JPH0237296A - Guided missile system - Google Patents

Abstract

PURPOSE:To guide a missile even if the target is obstructed by a mountain by producing the guide signal in a signal processing device based on the target information, and controlling the guided missile by a control device based on the guide signal. CONSTITUTION:Upon receiving the target reflection signal 18, 9 from a target 3, the front antenna 18 feeds the signals to the front receiver 19. The front receiver 19 detects the coordinates of the target, i.e. the pitch angle and the yaw angle, for instance, when the target 3 is viewed from the guided missile 5. The signal obtained by the receiver 19 is fed to a signal processing device 12. Based on the target information obtained by the front receiver 19, the signal processing device 12 produces the guide signal required for guiding the missile such as the angular speed of the sight line between the guided missile and the target. The output from the signal processing device 12 is fed to a control device 13, and, based on such signal, the control device 13 controls the guided missile 5.

Description

[Detailed description of the invention] [Industrial application field] The present invention relates to a guided spacecraft QSTEM.

More specifically, among the guidance methods for guided vehicles, it is related to the semi-active homing method for surface-to-air guided vehicles [Prior technology] The semi-active homing method for surface-to-air guided vehicles is This is a method in which a radar emits radio waves at a target and a guided flying object receives the reflected radio waves to obtain information about the target and track the target.

[Problem to be solved by the invention]

The semi-active homing method is a system in which radio waves are emitted from a ground radar to a target, and the guided aircraft receives the reflected radio waves. 1.It is a system in which Japan's topography has few plains and many mountains. If the target approaches at low altitude, the radio waves from the ground radar will be blocked by the mountains, making it impossible to irradiate the target Km wave, and the range in which the guided missile can be guided using the semi-active homing method is limited. There were issues such as being exposed.

[Means to solve the problem]

This invention was made in order to solve the problems of the above-mentioned semi-active homing method.

If there is a mountain that blocks the radio waves of ground radars, increase the number of ground radars, install ground radars in the shade, and avoid guided flying objects d′ regardless of the radio waves from any radar.
A frequency selection circuit is installed on the guided flying object so that it can receive certain waves.

It is designed to automatically select frequencies that can be received by guided missiles.

[Effect]

This invention is for installing multiple radars.

Even if a target approaches at low altitude, one of the radars can irradiate the target with radio waves, making it possible to track the target even if it is blocked by mountains.

〔Example〕

FIG. 1 is a diagram showing the operation of the guided flying object system according to the present invention.

(1) is the main radar, and (2) is the auxiliary radar.

In this operational diagram, one auxiliary radar is used, but there may be more than one auxiliary radar, and there is no particular limitation. The auxiliary radar is arranged to supplement the main radar. (3) is the goal, and (4) is the mountain. In the main radar (1), the target (3) is behind the mountain (4) and cannot be detected. However, the auxiliary radar (2)
) The target information obtained by the auxiliary radar (2), which is located in a position unaffected by the radar and capable of detecting the target (3), is sent to the main radar (11).The transmission method can be wireless or wired. But it's not something that's particularly determined.The mountains are an obstacle.

If it is not possible to transmit target information, there is no problem as long as a repeater is installed in the mountains. (6) shows the path of the guided projectile (5). Until the guided missile (5) crosses the mountain, the command signal (
The guided flying object is guided by 8). The command signal (7) is generated based on target information obtained by the auxiliary radar (2). The guided missile (5) crosses the mountain (4) and receives the reference signal (8) from the auxiliary radar (2), and at the same time receives the target reflected wave signal (9) from the auxiliary radar (2), and becomes semi-active. Start homing and continue semi-active homing until meeting the target.

In addition, in the operational diagram of FIG. 1, only the configuration necessary to explain the present invention is described, and of course the fire control device, launcher, communication device, power supply, etc. necessary for the guided missile system are omitted. This is omitted as it is held.

FIG. 2 is a block diagram showing an embodiment of the system according to the present invention. (1) is the main radar, and (2) is the auxiliary radar.

The guided flying object (5) is guided by a command guidance method until semi-active homing becomes possible.

(7) is a command signal transmitted from the king radar (1), and includes target information necessary to guide the guided flying object (5).

(7) is a command antenna, and command signal (7)
Command receiver that receives and sends to command receiver 0■
amplifies the signal sent from the command antenna and at the same time detects the target included in the command signal. The target information obtained by the command receiver is sent to the signal processing device υ. The signal processing device (2) detects a guidance control signal, such as a velocity vector signal, necessary to guide the guided flying object (5), and sends it to the control device side. The signal from the main radar (1) is based on the earth-fixed coordinates, and the control device (to) converts the guidance control signal sent from the signal processing device (2) from the earth-fixed coordinates to the guidance flight. The coordinates are converted to the body's body coordinates, and the guided spacecraft is controlled based on the guidance control signal obtained from the coordinate conversion.

(b) is a reference signal from the main radar (1), and (8) is a reference signal from the auxiliary radar (2). What are the frequencies of the main radar reference signal (b) and the auxiliary radar reference signal (8)?

Different frequencies are used to prevent radar interference. Q
S is a rear antenna which receives the reference signals a4 and (8) and sends them to the rear receiver (to). The rear receiver αe is
At the same time as amplifying the signal sent from the rear antenna,
The frequency of the local oscillator in the rear receiver is set according to a command from a frequency selection circuit aη, which will be described later. rear receiver σ
Q is equipped with an automatic frequency control circuit, so that the output frequency of the rear receiver is the sum of the transmission frequency of the main radar (1) or the transmission frequency of the auxiliary radar (2) plus a certain intermediate frequency. The set frequency selection circuit α7)#'i, 17A is for switching the frequency of the local oscillator of the receiver α, and in the case of the present invention, switching is performed in two stages. That is, the one frequency selection circuit, which is set to the number of switching stages corresponding to the number of radars, is programmed and operates to switch the frequency of the local oscillator of the rear receiver at predetermined intervals.

Due to the above switching operation, the output frequency of the rear receiver QQ becomes a value obtained by adding a certain intermediate frequency to the transmission frequency of the main radar (1).

It may be a value obtained by adding a certain intermediate frequency to the transmission frequency of the auxiliary radar (2).

(g) is a target reflected wave signal from the main radar (1), and (9) is a target reflected wave signal from the auxiliary radar (2). The front antenna (to) receives the target reflected wave signal (to) from the target (3) and (9), and the front receiver (to) receives the target reflected wave signal (to) from the target (3) and (9).
to). The front receiver σ value simultaneously amplifies the signal sent from the front antenna (to).

The target reflected wave signal used is to use the output signal of the rear receiver 00 to detect the pitch angle and yaw angle when the target (3) is viewed from the target coordinate 1 (for example, the guided flying object (5)). , is determined by the output frequency of the rear receiver α0, that is, the command of the frequency selection circuit.

The signal received by the front receiver (6) is sent to the signal processing device UK. The signal processing device @ obtains a guidance signal necessary for guiding the guided vehicle, such as the line-of-sight angular velocity between the guided vehicle and the target, from the target information obtained by the front receiver. The output of the signal processing device is sent to the control device, and the control device (to) controls the guided flying vehicle (5) based on this signal. The signal processing device (2) detects the signal-to-noise ratio of the output of the front receiver Ql, and when the signal-to-noise ratio exceeds a predetermined value, issues a command to the 9 frequency selection circuit αη to stop the frequency switching operation. That is, the use of the main radar (1) or the auxiliary radar (2) is finally determined by the above command.

At the same time, when the signal-to-noise ratio of the output of the front receiver α exceeds a predetermined value, the signal from the command receiver (b) is cut off.

In other words, the command guidance system is switched to the semi-active guidance system.

〔Effect of the invention〕

As described above, according to the present invention, even if the target approaches at low altitude from a mountain cover, the auxiliary radar can irradiate the target with radio waves, so even if the target is blocked by a mountain, Guided missiles can be guided using a semi-active homing method.

[Brief explanation of the drawing]

FIG. 1 is a diagram showing an operational diagram of a guided flying vehicle according to the present invention, and FIG. 2 is a diagram showing an embodiment of the system according to the present invention, in which (1) is a main radar, and (2) is an auxiliary radar. ,
(3) is the target, (4) is the mountain, (5) is the guided projectile,
(6) is the guided missile path, (7) is the command signal, (8) is the reference signal from the auxiliary radar (2), (9) is the target reflected wave signal from the auxiliary radar (to) is the command Antenna, 0 is a command receiver, 0 is a signal processing device, Q3 is a control device, α4 is a reference signal from the main radar (1), and (to) is a rear antenna. (G) is the rear receiver, αη is the frequency selection circuit, (G)
is the front antenna, and the gull is the front receiver.9
In the drawings, the same reference numerals and b indicate corresponding parts.

Claims (1)

[Claims] It has multiple radars consisting of a main radar and one or more auxiliary radars, a command antenna, a command receiver, a rear antenna, a rear receiver, a frequency selection circuit, a front antenna, a front receiver, a signal processing device, and a control device. It consists of guided missiles, and in order to prevent the radio waves of the main radar from being blocked by mountains and being unable to irradiate radio waves to the target, an auxiliary radar is installed behind the mountain, and both the main radar and the auxiliary radar use a semi-active homing method. In order to guide the guided missile, the frequency of the local oscillator in the rear receiver is switched according to instructions from a programmed frequency selection circuit, and either the main radar reference signal or the auxiliary radar reference signal is selected. By sending the signal selected above as a reference signal to the front receiver, the front receiver generates target information from the target signal obtained by the front antenna, and the signal processing device generates a guidance signal from the target information. , a guided spacecraft system in which a guided spacecraft is controlled by a control device based on the above-mentioned guidance signal.