JPH01260297A - Control of guidance for master and slave type guided missile - Google Patents

Abstract

PURPOSE:To obtain a missile having long range and all weather property, by a method wherein a master projectile has an antenna and a small size rocket motor and the drop of the master projective is restrained by the reverse injection of the same after discharging slave projectiles so as to position at the rear side of the slave projectiles than a target as the projector of slave projectile seakers. CONSTITUTION:When a master projectile 1 flying toward a target 12 has arrived at a predetermined position above the target 12 by inertia guidance or active radar homing guidance, slave projectiles 7 are discharged. The master projectile 1, which has discharged the slave projectiles 7, ignites a small size rocket motor 6 attached to the rear side surface of the master projectile 1 to prevent the dropping of the master projectile by injecting exhaust gas downwardly while the master projectile transmits radio waves 13 toward the target 12 at a given position of the projectile. The injecting direction and the amount of injection are controlled by a gyro 4 and a control device 5 to stabilize the master projectile spatially and secure the stabilized projection of radio waves as well as the position of standoff. The slave projectiles receive reflecting waves 14 from the target 12 of master projectile transmitting wave 13 to operate the steering blade 11 of the slave projectiles by a guidance control device 10 and track the target 12.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a guidance control method for a parent-child guided flying vehicle including a large number of submunitions having a guidance control device. [Prior Art] FIG. , Figure 4 is a diagram showing how a conventional parent-child guided flying vehicle searches for and tracks a target.
+21d Above 1 parent bullet (transmitter equipped in 11).

(3) is an antenna that transmits radio waves sent from the transmitter (2), (7) is a submunition, (1 (I is a submunition control device,
I is the submunition steering blade, α2 is the target, aS is the submunition Senna, αe
indicates the parachute attached to the rear of the submunition, and αη indicates the electromagnetic waves radiated from the target.

Next, the operation/effect will be explained. In FIG. 3, a parent bullet (1) flying toward a target az releases a sub-munition (7) when it approaches a predetermined position (by inertial guidance or active radar homing) to a target α2.

In FIG. 4, when the ejected submunition (7) falls to a predetermined altitude, it deploys a parachute ne.

The falling speed is reduced, the submunition sensor S is searched for the target α2, and the electromagnetic wave αη radiated from the target σ2 is detected.
The submunition control device αG operates the submunition steering wing aυ,
Capture and track target α2.

[Problem to be solved by the invention]

Since the conventional search and tracking method for parent-child guided flying vehicles is configured as described above, it is difficult to implement active radar homing guidance by equipping each sub-munition with a transmitter. In addition to dramatically increasing the size of the bullet, it would be difficult to operate due to the cost, and it would be limited to a passive homing guidance method that passively detects electromagnetic waves radiated from the target, resulting in a short range. There were problems such as a decline in detection ability in rainy weather.

This invention was made in order to solve the above-mentioned problems, and to obtain a semi-active homing guidance method that has a long range and all-weather performance that cannot be obtained with a passive homing guidance method as a guidance control method for submunitions. With the goal.

[Means to solve the problem]

In the guidance control method for a parent-child guided flying vehicle according to the present invention, the parent missile has a transmitter, an antenna, and a small rocket motor, and after ejecting the sub-munition, the fall of the parent missile is suppressed by reverse injection, and the sub-munition seeker is As a irradiator, it was possible to always be positioned behind the target bomb.

[Effect]

In this invention, after the submunition is released, a small rocket motor installed on the side of the main munition propulsion unit is ignited.

By ejecting in the opposite direction to the falling direction, it prevents the parent bullet from falling and continues to emit radio waves from the standoff position of the enemy's weapon toward the target, allowing the sub-munitions to receive reflected waves from the target. to capture and track the target.

〔Example〕

An embodiment of the present invention will be described below with reference to the drawings. 1st
In the figure and FIG. 2, (1) is the base bullet, (2) is the transmitter equipped on the base bullet, (3) is the antenna that transmits the radio waves sent from the transmitter (2), (4) is a gyro, (
5) is a control device, (6) is a small rocket motor installed on the rear side of the parent bullet (1), (7) is a sub-munition, and (8) is a receiver installed inside the sub-munition (7). , (9) is the submunition antenna, IIG is the submunition control device, αυ is the submunition steering blade,
α2 is the target, αj is the target α from the parent missile antenna (3)
The transmitted wave irradiated towards 2, fi41 shows the reflected wave from the target.

Next, the operation/effect will be explained. In Fig. 1, a parent bullet (1) flying towards target α2 is guided by inertial guidance or active radar homing guidance.
21, the submunition (7
) is released.

In Fig. 2, the parent bullet (11) is the one that released the sub-bullet (7).

A small rocket motor (6) attached to the rear side is ignited and exhaust is ejected downward to prevent the parent bullet (1) from falling and transmit radio wave 0 toward target α2 at a fixed position. The main bullet (1+ receives lateral force) due to air currents, etc.

If the rocket begins to fall or rise, it is detected by the gyro (4) installed inside the parent missile, and the control device (5) controls the ejection direction and amount of ejection from the small rocket motor (6). Main bullet (
1) to ensure stable radio wave irradiation and standoff position by spatially stabilizing the submunition antenna (7).The submunition (7) transmits the reflected wave α4 from the target of the parent munition transmission wave αj to the submunition antenna (9). ) and the submunition receiver (8), the guidance control device a1 captures the target (lz), operates the submunition steering blade αυ, and tracks the target aZ.

[Effects of the Invention] As described above, according to the present invention, the position of the parent bullet after ejecting the sub-munition is determined by the control that controls the injection of the rocket motor and the gyro that detects the reverse injection by the small rocket motor and the amount of movement of the parent bullet. The operation of the device spatially fixes the position of the parent munitions after releasing the submunitions, which enables semi-active guidance control of the submunitions using the parent munitions as the irradiation device, increases the range of the submunitions, and makes it possible to use the submunitions in all weather conditions. In addition to this, the standoff performance of the parent bullet as an irradiator is ensured.

[Brief explanation of the drawing]

FIG. 1 is a diagram showing the configuration of a parent-child guided flying object according to the present invention and how the flying object searches for a target. The second reason is a diagram showing how the submunitions track the target using a semi-active guidance method after the projectile releases the submunitions.
Figure 3 is a diagram showing the configuration of a conventional parent-child mW guided flying vehicle and how the flying vehicle searches for a target. Figure 4 shows that after the flying vehicle releases a submunition, the submunition is passively guided. Figure 9 shows how the target is tracked.
2) is the transmitter installed in the base bullet il+, (3) is the base bullet antenna, (4) is the base bullet gyro, (5) is the base bullet control device, and (G) is the base bullet (11). A small rocket motor installed on the rear side. (7) is a submunition, (8) is a submunition receiver, (9) is a submunition antenna. σG is a submunition control device, aD is a submunition steering blade, and az is a submunition control blade. the goal,
'a3 is a transmission wave sent out from the parent bullet (1) toward target σ2, and α4 is a reflected wave of the transmission wave α3 from target α2. α5 is a conventional submunition passive sensor, or the above submunition (7
), (lη is the target α2
It is an electromagnetic wave radiated from. Note that the same symbols in Figure 9 indicate the same or equivalent parts.

Claims (1)

[Claims] In a guidance control method for a parent-child guided flying vehicle having a large number of submunitions having a guidance control device, a transmitter is attached to the parent projectile, an antenna directly connected to the transmitter, and a small rocket attached to the rear side of the parent projectile. It has a motor, a gyro that detects a change in the position of the parent bullet, and a control device that controls the rocket motor to correct the amount of movement detected by the gyro,
The sub-munition has an antenna, a receiver, a steering blade, and a control device that controls the above-mentioned steering blades, and after the sub-munition is released, the parent munitions are suppressed from falling by back injection, and the parent munitions are prevented from falling due to lateral force due to air currents or the amount of rocket motor injection. Changes in the position of the bullet are detected by a gyro, and the control device controls the direction and amount of rocket motor injection to maintain the spatial position of the parent bullet and aim it at the target from the standoff position of enemy weapons. A parent-child type guided flying vehicle characterized in that the sub-munition captures and tracks the reflected wave from the target of the transmitted wave of the parent projectile sent out by the parent projectile, thereby performing semi-active guidance control of the sub-munition using the parent projectile as an irradiator. Guidance control method.