RU2235283C1 - Method to start a guided missile and a guided missile for its realization - Google Patents

Abstract

FIELD: defense industry; production of guided missiles.

SUBSTANCE: the invention is dealt with the field of rocketry and may be used in air-defense guided-missile systems. The invention provides, that the start of a guided missile is conducted by switching on its main jet engine on the launcher. At the moment of departure of the guided missile from the launcher the missile is rotated around of its own center of mass in a plane passing through a target sighting line, at the expense of creation of a lateral pulse by the padding engine. Guidance at a target begins from the moment of registration by the ground control system of radiation from a plume of the missile main jet engine. At that the thrust of the main jet engine to the moment of guidance initiation is magnified up to its peak value. The guided missile is supplied with the padding engine installed so, that its thrust direction should cross the missile longitudinal axis in the point, shifted in respect to the center of the missile masses and with a device to delay actuation of the padding engine, that is electrically connected with the missile guidance control system. The technical result of the invention is an increase of efficiency of fire.

EFFECT: the invention allows to increase efficiency of fire.

2 cl, 2 dwg

Description

The invention relates to rocket technology and can be used in the construction of small-sized rocket shots.

A known method of launching a guided missile (UR) (1), including UR acceleration by a primary thruster with a powder charge from low-smoke fuel, then by the main launch engine to the calculated final speed, and at the end of the operation of the primary launch engine, it is separated from the UR, and the main starting engine is delayed after separation of the primary thruster.

The method is implemented by a rocket equipped with a starting engine, an additional primary starting engine and a separation device for the primary starting engine.

The disadvantages of this launch method and the rocket that implements it are that, before the main starting engine is turned on, the rocket flies at a low speed, has a reduced lateral overload, is sensitive to wind, which leads to large variations in the position of the rocket in space, which increases the time it takes for the rocket to aim at the target, and, as a result, the minimum damage zone of the complex increases, that is, the “shooting efficiency" decreases, which is especially noticeable when shooting at high-speed anti-aircraft targets. The presence of a detachable primary starting engine is a danger to people and equipment located near the launcher. In addition, the primary launch engine increases the dimensions and passive mass of the rocket, which increases the power requirements of the guidance drives of the launcher, complicates the transportation and loading of the rocket to the launcher.

The disadvantages associated with the presence of a detachable primary starting engine are deprived of the method of launching the Medvedka guided missile according to the “mortar” scheme (2), selected as a prototype in which the missile is shot from the container up and aimed at the target, while first deploying the missile into direction to the target with an autonomous compartment of the control system, and then turn on the main rocket engine and direct the rocket to the steering gear.

The method is implemented by a missile equipped with a main rocket engine and an additional autonomous control compartment.

The disadvantage of this method is that the rotation of the rocket towards the target is carried out for a long time, since the rocket flies by inertia at a low speed and has a reduced lateral overload, in addition, the rocket is sensitive to wind, which leads to large variations in the position of the rocket in space, as a result of which the time it takes for the missile to aim at the target increases, which increases the minimum damage zone of the complex, especially when shooting at high-speed anti-aircraft targets. The presence of an autonomous control compartment providing a missile turn in the initial control section is difficult to implement in small guided missiles.

The problem to which the present invention is directed, is to reduce the minimum damage zone of the complex and increase the "firing efficiency".

To solve the problem in the known method of launching a guided missile, including firing a missile from a launcher with a deviation from the line of sight of the target and then pointing the missile at the target, it is new that the main rocket engine is turned on at the launcher at the moment the missile leaves the launcher the rocket is rotated relative to its center of mass in a plane passing through the line of sight of the target due to the creation of a side impulse by an additional engine. A controlled flight starts from the moment of registration of radiation from burning torch gases of the main rocket engine. By the time the control starts, the thrust of the main rocket engine is increased to its maximum value, for example, by choosing the geometric shape of the charge.

This method of launching a guided missile ensures the operation of the control system, since after a missile turn the smoke plume of the engine does not overlap the line of sight of the target and the communication line between the ground control equipment and the missile. The control begins immediately after the rocket’s rotation near the launcher, when the dispersion of the rocket’s position in space is small, in addition, by the time the control starts, the thrust of the main rocket engine is increased to its maximum value, which ensures maximum available lateral overload and minimal sensitivity to the effects of wind, i.e. the proposed method provides a decrease in the minimum damage zone of the complex and a decrease in the guidance time, which is especially important when shooting at high orostnym antiaircraft purposes.

The method is implemented by a guided missile containing control equipment and a main rocket engine, in which the rocket is equipped with an additional engine mounted to provide a thrust direction intersecting the longitudinal axis of the rocket at a point offset from the center of mass of the rocket and a delay device for turning on the additional engine, electrically connected to control equipment.

The invention is illustrated in graphic materials. Figure 1 shows a diagram of firing of UR 1 from the launcher 2, rotation of the UR relative to the center of mass and the passage of the starting portion of the trajectory, explaining the method of launch.

Figure 2 shows a schematic design of the SD that implements the specified method of launch. Guided missile contains a main rocket engine 3, an additional engine 4, a delayed-action beam igniter 5, electrically connected by wires 7 to control equipment 6.

Shooting UR in accordance with the invention is as follows. The launch of SD 1 starts with the main rocket engine 3 being turned on. At the moment the main rocket engine is turned on by a command transmitted from the control equipment 6 via wires 7, a delayed-action beam igniter 5 is turned on, which, after the SD leaves the launcher with a deviation from the target’s line of sight, turns on additional engine 4, generating momentum I. Impulse I, applied to the rocket at a point offset along the longitudinal axis of the SD from its center of mass of the CM, creates a moment M, which rotates the SD relative to its center of mass in the direction enii on target in a plane passing through the line of sight targets. As a result of the rotation of the SD, the plume of smoke from the main rocket engine passes away from the launcher, and ground-based control equipment detects the emission of burning gases from the main rocket engine. From the moment of registration of the radiation of the torch of the main rocket engine, control commands are issued on board the rocket, while by the time the control starts, the thrust of the main rocket engine is increased to its maximum value.

The magnitude of the impulse created by the additional engine, and the shoulder of its application relative to the center of mass of the rocket are selected in each case depending on the size and mass of the rocket, design considerations and are refined by the results of testing.

Thus, the proposed method of launching a guided missile and guided missile for its implementation, provide a decrease in the minimum zone of destruction of the complex and increase the "firing efficiency", which is especially important when shooting at high-speed anti-aircraft targets.

sources of information

1. Patent of the Russian Federation No. 2191985, IPC7 F 42 B 15/10, Bulletin No. 30 of 10.27.2002 - analogue.

2. Magazine “Military Parade” 1999, No. 3, p. 28-29 is a prototype.

Claims (2)

1. A method of launching a guided missile, including firing a missile from a launcher with a deviation from the line of sight of the target and then pointing the missile at the target, characterized in that the launch is made by turning on the main rocket engine on the launcher, at the moment the rocket leaves the launcher, the missile is rotated around own center of mass in the plane passing through the line of sight of the target, due to the creation of a side impulse by an additional engine, and guidance begins from the moment the ground vehicle is registered the control of radiation from the torch of the main rocket engine, while the thrust of the main rocket engine to the beginning of guidance is increased to its maximum value. 2. Guided missile, containing control equipment and a main rocket engine, characterized in that the rocket is equipped with an additional engine installed with a thrust direction intersecting the longitudinal axis of the rocket at a point offset from the center of mass of the rocket and an additional engine start delay device, electrically connected to control equipment.

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