particular to a fairing of a missile wing leading edge and belongs to the field of aviation. The fairing of the missile wing leading edge comprises a left skin and a right skin. The left skin and the right skin are identical in shape and are both in a missile wing chord shape. The left skin and the right skin are respectively provided with a roll welding area. The left skin and the right skin are welded and fixed together in the roll welding areas. Compared with the prior art, the fairing of the missile wing leading edge has the advantages that the forming method is simple, and the fairing can be widely applied to thin-wall structural parts with complicated appearances, especially the parts with the inner cavities in a sharp corner shape.

Description

A kind of missile wing leading edge radome fairing

Technical field

The utility model relates to a kind of missile wing leading edge structure, belongs to aviation field.

Background technology

For reducing in missile flight, missile wing leading edge is subject to the impact of aerodynamic drag, conventionally missile wing leading edge is carried out to rectification and repaiies type, makes it can meet pneumatic requirement, can meet again topology requirement.But missile wing leading edge radome fairing adopts thin-wall boards integrated sheet-metal to be shaped more conventionally, adopt the sheet metal component of this kind of method moulding need to ask part thickness to meet the curved radius of minimum metal plate, but for the aerodynamic configuration part of thinner thickness, particularly inner cavity of component is the thin-wall construction part of wedge angle form, and this kind of method is by inapplicable.

Utility model content

The purpose of this utility model is to solve problems of the prior art, provides a kind of manufacturing process simple, missile wing leading edge radome fairing applied widely.

For achieving the above object, the utility model adopts following technical scheme: a kind of missile wing leading edge radome fairing, and described radome fairing comprises left covering, right covering, left and right covering shape is consistent, is missile wing string shape; On described left and right covering, be respectively arranged with roll welding district, left and right covering is welded and fixed in roll welding district.

This missile wing leading edge radome fairing adopts two and presses the left covering of thin-wall boards missile wing string plane symmetry, that contour shape is consistent, right covering, select welding manner and welding scope that part is welded by loading characteristic, then use component die metal plate forming, after shaping, it is machined to design size and requirement.

Compared with prior art, tool has the following advantages the utility model: manufacturing process is simple, can be widely used in the thin-wall construction part of complex appearance (particularly inner cavity of component is wedge angle form).

Brief description of the drawings

Fig. 1 is the utility model metal plate forming pre-structure schematic diagram;

Fig. 2 is Figure 1A-A view;

Fig. 3 is that Figure 1B is to view;

Fig. 4 is that Fig. 1 C is to view;

Fig. 5 is the utility model structural representation.

Detailed description of the invention

Be further described below in conjunction with Fig. 1-5 pair the utility model: a kind of missile wing leading edge radome fairing, described radome fairing comprises left covering 1, right covering 2, left and right covering shape is consistent, is missile wing string shape; On described left and right covering, be respectively arranged with roll welding district 3,4, left and right covering is welded and fixed in roll welding district.

Concrete processing technology is as follows:

1. according to configuration design requirement, left missile wing leading edge covering 1, right covering 2 materials of missile wing leading edge are carried out to cutting (reserved allowance) by designing requirement;

2. weld along region shown in roll welding district 3,4;

By missile wing leading edge radome fairing mould in the 2nd article soldering part carry out metal plate punching, make it form Xiu Xing district 5 and theoretical profile 6;

4. the part forming in the 3rd article is cut to final design size, part missile wing leading edge radome fairing 7 has been manufactured.

Claims (1)

1. a missile wing leading edge radome fairing, is characterized in that: described radome fairing comprises left covering, right covering, and left and right covering shape is consistent, is missile wing string shape; On described left and right covering, be respectively arranged with roll welding district, left and right covering is welded and fixed in roll welding district.