RU118770U1 - Guided Missile Guidance - Google Patents

Abstract

1. A guided missile guidance device containing lenses and series-connected photodetectors, a coordinate selection unit, a command generation unit and a wire communication line, as well as a rudder control device, characterized in that a homing head and a switch are introduced into it, the first input is connected to a wire line communication, the second input - with the information output of the homing head, the control input - with the control output of the homing head, and the output - with the input of the rudder control device. ! 2. A guided missile guidance device according to claim 1, characterized in that it comprises a wire dumping device connected inlet to the control output of the homing head.

Description

The proposed guided missile guidance device relates to the development of missile control systems and can be used in anti-tank missile systems (ATGMs).

Known guidance systems [1, 2], containing a lens placed on the starting device, a radiation photodetector and serially connected coordinate allocation unit, a command generation unit and a wired communication line for transmitting control commands directly to the rocket rudder control device.

Closest to the proposed is a guided missile guidance device described in [3]. This guidance device contains lenses located on the launcher, radiation photodetectors of the onboard radiation source located on the rocket, a coordinate allocation unit of the onboard radiation source located on the rocket, a command generation unit and a wireline for transmitting control commands directly to the rocket rudder control device.

An onboard radiation source is located on one of the wings of the rocket at a fixed distance from its longitudinal axis. The missile rotates around its longitudinal axis during flight. For the coordinates of the rocket in the guidance device, the center of the circle of rotation of the onboard radiation source is taken. The center of the circle is determined by the selected coordinates of the rotating onboard radiation source, along which control commands are generated. Thus, the formation of missile control commands is based on the allocation of coordinates of the onboard radiation source, the radius of rotation of which (the distance from the source to the longitudinal axis of the rocket) has a fixed linear value.

A disadvantage of the known device is that when increasing the distance from the launcher to the missile during its flight, the angular dimensions of the circle of rotation of the onboard radiation source decrease and at ranges of more than 3 km (for the guidance devices under consideration) due to limitations in the resolution of the optical system, the onboard radiation source ceases to stand out as spinning. The inability to isolate the rotation of the onboard radiation source in the guidance devices under consideration makes it impossible to form control commands.

Also, the range of the guidance device limits the threshold sensitivity values of photodetectors, as with increasing distance from the launcher to the rocket, the amount of energy received from the onboard radiation source decreases. When reaching the values of the range at which (depending on the state of transparency of the atmosphere) the received energy becomes less than the threshold for photodetectors, the onboard radiation source ceases to be determined by the guidance device.

In addition, the range of the guidance device is also limited by the length of the wireline.

The objective of the proposed utility model is to develop a guidance device that would increase its range and increase the accuracy of guidance in the final section.

The solution to this problem is achieved by the fact that a homing head and a control signal switch located on the rocket are introduced into the composition of the guidance device. This will increase the range of the guidance device and the accuracy of the guidance in the final section.

The structural diagram of the proposed guided missile guidance device is shown in figure 1.

The guided missile guidance device operates as follows. At the initial guidance site, the input for the guidance device is the angular deviation of the onboard radiation source 1 of the guided missile 2 from the aiming line (as well as in the prototype). The radiation from the on-board source 1 by lenses 3 is focused on the photodetectors 4, the information from which is transmitted to the coordinate allocation unit 5. The coordinates of the on-board radiation source calculated in the coordinate allocation unit 5 are transmitted to the command generation unit 6, where they are converted to missile 2 control signals and via a wireline 7 are transmitted to the switch 8 located on the rocket 2. The rocket control signals from the wireline 7 through the switch 8 are fed to the steering control device 9.

When approaching missile 2 to the target, the target is captured by the homing head 10, which generates its missile control signals. After the formation of control signals begins, the homing head 10 generates a switching signal for the switch 8, through which control signals generated by the homing head 10 are supplied to the rudder control device 9.

In addition, after switching control of the rocket 2 from signals from the homing head 10, it is possible to use a device for resetting the wires 11 of the wireline 7.

Thus, the use of a homing head in the guidance device at the final section of the missile approach to the target allows this section to be independent of the limitations associated with the resolution and sensitivity of the lens-photodetector system and the length of the wired communication line. This, in turn, will increase the range of the guidance device and the accuracy of guidance on the final section of the rocket's approach to the target.

Information sources

1. RF patent No. 2290592 dated 05/03/2005

2. Technical description of the starting device 9P151.00.000 TO. - M.: Military Publishing House of the Ministry of Defense of the USSR, 1992

3. RF patent for utility model No. 95093 of February 25, 2010

Claims (2)

1. Guided missile guidance device containing lenses and series-connected photodetectors, a coordinate allocation unit, a command generation unit and a wired communication line, as well as rudder control device, characterized in that a homing head and a switch are introduced into it, the first input connected to the wired line communication, the second input - with the information output of the homing head, the control input - with the control output of the homing head, and the output - with the input of the steering wheel control device. 2. Guided missile guidance device according to claim 1, characterized in that it comprises a wire reset device connected in input to the control output of the homing head.