JPS60300A - Antiship guided missile - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a guided bullet that detects reflected signals of infrared rays generated from a target and captures and tracks the target. First, the conventional cage-guided bullet M will be briefly explained. In Figure 1, M is an anti-ship guided missile, (1) is the target that the anti-ship guided missile M captures and tracks, and (2) is the target (j+
Infrared rays or reflected signals (hereinafter collectively referred to as signals) generated from

(3) is an antenna that receives the signal (2) from the target (11).

(4) is a receiving device that extracts the target signal and the target signal from the signal received by the antenna (3), and (5) is the receiving device (4).
(6) is an EL error signal extraction circuit that extracts an EL error signal from the target signal output from the receiving device (4);
7) is the υ antenna (
3) is an antenna servo device that drives the signal (2) from the target +11 in the arrival direction, and (8) is the & error signal extraction circuit (
5) Output & error signal and ratio error signal extraction circuit (6)
A steering device that steers the guided missile M in the direction of meeting the target (1) using the EL error signal output from the EL error signal.

(9) is an explosive that detonates when the anti-ship guided missile M' meets the target (1,) and causes great damage to the target (1), (
IQ is the power source that supplies power to each component of guided missile M, <
111 is a φ propulsion device that provides thrust to the guided missile M.

However, as shown in Figure 2, the conventional anti-ship guided missile M can fly into target (1)'s fire control attack range B with a flight path as shown in Figure 2. , when approaching target (1), the target (fl)'s fire control system detects and is attacked, and as a result, the guided missile M approaches target (1).
) was destroyed at medium speed and could not reach target (1),
Target +1) It was hindering the ability to destroy the target. In recent years, it has become an important issue to improve the performance of target (1) fire control systems and to improve the above-mentioned drawbacks. This invention.

It is characterized by improving the above drawbacks.

The output of the antenna servo device (7) is input to a newly provided component to be described later, as shown in FIG.

For the target (11), the flight path shown in
1) fire control without intruding into the attack range of the target (1)
By approaching and meeting with 1, the target of anti-ship guided missile M (
1) Improved destruction ability.

Hereinafter, the anti-ship guided missile M' of the present invention will be explained using FIG. 4, which is a specific example.

In FIG. 4, (1) to I are the same as in FIG. α
A~(21) is a new device added to Fig. 1,
A2 is an altimeter that detects the altitude at which the anti-ship guided missile M is to fly and outputs an altitude signal, and Q3 is an altimeter that generates a control signal to fly at a constant altitude from the altitude signal output from the altimeter Qa. . A constant altitude flight signal generation circuit (14) detects the antenna gimbal angle from the output of the antenna servo device (7), and if it exceeds an arbitrarily set limit angle, outputs a no-fly level signal, Before that, the antenna angle limit detection circuit outputs a low level signal, and the QS is a signal generation circuit to fly at a constant altitude when the output of the antenna angle limit detection circuit U is a low level signal (the output of 13 is sent to the steering device (8) supply to,
After the output of the antenna angle mitt detection circuit α-hiro becomes a no-i level signal, the signal generation circuit for flying at a constant altitude (
The first 0N10FF circuit stops supplying the output of one country to the steering device (8), αQ is the EL error signal extraction circuit (6)
When the output of the antenna angle limit detection circuit I is a low level signal, the steering device (
A second ON10 F F circuit, which starts supplying to the steering device (8) after the output of the antenna angle detection circuit a4 becomes a high level signal, without supplying to the steering device (8), t1
7) is not output when the output of the antenna angle limit detection circuit (14) is a low level signal, and when the output of the antenna angle limit detection circuit (141) changes to a high level signal,
Generates a control signal for a certain period of time to cause the anti-ship missile M' to travel in the elevation direction 1~A constant rotation control signal generation circuit that supplies the steering device (8), α~ is the anti-ship missile M'
' is a speed detector that detects the flight speed and outputs a speed signal, and ■ is a speed signal that is the output of speed detector H when the output of antenna angle limit detection circuit α → changes to a high level signal. A comparator circuit that determines whether or not the level is higher than the set level, generates a signal proportional to the level that exceeds the set level, and does not output a signal otherwise. Thrust attenuation control mechanism (21) to attenuate the speed of the anti-ship guided missile M' in proportion to
A thrust attenuation control signal generation circuit (2L) generates a control signal for a certain period of time to control f, and (2L) generates a thrust force that attenuates the speed of the anti-ship guided missile M' by the output of the thrust attenuation control signal generation circuit (4) for a certain period of time. This is a damping control mechanism.

Since this invention is constructed as described above, as shown in Fig. 3, the anti-ship guided missile M' will fly toward the target (1) on the path shown as A'', and within the fire control attack range of the target (1). It is possible to approach and meet target (1) without penetrating the interior of target (1).Therefore, compared to the conventional anti-ship guided missile M, target (1)
On the way to target (1) without being attacked by target (1)
Therefore, the ability of the anti-ship guided missile M' to destroy target (1) can be improved. Although (12) to (21) are shown as independent circuits and devices in the examples, it goes without saying that these may be replaced with a single component having the functions of (12) to (21). stomach.

[Brief explanation of the drawing]

Figure 1 shows the configuration of a conventional anti-ship guided missile;
The figure shows the flight path of conventional anti-ship guided missiles.
Fig. 3 is a diagram showing the flight path of the anti-ship guided missile according to the present invention, and Fig. 4 is a diagram showing the configuration of the anti-ship guided missile according to the present invention, in which (1) is the target and (2) is the target. Signal from target, (3) antenna, (4) receiving device, (5) M error signal extraction circuit, (6) & error signal extraction circuit, (7)
is the antenna servo device, (8) is the steering device, (9) is the ammunition, On is the power supply, αυ is the propulsion device, 0-digit altimeter, 03 is the signal generation circuit to fly at a constant altitude, (14) is the antenna angle mitt detection circuit, a rise is the first 0N10FF circuit,
αe is the second ON10 F F circuit, +lη is a fixed period travel G control signal generation circuit, αe is a speed detector, OI is a comparison circuit, (A) is a fixed period thrust attenuation control signal generation circuit,
(21) Thrust attenuation control mechanism 2M is an anti-ship guided missile. A is the flight path of the anti-ship guided missile, and B is the fire control attack range of target (1). Note that the same parts in Figure 9 are indicated by the same reference numerals for corresponding parts. Agent Masuo Oiwa

Claims (1)

[Claims] An antenna that receives infrared rays or reflected signals generated from a target, a receiving device that extracts a target signal from the signal received by the antenna, and an M error signal extraction circuit that extracts an error signal in a direction away from the target signal. , an EL error signal extraction circuit that extracts an error signal in the BL direction from the target signal, an antenna servo device that drives the antenna in the target direction, a steering device that steers the guided missile toward the meeting point with the target, and each component. An altimeter that detects the flight altitude of an anti-ship guided missile that is equipped with a power supply that supplies electricity, ammunition that detonates upon meeting the target and causes great damage to the target, and a propulsion device that provides thrust to the guided missile. and a constant altitude flight signal generation circuit that generates a control signal to control the flight at a constant altitude, and an antenna angle limit detection circuit that detects the antenna angle and gimbal angle. The first 0N10FF circuit turns ON10FF the supply of the control signal to the steering device for flying at a constant altitude, the second (7) ON10FF circuit turns ON10FF the supply of the BL error signal to the steering device, and the antenna. A control signal generation circuit that generates a signal that causes the guided missile to travel for a certain period of time after the angle exceeds the gimbal limit, a speed detector that detects the speed of the guided missile, and a speed detector that detects the speed of the guided missile when the antenna angle exceeds the gimbal limit. a comparator circuit that determines whether the velocity of the guided missile exceeds a set level when the velocity exceeds the set level, and a fixed-period thrust attenuation control signal generation circuit that generates a control signal to attenuate the velocity of the guided missile for a fixed period. A pair of four guided missiles characterized by having a quasi-force attenuation control mechanism that attenuates the speed of the guided missiles using a control signal.