JPH06129799A - Controller for missile - Google Patents

Abstract

PURPOSE:To enhance a hitting accuracy by coping with demands for reductions in the size, weight and cost, and controlling (roughly) damping (convergence degree) of a body in lateral directions while correcting a time delay, an error, etc., caused at the time of rolling a body toward the target. CONSTITUTION:A controller for a missile 2 has two main wings at outer periphery of an intermediate part, two steering wings 3 of a linear servomechanism on an outer periphery of a tail, and two steering wings 4 of a spoiler type steering mechanism in a directional position perpendicular to the wings 3.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a control device for projectiles such as guided bullets.

[0002]

2. Description of the Related Art Conventional control devices for flying vehicles such as light anti-tank guided bullets include STT (Skid-to-Turn) type and B type.
There is a TT (Bunk-to-Turn) type.

As shown in FIG. 4, the STT type is a flying body 2 having four main wings 1 on the outer circumference of the middle part, and four steering wings 3 of a linear servo mechanism on the outer circumference of the tail part. Yes, as shown in FIG. 5, the pitch and yaw directions have the same performance. After stopping the roll (rotation) motion, the angle of attack is controlled in the direction to be guided by the distribution.
Generate force. Therefore, it is not necessary to roll the aircraft in the target direction, and the turning force can be generated vertically and horizontally independently,
Control performance and hit accuracy are good. However, since the maximum turning force cannot always be generated in the target direction, the turning ability is insufficient. In addition, four independent high-performance steering devices were required, resulting in heavy weight and high price. For this reason, it has not been possible to meet the recent demands for smaller size, lighter weight, and lower prices.

On the other hand, as shown in FIG. 6, the BTT type is a flying body 2 having two main wings 1 on the outer circumference of the middle part, and two steering wings 3 of a linear servo mechanism on the outer circumference of the tail part. Since the maximum turning force can always be generated in the target direction, compared to the STT type described above, higher turning in the target direction is possible, which is lighter, smaller, and less expensive, but the machine rolls in the target direction. When this is done, there will always be a time delay, an error, and the damping (convergence) of the airframe in the left-right direction will be poor.

[0005]

Therefore, the present invention can meet the demands for downsizing, weight reduction, and price reduction, and at the same time correct the time delay, error, etc. that occur when the machine body is rolled in the target direction, and Damping (convergence) of the aircraft in the left and right directions
By controlling (coarse control), it is intended to provide a flying body control device capable of increasing the accuracy of hit.

[0006]

In order to solve the above-mentioned problems, a control device for a flying vehicle of the present invention is a flying vehicle having two main wings on the outer periphery of an intermediate portion, and a linear servo mechanism of a linear servo mechanism on the outer periphery of a tail portion. Two steering blades are provided symmetrically, and two steering blades of the spoiler type steering mechanism are provided at a position orthogonal to the two steering blades.

[0007]

In the flying object control device of the present invention having the above-described structure, since the linear servo mechanism has two steering wings, a large force can be generated only in one of the pitch and yaw directions. After rotating the aircraft in the proper direction,
The angle of attack of the two steering wings of the linear servo mechanism is controlled to generate a force in the pitch direction. At the same time, regarding the yaw direction of the airframe, the turning force by controlling the angle of attack of the two steering blades of the spoiler type steering mechanism corrects the time delay and error due to BTT, and the damping of the airframe in the left and right directions. (Convergence) control (coarse control)
To do.

Thus, the time delay and error when the machine body is rotated in the direction to be guided can be corrected, and stable guidance can be achieved. Therefore, the accuracy of hitting the flying object is good.

[0009]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of a flying body control apparatus according to the present invention will be described with reference to FIG. 1. In a flying body 2 provided with two main wings 1 on the outer periphery of an intermediate portion, two linear servo mechanisms are provided on the outer periphery of the tail portion. The steering blades 3 are provided, and the two steering blades 4 of the spoiler type steering mechanism are provided at a position orthogonal to the two steering blades 3.

According to the control device for the flying vehicle 2 of the embodiment thus configured, after the flying vehicle 2 shown in FIG. 2 is launched, the aircraft is rotated 45 degrees in the direction to be guided as shown in FIG. Moreover, the elevation angle can be generated in the direction of the arrow by controlling the angle of attack of the two steering wings 3 of the linear servo mechanism. At the same time, with respect to the yaw direction of the airframe, the angle of attack of the two steering wings 4 of the spoiler type steering mechanism is controlled to control the damping (convergence degree) of the airframe in the left-right direction (coarse control). Thus, it is possible to correct the time delay and the error when the machine body is rotated in the direction to be guided. Further, a slight turning force is generated by controlling the angle of attack of the two steering wings 4 of the spoiler type steering mechanism. Therefore, the accuracy of the flying object 2 is high. Since the maximum turning force can always be generated in the direction to be guided, higher turning is possible as compared with the conventional STT type control device.

[0011]

As described above, according to the flying body control apparatus of the present invention, when the vehicle body is rolled in the target direction, the angle of attack of the steering blades of the spoiler type steering mechanism is controlled to control the aircraft body in the left-right direction. It is possible to control the damping (convergence degree), correct the time delay and the error, and generate a slight turning force, so that the accuracy of hitting the flying object is improved. Moreover, the maximum turning force can always be generated in the target direction, and high turning is possible.

Further, since the flying vehicle control device of the present invention has two steering blades of a linear servo mechanism and two steering blades of a simple spoiler type steering mechanism, the recent reduction in size and weight and cost can be achieved. Can sufficiently meet the requirements of.

[Brief description of drawings]

FIG. 1 is a schematic diagram showing a flying object including a control device of the present invention.

FIG. 2 is a diagram showing a tail portion of the flying object of FIG.

FIG. 3 is a diagram showing a state in which the flying object of FIG. 2 is rotated in a direction to be guided by 45 degrees.

FIG. 4 is a schematic view showing a flying object including a conventional STT type control device.

FIG. 5 is a diagram showing a tail portion in a state when controlling the flying object of FIG. 4 in a direction to be guided.

FIG. 6 is a schematic diagram showing a flying object including a conventional BTT type control device.

[Explanation of symbols]

 1 Main wing 2 Flying body 3 Steering wing of linear servo mechanism 4 Steering wing of spoiler type steering mechanism

 ─────────────────────────────────────────────────── ─── Continuation of front page (72) Inventor Yoshihiko Nishida 1 Kawasaki-cho, Kakamigahara-shi, Gifu Kawasaki Heavy Industries Ltd. Gifu factory

Claims (1)

[Claims] 1. A flying body having two main wings on the outer circumference of an intermediate part, and two steering wings of a linear servo mechanism symmetrically provided on the outer circumference of the tail part, and the direction position orthogonal to the two steering wings. A control device for a flying vehicle, comprising two spoiler-type steering mechanism steering wings.