RU2775903C1 - Method for destruction of underground targets by missiles separated from launch vehicle - Google Patents

Abstract

FIELD: missile guidance systems.

SUBSTANCE: in a defensive and offensive system (hereinafter – DOS), coordinates and sizes of areas of underground target location are received from the outside, a launch vehicle is assigned for missiles with geo-radars, and their data is transmitted to a control station, trajectories and speeds of the launch vehicle and missiles are calculated and transmitted to the control station, where the launch vehicle is launched. On the launch vehicle and missiles, their coordinates and speeds are determined and transmitted via the control station to DOS. On the control station, commands for separation of missiles from the launch vehicle, commands for guidance of the launch vehicle and missiles to areas of target location, and commands for separation of geo-radars from missiles are formed and transmitted to the launch vehicle and missiles. On geo-radars, after landing, their coordinates are determined, targets are detected, coordinates and specific features of targets are determined and transmitted together with coordinates of geo-radars via the control station to DOS, where accurate coordinates and target features are determined. In DOS, the second launch vehicle for missiles is assigned, and their data is transmitted to the control station, coordinates of aiming points for missiles are determined, trajectories and speeds of the second launch vehicle and missiles are calculated and transmitted to the control station, where the second launch vehicle is launched. On the second launch vehicle and missiles, their coordinates and speeds are determined and transmitted via the control station to DOS. On the control station, commands for separation of missiles from the second launch vehicle, and commands for guidance of the second launch vehicle and missiles to targets are formed and transmitted to the launch vehicle and missiles.

EFFECT: increase in the probability of destruction of underground targets with missiles.

1 cl, 1 dwg

Description

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

Known methods of destruction of underground targets missiles, separated from the launch vehicle (RU 2569971; EN 2644962), in each of which take from the outside the coordinates and sizes of areas where underground targets are located; designate a second launch vehicle for delivering missiles to the target area; determine the coordinates of the aiming points for detachable missiles; calculate the trajectory of the flight of the second launch vehicle and detachable missiles to the targets; launching a second booster; on the second launch vehicle and detachable missiles determine their current coordinates; form command separation of missiles from the second launch vehicle; commands are formed to guide the second launch vehicle and the separated missiles to the target along the calculated trajectories.

However, such methods do not provide: - determination of the exact coordinates and characteristics of underground targets, since they do not provide for sounding the areas of their location; - preventing the launch vehicle and missiles from colliding with third-party objects and bypassing the enemy's anti-missile defense zones by the launch vehicle, since they do not take into account information about such objects and zones.

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

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

The proposed method is that:

- in the defensive-offensive system (ONS), the coordinates and sizes of the areas where underground targets are located are taken from the outside;

- in the ONS, the first launch vehicle is assigned to deliver missiles with ground penetrating radars to the area where the targets are located and transmit their data to the control station;

- in the ONS, the trajectories and flight speeds of the first launch vehicle and detachable missiles to the target areas are calculated and transmitted to the control station;

- the first launch vehicle is launched at the control station;

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

- at the control station, teams are formed to separate the missiles from the first launch vehicle and transmit them to the launch vehicle;

- at the control station, commands are formed to guide the first launch vehicle and separated missiles to the area where targets are located along the calculated trajectories with estimated speeds and transmit them to the launch vehicle and missiles;

- at the control station, teams are formed to separate GPRs from missiles separated from the first launch vehicle, and transmit them to the missiles;

- on georadar after landing, their coordinates are determined, targets are detected, coordinates and characteristic features of targets are determined and they are transmitted together with the georadar coordinates through the control station to the ONS;

- in the ONS determine the exact coordinates and characteristics of the targets;

- in the ONS, a second launch vehicle is assigned to deliver missiles to the target area and transmit their data to the control station;

- in the ONS, the coordinates of the aiming points for the detachable missiles are determined;

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

- a second launch vehicle is launched at the control station;

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

- at the control station, teams are formed to separate the missiles from the second launch vehicle and transmit them to the launch vehicle;

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

ONS is similar to the known one (RU 2753498). The goals are similar to those known (RU 2240484). Target location data is received from aerospace reconnaissance equipment. The target area covers all relevant areas.

Launch vehicles, rockets and ground penetrating radars are assigned based on their effectiveness. GPRs are similar to the well-known system (US 7948829) and consist of blocks spaced apart in space, with the help of each of which the coordinates and characteristic features of targets are determined. The exact coordinates and characteristics of targets are determined by analyzing their coordinates and characteristic features determined from different directions to the target using blocks as part of GPR.

The aiming points are located on the ground. The coordinates of the aiming points are determined by analyzing the characteristics of the targets and identifying the most vulnerable places - for effective target engagement.

The coordinates and speeds of launch vehicles and missiles are determined using onboard inertial navigation systems corrected using a global satellite navigation system. Georadar coordinates are determined using the global satellite navigation system.

The trajectories and flight speeds of launch vehicles and missiles are calculated based on the need to prevent their collision with third-party objects and the need for launch vehicles to bypass the enemy’s anti-missile defense areas, as well as on the condition of collision of georadar with the ground and missiles with aiming points at the required angles with the required speeds. Commands for separating rockets from launch vehicles are formed at the beginning of the calculated flight paths of rockets, and commands for separating GPR from rockets are formed at the end of their calculated flight trajectories.

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 - the first launch vehicle with detachable missiles; 4 - missiles separated from the first launch vehicle; 5 - ground penetrating radars separated from missiles; 6 - second launch vehicle with detachable missiles; 7 - rockets separated from the second launch vehicle.

Connections between blocks: 1-2 - data of the first launch vehicle, detachable rockets and georadar, trajectory and flight speed of the first launch vehicle and detachable rockets to target areas, data of the second launch vehicle and detachable rockets, as well as trajectory and flight speed second launch vehicle and detachable missiles to targets; 2-1 - current coordinates and velocities of the first launch vehicle and detachable rockets, current coordinates and velocities of rockets separated from the first launch vehicle, georadar coordinates and coordinates and characteristic features of targets, current coordinates and velocities of the second launch vehicle and detachable rockets, as well as the current coordinates and speeds of the rockets separated from the second launch vehicle; 2-3 - commands for separating missiles from the first launch vehicle, as well as commands for guiding the first launch vehicle to the area where targets are located along the calculated trajectory at the calculated speed; 2-4 - commands for guiding missiles separated from the first launch vehicle to the area where targets are located along the calculated trajectories with calculated speeds, as well as commands for separating georadar from missiles separated from the first launch vehicle; 2-6 - commands for separating missiles from the second launch vehicle, as well as commands for pointing the second launch vehicle at the target along the calculated trajectory at the calculated speed; 2-7 - command guidance missiles, separated from the second launch vehicle, on the target along the estimated trajectories with estimated speeds; 3-2 - current coordinates and speeds of the first launch vehicle and detachable missiles; 4-2 - current coordinates and speeds of rockets separated from the first launch vehicle; 5-2 - georadar coordinates and coordinates and characteristic features of targets; 6-2 - current coordinates and speeds of the second launch vehicle and detachable missiles; 7-2 - current coordinates and speeds of rockets separated from the second launch vehicle; 8-1 - coordinates and sizes of areas where underground targets are located.

Claims (1)

A method for destroying underground targets with missiles separated from a launch vehicle, which consists in taking from the outside the coordinates and sizes of the areas where underground targets are located; designate a second launch vehicle for delivering missiles to the target area; determine the coordinates of the aiming points for detachable missiles; calculate the trajectory of the flight of the second launch vehicle and detachable missiles to the targets; launching a second booster; on the second launch vehicle and detachable missiles determine their current coordinates; form command separation of missiles from the second launch vehicle; form instructions for guiding the second launch vehicle and separated missiles to the target along the calculated trajectories; characterized in that the coordinates and sizes of areas where underground targets are located are taken in the defensive-offensive system (ONS); in the ONS, the first launch vehicle is assigned to deliver missiles with ground-penetrating radars to the area where the targets are located and transmit their data to the control station; in the ONS, the trajectories and flight speeds of the first launch vehicle and the detachable missiles to the areas where the targets are located are calculated and transmitted to the control station; the first launch vehicle is launched at the control station; on the first launch vehicle and detachable missiles, their current coordinates and speeds are determined and transmitted through the control station to the ONS; at the control station, teams are formed to separate the missiles from the first launch vehicle and transmit them to the launch vehicle; at the control station, commands are formed to guide the first launch vehicle and separated missiles to the area where targets are located along the calculated trajectories with estimated speeds and transmit them to the launch vehicle and missiles; at the control station, teams are formed to separate the georadar from the missiles separated from the first launch vehicle, and transmit them to the missiles; on ground penetrating radars after landing, their coordinates are determined, targets are detected, coordinates and characteristic features of targets are determined and they are transmitted together with the georadar coordinates through the control station to the ONS; in the ONS determine the exact coordinates and characteristics of the targets; a second launch vehicle for delivering missiles to the target area is assigned to the ONS and their data is transmitted to the control station; the coordinates of the aiming points for detachable missiles are determined in the ONS; the trajectories, as well as the flight speeds of the second launch vehicle and the detachable missiles to the targets, are calculated in the ONS and transmitted to the control station; the second launch vehicle is launched at the control station; on the second launch vehicle and detachable missiles, their current speeds are also determined and they are transmitted together with the current coordinates through the control station to the ONS; command separation missiles from the second booster form at the control station and transmit them to the booster; commands for guiding the second launch vehicle and the separated missiles to the targets along the calculated trajectories, as well as with the calculated speeds, are formed at the control station and transmitted to the launch vehicle and missiles.

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