JPS63217199A - Guidance system of 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 [Field of Industrial Application] The present invention relates to a method for guiding a projectile such as a guided missile. In particular, the present invention relates to an induction method in the final stage of induction of flying bodies.

[Prior art]

A method known as proportional navigation has been recommended as a guidance method for flying objects. This method performs control so that the relationship t=Na is maintained between the line-of-sight angle σ between the projectile and the target and the path angle γ.
Specifically, the homing device tracks the target and generates a line-of-sight angular velocity signal, which is amplified and used as a command signal to the autopilot system. If the projectile is an anti-tank guided projectile, the target is a tank;
The projectile is directed towards the tank and hits it.

By the way, in recent years tanks have developed bulletproof armor technology, so it is desired that the destructive power of guided bullets be improved. in general,
A tank's armor is weaker on the top than on the sides, so when attacking a tank tank with anti-tank guided missiles, it is thought that attacking from the top would have more destructive power. However, although conventional proportional navigation has very high accuracy, it does not control the angle of entry into the target.

In anti-ship guided missiles, when the guided missile reaches a predetermined distance from the target, a rising rudder is applied to increase the altitude of the guided missile.
Some guidance methods are programmed to then enter proportional navigation, but even this guidance method does not control the angle of entry into the target.

[Problem that the invention seeks to solve]

As described above, the present invention provides, in the conventional guidance method,
This solves the problem of not being able to control the angle of entry into the target.For example, the purpose is to provide a guidance method that can control the angle of entry into the target, so that a top attack can be performed with guided missiles. do.

[Means for solving problems]

In order to solve the above problems, in the present invention, in addition to the line-of-sight angular velocity signal used in conventional proportional navigation, etc., a signal related to the angle between the desired entry path to the target and the line-of-sight is provided. is used for control. That is, in the guidance method of a flying object according to the present invention, at the end of the guidance of the flying object, a signal related to the angular velocity of the visual line angle of the target from the flying object, a desired entry path to the target, and a line of sight is transmitted from the flying object to the target. It is characterized in that the angle of entry into the target is controlled by using the added signal obtained by adding the signals related to the angle as a guidance signal.

[For production]

According to the present invention, a flying object is guided toward a target using a normal method such as command guidance or inertial guidance, and then a homing device of the flying object captures the target and homing guidance is performed. At the final stage, as a guidance signal, a sum signal obtained by adding a signal related to the angular velocity of the visual line angle of the target from the projectile and a signal related to the angle formed by the desired path of entry to the target and the line of sight. is given to the autopilot system. Therefore, the autopilot system is
By performing steering in a direction in which this added signal decreases, the projectile is guided to a path with a desired angle of entry, and it will enter the target at the desired angle of entry. Therefore, in the case of anti-tank guided missiles, for example, it becomes possible to attack the target from above.

〔Example〕

Figure 1 shows the relationship between the projectile 1 and the target 2.

The line viewed from the projectile 1 to the target 2 is the line of sight 3, and forms an angle σ between it and the spatial reference line 4. 5 is a desired entry route, which forms an entry angle α with the spatial reference line 4.

The angle between the line of sight 3 and the desired entry path 5 is β, and the difference between the desired angle of entry α and the angle of line of sight σ is used as a reference.

FIG. 2 is a block diagram showing a calculation section of a guidance device according to an embodiment of the present invention, and this guidance device has a homing device 10 mounted on a flying object 1. As shown in FIG. This homing device 10 is for capturing a target, and has an eye angle σ
A signal corresponding to the temporal change in the line of sight, that is, the angular velocity of the eye's line of sight is generated. The output of the homing device 10 is amplified by an amplifier 11 and applied to the motorcycle loft system 13 of the spacecraft 1 via an adder 12. This configuration is the same as a conventional proportional navigation device.

Furthermore, the output of the homing device 10 is input to an eye angle calculation device 14 . This device 14 calculates the eye line angle σ from the eye line angular velocity signal a from the homing device 10. In the conventional homing device for proportional navigation, the target detection angle signal of the target detection unit corresponds to the line-of-sight angular velocity signal, and in this embodiment, the line-of-sight angle σ is calculated from this line-of-sight angular velocity signal. However, it is also possible to calculate from the gimbal angle of the homing device and the attitude angle of the projectile.

The output of the eye gaze angle calculation device 14 is input to an adder 15. The desired entry angle signal α from the entry angle setter 16 is also input to the adder 15 . The adder 15 receives the desired entry angle signal α
and the eye gaze angle σΦ difference signal β is output. The output of adder 15 is input to adder 12 via amplifier 17 and switch 18 .

Adder 12 adds the outputs of amplifiers 11 and 17 and provides the result to autopilot system 13 as a guidance signal.

A switching control device 19 is provided for controlling switch 18 . This control device 19 is for controlling the entry angle by closing the switch 18 at the initial stage of homing guidance. The signal β from the adder 15 is input to the control device 19 . The control device 19 receives this signal β and opens the switch 18 when the signal β becomes approximately 0.

In operation, at the initial stage of homing guidance, the switch 18 is closed by the switching control device 19, and the adder 12 is closed.
At , the signal from the amplifier 17 is added to the signal from the amplifier 11 and supplied to the autopilot system 13. Therefore, the autopilot system 13 performs steering in a direction in which the set angle difference β decreases. As a result of this steering, when the set angle difference β becomes approximately 0, the switching control device 1
9 opens switch 18 and the craft is guided by normal proportional navigation.

〔effect〕

As described above, in the present invention, the target is obtained by adding the signal related to the angular velocity of the apparent line of sight angle from the projectile to the signal related to the angle formed by the line of sight and the desired path of entry to the target. Since the added signal obtained by
It becomes possible to guide the projectile to a path along a desired angle of entry, and it becomes possible for the projectile to enter the target from, for example, from above.

[Brief explanation of the drawing]

Figure 1 is a diagram showing the relationship between the projectile and the target;
The figure is a block diagram of a calculation section for guidance showing an embodiment of the present invention. 1... Projectile, 2... Target, 3... Line of sight, 5... Desired entry route, σ... Line of sight angle,
lO...Homing device, 13...Motorcycle loft system, 16...Entry angle setting device

Claims (1)

[Claims] When guiding a flying object equipped with a homing device, a signal related to the angular velocity of the visual line angle of the target from the flying object and a signal related to the angle formed by the line of sight and the desired path to the target are added together. A guidance method for a flying object, characterized in that the angle of entry into a target is controlled using the added signal obtained as a guidance signal.