JP2014137203A - Range shortening device of rocket - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a range shortening device of a rocket, which has a simple structure and can select a range adaptably even after mounting to a launcher.SOLUTION: A range shortening device 30 for a rocket 15 is equipped with a rocket motor 20 which comprises a motor case 21 having an axis A extending in the longitudinal direction and having a propellant in the inside, and a nozzle 22 provided in communication with a rear end 21b of the motor case 21 and jetting gas generated from the propellant. The range shortening device comprises a plurality of flare plates 31 mounted to a rear end part 21d of an outer peripheral surface 21c of the motor case 21 to be swingable between an inner side and an outer side of an outer peripheral surface 20a of the rocket motor 20, and a drive device 40 driving the respective flare plates 31 for swinging between the inner side and the outer side of the outer peripheral surface 20a of the rocket motor 20.

Description

  The present invention relates to a rocket bullet shortening apparatus.

“Range” is the horizontal linear distance from the origin of the trajectory (hereinafter simply referred to as the origin) to the falling point.
The “ballistic origin” is the position of the center of gravity of the bullet at the moment of launch, and the “drop point” is the intersection of the horizontal plane including the origin and the trajectory.

  The range of the rocket is determined by the shape of the rocket, the amount and composition of the propellant of the rocket motor, the grain shape, and the like. Therefore, the range of rockets is determined at the time of manufacture.

However, when actually using a rocket, if the target is located closer to the origin than the drop point, that is, if the distance from the launch position to the target is shorter than the range, the rocket can not be used.
For this reason, techniques for shortening the range of rockets (hereinafter referred to as “short range”) have been developed.

FIG. 1 is an explanatory view of a conventional rocket projectile shortening device 1.
In a conventional rocket bullet shortening device 1 described in Patent Document 1, an igniter 5 including an igniting agent 4 is accommodated in an axial center portion of a rocket motor chamber 3. A propellant 7 is filled around the ignition device 5. The propellant 7 is formed with a thrust interruption port 6 extending obliquely forward from the axial center, and the tip of the thrust interruption port 6 is blocked. It is.

  When the range of the rocket is shortened, the thrust interruption port 6 is opened by a pyrotechnic or the like, and a flame generated by burning the propellant 7 is released from the thrust interruption port 6. Thereby, the flame emitted from the thrust interruption port 6 acts as a reverse injection force larger than the thrust in the traveling direction, and interrupts the thrust of the rocket motor. Alternatively, by releasing the flame from the thrust interruption port 6, the pressure in the rocket motor chamber 3 is lowered to stop the combustion of the propellant 7, thereby shortening the range of the rocket bullet.

FIG. 2 is an explanatory diagram of another conventional rocket 8 shortening device 9.
2 has a mechanism in which the leading portion 10 of the rocket bullet 8 can be removed. And before use, by attaching a drag ring 12 between the head 10 of the rocket bullet 8 and the main body 11 of the rocket bullet 8 and firing it, the drag ring 12 increases the air resistance and shortens the range of the rocket bullet 8 Was.

Japanese Patent No. 2904409

  In the rocket projectile shortening device 1 of Patent Document 1 described above, in order to interrupt the thrust, the thrust interrupting port 6 and a new pyrotechnic are required, the structure of the rocket is complicated, and the manufacturing cost is reduced. It was getting expensive.

Further, in the conventional short range device 9 for the rocket bullet 8 of FIG. 2, it takes time and effort to attach the drag ring 12.
Moreover, when the rocket 8 with the drag ring 12 attached is mounted in the launcher, the drag ring 12 cannot be removed. Therefore, it was not possible to respond flexibly when selecting the range.

  The present invention has been developed to solve the above-described problems. That is, an object of the present invention is to provide an apparatus for shortening the launch range of a rocket that has a simple structure and can select a range in a flexible manner even after being mounted on a launcher.

According to the present invention, a motor case having a shaft extending in the front-rear direction and having a propellant therein, a nozzle that is provided in communication with the rear end of the motor case and injects gas generated from the propellant backward, A rocket short range device including a rocket motor having
A plurality of flare plates attached to the rear end of the outer peripheral surface of the motor case so as to be swingable between the inner side and the outer side of the outer peripheral surface of the rocket motor;
There is provided a device for shortening the launch range of a rocket bullet, characterized in that it includes a drive device that swings and drives each flare plate between the inside and outside of the outer peripheral surface of the rocket motor.

The drive device has a link rod having one end rotatably connected to the flare plate and extending inside the rocket motor;
An actuator connected to the other end of the link rod and moving so that each flare plate swings between the inside and outside of the outer peripheral surface of the rocket motor;
And a control device for controlling the actuator.

The actuator is a ball screw including a screw shaft that is rotated by a motor and a nut that is screwed onto the screw shaft,
The other end of the link bar is connected to the nut.

Alternatively, the actuator is a cylinder that slides a rod along a cylindrical outer cylinder connected to a rocket motor,
The other end of the link rod is connected to the tip of the rod.

  Each flare plate is an arcuate surface along the outer peripheral surface of the rocket motor, is present on a plane in contact with the outer peripheral surface of the rocket motor, and is densely swingable about a rotation axis orthogonal to the axis. Attached to.

  Further, the driving device is installed between the outer wall of the rear end of the motor case and the outer wall of the nozzle.

  According to the rocket projectile shortening apparatus of the present invention described above, the structure is simple because the shortening apparatus includes a plurality of flare plates and a drive device, and the drive device includes a link rod, an actuator, and a control device. It is.

  In addition, a control device that receives the operation command wirelessly is provided, and the actuator moves the flare plate by a control signal output from the control device, so that the range of the rocket can be selected even after the rocket is mounted on the launcher. .

It is explanatory drawing of the short range apparatus of the rocket bullet of a prior art example. It is explanatory drawing of the short range apparatus of the rocket bullet of another prior art example. It is a block diagram of a rocket bullet provided with the short range shortening apparatus of this invention. It is an expansion explanatory view of the short range shortening device of a 1st embodiment of the present invention. It is expansion explanatory drawing of the short range shortening apparatus of 2nd Embodiment of this invention.

  Hereinafter, embodiments of the present invention will be described with reference to the drawings. In addition, the same code | symbol is attached | subjected to the common part in each figure, and the overlapping description is abbreviate | omitted.

FIG. 3 is a configuration diagram of the rocket bullet 15 provided with the short range shortening device 30 of the present invention. FIG. 3A shows a case where the flare plate 31 is installed on the rear end portion 21d of the outer peripheral surface 21c of the motor case 21 so that the outer wall surface 31a of the flare plate 31 is disposed as an extension of the outer peripheral surface 20a of the rocket motor 20. FIG. 3B is a configuration diagram when the flare plate 31 is swung outward from the outer peripheral surface 20 a of the rocket motor 20.
Hereinafter, the flare plate 31 is arranged so that the outer wall surface 31a of the flare plate 31 is an extension of the outer peripheral surface 20a of the rocket motor 20, that is, the outer wall surface 31a of the flare plate 31 is flared along the outer peripheral surface 20a of the rocket motor 20. The installation of the plate 31 is referred to as “closing the flare plate 31”, and the installation of the flare plate 31 so that the outer wall surface 31a of the flare plate 31 intersects the axis A is referred to as “opening the flare plate 31”. In addition, “close the flare plate 31” and “open the flare plate 31” together are “open and close the flare plate 31”.

  The rocket bullet 15 provided with the short range apparatus 30 of the present invention includes a rocket motor 20 having an axis A extending in the front-rear direction. The front part of the rocket 15 may be a pointed head or a circular head.

The rocket motor 20 includes a motor case 21 having a propellant therein, and a nozzle 22 that is provided in communication with the rear end 21b of the motor case 21 and injects gas generated from the propellant backward.
The rocket motor 20 has an outer peripheral surface 20a centering on an axis A extending in the front-rear direction. The outer peripheral surface 20a is preferably a hollow cylinder. However, the present invention is not limited to this, and the cross-sectional shape of the outer peripheral surface 20a orthogonal to the axis A may be a polygon.

  The motor case 21 is filled with propellant. A plurality of flare plates 31 are installed at the rear end 21 d of the outer peripheral surface 21 c of the motor case 21 so as to be swingable between the inner side and the outer side of the outer peripheral surface 20 a of the rocket motor 20.

  The nozzle 22 is provided in communication with the rear end 21b of the motor case 21 and injects gas generated from the propellant backward. The shape of the nozzle 22 may be conical or bell-shaped.

FIG. 4 is an enlarged explanatory view of the short range shortening device 30 according to the first embodiment of the present invention. FIG. 4A is an explanatory diagram when the flare plate 31 is closed, and FIG. 4B is an explanatory diagram when the flare plate 31 is opened to the first stage. FIG. 4C is an explanatory diagram when the flare plate 31 opens to the second stage.
The short range shortening device 30 includes a plurality of flare plates 31 and a driving device 40. The drive device 40 includes a link bar 32, an actuator 33, and a control device 34.

The flare plate 31 is attached to the metal fitting 21e of the rear end portion 21d of the outer peripheral surface 21c of the motor case 21 so as to be able to swing between the inner side and the outer side of the outer peripheral surface 20a of the rocket motor 20.
When the flare plate 31 is closed, the outer wall surface 31 a of the flare plate 31 extends rearward from the rear end portion 21 d of the outer peripheral surface 21 c of the motor case 21. Preferably, when the flare plate 31 is closed, the outer wall surface 31a of the flare plate 31 may extend parallel to the axis A.

Each flare plate 31 is preferably an arc surface along the outer peripheral surface 20 a of the rocket motor 20. That is, the shape of the flare plate 31 is a curved plate, and the outer wall surface 31 a is an arc surface along the outer peripheral surface 20 a of the rocket motor 20.
However, the present invention is not limited to this, and the flare plate 31 may be a flat plate.

The metal fitting 21e attached to the rear end portion 21d of the outer peripheral surface 21c of the motor case 21 and one side of the flare plate 31 are present on a plane in contact with the outer peripheral surface 20a of the rocket motor 20 and are orthogonal to each other regardless of the axis A. A hinge provided with a rotating shaft 31b is provided, and each flare plate 31 is closely attached so as to be swingable about the rotating shaft 31b of the hinge.
However, the present invention is not limited to this, and other methods may be used for swinging the flare plate 31. The hinge rotation shaft 31 b may be provided on the outer peripheral surface 20 a of the rocket motor 20.

The drive device 40 drives each flare plate 31 to swing between the inner side and the outer side of the outer peripheral surface 20 a of the rocket motor 20.
The driving device 40 has one end 32 a rotatably connected to the flare plate 31 and connected to the link rod 32 extending inside the rocket motor 20 and the other end 32 b of the link rod 32, and each flare plate 31 is connected to the outer periphery of the rocket motor 20. The actuator 33 moves so as to oscillate between the inside and the outside of the surface 20a, and a control device 34 that controls the actuator 33.

The driving device 40 is preferably installed between the outer wall 21 a of the rear end 21 b of the motor case 21 and the outer wall 22 a of the nozzle 22. However, the present invention is not limited to this, and the driving device 40 may be provided at any part of the rear end portion 21d of the outer peripheral surface 21c of the motor case 21 as long as each flare plate 31 can swing.
The drive device 40 opens and closes the flare plate 31 so as to swing between the inner side and the outer side of the outer peripheral surface 20a of the rocket motor 20 by moving the other end 32b of the link rod 32 in the front-rear direction.

The actuator 33 according to the first embodiment is a ball screw 35 including a screw shaft 35b that is rotated by a motor and a nut 35c that is screwed to the screw shaft 35b. The other end 32b of the link bar 32 is connected to the nut 35c. . One end 32a of the link bar 32 is slidably connected to the inner wall surface 31c of the flare plate 31.
Then, when the flare plate 31 is opened, the actuator 33 moves the rocket motor 20 around the rotating shaft 31b provided at the rear end 21d of the outer peripheral surface 21c of the motor case 21 or the outer peripheral surface 20a of the rocket motor 20. Each flare plate 31 is swung between the inner side and the outer side from the outer peripheral surface 20a.

One end 32 a of the link bar 32 is connected to the inner wall surface 31 c of the flare plate 31, and the other end 32 b is pulled and moved by the actuator 33. The other end 32b of the link bar 32 of this embodiment is connected to the nut 35c.
The inclination of the link bar 32 with respect to the axis A is greater when the flare plate 31 is open than when it is closed. That is, the distance in the front-rear direction between the one end 32a and the other end 32b of the link bar 32 when the flare plate 31 is closed is larger than when the flare plate 31 is open. When the other end 32b of the link bar 32 moves toward the one end 32a in the front-rear direction, the inner wall surface 31c is pushed by the one end 32a, and the flare plate 31 moves outward from the outer peripheral surface 20a of the rocket motor 20 around one side. Swing open.

The control device 34 is also installed between the outer wall 21 a of the rear end 21 b of the motor case 21 and the outer wall 22 a of the nozzle 22. Further, the control device 34 controls the actuator 33 by outputting a control signal to the actuator 33 in accordance with an operation command for controlling the movement of the actuator 33.
The control device 34 controls the movement of the actuator 33 to adjust the timing for opening the flare plate 31 and the angle for opening the flare plate 31. The timing for opening the flare plate 31 is preferably measured by the number of seconds or altitude after the launch or the distance from the launch point.

  The operation command received by the control device 34 is preferably transmitted wirelessly from the outside of the launcher or remotely.

  Further, the short range device 30 includes a battery 36 that supplies power to the control device 34 and the motor 35a. The battery 36 is also preferably installed between the outer wall 21 a of the rear end 21 b of the motor case 21 and the outer wall 22 a of the nozzle 22. The battery 36 may be integrated with the control device 34.

Next, the usage method of the short range apparatus 30 of the rocket bullet 15 of 1st Embodiment is demonstrated.
(1) An operation command is transmitted to the control device 34 wirelessly after or before the rocket 15 is mounted on the launcher, and then the rocket 15 is fired. The flare plate 31 is preferably closed and the rocket bullet 15 is mounted.
(2) The control device 34 outputs a control signal to the actuator 33 at a predetermined timing.

(3) When the control signal is input to the actuator 33, the screw shaft 35b is rotated by the motor 35a, and the nut 35c is moved toward the one end 32a at a distance in the front-rear direction. Accordingly, the inner wall surface 31c of the flare plate 31 is pushed by one end 32a of the link bar 32, and the flare plate 31 swings outside the outer peripheral surface 20a of the rocket motor 20 around one side and is opened.

  FIG. 5 is an enlarged explanatory view of the short range shortening device 30 according to the second embodiment of the present invention. FIG. 5A is an explanatory view when the flare plate 31 is closed, and FIG. 5B is an explanatory view when the flare plate 31 is opened to the first stage. FIG. 5C is an explanatory diagram when the flare plate 31 opens to the second stage.

The actuator 33 of the short range shortening device 30 of the second embodiment of the present invention is a cylinder 37 that slides a rod 37b along a cylindrical outer cylinder 37a connected to the rocket motor 20. The cylinder 37 is preferably a hydraulic cylinder. However, the invention is not limited to this, and a pneumatic cylinder or an electric cylinder may be used.
Further, the outer cylinder 37a of the cylinder 37 is preferably connected to the motor case 21 or the nozzle 22 in a swingable manner.

The other end 32b of the link rod 32 of the present embodiment is pivotably connected to the tip of the rod 37b. In addition, this embodiment preferably has an auxiliary link bar 38.
The auxiliary link rod 38 is preferably connected at one end 38 a to the other end 32 b of the link rod 32 and the rod 37 b in a swingable manner and at the other end 38 b to the motor case 21 or the nozzle 22 in a swingable manner.

The auxiliary link bar 38 may not be provided. In that case, the outer cylinder 37 a is preferably fixed to the motor case 21 or the nozzle 22.
Other configurations of the short range shortening device 30 of the second embodiment are the same as those of the first embodiment.

  According to the above-described short range device 30 of the rocket bullet 15 according to the present invention, the short range device 30 includes the plurality of flare plates 31 and the drive device 40, and the drive device 40 includes the link rod 32, the actuator 33, and the control device. Therefore, the structure is simple.

  In addition, a control device 34 that wirelessly receives an operation command is provided, and the actuator 33 moves the flare plate 31 by a control signal output from the control device 34. Therefore, the range of the rocket bullet 15 even after the rocket bullet 15 is mounted on the launcher. Can be selected.

  Note that the present invention is not limited to the above-described embodiment, and it is needless to say that various modifications can be made without departing from the gist of the present invention.

1 Short-range device,
3 rocket motor chamber, 4 ignition powder,
5 ignition device, 6 thrust interruption port, 7 propellant,
8 rockets, 9 short range device,
10 head, 11 body,
12 Drag ring,
15 Rocket,
20 rocket motors,
20a The outer peripheral surface of the rocket motor,
21 motor case, 21a outer wall of motor case,
21b Rear end of motor case,
21c The outer peripheral surface of the motor case,
21d rear end, 21e bracket,
22 nozzle, 22a outer wall of nozzle 22,
30 Short-range device,
31 flare plate, 31a outer wall surface,
31b rotating shaft, 31c inner wall surface,
32 link rod, 32a one end, 32b other end,
33 Actuator, 34 Control device,
35 ball screw, 35a motor,
35b screw shaft, 35c nut,
36 batteries,
37 cylinders,
37a outer cylinder, 37b rod,
38 Auxiliary link bar,
38a one end, 38b other end,
A axis

Claims (6)

A rocket motor having a shaft extending in the front-rear direction and having a propellant therein, and a nozzle provided in communication with the rear end of the motor case and injecting a gas generated from the propellant backward. A device for shortening the range of rockets,
A plurality of flare plates attached to the rear end of the outer peripheral surface of the motor case so as to be swingable between the inner side and the outer side of the outer peripheral surface of the rocket motor;
A device for shortening the launch range of a rocket, comprising: a drive device that drives each flare plate to swing between an inner side and an outer side of the outer peripheral surface of the rocket motor. The drive device has a link rod having one end rotatably connected to the flare plate and extending inside the rocket motor;
An actuator connected to the other end of the link rod and moving so that each flare plate swings between the inside and outside of the outer peripheral surface of the rocket motor;
The rocket projectile shortening device according to claim 1, comprising: a control device that controls the actuator. The actuator is a ball screw including a screw shaft that is rotated by a motor and a nut that is screwed onto the screw shaft,
The short-range device for a rocket bullet according to claim 2, wherein the other end of the link bar is connected to the nut. The actuator is a cylinder that slides a rod along a cylindrical outer cylinder connected to a rocket motor,
The rocket bullet shortening device according to claim 2, wherein the other end of the link rod is connected to a tip of the rod.   Each flare plate is a circular arc surface along the outer peripheral surface of the rocket motor, is present on a plane in contact with the outer peripheral surface of the rocket motor, and is densely swingable about a rotation axis that is orthogonal to the axis without intersecting the axis. The rocket bullet range-reducing device according to claim 1, wherein the rocket bullet range-attaching device is attached. 2. The rocket bullet shortening device according to claim 1, wherein the driving device is installed between an outer wall of a rear end of the motor case and an outer wall of the nozzle. 3.

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