JPH04278200A - Attitude controller for missile - Google Patents

Abstract

PURPOSE:To provide an attitude controller for a missile, comparatively simple in the structure, light in the weight and capable of restricting the loss of a driving force. CONSTITUTION:In a rocket motor 1 equipped with steering winds and movable nozzles 6, a separating mechanism is provided which operates one part or all of the driving system for the steering wings and the movable nozzles 6 by the same driving source 21 and separates only the movable nozzles 6 from the driving system, is provided.

Description

[Detailed description of the invention]

0001

[Field of Industrial Application] This invention relates to an attitude control device for a flying object, which is used to control the attitude of a flying object and is equipped with both an aerodynamic control mechanism using a steering blade and a thrust direction control mechanism using a movable nozzle. It is.

0002

[Prior Art] Conventionally, mechanisms for controlling the attitude of a flying object include those using aerodynamic control and those using thrust direction control. In contrast, the latter type of thrust direction control operates independently of the presence of air because it directly controls the thrust direction; Examples of these methods include a movable nozzle method, a deflector method using a baffle plate, and a secondary injection method (for example, Japanese Patent Application Laid-Open No. 56-2354
No. 2, JP-A-61-155653).

[0003] Furthermore, there are flying bodies having a structure in which an auxiliary propulsion means is detachable from a main body of the flying body, which is equipped with a main propulsion means and control fins (for example, Japanese Patent Laid-Open No. 62-125
Publication No. 300).

Furthermore, in order to control the attitude of a flying object, some flying objects have a structure that has both aerodynamic control using steering wings and thrust direction control using movable nozzles.
An example is shown in FIGS. 4 to 7.

The flying object 51 shown in FIGS. 4 and 5 is roughly divided into a payload section 51a consisting of a guiding section, a warhead, etc., a rocket motor section 51b serving as a propulsion source for the flying object 51, and a control mechanism section 51c. be done.

The control mechanism 51c is provided to change the flight path of the flying object 51, and controls the control mechanism 51c.
2 and a thrust direction control mechanism using a movable nozzle 53.

FIG. 6 shows an example of the structure of the drive system of the aerodynamic control mechanism and the thrust direction control mechanism, in which the steering blade 52 has a rotation shaft 55 provided at the root of the blade facing toward the main body of the flying object. By fitting into the fixed steering blade bearings 56, 56, it is possible to rotate with respect to the flying object body, and one end side of a steering blade drive link 57 is fixed to the rotation shaft 55.

On the other hand, the movable nozzle 53, as shown in FIG. A nozzle bearing 62 is attached to the movable nozzle drive link 63 in a state in which a rotation shaft 61 is provided parallel to the rotation shaft 55 of the steering blade 52 and is fixed to the flying object body side.
, 62, it can be rotated relative to the flying object body.

The other end of the steering blade drive link 57 and the movable nozzle drive link 63 are pivotally connected via a connecting link 64 at pivot shafts 65 and 66, respectively.

Furthermore, a power transmission block 68 is pivotally connected to the other end of the steering blade drive link 57 via a pivot shaft 67, and this power transmission block 68 is connected to a rod 71a of an actuator 71. There is.

Therefore, in such a structure, when the actuator 71 operates, the advancement of the rod 71a causes the rotation of the steering blade 52 via the power transmission block 68, the steering blade drive link 57, and the rotation shaft 55 of the steering blade 52. is converted to At the same time, the rotation is converted into rotation of the movable nozzle 53 via the connecting link 64, the movable nozzle drive link 63, and the rotation shaft 61 of the movable nozzle 53.

[0012] As a result, aerodynamic control by the steering blade 52 and thrust direction control by the movable nozzle 53 are performed simultaneously.

FIG. 8 shows another structural example of the drive system of the aerodynamic control mechanism and the thrust direction control mechanism, in which the steering blade 5
The rotation shaft 55 of No. 2 is fixed to the center portion of a steering vane/movable nozzle drive link 74 fitted to the movable nozzle 53.
By fitting this rotation shaft 55 into the steering blade/movable nozzle bearing 73 fixed to the flying body side, the steering blade 5
2 and the movable nozzle 53 are rotatable relative to the flying object body.

[0014] Then, the steering vane/movable nozzle drive link 7
4 is pivotally connected to a power transmission block 68 via a pivot shaft 75, and this power transmission block 68 is connected to a rod 71a of an actuator 71.

Therefore, in such a structure, when the actuator 71 operates, the rod 71a moves forward through the power transmission block 68, the steering vane/movable nozzle drive link 74, and the rotation shaft 55 of the steering vane 52. 52 and the movable nozzle 53 are integrally rotated.

[0016] Also in this manner, aerodynamic control by the steering blade 52 and thrust direction control by the movable nozzle 53 are performed simultaneously.

FIG. 9 shows still another structural example of the drive system of the aerodynamic control mechanism and the thrust direction control mechanism, in which a movable nozzle drive link is used instead of the connecting link 64 in the structure shown in FIG. 63 is pivotally connected to another power transmission block 78 via a pivot shaft 77, and this power transmission block 78 is connected to a rod 79a of an actuator 79.

[0018] Therefore, in such a structure,
The operation of one actuator 71 causes the steering blade 52 to rotate, and the operation of the other actuator 79 causes the movable nozzle 53 to rotate, so that the aerodynamic control by the steering blade 52 and the thrust direction control by the movable nozzle 53 are independent of each other. It is supposed to be done.

[0019]

However, in such a conventional attitude control system for a flying object, as shown in FIGS. 6 and 8, the movable nozzle 53 of the steering blade 52 is driven by a common actuator 71. In such an attitude control device, one attitude control mechanism, for example, the thrust direction control mechanism using the movable nozzle 53, cannot be separated even after it becomes unnecessary, and the other attitude control mechanism, i.e. Even while aerodynamic control is being performed by the aerodynamic control mechanism using the steering blades 52, the movable nozzle 53 is always moving, and there is a problem in that the movement of the movable nozzle inevitably involves power loss. Ta.

Further, as shown in FIG. 9, the steering blade 52 and the movable nozzle 53 are connected to separate actuators 71, 7
In the case of an attitude control device that is driven by The problem was that the attitude control device became large and heavy because it was equipped with two drive mechanisms.

[0021]

OBJECT OF THE INVENTION The present invention has been made in view of the above-mentioned problems in the prior art. Since it is possible to drive the control mechanism and the thrust direction control mechanism, the attitude control device can be made relatively simple and lightweight without becoming bulky or heavy, and when the thrust direction control mechanism is no longer required, It is an object of the present invention to provide an attitude control device for a flying object, in which only a movable nozzle portion constituting the device can be separated in a large size, and driving force loss can be minimized.

[0022]

SUMMARY OF THE INVENTION (Means for Solving the Problems) The present invention includes a steering blade as an aerodynamic control mechanism and a movable nozzle as a thrust direction control mechanism, and connects the steering blade and the movable nozzle via a drive system. In a flying object equipped with a drive source for driving, the drive source is the same as a part or all of the drive system for the steering blade and the movable nozzle, and a separation mechanism is provided for separating only the movable nozzle part from the drive system. The structure of the flying object attitude control device is a means for solving the above-mentioned conventional problems.

[0023]

Effect of the Invention Since the flying object attitude control device according to the present invention has the above-described configuration, when the movable nozzle as a thrust direction control mechanism is no longer required, the movable nozzle can be removed from the drive system by the separation mechanism. Since only the movable nozzle section is separated, and therefore no power is required to drive the movable nozzle section, there is no loss of power consumed in driving the movable nozzle.

[0024]

DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be explained below based on the drawings.

FIGS. 1 to 3 are diagrams showing an embodiment of a flying object attitude control device according to the present invention.

FIGS. 1 and 2 show the structure of a flying object attitude control device according to the present invention.
A mirror plate 2 is provided on the tail side of the rocket motor 1, and a mounting base 3 for a flying object attitude control device is attached to the mirror plate 2.

A flange portion 4a of an extension tube nozzle 4 is fixed to the opposite side of the attitude control device mounting base 3 from the end plate 2, and is secured by an O-ring 5 provided between the extension tube nozzle 4 and the end plate 2. Airtightness is maintained.

At the outlet of the extension tube nozzle 4, movable nozzles 6 are provided in a substantially spherical pair. This movable nozzle 6 is attached to the attitude control device mount 3 via a gimbal 8, and the swing axes 8A, 8B of the gimbal 8 are attached to bearings 9a, 9b provided in the radial direction of the attitude control device mount 3. By supporting it, it is possible to swing together with the gimbal 8 in a direction perpendicular to the radial direction of the rocket motor 1.

In this case, near the center of the rocket motor 1, there is a piston 1 with a piston shaft 12a projecting in the radial direction.
2 is provided, and this piston 12 is biased in the centrifugal direction by the elastic force of a spring 13. Then, the tip of the piston shaft 12a is fitted between both ends of the retaining ring 11 fitted into the movable nozzle 6, and the retaining ring 1 is inserted into the movable nozzle 6.
The groove 8a of the gimbal 8 is expanded so that the aperture of 1 becomes larger.
By engaging with the movable nozzle 6, the movable nozzle 6 is fixed to the gimbal 8.

The gimbal 8 is equipped with a pivot portion 8c, and by connecting this pivot portion 8c and a power transmission block 22 driven by the drive source 21 via a pivot shaft 23, the drive source 21 can be controlled. By actuation, the movable nozzle 6
It is designed so that it can be swung.

[0031] Also, the swing axis 8 of the gimbal 8 on the outer surface side of the aircraft body
A steering blade mounting bracket 16 for attaching a steering blade (not shown) is attached with a screw 17, so that the driving source for the steering blade and the movable nozzle 6 is the same.

The rocket motor 1 further includes a potentiometer 25 for detecting the swing angle of the movable nozzle 6 that swings together with the gimbal 8.

The rocket motor 1 has a plurality of steering blades (not shown) serving as an aerodynamic control mechanism and a plurality of movable nozzles 6 serving as a thrust direction control mechanism in the circumferential direction. Built-in cylinder 32
It has multiple . The inside of these cylinders 32 is
It is in communication with a gas cylinder 30 filled with high-pressure gas provided on the attitude control mount 3 via a solenoid valve 31, and by opening the solenoid valve 31, high pressure is applied inside each of the plurality of cylinders 32. It is designed to supply gas.

Furthermore, the gimbal 8 is provided with a separation spring storage part 8d, and the separation spring 35 stored in this separation spring storage part 8d is attached to the retaining ring 1.
It is in a compressed state by the movable nozzle 6 fixed by 1.

The outer cylinder 37 surrounding the extension tube nozzle 4 and the like is screwed to the lower and upper ends of the attitude control device mounting base 3.

Here, it is also possible to use a gas generator instead of the gas cylinder 30, and in this case, the solenoid valve 3
1 will be replaced by an ignition device for operating the gas generator.

Next, the operation of the flying object attitude control device 1 having such a configuration will be explained.

At the beginning of flight of the projectile, the drive source 21
As a result of the operation, the power transmission block 22 moves in its axial direction, causing the gimbal 8 supported by the bearings 9a and 9b via the pivot shaft 23 to swing.

From this, the attitude of the rocket motor 1 is controlled by changing the direction of the movable nozzle 6 fixed to the gimbal 8 and at the same time changing the rudder angle of the unillustrated steering blade fixed to the gimbal 8. .

During the flight of the rocket motor 1, when the thrust direction control by the movable nozzle 6 is no longer necessary, when the solenoid valve 31 is opened by an electric signal, the high pressure gas in the gas cylinder 30 is released into each of the plurality of cylinders 32. The plurality of pistons 12 simultaneously move toward the center of the fuselage against the elastic force of the spring 13.

When the piston 12 moves toward the center of the aircraft, the tip of the piston shaft 12a comes off from between both ends of the retaining ring 11, and the retaining ring 11 contracts due to its own elastic force, reducing its diameter, and the gimbal 8 groove 8a
The retaining ring 11 will come off.

At this time, the movable nozzle 6 by the retaining ring 11
Since the restraint is released, the separation spring 35 is expanded by its elastic force, and the movable nozzle 6 and the separation spring 35 are separated from the gimbal 8 together with the retaining ring 11, as shown in FIG.

[0043]

As explained above, according to the attitude control device for a flying object according to the present invention, part or all of the drive system of the steering blade as an aerodynamic control mechanism and the movable nozzle as a thrust direction control mechanism is provided. Since the drive source is the same as that of the drive system, and the structure is equipped with a separation mechanism that separates only the movable nozzle section from the drive system, one drive system can control the steering blade as an aerodynamic control mechanism and the movable thrust direction control mechanism. Since it becomes possible to drive the nozzle, it does not have to be large and heavy like an attitude control device equipped with two drive systems, and can be made simple and lightweight. The movable nozzle as a direction control mechanism can be easily separated when it is no longer needed.
In addition to being able to suppress the loss of driving force, it is also possible to prevent a decrease in the thrust of the rocket motor.

[Brief explanation of the drawing]

FIG. 1 is a partially enlarged explanatory view of an embodiment of a flying object attitude control device according to the present invention, viewed from the tail side of a flying object.

FIG. 2 is an enlarged cross-sectional view of the flying object attitude control device shown in FIG. 1;

FIG. 3 is an operation explanatory diagram showing a state in which the movable nozzle from the flying object attitude control device shown in FIG. 1 is separated, partially in cross section.

FIG. 4 is a fragmented side view showing a state in which a conventional flying object attitude control device is installed on a flying object.

FIG. 5 is an explanatory bottom view showing a state in which a conventional flying object attitude control device is installed on a flying object.

FIG. 6 is an overall perspective explanatory view of the flying object attitude control device in FIG. 4;

FIG. 7 is an explanatory cross-sectional view showing a state of connection between a rocket motor nozzle and a movable nozzle.

FIG. 8 is an overall perspective explanatory view showing another conventional example of a flying object attitude control device.

FIG. 9 is an overall perspective view showing still another conventional example of a flying object attitude control device.

[Explanation of symbols]

1 Rocket motor (flying object) 6 Movable nozzle 11 Retaining ring (separation mechanism) 12 Piston (separation mechanism) 21 Drive source 30 Gas cylinder (separation mechanism) 31 Solenoid valve (separation mechanism) 35...Separation spring (separation mechanism)

Claims (1)

[Claims] Claim 1: Comprising a steering vane and a movable nozzle,
In a flying object equipped with a drive source that drives the steering vane and the movable nozzle via a drive system, the drive source is the same as part or all of the drive system for the steering vane and the movable nozzle, and
An attitude control device for a flying object, comprising a separation mechanism that separates only the movable nozzle portion from the drive system.