RU2383851C1 - Hydrid rocket - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: hydrid ballistic cruise rocket (BCR) comprises separable tail part, i.e. ballistic rocket, and warhead. The latter represents a cruise missile (CM) with engine for independent flight towards the target. BCR incorporates rocket engine with its nozzle directed opposite BCR flight. Antiwing with controlled angle of attack is arranged in the nozzle gas flow to change BCR in decelerated descent conditions.

EFFECT: higher efficiency.

1 dwg

Description

The invention relates to designs of combat missiles designed to launch missiles at remote targets and medium-range targets.

Various designs of ballistic and cruise missiles are known, having both certain advantages and the inherent disadvantages of these types of missiles. For example, ballistic missiles are easy to detect and intercept, and cruise missiles have a limited speed.

The objective of the invention is to develop the design of an intercontinental missile and a medium-range missile, which simultaneously has the advantages of both a ballistic and a cruise missile, which will approach the target from the depth of defense at high speed and covertly attack the target on a low flight path.

The required technical result is achieved by the development of the design of a ballistic-cruise missile (BKR), which includes a detachable tail part, providing ballistic flight, and a head part, which is a cruise missile, equipped with, possibly, expanding wings, a stabilizer and its own engine.

Such a missile starts and flies a significant part of the path to the target as a ballistic one, and then, at a given point in the trajectory or when the need arises to evade a missile defense, it goes down.

The missile is reduced by reactive braking using a device in the "wing in front of the nozzle" type. As shown in the drawing, this device contains a rocket engine 1, the nozzle of which is directed against the movement of the rocket, and in front of the nozzle there is a wing 2 with the ability to change the angle of attack.

When exposed to the gas flow of the rocket engine 1 on the wing panel 2, a downward force arises, which puts the hybrid rocket into a braking descent mode. By changing the angle of attack of the wing 2, it is possible to accelerate or slow down the rate of decline, as well as to perform braking during horizontal rocket movement.

At a given height in the dense layers of the atmosphere, the head of the rocket opens its wings and stabilizer and is separated from the tail, continuing the planning decline. After the speed drops to a predetermined value, the winged part of the BKR turns on its own engine and continues flying to the target according to the given program.

A hybrid rocket of the proposed design can carry either one or several devices of the type “wing in front of the nozzle”, with the help of which it can not only decrease, but also gain height by means of the afterburner of the main engine.

If the winged part of a hybrid missile equipped with a nuclear warhead reaches enemy territory, it will be impossible to defend against it.

Claims (1)

A hybrid ballistic-winged missile (BKR) containing a detachable tail, a head part in the form of a cruise missile with an engine for independent movement to the target, a rocket engine, the nozzle of which is directed against the movement of the BKR, and a wing with a controlled angle located in the gas stream of the nozzle of a rocket engine attacks designed to transfer the BKR into a braking decline mode.

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