JP2019078423A - Drum body sliding device and method thereof - Google Patents

Abstract

To provide a drum body sliding device and a method thereof which can make a flying body for a long range that flies within atmosphere launch, and make the flying body fly within a long range.SOLUTION: This invention is a drum body sliding device 2 which comprises a launcher 7 to launch a flying body 5 that stores inside by a drum body sliding method. The launcher 7 has a plurality of rollers 9. The plurality of rollers 9 are respectively arranged with intervals in the airframe axis direction and the circumferential direction of the flying body 5 which is stored in the launcher 7, and are provided to be able to rotate freely in the airframe axis direction as coming in contact with an outer face of the flying body 5.SELECTED DRAWING: Figure 4

Description

  The present invention relates to a fuselage gliding device and method for launching a projectile such as a rocket.

  As a gliding device of this type of projectile, there is a device for providing a shoe engaged with the launch rail at least on the head side and the tail side on the body surface of the rocket to guide the rocket at the time of launch . Besides, as described in Non-Patent Document 1, there are various rocket bullet restraint systems.

“Handbook of Firearms and Ammunition Technology”, General Defense Foundation Defense Technology Association, April 23, 2012, p. 707

  Heretofore, as a method for launching rockets in the launch cylinder, there have been a fuselage sliding method, a lower shoe sliding method, and a hanging shoe sliding method.

The fuselage sliding method is to slide on the surface of the fuselage at the time of launch of the rocket.
Recently, there has been a demand for longer range of rockets to be launched from fuselage planners. For long range rockets that fly into the atmosphere, it is necessary to apply insulation to the body surface.
However, when using the conventional fuselage glide method, the heat insulating material is damaged by the friction with the launch rail. Therefore, this method could not be adopted for rockets for long range flight in the atmosphere.

  FIG. 1 is an explanatory view of a conventional launcher 27 and rocket bullet 25 adopting the lower shoe slide system. 1A is a perspective view, FIG. 1B is a longitudinal sectional view, and FIG. 1C is a transverse sectional view.

  As shown in FIG. 1 (A), FIG. 1 (B) and FIG. 1 (C), the lower shoe gliding system is launched while the shoe 31 provided on the body surface of the rocket bullet 25 supports the rocket bullet 25. It is a method of sliding on a rail. A launch rail 29 of this type is provided under the rocket bullet 25 inside the launch barrel.

FIG. 2 is an explanatory view of a conventional launch tube 27 and rocket bullet 25 adopting the suspension shoe sliding method. 2A is a longitudinal sectional view, and FIG. 2B is a transverse sectional view.
As shown in FIG. 2 (A) and FIG. 2 (B), the suspension shoe sliding method is a method in which the shoe 31 provided on the surface of the rocket shell 25 is made to slide along the firing rail 29 in a suspended state. is there. A launch rail 29 of this type is provided on the rocket shell 25 inside the launch barrel.

As described above, in order to adopt the lower shoe sliding method and the suspension shoe sliding method, it is necessary to attach the shoes 31 to the surface of the rocket shell 25 fuselage surface.
However, when the shoe 31 is provided, the air resistance increases due to the projection of the shoe 31 during the flight of the rocket bullet 25 and the range of the rocket bullet 25 becomes short. Further, since the heat insulating material can not be provided in the portion where the shoes 31 are provided, there is a problem that heat flows into the rocket bullet 25 from the portion where the shoes 31 are provided.

  In the lower shoe sliding method and the hanging shoe sliding method, the rocket 31 is prevented from moving in the launch tube by fixing the shoe 31 with a fixing tool such as a bolt when moving the moving object.

  The present invention has been made to solve the above-mentioned problems. That is, an object of the present invention is to provide a body gliding device and method capable of causing a long range flight object flying in the atmosphere to be launched and a long range flight.

According to the apparatus of the present invention, the apparatus comprises a launch tube for launching a projectile accommodated therein;
A plurality of fuselage gliding devices having a plurality of rollers disposed at intervals in the machine axis direction and circumferential direction of the projectile accommodated in the inside of the discharge tube, and capable of freely rotating in the machine axis direction while in contact with the peripheral surface of the projectile Is provided.

Further, according to the method of the present invention, the projectile is accommodated inside, and a launcher capable of firing the projectile is prepared;
A plurality of rollers, which can freely rotate in the axial direction of the projectile while being in contact with the circumferential surface of the projectile accommodated in the interior of the launcher, are spaced apart in the machine axial direction and circumferential direction respectively inside the launcher A torso gliding method is provided for placement.

According to the apparatus and method of the present invention described above, the roller rotates along the peripheral surface of the projectile because it has a plurality of rollers rotatable in the axial direction while in contact with the peripheral surface of the projectile. As a result, since the roller guides the projectile in the axial direction at the time of launch, the launch rail and the shoe are not necessary for launch of the projectile.
Therefore, even with a long range flying object flying in the atmosphere, the air resistance does not increase and the range becomes short.

  Moreover, since the roller is provided so as to freely rotate, when the projectile is fired, the roller rotates in accordance with the movement of the projectile. Therefore, since friction hardly occurs between the projectile and the roller, the projectile can be launched without damaging the heat insulating material applied to the circumferential surface.

  In addition, since the projectile is not provided with a shoe, air resistance during flight can be reduced more than conventional rockets. Therefore, the range of the projectile can be further extended.

It is explanatory drawing of the conventional launch tube and projectile which employ | adopted the downward shoe slide system. It is explanatory drawing of the conventional launch tube and projectile which employ | adopted the suspension shoe sliding system. It is an explanatory view of a launcher provided with a fuselage gliding device of the present invention. It is an explanatory view of each ejection pipe of an embodiment of the present invention. It is explanatory drawing of the roller of embodiment of this invention. It is an explanatory view of operation of a stopper mechanism of an embodiment of the present invention.

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

FIG. 3 is an explanatory view of a launcher 1 provided with the torso sliding device 2 according to the embodiment of the present invention. FIG. 3A is a perspective view of the launcher 1, and FIG. 3B is a perspective view of the launch tube 7.
For example, as shown in this figure, the fuselage gliding device 2 of the present embodiment may be provided to the launcher 1 together with the moving body 3. The body planing device 2 of the present embodiment is provided with a launch tube 7.

In the embodiment of this figure, the mobile 3 is a vehicle. However, the mobile body 3 of the present invention is not limited to this, and may be an aircraft, a ship, or the like.
The mobile unit 3 moves with the torso sliding device 2 mounted. In the movable body 3 of this embodiment, a plurality of launch tubes 7 are provided in parallel with the front facing in the same direction. For example, twelve launch tubes 7 in the example of this figure are provided for one mobile unit 3.
However, the invention is not limited thereto, and one mobile unit 3 may have only one launcher 7 mounted thereon.

  Also, for example, the firing barrel 7 may be provided so as to be able to swing around a rotation axis orthogonal to the axis 5 a of the flying object 5 on the moving body. As a result, the movable body 3 in the example shown in the drawing maintains the launch tube 7 horizontally during movement, and inclines the launch tube 7 at the projection angle when the projectile 5 is fired.

The launcher 7 has both a function as a container for accommodating the projectile inside at the time of transportation and a function as a launcher when the projectile is launched. The projectile 5 is transported while being accommodated in the inside of the launch tube 7, and is fired directly from the launch tube 7 at the time of launch. The projectile 5 is preferably, for example, a rocket, but is not limited thereto.
The launch tube 7 in this figure has a rectangular parallelepiped shape extending in the axial direction of the projectile 5, but may have a cylindrical shape. A detachable front cover 7 a and a rear cover 7 b are provided at the front end portion and the rear end portion of the firing barrel 7.

FIG. 4 is an explanatory view of each launch tube 7 of the embodiment of the present invention. 4A is a longitudinal sectional view, FIG. 4B is a transverse sectional view, and FIG. 4C is an enlarged view of a portion P of FIG. 4B.
FIG. 5 is an explanatory view of the roller 9 according to the embodiment of this invention. 5A and 5B are spherical rollers 9, FIG. 5C is an ellipsoidal roller 9, and FIG. 5D is a recess on the outer peripheral surface along the peripheral surface of the projectile 5. It is explanatory drawing of roller 9 of substantially cylindrical shape.
As shown in these figures, the firing barrel 7 has a plurality of rollers 9, a roller support device 11, and a stopper mechanism 13.

A plurality of rollers 9 are arranged at intervals in the axial direction and circumferential direction of the flying object 5 accommodated in the inside of the launch tube 7 respectively. Each of the rollers 9 is in contact with the circumferential surface of the flying object 5 and is supported by the roller supporting device 11 so as to be freely rotatable in the axial direction. For example, as shown in FIG. 4 (B), the roller 9 may be provided rotatably in the machine axis direction by having a rotation axis 9a extending in the direction orthogonal to the machine axis 5a of the flying object 5.
However, not only that, the roller 9 may be provided so as to be freely rotatable in any direction. For example, as shown in FIG. 5A, the roller support device 11 can rotatably support the roller 9 in any direction by rolling the roller 9 inside the spherical holding hollow 11a. In this case, the holding hollow 11a has an opening 11b smaller than the diameter of the roller 9 on the side of the projectile. A part of the roller 9 protrudes from the opening 11 b and contacts the body surface of the flying object 5.

The roller 9 preferably has a non-slip layer 9 b on the outer peripheral surface thereof. The non-slip layer 9 b is a layer that improves the coefficient of friction with the projectile 5. The non-slip layer 9 b may be, for example, a layer of rubber or resin.
Since the roller 9 has the anti-slip layer 9b, the movement of the flying object 5 can be stopped by the friction with the anti-slip layer 9b when the rotation of the roller 9 is stopped by the stopper mechanism 13 described later.

  For example, the roller 9 in the embodiment of FIG. 4 is provided in a cylindrical shape. However, the shape of the roller 9 of the present invention is not limited to this.

As shown in FIG. 5 (B), FIG. 5 (C) and FIG. 5 (D), the roller 9 of the present embodiment has a spherical or ellipsoidal body or a recess along the circumferential surface of the projectile 5 as the outer circumferential surface. It may have a substantially cylindrical shape.
For example, the rotary shaft 9a of the roller 9 in FIG. 5B is supported at both ends, and the center is bent at two points. The plurality of spherical rollers 9 are freely rotatably passed through the bent rotational shaft 9a.

The roller support device 11 is a device that supports the roller 9 so as to freely rotate.
The roller support device 11 of the embodiment shown in FIGS. 4 and 5 supports the rotation shafts 9 a of the plurality of rollers 9 in which one roller support device 11 extends in different directions. Each of these rotary shafts 9a is orthogonal to the machine shaft 5a.
However, the roller support device 11 of the present invention is not limited to this. For example, one roller support device 11 may support one roller 9 and a plurality of roller support devices 11 may be provided at opposing positions in the inside of the discharge cylinder.

  As shown in FIG. 4B, the plurality of roller supporting devices 11 arranged at intervals in the circumferential direction of the flying object 5 are provided at mutually opposing positions with the flying object 5 interposed therebetween. It is preferable that the plurality of roller support devices 11 be provided so as to face the upper and lower portions inside the launch cylinder with the projectile 5 interposed therebetween. As a result, the flying object 5 can be fired without the air axis 5a of the flying object 5 being shaken.

  Further, a plurality of these roller support devices 11 are provided at intervals in the machine axis direction of the projectile 5. As a result, the projectile 5 can be fired while maintaining the axis 5 a parallel to the launch cylinder 7 until the projectile 5 finishes coming out of the launch cylinder 7.

The stopper mechanism 13 is a device for stopping the movement of the projectile 5 in the axial direction.
For example, the stopper mechanism 13 may be a device that stops the movement of the flying object 5 in the axial direction by stopping the free rotation of the roller 9. However, the stopper mechanism 13 is not limited to this. For example, the stopper mechanism 13 includes an actuator fixed to the upper surface inside the discharge cylinder and an elastic member such as rubber attached to the tip thereof, and the projectile 5 is obtained by pressing the elastic member directly on the body surface of the projectile 5 May stop moving.

  The stopper mechanism 13 shown in FIG. 4 is a device for stopping the movement of the flying object 5 in the axial direction by stopping the free rotation of the roller 9. The stopper mechanism 13 in this figure has, for example, a contact portion 13a, an actuator 13b, and a control mechanism 13c.

The contact portion 13 a is a portion pressed against the roller 9 to stop the rotation of the roller 9.
The contact portion 13a may be, for example, a rod-like member or a plate-like member capable of coming into contact with the plurality of rollers 9 extending in the machine axis direction and spaced apart in the machine axis direction and the rotation shaft 9a. For example, the contact portion 13a shown in FIG. 4A is a rod-like member or a plate-like member whose front end is located forward of the frontmost roller 9 and whose rear end is located rearward of the rearmost roller 9. . Thereby, the contact part 13a of FIG. 4 (A) can move the roller 9 ranging from the foremost part located at the same position in the circumferential direction of the flying object 5 with one actuator 13b.
However, the contact portion 13a is not limited to this. The contact portion 13a may be, for example, a bearing provided at both ends of the rotary shaft 9a or a lock mechanism that locks the rotation of the rotary shaft itself. Moreover, the contact part 13a may be provided, respectively for each roller.

  FIG. 6 is an explanatory view of the operation of the stopper mechanism 13 according to the embodiment of this invention. 6 (A) and 6 (B) are explanatory views at the time of movement of the movable body 3, and FIG. 6 (C) and FIG. 6 (D) are explanatory views at the time of launch of the projectile 5. 6 (A) and 6 (C) are longitudinal sectional views of the discharge cylinder 7, and FIGS. 6 (B) and 6 (D) are front views of the stopper mechanism 13.

  As shown in this figure, the actuator 13 b moves the contact portion 13 a between the contact position 15 contacting the roller 9 and the non-contact position 17 not contacting the roller 9. The actuator 13 b may be an electric, pneumatic, hydraulic or electromagnetic direct acting actuator.

The control mechanism 13c is a control device that controls the drive of the actuator 13b.
When the moving body 3 moves or the torso gliding device 2 pivots or swings the launch tube 7, an inertial force is exerted on the projectile 5 inside the launch tube with the movement of the launch tube 7 due to the movement, and the projectile 5 tries to swing inside the launch tube 7.
In order to prevent this, the control mechanism 13c controls the actuator 13b so that the contact portion 13a is positioned at the contact position 15 as shown in FIG. 6B when the firing barrel 7 moves. The roller 9 is fixed by this. Since the non-slip layer 9b is applied to the outer peripheral surface of the roller 9 and the projectile 5 is sandwiched between the rollers 9 provided at opposing positions, the discharge tube 7 is moved even if the discharge tube 7 moves. Can prevent the projectile 5 from moving back and forth. Therefore, by having the stopper mechanism 13, the projectile 5 can be transported stably.

Further, when the projectile 5 is fired, the control mechanism 13c controls the actuator 13b so that the contact portion 13a is positioned at the non-contact position 17 as shown in FIG. 6 (D).
Thus, each roller 9 can freely rotate in the machine axis direction. Therefore, the aircraft 5 can be fired with the air shaft 5a stabilized without using the shoes 31.

Next, the method of gliding the torso according to the present invention will be described.
First, a launcher 7 capable of containing the projectile 5 inside and capable of firing the projectile 5 is prepared.
Next, a plurality of rollers 9 that can freely rotate in the axial direction of the projectile 5 accommodated in the inside of the launch cylinder are disposed inside the launch cylinder 7. A plurality of rollers 9 are disposed in contact with the circumferential surface of the flying object 5 housed inside the launch tube. Further, a plurality of rollers 9 are disposed at intervals in the machine axis direction and circumferential direction of the flying object 5 inside the launch tube, respectively.

  Next, the flying object 5 is accommodated between the rollers 9 arranged in the circumferential direction. Thereby, when the projectile 5 is fired, the roller 9 rotates in the axial direction along with the propulsion of the projectile 5, so that the space between the projectile 5 and the roller 9 is not damaged without damaging the circumferential surface of the projectile 5. The projectile 5 can be fired with almost no friction.

  Therefore, according to this method, it is possible to launch the long range flight vehicle 5 flying in the atmosphere by the body gliding method without using the launch rails 29 and the shoes 31.

  According to the apparatus and method of the present invention described above, the roller 9 rotates along the circumferential surface of the flying object 5 because it has a plurality of rollers 9 rotatable in the axial direction while in contact with the circumferential surface of the flying object 5. As a result, since the roller 9 guides the projectile 5 in the axial direction at the time of launch, the launch rail 29 and the shoe 31 are not necessary for the launch of the projectile 5.

Furthermore, since the roller 9 is provided so as to freely rotate, when the projectile 5 is fired, the roller 9 rotates in accordance with the movement of the projectile 5. Therefore, since friction hardly occurs between the projectile 5 and the roller 9, the projectile 5 can be fired without damaging the heat insulating material applied to the circumferential surface.
Therefore, even the long range flight vehicle 5 that flies in the atmosphere requiring the heat insulating material applied to the circumferential surface can be fired by the launch tube 7 of the fuselage sliding device 2.

  Further, since the shoe 31 is not provided to the flying object 5, the air resistance during flight can be reduced more than the conventional rocket bullet 25. Therefore, the range of the flying object 5 can be further extended.

  The present invention is not limited to the above-described embodiment, and it goes without saying that various modifications can be made without departing from the scope of the present invention.

1 launcher, 2 body gliding device, 3 moving body,
5 aircraft, 5a axis,
7, 27 launcher, 7a front cover, 7b rear cover,
9 rollers, 9a axis of rotation, 9b anti-slip layer,
11 roller support device, 11a holding hollow, 11b opening,
13 stopper mechanism, 13a contact part,
13b actuator, 13c control mechanism,
15 contact positions, 17 non-contact positions,
25 rockets, 29 launch rails,
31 Shoe

Claims (8)

Equipped with a launcher for launching the projectile housed inside,
A plurality of fuselage gliding devices having a plurality of rollers disposed at intervals in the machine axis direction and circumferential direction of the projectile accommodated in the inside of the discharge tube, and capable of freely rotating in the machine axis direction while in contact with the peripheral surface of the projectile . The roller has a cylindrical shape having a rotation axis orthogonal to the axis of the projectile,
The fuselage gliding device according to claim 1, wherein the launcher has a roller support device that supports a plurality of the rollers having rotation axes extending in different directions.   The torso gliding device according to claim 2, wherein the plurality of roller support devices arranged at intervals in the circumferential direction of the projectile are provided at positions facing each other with the projectile interposed therebetween.   The fuselage gliding device according to any one of claims 1 to 3, further comprising a stopper mechanism that stops movement of the projectile in the axial direction. The roller has an anti-slip layer on its outer peripheral surface to improve the coefficient of friction with the projectile,
The fuselage gliding device according to claim 4, wherein the stopper mechanism is a device for stopping movement of the projectile in the axial direction by stopping free rotation of the roller. The stopper mechanism is a contact portion which is pressed against the roller and stops the rotation of the roller.
An actuator for moving the contact portion between a contact position contacting the roller and a non-contact position not contacting the roller;
And a control mechanism that controls driving of the actuator.
The control mechanism is configured such that the contact portion is located at the contact position when the launch tube moves.
The fuselage gliding device according to claim 5, wherein the contact portion is controlled to be positioned at the non-contact position when the projectile is launched.   The fuselage gliding device according to claim 6, wherein the contact portion is a rod-like member or a plate-like member capable of contacting a plurality of the rollers extending in the axial direction and spaced apart in the axial direction. Prepare a launcher capable of containing the projectile inside and firing the projectile,
A plurality of rollers, which can freely rotate in the axial direction of the projectile while being in contact with the circumferential surface of the projectile accommodated in the interior of the launcher, are spaced apart in the machine axial direction and circumferential direction respectively inside the launcher How to place the torso gliding method.

Images