RU2768062C1 - Method for destroying hypersonic maneuvering target by rocket - Google Patents

Abstract

FIELD: missile guidance systems.

SUBSTANCE: invention relates to missile guidance systems, namely to defensive-offensive systems. In a defensive-offensive system (DOS), a target is detected and tracked and its coordinates and speed are determined. In the DOS, the trajectory of the target is determined, relative to which it maneuvers, its continuation is predicted and the coordinates of the place where the missile enters the oncoming course are determined, as well as the missile and the control station are assigned to bring the missile to the oncoming course and destroy the target in the minimum time and transmit the missile data to the control station where the rocket is launched. On the rocket, its coordinates and speed are determined and transmitted, through the control station, to the DOS, where the trajectory and flight speed of the rocket to the point of entry into the oncoming course are calculated and transmitted to the control station, where commands are formed to guide the rocket to the place of entry into the oncoming course and transfer them to the rocket. The DOS determines the current coordinates of the aiming point for the missile, and also calculates the trajectory and speed of the missile to the target and transmits them to the control station, where commands are formed to aim the missile at the target and transmit them to the missile.

EFFECT: invention increases the probability of destroying the target.

1 cl, 1 dwg

Description

The invention relates to missile guidance systems, namely to defensive-offensive systems, and can be used to destroy hypersonic maneuvering targets with missiles.

There is a method of destroying a hypersonic maneuvering target with a rocket (RU 2751378), in which the target is detected and tracked and its current coordinates and speed are determined; launch a rocket; on the rocket determine its current coordinates and speed; calculate the trajectory of the missile to the target; commands are formed to guide the missile to the target along the calculated trajectory.

Closest to the present invention is a method of destroying a hypersonic maneuvering target with a rocket (RU 2741132), in which the target is detected and tracked and its current coordinates and speed are determined; a rocket is launched at the control station; determine the current coordinates and speed of the rocket and transmit them to the control station; calculate the trajectory and speed of the missile to the target; at the control station, commands are formed to aim the missile at the target along the calculated trajectory at the calculated speed and transmit them to the missile.

However, such methods do not provide: - high reliability of detection and tracking of the target and high accuracy of determining its coordinates, since they do not provide for an overview of the target from different directions; - preventing a missile from colliding with third-party objects and bypassing the enemy's anti-missile defense zones by the missile, since they do not take into account information about such objects and zones; - optimization of the direction of the missile's approach to the target, because do not determine the course of its following to bring the rocket to a counter course; - protection of missile guidance from opposition from the target, directed at the missile's homing head.

These shortcomings of the known methods reduce the probability of destroying the target.

The purpose of the invention is to increase the probability of destroying a hypersonic maneuvering target by a missile.

The proposed method is that:

- in the defensive-offensive system (ONS) they detect and accompany the target and determine its current coordinates and speed;

- in the ONS determine the trajectory of the target, relative to which it maneuvers, predict its continuation and determine the current coordinates of the place where the missile enters the oncoming course;

- in the ONS, a missile and a control station are assigned to bring the missile into a collision course and destroy the target in the minimum time and transmit the missile data to the control station;

- a rocket is launched at the control station;

- on the rocket, its current coordinates and speed are determined and transmitted, through the control station, to the ONS;

- in the ONS, the trajectory and speed of the rocket flight to the place of entry into the oncoming course are calculated and transmitted to the control station;

- at the control station, commands are formed to guide the rocket to the place where it enters the oncoming course along the calculated trajectory at the calculated speed and transmit them to the rocket;

- in the ONS, after the missile enters the oncoming course, the current coordinates of the aiming point for the missile are determined;

- in the ONS, the trajectory and speed of the missile to the target are calculated and transmitted to the control station;

- at the control station, commands are formed to aim the missile at the target along the calculated trajectory at the calculated speed and transmit them to the missile.

The well-known method (RU 2753498) is implemented in ONS. The target can be air or space.

The trajectory of the target, relative to which it maneuvers, is determined based on the analysis of its actual trajectory - to determine the course of the target and the launch of the missile on a collision course. The place where the missile enters the oncoming course is chosen on the predicted continuation of the target's trajectory, based on the need to provide the missile with enough time to destroy the target.

A rocket is assigned based on its effectiveness. On a rocket, its coordinates and speed are determined using an onboard inertial navigation system corrected using a global satellite navigation system.

The coordinates of the aiming point for the missile are determined by selecting the most vulnerable spot of the target based on the information obtained by the search and tracking stations as a result of reviewing the target from various directions. Due to the accurate determination of the coordinates and speed of the target, the homing head on the missile is not required.

The missile's trajectory and flight speed are calculated based on the need to prevent its collision with third-party objects, the need for the missile to bypass the enemy's anti-missile defense zones, and the need for the missile to collide with the aiming point at the required angle at the required speed.

The higher the rocket speed, the higher its inertia and lower maneuverability. The ratio of speed and maneuverability for a missile in the final section of the trajectory is optimized by setting the speed necessary and sufficient to destroy the target in a collision.

The proposed method can be implemented in the system, the block diagram of which is shown in the drawing.

Blocks: 1 - ONS; 2 - control station; 3 - a rocket launched from a control station.

Connections between blocks: 1-2 - data of the missile assigned to destroy the target, the estimated trajectory and speed of the missile to the place of entry into the oncoming course, as well as the calculated trajectory and speed of the missile to the target; 2-1 - current coordinates and rocket speed; 2-3 - commands for guiding the missile to the place of entry into the oncoming course along the calculated trajectory at the calculated speed, as well as commands for guiding the missile to the target along the calculated trajectory at the calculated speed; 3-2 - current coordinates and rocket speed.

Claims (1)

A method for destroying a hypersonic maneuvering target with a missile, which consists in detecting and tracking the target and determining its current coordinates and speed; a rocket is launched at the control station; determine the current coordinates and speed of the rocket and transmit them to the control station; calculate the trajectory and speed of the missile to the target; at the control station, commands are formed to guide the missile to the target along the estimated trajectory at the estimated speed and transmit them to the missile; characterized in that the detection and tracking of the target and the determination of its current coordinates and speed are carried out in a defensive-offensive system (ONS); in the ONS determine the trajectory of the target, relative to which it maneuvers, predict its continuation and determine the current coordinates of the exit point of the missile on a collision course; in the ONS, a missile and a control station are assigned to bring the missile into a collision course and destroy the target in the minimum time and transmit the missile data to the control station; the current coordinates and speed of the rocket are determined on the rocket and transmitted from the control station to the ONS; in the ONS calculate the trajectory and speed of the missile to the place of entry into the collision course and transmit them to the control station; at the control station, commands are formed to guide the rocket to the place of exit to the oncoming course along the calculated trajectory at the calculated speed and transmit them to the rocket; in the ONS, after the missile enters the oncoming course, the current coordinates of the aiming point for the missile are determined; the trajectory and speed of the missile to the target are calculated in the ONS and transmitted to the control station.

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