CN114467003A - Missile (missile) - Google Patents

Abstract

The invention relates to a missile with a pneumatic control system, which can be used for guiding missiles, intercepting missiles and ballistic missiles. By reducing the influence of washing on the missile, namely controlling the reversal of the rolling torque, the missile control efficiency is improved. The missile is based on a pneumatic duck-type configuration and comprises a fuselage. Disposed within the fuselage are a propulsion system, a power system, a payload, and a control system arrangement. The device comprises four aerodynamic fins. Four missile wings are arranged on the fuselage and are symmetrically arranged about the longitudinal axis thereof. In order to reduce the influence of the downwash generated at the rear of the pneumatic wing and the body of the missile on the control of the rolling torque reversal and the integral pneumatic resistance of the missile in the non-zero attack angle flight process, the combined missile wing component is used. The missile wing assembly structurally combines four missile wings of a missile into one assembly. The assembly is mounted on an annular bearing for movement relative to the body of the projectile. During flight, the assembly is free to rotate about the missile's reference axis and allows the missile wings to self-align by feathering effects, according to the air wash behind the aerodynamic fins and the missile fuselage.

Description

Missile (missile)

Technical Field

The invention relates to the technical field of military affairs, in particular to a pneumatic missile with a duck-shaped structure, which can be used for developing guided missiles, intercepted missiles and ballistic missiles.

Background

The prior art known in the field of missile control and stabilization systems includes:

-A.V.Karpenko Russian missile weapons 1943-1993,guidebook,second edition,SPB,PIKA,1993,page 135,145,146；

-Air defense aircraft and the progress in science and technology:Integrated combat systems of yesterday,today,tomorrow/edited by E.A.Fedosova,M.,Drofa,2001,pages 214,215,282,286-290.

patent RU 2071027, B64G 1/00, publication No. 27.12.1996;

-patent RU 2094748 c 1, B64G 1/00, kokai ri 27.10.1997;

-patent RU 2111446 c 1, B64G 1/00, kokai ri 20.05.1998;

-patent RU 2114382 c 1, B64G 1/00, kokai ri 27.06.1998;

patent RU 245747U 1, B64G 1/00, published Japanese 10.08.2002;

patent RU 1257614 a, B64G 1/00, publication No. 07.04.1961;

patents US 3063375 a, B64G 1/00, published under No. 13.11.1962;

WO 8100908, B64G 1/00, published on No. 02.04.1981.

In our view, a common disadvantage of these inventions is that during flight, when the angle of attack is not zero (controlling the roll moment reversal), the air behind the aerodynamic wing and projectile body is washed down a significant amount due to the aerodynamic duck configuration used.

As a prototype of the present invention, the technical solution proposed in RF patent No. ru 2259536 c 1 "air sized mission" published 8, 27/2004 may be used. The solution consists of placing on the framework of the missile four fixed fins coupled in series and positioned symmetrically around the longitudinal axis of the missile, four aerodynamic fins of large span, a variable swept-back and narrowed root along the leading edge, and four fixed destabilizers placed in front of the fins.

The developer of this solution believes that the use of a material with a low elongation lambda_detab<0.6, smaller relative surface area and destabilizing moment, large span aero fins, variable sweep back along the leading edge and narrowing root (enlarged tip portion) destabilizers may not completely avoid air wash-down behind aerodynamic fins and projectiles when flying at non-zero angles of attack (controlling the reversal of roll moment), but it allows the required static stability margin to be maintained over the entire mach number range at higher trim angles of attack.

The disadvantages of the invention are:

large additional aerodynamic surfaces, which lead to additional aerodynamic drag of the missile fuselage, especially occurring at high angles of attack;

an enlarged airfoil surface tip portion, which increases the tip vortices at the airfoil tip and leads to additional induced drag of the fuselage, especially occurring at high angles of attack.

The above-mentioned drawbacks reduce the aerodynamic characteristics of the fuselage and reduce the flying speed at the same engine thrust.

Disclosure of Invention

The essential feature of the proposed solution is that the four wings of the missile are structurally combined into one assembly, mounted on an annular bearing, so as to move with respect to the missile fuselage, free to rotate during flight. It allows the missile wing to self-align by feathering effects according to the guiding surface and the down wash of the air stream behind the missile fuselage.

The positive effect of the proposed method is to greatly reduce the impact of the wash-down on the missile (control of the reversal of the roll moment) while maintaining the load-bearing characteristics of the missile in the simplest way, instead of increasing the surface area of the fuselage by adding aerodynamic elements.

Detailed Description

An example of an embodiment of the invention is given in the figure "layout of a device embodying the proposed solution", where

1. Ring bearing of missile wing assembly

2. Missile wing assembly

Indicated by a number.

Claims (1)

1. A missile manufactured according to an aerodynamic canard configuration comprises a body, a propulsion system, a power supply system, a payload and control system device and is provided with four pneumatic wings and four missile wings, wherein the four missile wings are positioned on the body symmetrical to the longitudinal axis of the missile wings.

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