JPH01169300A - Master/subordinate type guided missile - Google Patents

Abstract

PURPOSE:To extend the range of subordinate missiles by conveying the target information acquired by the master missile to the subordinate missiles before launching them, and launching the subordinate missiles only after the respective subordinate missiles select and acquire different targets. CONSTITUTION:The master missile has a guidance control device and a steering control device and control vanes for tracking the targets based on the target information. When the master missile 1 launched from a launcher 8 has travelled over the targets 11 by operating its control vanes, it illuminates the radio wave 12 from its antenna 2 to search for the targets 11, and, at the same time, exposes its subordinate missiles 9 by opening the shell 10. After the respective subordinate missiles 9 determine their respective targets based on the information from the master missile 1, their rocket motor 20 is fired and the missiles dive for their respective targets 11. As the master missile 1 illuminate the radio wave from its antenna 2 to the entire targets, it descends slowly toward the center of the target area, following the subordinate missiles 9. By receiving the reflection 13 from the targets 11 of the radio waves 12 transmitted from the master missile 1, the subordinate missiles 9 track their respective targets 11. Because the target search and tracking by the subordinate missiles 11 is semi-active, using the transmitter of the master missile 1 as their illuminator, their range can be extended.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a parent-child guided flying object that includes a large number of submunitions and has a guidance control device.

[Conventional technology]

Figure 6 shows how a parent bullet releases a sub-bullet in a conventional parent-child guided flying vehicle.
O is the deployment shell for releasing the reed submunition into the main shell body, (9) is the submunition, and (lυ is the target).

Next, Figure 7 shows how a conventional parent-child guided flying vehicle searches for and tracks a target. is the above submunition (9)
parashoes attached to the rear of), (Ill are the targets, (
) indicates the electromagnetic waves radiated from the target.

Next, the operation/effect will be explained. In FIG. 6, the parent bullet (11) flying toward the target (9) deploys its shell when it reaches a predetermined position.

Drop the submunition (9). In Fig. 7, the submunition (9) that turns to the target and falls, when it falls to a predetermined position,
Deploy the parachute (to) equipped at the rear.

A search is made for the target aυ, and the submunition antenna αe receives electromagnetic waves radiated from the target to track the target α9.

[Problem that the invention seeks to solve]

Conventional parent-child guided flying vehicles are configured as described above, so after the submunitions are released from the parent projectile, they must search for the target again using a passive method that receives electromagnetic waves radiated from the target. Due to its short range and the fact that it was equipped with a parachute to significantly reduce its falling speed, there was a high possibility that it would be detected and attacked by its target. Additionally, even if multiple submunitions were used, they would sometimes attack the same target.

This invention was made to solve the above-mentioned problems, and aims to provide a device that extends the range of submunitions and improves the rapid attack ability and target identification ability of submunitions. [Means for Solving the Problems] The parent-child guided flying object according to the present invention includes an antenna and an antenna on the parent missile.
It has a transmitter, a receiver, a signal processing device, a steering control device for tracking the target based on the target information obtained by these, and a steering blade, and is detachable so that the target information obtained by the base missile can be transmitted. Connect the submunition with the connector,
At the same time, the submunition grasping device is capable of being deployed outside the main munitions and can also serve as a launcher for firing submunitions. In addition, the submunition had an antenna, receiver, signal processing device, steering control device, deployable control wing, and rocket motor, and was able to receive waves emitted from the target and track and attack the target at high speed. It is something.

[Effect]

The parent-child guided flying object according to the present invention transmits target information obtained by the parent bullet to the sub-munition before launching the sub-munition, and each sub-munition is fired after selecting and capturing a different target. In addition, a rocket motor is attached to the submunitions, and after the submunitions are launched, the parent munitions continue to track the target behind the submunitions and continue to emit radio waves to the target, and the submunitions receive reflected waves from the target. to capture and track each target.

〔Example〕

An embodiment of the present invention will be described below with reference to the drawings. 1st
From the figure to Figure 4, (1) is the base bullet, (2) is the antenna, (3) is the guidance control device including the transmitter, receiver, and signal processing device, (4) is the radio wave altitude resistance, (5) is the ) is the steering control device, (6) is the steering wing, (7) is the tail, (8) is the main projectile launcher, (9) is the submunition, and αG is the part of the main projectile that stores the submunition (9). Deployed shell, αυ is the target, az is the transmitted wave irradiated from the parent missile antenna (2) toward the target aD,
0 is the reflected wave from the target U, α7 is the submunition (9) and the parent bullet (1
) is a connector that is fixed in a state where signals can be sent and received, (I5
is the submunition deployment wing, αe is the submunition antenna, (lη is the receiver,
The arrow indicates the signal processing device, Q9 indicates the submunition steering control device, and ■ indicates the submunition rocket motor.

Next, the operation/effect will be explained. In Figure 1, the parent bullet (1) fired by the 9-shot launcher (8) is.

When it flies over the target by driving the steering wheel x (4), it irradiates the antenna (2) with a stain wave αzt to search for target I, and at the same time deploys the deployable shell (1 (l) to expose the submunition (9). When the sub-bullets (9) determine their respective targets based on the information from the parent bomb, the rocket motor (■) is ignited.

The main bullet (11) rapidly descends toward each target (111) while irradiating radio waves to the entire target group from the antenna (2).

It slowly descends from above the submunition (9) toward the center of the target group. The sub-bullet (9) receives the reflected wave α3 of the parent bullet transmission wave r1 from each target and tracks each target αυ.

Next, the detailed structure of the submunition storage and deployment mechanism and the submunition will be described. Figure 2 is a cross-sectional view of Figure 1 taken along cross-section AA, and Figure 3 is a sectional view of the main bullet's deployment shell +l in Figure 2.
tl is deployed and the submunition (9) is shown facing the target. Further, FIG. 4 is an enlarged view of the sub-munition storage portion in FIG. 1, showing details of the sub-munition.

Next, we will explain in detail the actions of parent and submunitions from searching for targets to tracking them. In Figure 5, c! D ~ (b)
shows the actions and effects of the parent bullet and sub-bullet at each stage.

In step Qυ, when it is confirmed that the parent bullet (11) flying over the target has reached the predetermined X1ffi using the radio wave altitude at (4), in step 4 the transmitter of the guidance control device (4) sends a smudge wave α2 is transmitted, and the antenna (2) is driven to search for the target aυ.In step 2, the guidance control device (4
) confirms that it has captured the target aυ.

A shell deployment command is given, and the deployment shell αG is deployed (step c!4). At the same time, target position information is given to the submunition (9) through the connector (14+), and the antenna αG of the submunition starts searching for the target (step (c)). Each submunition (9
) identifies the target to attack (step @), transmits the target information to each submunition (9), and the submunition (9) performs the step until each submunition (9) acquires the selected target. (c) Repeat the target search, capture, and selection of ~■. When the sub-bullet (9) captures the target αυ instructed by the parent bullet 111.

A target acquisition completion signal is transmitted from the sub-munition (9) to the parent munition (1).

Step-Kan's submunition is confirmed to be launched using the main munitions (!).

Therefore, a submunition launch command is given to the submunition (9), and the submunition rocket motor (2) is ignited in step (7).

The connector is detached at step 6υ a little later than the step, and the submunition (9) is fired. After firing a submunition.

The deployable wing αS is deployed (step G3), and the antenna αG receives the reflected wave αj from the target of the transmitted wave α2 of the parent bullet, thereby executing target tracking. On the other hand, at the step (to) the submunition (
When it is confirmed that the firing in step 9) has been completed, the deployment shell Oα that has fired the submunition is closed (step (b)).

[Effects of the Invention] As described above, according to the present invention, the target search and tracking method for submunitions is a semi-active method using the parent munition transmitter as the irradiator, which makes it possible to achieve longer firing ranges. , a rocket motor was added to the sub-munition as a means of positioning the parent munitions behind the sub-munitions.

It has the added effect of increasing the speed of attack of submunitions, and improving target identification ability because each submunition is fired after capturing a different target.

[Brief explanation of the drawing]

Fig. 1 is a diagram showing how the parent-child guided flying vehicle according to the present invention approaches a target, Fig. 2 is a sectional view taken along section AA of Fig. 1 and shows the submunition storage state, and Fig. 3 is Fig. 2 is a cross-sectional view showing the state in which the deployment shell is deployed and the submunition faces the target; The figure is a block diagram explaining the method of target search and tracking of a parent-child guided flying vehicle. Figure 6 is a diagram showing how a parent bullet releases a sub-munition in a conventional parent-child guided flying vehicle. Figure 1 is a conventional A parent-child guided flying vehicle searches for a target.
FIG. 3 is a diagram showing how tracking is performed. 1 to 1, (1) is the parent bullet, (2) is the antenna, (3) is the guidance control device including the transmitter, receiver, and signal processing device, (4) is Denpa Kokosha, (5) is the steering control device, (6) is the steering wing, (7) is the tail, C8) is the parent bullet launcher, (9) is the submunition, and the handle is the part that stores the submunition (9). Deployment shell, C9 is the target, a'a is the transmission wave from the parent bullet antenna (2), (13 is the reflected wave from the target U, α core is the sub-munition (9) and the parent bullet (11 can send and receive signals) C9 is the submunition deployment wing, αe
is a submunition antenna. (171 is the receiver, (1& is the signal processing device, (19 is the submunition steering control device, j is the submunition rocket motor, c!υ~
(b) is a block showing the operation of the parent bullet and submunition at each stage in Figure 5, (to) is the parachute installed at the rear of the submunition in a conventional parent-child guided flying vehicle, (to) is the target Shows the electromagnetic waves radiated from. Note that the same reference numerals in each figure indicate the same or corresponding parts.

Claims (1)

[Claims] In a parent-child guided flying vehicle with a large number of submunitions each having a guidance control device, the parent projectile is equipped with a transmitter, an antenna, a receiver, a signal processing device, an altimeter, a steering wing, a steering control device, and submunition storage in the main projectile body. Equipped with a deployment mechanism that allows the partial shell to be deployed, and a connector attached to the inner wall of the deployable shell fixes the sub-munition to the parent munition in a state where it can send and receive signals. By being equipped with an antenna, a receiver, a signal processing device, an deployable steering wing, a steering control device, and a rocket motor that have a band similar to the transmitter frequency, each submunition receives target information from the parent munition before launching. Receipt,
The sub-munitions are fired after capturing different targets, and the sub-munitions are guided by a semi-active guidance control method by emitting radio waves towards the target until the sub-munitions hit the target. A characteristic parent-child guided flying object.