RU2818799C1 - Method of destroying orbital targets by missiles separated from carrier rocket - Google Patents

Abstract

FIELD: ammunition; missile guidance systems.

SUBSTANCE: invention relates to missile guidance systems for destroying orbital targets, such as space debris or satellites. In a defensive-offensive system (DOS), coordinates, speeds and characteristics of targets and characteristics of their orbit are determined, a carrier rocket (CR) with missiles is assigned and CR data is transmitted to a control station (CS), where the CR is launched. In DOS, coordinates of places and angles of collision of missiles with targets are determined. On CR and missiles their coordinates and speeds are determined and transmitted through CS to DOS, where trajectories and speeds of CR and missiles to targets are calculated and transmitted to CS, where commands for separation of missiles from CR are generated and transmitted to CR. On CS, commands for controlling flight of CR and missiles to targets are generated and transmitted to CR and missiles, where targets are fixed after collision with targets. In DOS, flight paths and speeds of missiles with fixed targets into the atmosphere are calculated and transmitted to the CS, where commands for controlling the flight of missiles with fixed targets are generated and transmitted to the missiles. On CS, commands for detonation of missile warheads with fixed targets in atmosphere are generated and transmitted to missiles.

EFFECT: high probability of destroying orbital targets.

1 cl, 1 dwg

Description

The invention relates to missile guidance systems, namely defensive-offensive systems, and can be used to destroy groups of orbital targets by lowering them into the atmosphere in groups of missiles separated from the launch vehicles and detonating warheads.

The closest to the proposed method is the method of destroying orbital targets with rockets separated from the launch vehicle (RU 2678392), where orbital targets are detected and tracked and their current coordinates are determined; assign a launch vehicle (LV) with missiles to lower targets into the atmosphere; at the control station (CS) the launch vehicle is launched; determine the current coordinates of missile-target collision sites; on the launch vehicle and detachable missiles, their current coordinates are determined and transmitted to the control system; at the control center, commands are formed for separating missiles from the launch vehicle and transmitting them to the launch vehicle; at the control system, commands are formed to control the flight of the launch vehicle and separated missiles to targets and transmit them to the launch vehicle and separated missiles; on missiles, after collision with targets, targets are fixed; At the control system, commands are formed to control the flight of missiles with assigned targets into the atmosphere and transmit them to the missiles.

However, this method does not provide: high reliability of target detection and tracking and high accuracy in determining their coordinates, as well as optimization of the choice of missile-target collision sites, because does not provide for an overview of targets and their area from various directions and determination of the characteristics of targets; preventing missiles from colliding with third-party objects and bypassing missile defense zones of the enemy, because does not take into account information about such objects and zones; optimization of missile approach to targets, because does not provide for determining the speeds of targets and the characteristics of their orbit, as well as calculating the trajectories and speeds of missiles; protection from targets impacting missile sensors.

These shortcomings reduce the likelihood of targets being destroyed.

The purpose of the invention is to increase the likelihood of destroying orbital targets.

The proposed method is that:

- in a defensive-offensive system (ODS), they detect and track orbital targets and determine the current coordinates and velocities of targets, as well as the characteristics of targets and their orbit;

- the ONS assigns a launch vehicle with missiles, as well as a control system, for lowering targets into the atmosphere and transmits the data from the launch vehicle to the control system;

- the launch vehicle is launched on the control system;

- in the ONS, the current coordinates of places and angles of collision of missiles with targets are determined;

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

- the ONS calculates the trajectories and flight speeds of launch vehicles and detachable missiles to targets and transmits them to the control system;

- commands are generated at the control system for separating missiles from the launch vehicle at the beginning of the design trajectories and transmit them to the launch vehicle;

- at the control system, commands are formed to control the flight of the launch vehicle and separated missiles to targets along calculated trajectories with design speeds and transmit them to the launch vehicle and separated missiles;

- targets are fixed on missiles after collision with targets;

- the ONS calculates the trajectories and flight speeds of missiles with assigned targets into the atmosphere and transmits them to the control system;

- at the control system, commands are formed to control the flight of missiles with fixed targets into the atmosphere along calculated trajectories with calculated speeds and transmit them to the missiles;

- at the control center, teams are formed to detonate warheads of missiles with fixed targets at the end of the calculated trajectories and transmit them to the missiles.

ONS is similar to the well-known one (RU 2753498). The targets could be satellites or large objects of space debris. The coordinates and velocities of targets are determined as a result of their viewing from various directions, and the characteristics of targets and their orbits are determined as a result of target tracking.

The locations and angles of collision of missiles with targets are selected from the condition of the passage of the missile axes through the expected centers of mass of the targets in accordance with their characteristics. In the case of using several missiles to destroy one target, the locations and angles of collision of the missiles with the target are chosen so that the axes of the missiles are parallel, and the impact of the missiles on the target does not create a torque.

The coordinates and speeds of launch vehicles and missiles are determined in on-board inertial navigation systems, corrected using a global satellite navigation system. The trajectories and flight speeds of launch vehicles and missiles towards targets are calculated from the condition that they bypass third-party objects and, if possible, the enemy’s missile defense coverage zones, as well as from the condition of missiles colliding with targets at the required angles with the required speeds.

After the missiles are separated from the launch vehicle, the redistribution of targets between them is carried out by adjusting the calculated trajectories and speeds of the missiles. The higher the speed of the missiles, the higher their inertia and the lower their maneuverability. The ratio of speed and maneuverability for missiles in the final part of their trajectories is optimized by setting the speeds necessary and sufficient to secure targets on the missiles after a collision. Attachment of targets is accomplished by plunging a pin on the nose of the missiles into the targets or by gluing missiles without a nose cone to the targets.

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

Blocks: 1 - ONS; 2 - SU; 3 - launch vehicle with detachable missiles; 4 - missiles separated from the launch vehicle.

Connections between blocks: 1-2 - data on launch vehicles with detachable missiles, calculated trajectories and flight speeds of launch vehicles and detachable missiles to targets, calculated trajectories and flight speeds of missiles with fixed targets into the atmosphere; 2-1 - current coordinates and velocities of launch vehicles and missiles; 2-3 - commands for separation of missiles from the launch vehicle at the beginning of the design trajectories, commands for controlling the flight of the launch vehicle to targets along the design trajectory at the design speed; 2-4 - commands for controlling the flight of separated missiles to targets along calculated trajectories with calculated speeds, commands for controlling the flight of missiles with fixed targets into the atmosphere along calculated trajectories with calculated speeds, commands for detonating warheads of missiles with fixed targets at the end of the calculated trajectories; 3-2 - current coordinates and velocities of the launch vehicle and detachable missiles; 4-2 - current coordinates and velocities of separated missiles.

Claims (1)

A method for destroying orbital targets by rockets separated from the launch vehicle, which consists in detecting and tracking orbital targets and determining their current coordinates; assign a launch vehicle (LV) with missiles to lower targets into the atmosphere; at the control station (CS) the launch vehicle is launched; determine the current coordinates of missile-target collision sites; on the launch vehicle and detachable missiles, their current coordinates are determined and transmitted to the control system; at the control center, commands are formed for separating missiles from the launch vehicle and transmitting them to the launch vehicle; at the control system, commands are formed to control the flight of the launch vehicle and separated missiles to targets and transmit them to the launch vehicle and separated missiles; on missiles, after colliding with targets, targets are fixed; at the control system, commands are formed to control the flight of missiles with assigned targets into the atmosphere and transmit them to the missiles; characterized in that in a defensive-offensive system (ONS) orbital targets are detected and tracked and the current coordinates and velocities of targets are determined, as well as the characteristics of targets and their orbits; The RN, as well as the control system, are assigned to the ONS and transmit the RN data to the control system; coordinates of places, as well as angles, collisions of missiles with targets are determined in the ONS; on launch vehicles and missiles, their current speeds are also determined and transmitted along with coordinates through the control system to the ONS; in the ONS they calculate the trajectories and flight speeds of launch vehicles and detachable missiles to targets and transmit them to the control system; commands for separating missiles from the launch vehicle are formed on the control system at the beginning of the design trajectories; commands are generated at the control system to control the flight of launch vehicles and missiles along calculated trajectories with calculated speeds; in the ONS they calculate the trajectories and flight speeds of missiles with assigned targets into the atmosphere and transmit them to the control system; commands are formed on the control system to control the flight of missiles with fixed targets along calculated trajectories with calculated speeds; on the control control commands are formed to detonate warheads of missiles with fixed targets at the end of the calculated trajectories and transmit them to the missiles.

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