RU2777874C1 - Method for destruction of hypersonic maneuvering targets with missiles separated from the launch vehicle - Google Patents

Abstract

FIELD: military technology.

SUBSTANCE: the invention relates to missile guidance systems. In the defensive-offensive system (ONS), the coordinates and speeds of targets are determined, as well as the trajectory relative to which they maneuver, predict its continuation and determine the coordinates of the place where the launch vehicle enters the oncoming course, designate the launch vehicle and transmit its data to the control station, where the launch vehicle is launched. On the launch vehicle and the separated missiles, their coordinates and speeds are determined and transmitted through the control station to the ONS, where the trajectory and flight speed of the launch vehicle to the point of entry into the oncoming course are calculated and transmitted to the control station, where the launch vehicle guidance commands are formed and transfer them to the launch vehicle. The ONS determines the coordinates of the aiming points for the detachable missiles, and also calculates the trajectories and flight speeds of the launch vehicle and the detachable missiles to the targets and transmits them to the control station, where commands are formed to separate the missiles from the launch vehicle and transmit them to the launch vehicle, and as well as commands to guide the launch vehicle and the separated missiles to the target and transmit them to the launch vehicle and the separated missiles.

EFFECT: the method provides an increase in the probability of destroying targets.

1 cl, 1 dwg

Description

SUBSTANCE: invention relates to missile guidance systems, namely to defensive-offensive systems, and can be used to destroy group hypersonic maneuvering targets by groups of missiles separated from launch vehicles.

A known method of destruction of hypersonic maneuvering targets missiles, separated from the launch vehicle (US 8371201), which detect and accompany targets and determine their current coordinates; a launch vehicle is launched at the control station; on the carrier rocket and detachable rockets, their current coordinates are determined; calculate the flight paths of the separated missiles to the targets; command is formed to separate the missiles from the launch vehicle at the beginning of the calculated trajectories of their flight; commands are formed to point the separated missiles at the targets along the calculated trajectories and transmit them to the separated missiles.

Closest to the present invention is a method of destroying hypersonic maneuvering targets with missiles separated from the launch vehicle (US 7494089), in which targets are detected and tracked and their current coordinates are determined; a launch vehicle is launched at the control station; on the carrier rocket and detachable rockets, their current coordinates are determined; determine the current coordinates of the aiming points for detachable missiles; calculate the flight paths of the separated missiles to the targets; command is formed to separate the missiles from the launch vehicle at the beginning of the calculated trajectories of their flight; commands are formed to point the separated missiles at the targets along the calculated trajectories and transmit them to the separated missiles.

However, such methods do not provide: - high reliability of detection and tracking of targets and high accuracy of determining their coordinates, since they do not provide for an overview of targets and their location from different directions; - preventing missiles from colliding with third-party objects and bypassing enemy missile defense zones by missiles, since they do not take into account information about such objects and zones; - optimization of the direction of approach of the launch vehicle to the targets, because do not determine the course of their following to bring the launch vehicle into a collision course; - optimization of the ratio of speed and maneuverability for missiles, since they do not take into account the speed of missiles and targets; - protection of missile guidance from counteraction from targets directed at missile homing heads.

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

The purpose of the invention is to increase the probability of destroying hypersonic maneuvering targets with missiles.

The proposed method is that:

- in the defensive-offensive system (ONS) they detect and accompany targets and determine their current coordinates and speeds;

- in the ONS they determine the trajectory of the targets, relative to which they maneuver, predict its continuation and determine the current coordinates of the place where the launch vehicle enters the oncoming course;

- in the ONS, a launch vehicle and a control station are assigned to bring the launch vehicle into a collision course and destroy targets in the minimum time and transmit the data of the launch vehicle to the control station;

- a launch vehicle is launched at the control station;

- on the launch vehicle and detachable missiles, their current coordinates and speeds are determined and transmitted, through the control station, to the ONS;

- in the ONS, the trajectory and speed of the launch vehicle 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 launch vehicle to the place of exit to the oncoming course along the estimated trajectory at the estimated speed and transmit them to the launch vehicle;

- in the ONS, after the launch vehicle enters the oncoming course, the current coordinates of the aiming points for the detachable missiles are determined;

- in the ONS, the trajectories and flight speeds of the launch vehicle and the missiles to be separated to the targets are calculated and transmitted to the control station;

- at the control station, teams form the separation of missiles from the launch vehicle at the beginning of the calculated trajectories of their flight and transmit them to the launch vehicle;

- at the control station, commands are formed to guide the launch vehicle and separated missiles to targets along the calculated trajectories with calculated speeds and transmit them to the launch vehicle and separated missiles.

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

The trajectory of the targets, relative to which they maneuver, is determined on the basis of an analysis of their actual trajectories - to determine the course of the targets and bring the launch vehicle into a collision course. The place where the launch vehicle enters the oncoming course is chosen on the predicted continuation of the target trajectory, based on the need to provide the launch vehicle with sufficient time to separate the missiles and destroy the targets.

The launch vehicle is assigned based on its effectiveness. On the launch vehicle and missiles, their coordinates and speeds are determined using onboard inertial navigation systems, corrected using the global satellite navigation system.

The coordinates of aiming points for missiles are determined by selecting the most vulnerable target locations based on information obtained from search and tracking stations as a result of reviewing targets and their area from various directions. Due to the accurate determination of the coordinates and speeds of targets, homing heads on missiles are not required.

The trajectories and flight speeds of the launch vehicle and missiles are calculated based on the need to prevent their collision with third-party objects and with each other, the need for the launch vehicle to bypass the enemy's anti-missile defense areas and the need for missiles to collide with aiming points at the required angles at the required speeds.

The higher the speed of missiles, the higher their inertia and lower maneuverability. The ratio of speed and maneuverability for missiles in the final sections of the trajectories is optimized by setting the speeds necessary and sufficient to destroy targets in a collision.

Commands for the separation of missiles from the launch vehicle are formed when the coordinates of the missiles coincide with the coordinates of the beginning of the calculated trajectories of their flight.

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 - launch vehicle with detachable missiles launched from a control station; 4 - rockets separated from the launch vehicle.

Connections between blocks: 1-2 - data of the launch vehicle assigned to destroy targets, the estimated trajectory and flight speed of the launch vehicle to the place of entry into the oncoming course, as well as the calculated trajectories and flight speeds of the launch vehicle and detachable missiles to the targets; 2-1 - current coordinates and velocities of the launch vehicle and rockets to be separated; 2-3 - commands for guiding the launch vehicle to the place of entry into a collision course along the calculated trajectory at the calculated speed, commands for separating missiles from the launch vehicle at the beginning of the calculated trajectories of their flight, as well as commands for guiding the launch vehicle with detachable missiles at the target according to the calculated trajectories with estimated speed; 2-4 - commands for guiding missiles separated from the launch vehicle to targets along calculated trajectories with estimated speeds; 3-2 - current coordinates and speed of the launch vehicle with detachable missiles; 4-2 - current coordinates and speeds of rockets separated from the launch vehicle.

Claims (1)

A method for destroying hypersonic maneuvering targets with missiles separated from a launch vehicle, which consists in detecting and tracking targets and determining their current coordinates; a launch vehicle is launched at the control station; on the carrier rocket and detachable rockets, their current coordinates are determined; determine the current coordinates of the aiming points for detachable missiles; calculate the flight paths of the separated missiles to the targets; command is formed to separate the missiles from the launch vehicle at the beginning of the calculated trajectories of their flight; form commands to guide the separated missiles to the target along the calculated trajectories and transmit them to the separated missiles; characterized in that the detection and tracking of targets and the determination of their current coordinates are carried out in a defensive-offensive system (ONS), in which the current speeds of targets are also determined; in the ONS determine the trajectory of the targets, relative to which they maneuver, predict its continuation and determine the current coordinates of the place where the launch vehicle enters the oncoming course; in the ONS, a launch vehicle and a control station are assigned to launch the launch vehicle on a collision course and destroy targets in the minimum time and transmit the data of the launch vehicle to the control station; on the launch vehicle and the missiles to be separated, their current speeds are also determined and they are transmitted, together with the current coordinates of the launch vehicle and the missiles to be separated, through the control station, to the ONS; in the ONS, the trajectory and speed of the launch vehicle 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 launch vehicle to the place of exit to the oncoming course along the estimated trajectory at the estimated speed and transmit them to the launch vehicle; the current coordinates of the aiming points for the detachable missiles are determined in the ONS, after the launch vehicle enters the oncoming course; the flight trajectories of the separated missiles to the targets are calculated in the ONS, in which the flight speeds of the separated missiles to the targets and the trajectory and flight speed of the launch vehicle to the targets are also calculated and transmitted together with the flight trajectories of the separated missiles to the targets to the control station; command separation of missiles from the launch vehicle at the beginning of the calculated trajectories of their flight form at the control station and transmit them to the launch vehicle; commands for aiming separated missiles at targets along calculated trajectories are formed at the control station, which takes into account the estimated speeds of separated missiles, and also generate commands for aiming the launch vehicle at targets along the calculated trajectory at the calculated speed and transmit them to the launch vehicle.

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