JPS58198700A - 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 missile that detects infrared rays or reflected signals generated from a target, and captures and tracks a target f. First, a conventional guided missile M of this type will be briefly explained. In FIG. 1, (a target to be captured and tracked by the llfl guided missile M, SE I is an infrared ray or reflected signal (hereinafter collectively referred to as a signal) generated from the target (1), (31 is an antenna that receives signals from the target).

(4+ is a receiving device that extracts an error signal from the signal received by antenna (3), @ is an antenna that drives the receiving device (antenna port) in the direction of arrival of signal (2) from the target by the error signal output from 4. Servo device, tan receiving device (
A steering device (7) steers the aircraft in the direction of the meeting point with the target based on the error signal of the output of 41, and (7) is a rocket motor that provides thrust to the guided missile M. It is constructed in a manner similar to that of the conventional guided missile MFi, and its purpose is to capture and track a target, guide it to the meeting point with the aircraft tube target, and ultimately shoot down the target.

However, since the conventional guided missile M has a velocity characteristic curve as shown in FIG. 2, the longer it takes to reach the target, the lower the velocity. Therefore, it becomes impossible to follow the target's sudden movement (such as when it suddenly increases speed),
This was hindering the ability to shoot down targets. Particularly in recent years, there has been a strong tendency to extend the range of guided missiles, and the above drawbacks have become an important issue. This invention is characterized by improving the above-mentioned drawbacks.The output of the receiving device (41) is input to a newly provided component to be described later, and when the target starts a sudden avoidance movement at the end of guidance. Correct the speed characteristic (V),
The ability to shoot down a target is improved by achieving a predetermined tracking characteristic at the meeting point. Hereinafter, M' of the present invention will be explained using FIG. 3, which is a specific example.

In FIG. 3, 2 ports) to (7) are the same as in FIG. 1.

(8)~at+ is a new device added to Figure 1,
(The sum is the receiving device (calculates the meeting time until the target based on the output of 41, and any period 0 before the set meeting time)) The operating period in which a high level signal is output and a low level signal is output at other times. The setting circuit (9) is an error signal threshold circuit that outputs a high level signal when the error signal of the output of the receiving device (41 is above a predetermined level, and outputs a low level signal when it is below a predetermined level, a value are the operating period setting circuit (8) and the error signal threshold circuit (9)
α11 is an auxiliary propulsion device control circuit that operates the auxiliary propulsion device α1 when the output of the auxiliary propulsion device 11111 circuit 11G is outputted from a high-level signal tube. .

Because this invention is configured as one or more.

When the target starts a rapid evasive movement at the end of guided missile guidance, the velocity characteristics of the guided missile are corrected as shown in FIG. Thereby, the ability of guided missiles to shoot down targets can be improved. In addition, in the example, (8) to (IB
'fr is shown as an independent circuit, but this is (
It goes without saying that it may be replaced with one component having the functions of 81 to αD.

[Brief explanation of the drawing]

FIG. 1 is a diagram showing the configuration of a conventional guided missile. FIG. 2 is a diagram showing the velocity characteristics of a conventional guided missile, FIG. 3 is a diagram showing a configuration example of the guided missile according to the present invention, and FIG. 4 is a diagram showing the velocity characteristics of the guided missile of the present invention. Medium+lit;
is the target, (2) is the signal from the target, (3) is the antenna,
(4) is a receiving device, and (5) is an antenna servo device. (Button is the steering device, (n is the four-ket motor, (8) is the operating period setting circuit, c is the error signal threshold circuit, lI is the auxiliary propulsion device control circuit, Qll is the auxiliary propulsion device, (v) tj speed Characteristics. In Figure 1, the same or equivalent parts are indicated by the same reference numerals. Agent: Shin Tameno - Seifuku

Claims (1)

[Claims] In a guided missile that detects angular information from infrared rays or reflected signals generated from the target, and uses that information to capture and track the target, if the target makes an evasive movement at the end of guidance,
A guided missile designated as 4111 is equipped with means for detecting this and correcting the speed of the guided missile.