JPS6318118B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a guided missile that detects infrared rays or reflected signals generated from a target and captures and tracks the target. First, the conventional guided missile M
I will briefly explain about. In Fig. 1, M is a guided missile, 1 is a target captured and tracked by guided missile M, 2 is an infrared ray or reflected signal generated from target 1 (hereinafter collectively referred to as "signal"), and 3 is a signal 2 from target 1. 4 is a receiving device that extracts the target signal from the signal received by the antenna 3; 5 is an EL error signal generation circuit that extracts the EL error signal from the target signal output from the receiving device 4; 6 is the output of the receiving device 4. 7 is an AZ error signal generation circuit which extracts an AZ error signal from a target signal of An antenna servo device 8 drives the guided missile M in the arrival direction of the signal 2 using the EL error signal output from the EL error signal generation circuit 5 and the AZ error signal output from the AZ error signal generation circuit 6. A steering device for steering in the direction of the rendezvous point, 9 a lower side antenna for receiving a signal 2 from the target 1 when the guided missile M passes near the upper side of the target 1, and 10 a lower side antenna for receiving the signal 2 from the target 1 when the guided missile M passes near the lower side of the target 1; 11 is an upper side antenna that receives signal 2 from target 1 when the guided missile M passes near the right side of target 1; 12 is a left side antenna that receives signal 2 from target 1 when guided missile M passes near the right side of target 1; A right side antenna 13 receives the signal 2 from the target 1 when passing near the left side of the target 1, and 13 is a target signal output from the receiving device 4 and a lower side antenna 9 or an upper side antenna 10 or a left side antenna 11 or the right side. a proximity fuze circuit 14 that generates a proximity detonation pulse when the guided missile M passes near the target 1 based on the signal 2 from the target 1 received by the antenna 12;
Reference numeral 15 indicates an arrival tube that generates an arrival detonation pulse when the guided missile M directly hits target 1, and 15 a proximity detonation pulse output from the proximity fuze circuit 13 or an arrival detonation pulse output from the arrival tube 14. A detonation signal generation circuit 16 generates a detonation signal that detonates the ammunition 16 when the guided missile M passes near the target 1 or hits the target 1 directly. The ammunition 17 that destroys the guided missile M is a power source that supplies power to each component of the guided missile M, and 18 is a propulsion device that provides thrust to the guided missile M. The conventional guided missile M is configured as described above, and is guided toward the meeting point with the target 1, and when the guided missile M finally passes near the target 1 or hits the target 1 directly, the ammunition 16 is detonated and the target 1 is detonated. The purpose is to inflict great damage on the target and shoot it down.

However, in the conventional guided missile M, when the meeting point with the target 1 is low in the sky, the signal from the ground is received by the lower side antenna 9, so if the signal level from the ground is high, the proximity fuse circuit 13 receives the proximity detonation pulse. As a result, the guided missile M detonates at an early stage when the ammunition 16 detonates before reaching the meeting point with the target 1, which hinders the ability of the guided missile M to shoot down the target 1. Particularly in recent years, there has been a strong desire to improve the ability of guided missiles to shoot down targets 1 at low altitudes.
The above drawbacks have become important issues. This invention is characterized by improving the above-mentioned drawbacks, and the outputs of the receiving device 4 and the EL error signal generating circuit 5 are inputted to newly provided components to be described later.
To reach a target 1 at a low altitude of M' and correct the route passing near the target 1 so as to always hit the target 1 directly or pass below the target 1, and control the reception signal received by the lower side antenna 9. guided missiles by preventing proximity detonation pulses from occurring even when the signal level from the ground is high.
This prevents the early detonation of M' and improves the ability of guided missile M' to shoot down target 1.

The guided missile M' of the present invention will be explained below with reference to FIG. 2, which is a specific example.

In FIG. 2, 1 to 18 are the same as in FIG. 19 to 25 are devices newly added to FIG. 1; 19 is a clutter level detection circuit that extracts the signal level from the ground from the output of the receiving device 4;
20 determines whether the signal level from the ground of the output of the clutter level detection circuit 19 exceeds an arbitrarily set level; if it exceeds the set level, a high level signal is sent; if not, a low level signal is sent. The comparator circuits 1 and 21 output the guided missile M and the target 1 from the output of the receiving device 4 and the output of the steering device 8.
An expected meeting altitude extraction circuit 22 extracts a meeting point altitude signal from the expected meeting altitude extraction circuit 21, and determines whether the meeting altitude signal output from the expected meeting altitude extraction circuit 21 is above or below an arbitrarily set altitude level. The comparator circuits 2 and 23 output a low level signal when the altitude is lower than the set altitude, and output a high level signal when the altitude is lower than the set altitude. , 24 is the output of the EL error signal generation circuit 5 when the output of the OR circuit 23 is a low level signal.
The EL error signal is supplied as is to the steering device 8, and the OR
When the output of the circuit 23 is a high level signal, by correcting the EL error signal output from the EL error signal generation circuit 5 by adding a bias signal, the guided missile M' is steered so as to directly hit the target 1 or pass below it. an EL error bias signal generation circuit that generates an EL error bias signal that is an EL control signal for controlling the device 8;
25, when the output of the OR circuit 23 is a low level signal, the received signal of the lower side antenna is passed to the proximity fuze circuit 1.
3, and if the output of the OR circuit 23 is a high level signal, the signal received by the lower side antenna 9 is stopped being supplied to the proximity fuze circuit 13.
This is an OFF circuit.

Since this invention is configured as described above,
If the meeting point with target 1 is at a low altitude or the signal level from the ground is high, guided missile M' will reach target 1 and always hit target 1 directly or pass below it on a nearby overpass path. At the same time, the supply of the reception signal received by the lower side antenna 9 to the proximity fuze circuit 13 can be stopped. Therefore, early detonation of the guided missile M' at low altitude can be prevented, and the ability of the guided missile M' to shoot down the target 1 can be improved.

In the example, 19 to 25 are shown as independent circuits and devices;
Needless to say, it may be replaced with a single component having the following functions.

[Brief explanation of the drawing]

Figure 1 is a diagram showing the configuration of a conventional guided missile.
FIG. 2 is a diagram showing the configuration of a guided missile according to the present invention. In the figure, 1 is a target, 2 is a signal from the target, 3 is an antenna, 4 is a receiving device, 5 is an EL error signal generation circuit, and 6 is an AZ Error signal generation circuit, 7 antenna servo device, 8 steering device, 9 lower side antenna, 10 upper side antenna, 11 left side antenna, 12 right side antenna, 13 proximity fuse circuit, 14 incoming and outgoing transmitter tube, 15 is a detonation signal generation circuit, 16 is ammunition, 17 is a power source, 18 is a propulsion device,
19 is a clutter level detection circuit, 20 is a comparison circuit 1, 21 is an expected meeting height extraction circuit, 22 is a comparison circuit 2, 23 is an OR circuit, 24 is an EL error bias signal generation circuit, 25 is an ON/OFF circuit, and M is an induction circuit. It's a bullet. In the drawings, the same or corresponding parts are denoted by the same reference numerals.

Claims (1)

[Claims] 1 An antenna that receives infrared rays or reflected signals generated from a target, a receiver that extracts a target signal from the signal received by this antenna, an EL error signal generation circuit that extracts an EL error signal from the target signal, and an AZ error signal from the target signal. an AZ error signal generation circuit that extracts the A lower side antenna, an upper side antenna, a left side antenna, a right side antenna that receive reflected waves, and a proximity fuse that generates a proximity detonation pulse when the target passes near the guided missile using either the target signal or each side antenna. circuit, a landing tube that generates a landing detonation pulse when a guided missile hits a target directly, and a detonation signal generation circuit that generates a detonation signal to detonate the ammunition when a proximity detonation pulse or a landing detonation pulse is input. and Kuratsuta level detection, which detects the level of reflected signals from the ground in guided missiles that are equipped with ammunition that detonates and destroys the target when it meets the target, a power source that supplies power to each component, and a propulsion device that provides thrust. a comparison circuit 1 for determining whether the clutter level exceeds a set level; an expected meeting height extraction circuit for extracting a predicted meeting point altitude signal with the target; and a comparison circuit 1 for determining whether the expected meeting point altitude has exceeded the set level. A comparison circuit 2 that makes a judgment, an OR circuit that outputs a high level signal if either the clutter level or the expected meeting point altitude exceeds a set level, and a low level signal otherwise, and the output of the OR circuit. In the case of a low level signal, the EL error signal is supplied to the steering device as is, and in the case of a high level signal, the output of the EL error bias signal generation circuit that adds a negative bias to the EL error signal and the OR circuit is a low level signal. A guided missile characterized by having an ON/OFF circuit that supplies the signal received by the lower side antenna as it is to the proximity fuze circuit, but does not supply the signal received by the lower side antenna to the proximity fuze circuit in the case of a high level signal.