WO2021015645A1

WO2021015645A1 - Missile

Info

Publication number: WO2021015645A1
Application number: PCT/RU2020/000379
Authority: WO
Inventors: Виктор Валентинович ДОРОНИН; Виктор Владимирович СОКОЛОВСКИЙ; Владимир Григорьевич Светлов; Виктор Алексеевич САМОНОВ; Владимир Сергеевич ФИЛИППОВ; Иван Петрович КИРИЛЛОВ
Original assignee: Акционерное общество "Машиностроительное конструкторское бюро "Факел" имени Академика П.Д. Грушина"; Акционерное общество "Концерн воздушно-космической обороны "Алмаз-Антей"
Priority date: 2019-07-25
Filing date: 2020-07-24
Publication date: 2021-01-28
Also published as: RU2722329C1; CN114467003A

Abstract

The invention relates to missiles having an aerodynamic control system, and can be used in guided missiles, interceptor missiles and ballistic missiles. Missile control efficiency is increased by reducing the effect of downwash on the missile, i.e. reversal of the control rolling moment. The present missile is based on an aerodynamic canard configuration and comprises an airframe. Disposed in the airframe are a propulsion system, a power supply system, a payload, and control system apparatus. Said apparatus contains four aerodynamic fins. Four wings are arranged on the airframe, symmetrically about the longitudinal axis thereof. To reduce the effect of downwash occurring behind the aerodynamic fins and the airframe of the missile during flight at a non-zero angle of attack on the reversal of the control rolling moment and the aerodynamic resistance of the missile as a whole, a unitized wing assembly is used. The latter structurally unites the four wings of the missile into a single assembly. Said assembly is mounted on a ring bearing for movement relative to the airframe of the missile. During flight, the assembly is capable of rotating freely about the reference axis of the missile and allows the wings to self-adjust by virtue of a feathering effect in accordance with the downwash of air behind the aerodynamic fins and the airframe of the missile.

Description

ROCKET

The technical field to which the invention relates

The invention relates to the field of military technology, namely missiles with an aerodynamic "duck" scheme, and can be used in the development of guided missiles, anti-missiles and ballistic missiles.

State of the art

Known designs of missile control and stabilization systems:

- A.V. Karpenko Russian missile weapons 1943-1993, reference book, second edition, SPB, "PIKA", 1993, pp. 135, 145, 146;

- Air Defense Aviation of Russia and Scientific and Technological Progress: Combat Complexes and Systems Yesterday, Today, Tomorrow / ed. E.A. Fedosova, M., Bustard, 2001, pp. 214, 215, 282, 286-290.

- RF patent 2071027, B64G 1/00, publication date: 12/27/1996;

- RF patent 2094748 Cl, B64G 1/00, publication date: 10/27/1997;

- RF patent 2111446 Cl, B64G 1/00, publication date: 20.05.1998;

- RF patent 2114382 Cl, B64G 1/00, publication date: 06/27/1998;

- RF patent 24547 Ul, B64G 1/00, publication date: 10.08. 2002;

- Patent FR 1257614 A, B64G 1/00, publication date: 04/07/1961;

- Patent US 3063375 A, B64G 1/00, publication date: 11/13/1962;

- Patent WO 8100908, B64G 1/00, publication date: 02.04.1981.

A common drawback of these inventions, in our opinion, is the significant flow slope behind the aerodynamic rudders and the rocket body during its flight with a nonzero angle of attack (reverse of the control roll moment) caused by the use of the aerodynamic “duck” scheme.

As a prototype of the invention can be considered the technical solution proposed in the patent of the Russian Federation - Aircraft guided missile, patent JV "RU 2259536 Cl, publication date 27.08.2004. This technical solution includes the use of four fixed wings, four aerodynamic rudders with a large span, tandemly and symmetrically located relative to the longitudinal axis of the rocket on the rocket body, variable sweep along the leading edge and tapered root part, as well as four fixed destabilizers installed in front of the rudders.

According to the developers of this technical solution, the use of destabilizers, which are characterized by low elongation l _{ib T} <0.6, relative area and destabilizing moment, as well as aerodynamic control surfaces with a large span, variable sweep along the leading edge and a narrowed root part (extended end part), does not allow to completely parry the flow slope behind the aerodynamic control surfaces and the rocket body during its flight with a non-zero angle of attack (reverse of the control roll moment), however, it allows maintaining the static stability margin within the required limits at large values of the balancing angle of attack in the entire range of Mach numbers.

The disadvantages of the prototype of the invention are:

- a significant area of additional aerodynamic surfaces, causing additional aerodynamic resistance of the rocket airframe, especially at high angles of attack;

- widened end part of the control surfaces, which increases the value of the end vortices at the edges of the wings and causes additional inductive resistance of the rocket airframe, especially at high angles of attack.

These disadvantages reduce the aerodynamic quality of the rocket airframe, cause a decrease in the rocket flight speed with the same engine thrust.

Disclosure of the essence of the invention.

The essence of the proposed technical solution for the design of the rocket body lies in the fact that four rocket wings are structurally combined into one wing block, which is mounted on an annular bearing movably relative to the rocket body and freely in flight rotates. This allows self-alignment of the wings in accordance with the canted air flow behind the steering surfaces and the rocket body due to the weather vane effect.

The positive effect of the proposed method consists in a significant reduction in the effect on the rocket of the "oblique blowing" moment (reverse of the control roll moment) while maintaining the bearing properties of the rocket in the simplest way without increasing the surface of the body due to additional aerodynamic surfaces.

Implementation of the invention

An example of implementation of the invention is shown in the Figure "Diagram of a device that implements the proposed technical solution", where the numbers indicate:

1. Wing block ring bearing.

2. Block of wings.

Claims

FORMULA

A rocket made according to the aerodynamic "duck" configuration, containing a body, a propulsion system located in it, a power supply system, combat equipment, control system equipment with four aerodynamic rudders, as well as four wings located on the body symmetrically relative to its longitudinal axis, characterized in that to reduce the influence of the flow slope behind the aerodynamic control surfaces and the rocket body during its flight with a non-zero angle of attack on the reverse of the control roll moment and the rocket aerodynamic drag, a single wing block was used as a whole, structurally combining four rocket wings, which is mounted movably on an annular bearing relative to the rocket body and in flight, it is provided with the possibility of free rotation relative to the structural axis of the rocket and self-alignment of the wings due to the weather vane effect in accordance with the canted air flow behind the steering surfaces and the rocket body.