JP2001248999A - Launching machine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a launching machine capable of improving a flying performance of a missile and facilitating a loading operation for the missile. SOLUTION: This launching machine is characterized in that the same is comprised of a structure including an inner cylinder containing a missile therein with a wrap-around wing being stored in a barrel of the missile, a guide section formed along an axial direction of the inner cylinder to guide the inner cylinder into the launching machine, and a first electrical signal line connected from an external side to the missile; rail segments installed in the launching machine and formed to be fitted to the guide section of the structure loaded in the launching machine; a launching port formed at an outlet end surface of the missile in a launching direction; a second electrical signal line for transmitting a launching control signal for the missile; and an electrical connector for connecting the electrical wiring with the electrical signal line.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a projectile of a projectile such as a small rocket, and more particularly to a projectile of a projectile having a wraparound type deployable wing.

[0002]

2. Description of the Related Art As a device for launching a flying object from the ground or on a ship, there is a launcher including a launching tube and a support for the launching tube. To facilitate the work of loading projectiles into the launch tube,
A rail is installed on the launch tube, and the flying object is inserted along the rail. FIG. 2 shows a state in which the launching cylinder 3 on which the rail 4 is suspended and the flying object 8 are inserted. The flying object 8 is fixed by the fixing device 20 so as not to move due to the motion of the ship until immediately before the launch. This locking device is released by remote control just before firing. The flying object 8 slides along the rail 4 and accelerates.

[0003] In the conventional launching tube 3 and the flying body 8 described above, it is necessary to provide a projection 15 on the flying body to be fitted to the rail 4 installed on the launching tube. This projection is a small flying object,
A flying object without guidance control has a large effect on flight performance, and is difficult to mount. Further, in the case of the flying object shown in FIG. 2, the space for storing the flying object is increased by the amount by which the tail wing 14 protrudes. On the other hand, there is an attempt to reduce the storage space of the flying object by folding the wing.

[0004] For this purpose, a curved tail is wound around the body of the flying object so as to be wrapped around the body of the flying object, and a so-called wrap-around wing is used in which the curved tail deploys during flight. Sometimes. FIG. 3 shows a flying object having wrap-around wings. The wrap-around wings 9 are such that the wings can be deployed in a fan shape on the flying body with the axis 16 attached to the rear fuselage 18 of the flying body 8 as a center of rotation. The deployment of the wing is the rotation axis 1 described above.
6 is performed by the spring force of the coil 17 inserted into the coil 6.

FIG. 4 shows a state in which a projectile 8 having wraparound wings is mounted on a launch vehicle. The launcher is composed of a base 7, a column 6, a launch tube 3, and a drive device for raising and turning directions. However, the description of the driving device is omitted in FIG. With the wraparound wing 9 wound around the body of the flying object, the flying object 8 is loaded into the launch tube 3. At the time of firing, the projectile 8 starts to slide in the firing tube 3 by ignition of the propellant. The wrap-around wing 9 tries to expand by the spring force of the coil mounted on the rotating shaft, and slides while contacting the inner wall of the launch tube. Since the outer diameter of the flying object 8 and the inner diameter of the launching cylinder 3 are the same size, the flying object moves along the axial direction of the launching cylinder 3 with little rattling of the flying object in the launching cylinder. After leaving the launcher, there is nothing to restrain the wing deployment, so as shown in FIG.
The wings are deployed to a specified deployment angle by a spring force of a coil mounted on a rotating shaft, and generate a lift required for stable flight of the flying object. In the case of the launcher shown in FIG. 4, there is no auxiliary tool such as a rail in the launcher to reduce the load at the time of loading, so that loading the flying object requires labor.

On the other hand, considering the work of loading the projectile 8 into the launcher, the projectile confirms the soundness of the electronic circuit installed inside the body and its power supply by exchanging signals with the outside of the launcher immediately before launching. May be. In order to exchange (adjust) a series of signals before the launch, the flying object is wired with an electric signal line connected to a control unit (not shown) outside the launcher via the launcher. Since the external connection electric wire 36 such as the adjustment line is guided from the outside of the launcher, in the case of the structure of the launcher shown in FIG. Must be provided with an opening 19 reaching the inner surface of the launch cylinder from the outside. From this opening,
Since rainwater may infiltrate the inner surface of the launch cylinder, it is not possible to secure an unnecessarily large area, and conversely, it is difficult to wire the connection electric wire 36 at the time of wiring work to the flying object 8,
Wiring work efficiency is extremely poor. Upon completion of this wiring work, the flying object 8 is ready to fire. In other words, the electric wiring work makes the propellant of the flying object ignitable. Since the projectile contains explosives, etc. in addition to the propellant, electrical wiring work around these launchers is performed promptly, and the work time when loading the projectile is expected to be completed as short as possible. It is rare. In the launcher shown in FIG.
When the flying object 8 is to be fixed inside the launching cylinder, a fixing device cannot be installed in the launching cylinder. Therefore, a securing device that can be inserted into the launching cylinder from the outside through the side wall of the launching cylinder must be installed. It is necessary to provide an opening similar to the opening 19 for electric wiring on the side surface of the launch tube. There is a possibility that rainwater may enter from this opening as in the case of 19.

[0007]

In the above prior art,
In the case of the launching tube shown in FIG. 2, when applied to a small-sized projectile launcher having wraparound wings, the rail 4 for facilitating mounting on the launcher has a projection 1 fitted to the rail 4.
Since 5 is attached to the body of the flying object 8, the flying performance of the flying object is significantly affected. In addition, in the case of the launcher shown in FIG. 4, it takes a lot of effort to load the flying object, and it is difficult to attach electric wiring such as adjustment lines to the launcher when loading the flying object. The time required for it becomes enormous. The present invention has been made in view of the above points, and an object of the present invention is to provide a launcher capable of improving the flying performance of a flying object and facilitating the loading operation of the flying object. It is in.

[0008]

SUMMARY OF THE INVENTION In order to achieve the above object, a launcher according to the present invention is provided with a wrap formed so that curved wings are wound around a flying body and deployed at the time of launch. In a launcher that fires a flying object having around wings, an inner cylinder containing a flying object in which the wraparound wing is housed in a flying body, and formed along the axial direction of the inner cylinder, A structure provided with a guide portion for guiding an inner cylinder into the launcher, and a first electric signal line connected to the flying object from the outside, and installed in the launcher;
A rail portion formed to fit with a guide portion of the structure loaded in the launcher, a launch port formed on an exit end face of the launch vehicle in a launch direction, and a launch control signal of the launch vehicle , And an electric connector for connecting the electric wiring and the electric signal line.

[0009]

FIG. 1 shows an embodiment of the present invention. The flying object 8 having the wrap-around wing 9 is mounted on the inner cylinder 1 in a housed state in which the wrap-around wing 9 is wound around the body of the flying object. In this embodiment, the wrap-around wings 9 are provided so as to facilitate loading into the launcher without adding a projecting portion to the flying object 8 and to prevent the wrap-around wings from deploying in the launcher. Is wound around the body of the flying object 8, and the inner cylinder 1 having a cylindrical shape capable of containing the flying object 8 and having a small gap with the flying object 8 is used. A guide 2 extending in the axial direction of the cylinder is attached to the lower surface of the inner cylinder 1, and the inner cylinder 1 is formed as an integral structure 13 with the guide 2. A fixing device 2 that can enter and exit the inner surface of the inner cylinder and fixes the flying object is provided in the guide portion 2.
A wire mounting port 21 is provided for connecting an electrical wire 34 such as a zero and an adjustment wire or an ignition wire to a mounting portion 46 of the flying object 8.

[0010] The fixing device 20 is installed in the guide portion 2, and when the flying object 8 is fixed, the flying object fixing device 25 is moved from the fixing device opening 22 opened in the inner cylinder 1 to the flying object 8.
To push the flying object 8 against the inner cylinder surface opposite to the side where the fixing device 20 is installed, and fix the flying object 8 inserted into the inner cylinder to the inner cylinder surface. The vertical movement of the flying object fixture 25 electrically drives a driving means such as a screw drive. The connection wire 24 is drawn out of the guide portion from the rear of the guide portion through the inside of the guide portion 2. A series of flying object setting operations such as insertion, fixing, and connection of electric wiring of the flying object 8 in a state in which the wraparound wing 9 is wound around the body of the flying object 8 are performed by the inner cylinder of the launcher body. Before being installed at 10, the inner cylinder can be taken out of the launcher and performed independently of work around the launcher.

The launcher body 10 comprises a launching cylinder 3 capable of containing the inner cylinder 1, a support 6 for supporting the launching cylinder, and a base 7 on which the support 6 is installed. In addition, the rail unit 4 fitted to the guide unit 2 of the inner cylinder 1 is provided on the launcher body 10.
In addition, a connector that is connected to electric wiring led from the outside of the launcher body 10 is provided inside the launcher. Further, a discharge port 5 having a size equal to the outer diameter of the inner cylinder is formed on the end face in the front in the firing direction. Note that, in the launcher of the present embodiment, the description of the drive unit that moves the launching cylinder 3 up and down in the turning direction is omitted.

The rail 4 is installed in the launch tube 3 as described above. The integrated structure 13 in which the inner cylinder 1 in which the flying object 8 is inserted and the guide part 2 are integrally formed, the guide part 2 is fitted to the rail part 4 installed in the launching cylinder 3 of the launcher body 10. To be loaded into the launch tube 3. A ball or a roller is embedded in the sliding portion between the guide portion 2 and the rail portion 4 so that the integrated structure 13 can be smoothly loaded into the launcher body 10.

After the integrated structure 13 of the inner cylinder 1 and the guide part 2 is inserted, the guide part 2 is fixed to the rail part 4 by the guide part fixing device 11 provided behind the rail part 4, and The external connection connector 35 of the connection line 24 drawn out from the rear of the guide unit 2 is attached to the external connection outlet 12 installed at the rear of the launch direction for guiding electric wiring to the outside of the launcher. The external connection outlet 12 is connected to an external electric wire 47, and the launcher and the flying object are electrically connected to a launch control device or a launch control device (not shown) by the electric wire 47.

To attach the flying object 8 to the launcher body 10, the guide part 2 is fitted to the rail part 4, the guide part 2 is slid and inserted into the rail part 4, and after the insertion, the guide part 2 is fixed. Complete when you connect the electrical wiring. These operations are only for the rear part of the launching cylinder 3, and the inner cylinder 1 and the guide 2
After the insertion of the integrated structure 13 into the firing cylinder 3, the guide portion 2
, And only the connection of the connection line 24 to the connector, it is very easy to carry out and the working time can be shortened.

At the time of projectile launch, the projectile fixture 25 is driven by remote control to return to the position before the projectile fixation, that is, the state in which the projectile fixture 25 is stored in the guide portion 2. With the above operation, there is no object in the inner cylinder 1 that restricts the movement of the flying object 8 in the axial direction. In this state, when an ignition current is applied to the propellant of the projectile 8 by electric wiring from the outside of the launcher, the propellant burns and the projectile 8 starts to move forward in the axial direction of the inner cylinder. While the flying object 8 slides in the inner cylinder 1, the wrap-around wing 9 cannot be deployed due to the wall surface of the inner cylinder 1 and contacts the inner surface of the inner cylinder 1 in a state where a spring force for deployment acts. Go.

In contrast to the flying object 8 having the projection 15 shown in FIG. 2, the projection shown in FIG. 1 has no projection formed in the inner cylinder. There is no obstacle to the movement, and the flying object 8 slides smoothly in the inner cylinder 1. The flying object 8 is shot out of the launcher body 10 from the launch port 5 opened at the front end of the launch tube 3. The combustion flame of the propellant of the flying object 8 is discharged from the rear end of the inner cylinder 1 to the outside. Since the outer diameter of the inner cylinder 1 and the launch port 5 have the same size, the combustion flame of the propellant of the flying body 8 enters the inner cylinder 1 even after the flying body 8 jumps out of the launcher. However, it does not diffuse into the launch tube 3. For this reason,
Only the inner surface of the inner cylinder 1 is exposed to the combustion flame at the time of firing, and the inner surface of the launcher body 10 is not affected by the flame at all. After the projectile 8 has been fired, the portion exposed to the flame can be cleaned and removed by removing the inner cylinder 1 from the launcher body 10. Although the embodiment of FIG. 1 shows a case where the launching cylinder is one,
A similar effect can be obtained with a launcher having a plurality of launch cylinders.

According to this embodiment, the wrap-around wing 9
Since the projectile having wraparound wings can be loaded into the launcher without attaching necessary projections to the fuselage of the projectile 8 having the wingaround, the projectile having wraparound wings can be stably fly. There is an effect that it can be.

Further, in the configuration shown in FIG. 4, the fixing device 20 for the flying object 8 in the launching tube becomes an obstacle to the wraparound wing which starts deployment in the launching tube, and in some cases, the wing may be damaged. Was. On the other hand, in this embodiment, since the flying object fixing tool protruding from the inner surface of the inner cylinder 1 is drawn into the guide, there is no obstacle on the inner surface of the inner cylinder. When rubbing the cylinder surface, there is nothing obstructing the movement of the wings, and the flying object 8 smoothly slides inside the inner cylinder 1 and can obtain sufficient acceleration for the flight at the exit of the launcher.

In addition, in the case of the launcher shown in FIG. 4, it takes a lot of effort to load the flying object, and it is difficult to attach electric wiring such as adjustment lines to the launcher when loading the flying object. The time required to complete the loading operation was enormous.
On the other hand, in this embodiment, the operation of fixing the flying object 8 and attaching the adjusting line and the ignition wire can be performed independently of the operation around the launcher main body. The part 2 is slid into the rail part 4 and inserted, and only the fixing of the guide part 4 and the connection of the electrical wiring connector behind the launcher are performed, so that the fixing of the flying object until the launch becomes easy. The time required is significantly reduced,
There is an effect that the installation of the flying object on the launcher body becomes extremely easy. Although the inner cylinder 1 containing the flying object 8 becomes heavier than the single flying object, the loading of the
The guide portion 2 is slidably inserted into the rail portion 4 of the launcher body 10, so that it can be smoothly performed and the load at the time of insertion is small.

Since the connection of the electric wiring is only to connect the wiring drawn out from the guide portion 2 to the connector provided on the launcher side, no matter where the electric wiring take-out portion of the flying body 8 is located, Since the extraction of the electric wiring from the flying object 8 has been completed before the loading into the launcher body 10 of
Since the connection operation can be performed within a range sufficiently accessible from the rear part of the launcher, the electric wiring work around the launcher when the flying object is loaded becomes easy in an extremely short time.

Further, since the inside of the launcher is exposed by the flame of the propellant, soot and combustion emissions adhere thereto. For this reason, the launcher requires cleaning and maintenance inside the launcher every time it is fired.However, since the launcher has an elongated shape, and the launcher of a small projectile has a smaller inner diameter of the launcher, cleaning is necessary. It becomes difficult to remove. On the other hand, in this embodiment, since the inside of the launcher body 10 is not exposed to the combustion flame of the flying object 8,
There is almost no need for cleaning and maintenance of the launcher, and the maintenance of the launcher can be simplified. In the present embodiment, since the flame of the flying object 8 does not enter the launcher other than the inner surface of the inner cylinder 1, the launcher is not exposed to the flame by the launching of the flying object 8, and there is no sticking of combustion substances such as soot. Keeps clean. The inner cylinder 1 is pulled out from the launcher body after launching the flying object,
Since the inner surface can be moved to a place where it can be easily cleaned, maintenance including cleaning after firing can be facilitated.

As described above, according to the present embodiment, the inner cylinder for enclosing the flying object with the wraparound wing wound around the body of the flying object, and the fixture for fixing the flying object in the inner cylinder are provided. Uses an integrated structure in which a guide for installing electric wiring for guiding electric wiring from the flying object to the connection connector in the launcher is attached to the inner cylinder, and further installs a rail that fits with the above guide in the launcher As a result, the projectile can be smoothly loaded into the launcher without providing any projections on the fuselage part of the projectile, and the electric wiring of the adjustment line and ignition wire can be easily set when the launcher is loaded. This has the effect of shortening the time required for loading work. In addition, the projectile is securely fixed until immediately before launch, the inside of the projectile body after launch is not exposed to the projectile flame, and cleaning of the projectile body is almost unnecessary, so maintenance work is omitted. A projectile launching device having a wraparound wing that can be provided can be provided. In addition, since there is no need to provide a projection on the body of the flying object, there is an effect that a flying object having wrap-around wings can achieve stable flight.

FIG. 5 is a diagram showing another embodiment of the present invention. FIG. 5 is a diagram showing an integrated structure 13 of the inner cylinder 1 and the guide portion 2. In the following description, the description of the same configuration as that shown in FIG. 1 will be omitted. In the embodiment of FIG. 5, the flying object 8 has an opening 31 having a central axis in a direction perpendicular to the axial direction of the fuselage. At the rear end of the inner cylinder 1, a flying object fall prevention lid 33 having an opening 32 smaller than the outer diameter of the flying object is attached. The flying object fall prevention lid 33 is partially attached to the inner cylinder 1 by a hinge or the like, and can be opened and closed. FIG.
Indicates a state in which the flying object fall prevention lid 33 is opened.

The fixing device 20 is a flying object fixing device 2 that moves up and down in the inner cylinder 1 and the guide portion 2 through the fixing device opening 22.
5 and a projectile fixture support 2 for supporting the projectile fixture 25
6 and a fixture driving device 27 including an electric motor and the like. The rotational motion of the fixture driving device 27 is transmitted as a driving force of the vertical motion of the flying object fixture 25 by a drive transmission device such as a rack and a worm or a pinion. In FIG. 5, since the flying object 8 is not inserted into the inner cylinder 1, the flying object fixing device 25 has been returned to the guide portion 2, and no protrusion is present on the inner surface of the inner cylinder 1. Since the power source of the fixture driving device 27 is taken from outside the guide portion, the electric wiring 2
4 is attached.

The guide section 2 is provided with a projectile electric wiring mounting opening 28 for mounting an electric wiring 34 with a flying object connection connector such as an adjusting wire or an ignition wire to the flying object. The connector-equipped electrical wiring 34 can be mounted from outside the guide portion 2. Since the integrated structure 13 is mounted in the launching tube 3, there is no need to consider the prevention of rainwater infiltration directly with the outside air, so that the flying object electric wiring mounting opening 28 can be easily connected to the connector. A sufficiently large area can be opened.

The electric wiring 24 of the fixture driving device 27 and the electric wiring 34 with the flying object connecting connector are gathered in the guide connector 29 behind the guide 2 and drawn out of the guide. In this embodiment shown in FIG. 5, an external connection connector 35 is provided on the rear end face of the guide portion 2, and the electric wiring 24 of the fixture driving device 27 and the electric wiring 34 with the flying object connection connector are connected here. External connector 3
5 is drawn out of the guide section.

FIG. 6 shows a state in which a flying object 8 is installed in the inner cylinder 1 of FIG. Electricity supplied from a launch control device or a launch control device (not shown) is supplied to the fixture driving device 27 through an external connection electric wire 36 to move the projectile fixture 25 upward, and the projectile opening 3
Insert into 1. The flying object 8 is pressed against the lower surface of the inner cylinder by its own weight.
5 is securely fixed to the inner surface of the inner cylinder 1.

When the projectile 8 is fired, the projectile fixture 25 is pulled down by the fixture driving device 27 and removed from the projectile. Although the flying object is provided with the flying object connection connector 48, there is no other thing that restricts the flying object to the inner cylinder 1. Also, since the launch angle of the flying object 8 is normally set to be higher than the horizontal direction, when the flying object fixing device 25 is detached, the flying object 8 is caused to move by its own weight in the direction of the inner cylinder surface. Although it is pulled backward, the flying object 8 can be prevented from falling because the flying object fall prevention lid 33 is provided on the rear end face of the inner cylinder 1.

The combustion of the propellant of the projectile 8 causes the projectile 8
When the propulsive force is generated and the propulsive force reaches or exceeds the shear strength of the flying object connector 48, the flying object connector 48 is separated from the flying object and starts to slide.

According to the present embodiment, there is an effect that it is easy to install the flying object 8 in the inner cylinder 1 and to fix the flying object 8 before firing. Further, it is possible to prevent the set position of the flying object 8 from being shifted from the time after the release of the fixing of the flying object 8 at the time of launching to the launching, and there is an effect that the flying object 8 can be launched stably.

FIG. 7 is a diagram showing another embodiment of the present invention. FIG. 7 shows the launch tube 3 of the launcher body.
A rail 4 is provided on the lower surface of the launch tube 3. Also,
Behind the rail (left side in FIG. 7), a guide unit fixing device 1
1 and an external connection outlet 12 are provided. An end plate 37 is attached to the front end face of the firing cylinder (right side in FIG. 7) at a position coinciding with the height of the axial center line of the inner cylinder 1 and having a circular opening 5 having a center and having the same outer diameter as the inner cylinder. I have. Also,
A front door 38 that covers the opening is attached to the opening 5. The front door 38 rotates the outer surface of the front end plate 37 about the front door rotation shaft 40 by the front door driving device 39 installed in the firing tube 3 to open the firing port 5.
The front door driving device 39 has an electric wiring 50 guided from the outside of the firing tube 3 through an external outlet 49 so that the front door driving device 39 can be remotely operated. In addition, a rear lid 41 that can cover the entire end of the launch cylinder is attached to the rear end face of the launch cylinder 3. Similarly to the front lid 38, the rear lid driving device 42 can be driven by the electric wire 50 led from the external outlet 49, so that the opening and closing of the rear lid 41 can be remotely controlled.

The guide part of the integrated structure of the inner cylinder and the guide part is inserted in accordance with the rail part 4. After the insertion, the guide portion and the rail portion are fastened by the guide portion fixing device 11 behind the rail portion 4. Also, the external connection connector 35 (shown in FIG. 6) that is pulled out from the rear end of the guide portion is connected to the external connection outlet 12. By these three operations, the loading and fixing of the flying object to the launcher and the connection of the electric wiring are completed. When the front cover 38 and the rear cover 41 are closed, the launching tube can be sealed with the flying object loaded therein, so that rain and waves can be prevented from entering.

At the time of firing, the front lid 38 and the rear lid 41 of the firing cylinder are opened by remote control, and control signals from an external device such as a control device (not shown) are transmitted to the external electric wire 47, the external connection outlet 12 and It is transmitted to the flying object 8 and the fixing device 20 via the external connection electric wire 36. The projectile 8 is shot out of the projectile by a series of launching processes such as adjustment of the projectile 8, release of the fixture, ignition of the propellant, and the like. The wrap-around wings of the flying object 8 start to deploy when passing through the launch port 5 of the launch tube 3, but the front door 38 is opened parallel to the front end plate (two points of the front door in FIG. 7). (Dashed line), does not hinder wrap-around wing deployment. Furthermore, the combustion flame of the propellant is discharged to the rear and outside of the launching cylinder 3 through the inner surface of the inner cylinder,
Further, among the combustion flames discharged from the projectile 3 from the projectile 8 into the atmosphere, those that enter the launcher from the launch port are also exhausted to the rear of the projectile 3 through the inner tube 1.
Therefore, the inner surface of the launch cylinder 3 is not directly exposed to the flame of the flying object.

According to the present embodiment, when the projectile 8 is loaded into the launcher, the guide 2 of the integrated structure of the inner cylinder 1 and the guide 2 is inserted into the rail 4 and then the rail 4 is inserted. Part 4
Of the guide portion 2 by the guide portion fixing device 11 behind the
And the rail portion 4, and finally, the external connection electric wire 36 (described in FIG. 6) drawn from the rear end of the guide portion is connected to the external connection outlet 12. By these three operations, the loading and fixing of the flying object 8 to the projectile main body 10 and the connection of the electric wiring are completed, so that the operation time required for the loading is extremely reduced. Further, since the inside of the projectile main body is not exposed by the combustion flame of the propellant at the time of projectile launch, cleaning and maintenance of the projectile main body are significantly reduced.

FIG. 8 is a diagram showing another embodiment of the present invention. The embodiment shown in FIG. 8 has the same components as the embodiment shown in FIG.
Is attached to the upper surface side of the inner cylinder instead of the lower surface side. The flying object fixing device 25 does not insert into the specific opening of the flying object 8 but presses the body surface of the flying object 8.
Since the flying object 8 is pressed against the lower surface of the inner cylinder by its own weight,
By the pressing force of the flying object fixing device 25, the surface of the flying body is pressed uniformly over the inner cylinder surface in the axial direction. Therefore, the flying object 8 is securely fixed. Further, no special processing such as an opening for fixing is required on the body surface of the flying object 8.

FIG. 9 shows an integrated structure 13 of the inner cylinder 1 and the guide 2 in which the guide shown in FIG. 8 is mounted above the inner cylinder.
This shows the structure of the launching cylinder when the rocket is inserted into the launching cylinder 3, but the components are the same as those of the embodiment shown in FIG. However, the description of the drive device for opening and closing the rear door behind the launch tube (left side in FIG. 9) is omitted.

According to this embodiment, there is an effect that the flying object 8 can be securely fixed in the inner cylinder 1 without performing any specific processing on the body portion of the flying object 8. In addition, the integrated structure of the inner cylinder 1 and the guide unit 1 in which the flying body 8 that does not perform the specific processing is inserted into the body of the flying body 8 can be easily loaded into the launching cylinder, and the loading work around the launcher can be performed. There is an effect that the operation can be performed in an extremely short time. Furthermore, since the inside of the projectile main body is not exposed by the combustion flame of the propellant at the time of projectile launch, the cleaning maintenance of the projectile main body is significantly reduced.

In the above embodiment, the electric wiring connected to the flying object 8 has been described in the case where there is only one flying object connection connector. However, as shown in FIG.
Even in the case of a plurality of locations, the function of the integrated structure does not change. FIG. 10 shows an example in which the ignition wire 53 is separated from the adjustment line 34.
The inner cylinder 1 is provided with an opening 54 for passing an ignition wire. Although the number of connection lines to the flying object 8 increases, the number of openings to be opened in the wall surface of the inner cylinder 1 and the number of connection connectors 55 to the outside increase, the ease of loading the flying object 8 does not change. FIG.
In the embodiment, the ignition wire is made independent of the other electric signal lines, whereby there is an effect that misfire of the propellant can be prevented.

FIG. 11 is a diagram showing another embodiment of the present invention. In the embodiments described above, the electric wiring for adjustment is connected to the flying object via the flying object connection connector. FIG.
In this embodiment, the adjustment signal is transmitted to the flying object 8 by optical transmission instead of through a connector by solid contact. A photoelectric conversion device 56 that converts electricity into light or light into electricity is installed in the flying object connector 48. Further, a similar photoelectric conversion device 57 is installed on the flying body corresponding to the installation position of the photoelectric conversion device 56. The adjustment signal is transmitted to the photoelectric conversion device 5 on the integrated structure 13 side.
Light is transmitted as a transmission medium in a non-contact manner between the photoelectric conversion device 6 and the photoelectric conversion device 57 on the flying object 8 side.

In many cases, the flying object 8 has a power supply for executing various operations during flight. The power-on command itself is also provided by a regulating line (the electric wiring 34 with a flying object connector). Done through. For this reason, the flying object needs a power supply for operating the photoelectric conversion device 57 at the initial stage of adjustment. The photoelectric conversion device power supply line 58 is an electric line that supplies electricity to the photoelectric conversion device 57 from outside the flying object in the adjustment stage. In the embodiment of FIG. 11, although the ignition wire 53 and the power supply line 58 for the photoelectric conversion device are connected to the flying object from outside the flying object, many wirings required for adjustment do not depend on solid contact such as a pin connector. Signals can be transmitted and received without contact. For this reason, it is not necessary to use a special mechanism or structure for disconnecting the connection connector for solid contact when the flying object 8 is fired, and the structure of the connection portion is simplified.

FIG. 12 is a diagram showing another embodiment of the present invention. In the present embodiment shown in FIG.
The inner cylinder 1 has a portion corresponding to the length of the flying object from the rear end in a half-shape, and the upper half is detachable. When the flying object 8 is inserted into the inner cylinder 1, the inner cylinder lid 4
3 is removed from the inner cylinder 1 and the flying object 8 is inserted. After the flying object 8 is installed in the inner cylinder 1, the inner cylinder lid 43 is attached to the inner cylinder 1 and fixed with the inner cylinder lid lock 44. After the firing is completed, the inner cylinder 1 is removed from the firing cylinder, and when cleaning and inspecting the inner surface of the inner cylinder 1 exposed to the flame of the flying object 8, the inner surface can be directly touched by opening the inner cylinder cover 43. Therefore, cleaning becomes easy, and fine parts such as the entrance and exit of the fixture can be sufficiently cleaned.

FIG. 13 shows the inner cylinder 1 from the rear end in order to facilitate the insertion of the flying object into the inner cylinder 1 and the cleaning of the inner surface of the inner cylinder after firing, similarly to FIG. The upper half of the portion corresponding to the length of the flying object is divided into two equal parts so that it can be opened and closed like a double door. The double door 45 can be fixed with the inner cylinder lid lock 44.

According to the embodiments shown in FIGS. 12 and 13, it is possible to easily attach the flying object to the inner cylinder and to easily clean the inner surface of the inner cylinder after firing.

FIG. 14 is a diagram showing another embodiment of the present invention. In this embodiment shown in FIG.
It can be separated from Flying object fixture 2
The inner cylinder 1 is mounted on the guide portion 2 with the 5 pulled into the guide portion 2 to form an integral structure. Moreover, inner cylinder 1
Is formed of an inexpensive and lightweight material such as plastic.
The flying object 8 is inserted therein. After firing, the integrated structure of the inner cylinder 1 and the guide portion 2 taken out of the firing cylinder is disassembled into the inner cylinder 1 and the guide portion 2. Since the inner cylinder has been exposed to the flame of the flying object, it is discarded without cleaning and replaced with a new inner cylinder. A new inner cylinder 1 that has not been exposed to the flame is mounted on the guide portion 2 and prepared for loading the next flying object 8.

According to the present invention, since the inner cylinder is disposable, it is not necessary to carry out cleaning after firing, so that there is an effect that the operation of loading the flying object can be performed efficiently.

[0046]

According to the present invention, it is possible to improve the flight performance of a flying object and to provide a launcher that facilitates the loading operation of the flying object.

[Brief description of the drawings]

FIG. 1 is a schematic diagram showing one embodiment of the present invention.

FIG. 2 is a diagram illustrating a schematic configuration of a conventional launch cylinder.

FIG. 3 is a view showing a flying object having a wrap-around wing.

FIG. 4 shows a schematic structure of a projectile launcher having wraparound wings.

FIG. 5 is a schematic view showing another embodiment of the present invention.

FIG. 6 is a schematic diagram showing another embodiment of the present invention.

FIG. 7 is a schematic diagram showing another embodiment of the present invention.

FIG. 8 is a schematic diagram showing another embodiment of the present invention.

FIG. 9 is a schematic view showing another embodiment of the present invention.

FIG. 10 is a schematic view showing another embodiment of the present invention.

FIG. 11 is a schematic view showing another embodiment of the present invention.

FIG. 12 is a schematic view showing another embodiment of the present invention.

FIG. 13 is a schematic view showing another embodiment of the present invention.

FIG. 14 is a schematic view showing another embodiment of the present invention.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... Inner cylinder, 2 ... Guide part, 3 ... Launch cylinder, 4 ... Rail part,
5 ... launch port, 8 ... flying object, 9 ... wraparound wing, 1
0: launcher body, 11: guide fixing device, 12: external connection outlet, 13: integrated structure, 20: fixing device,
Reference numeral 21 denotes a wiring attachment port, 22 denotes an opening for a fixture, 23.
Projectile wiring opening, 25: Projectile fixture, 26: Projectile fixture support, 27: Fixture driving device, 28: Projectile electrical wiring attachment opening, 31: Projectile opening, 32: Rear end Opening part, 33: Fall prevention lid, 34: Electric wiring with flying object connection connector, 35: External connection connector, 36: External connection electric wire, 37: Front end plate, 38: Front door, 39: Front door driving device, 41: rear lid, 42: rear lid driving device,
43: inner cylinder lid, 44: inner cylinder lid lock, 45: double door, 4
7: external electric wire, 53: ignition wire, 56: fixed-side photoelectric converter, 57: flying object-side photoelectric converter, 58: power supply line for photoelectric converter.

 ──────────────────────────────────────────────────続 き Continuing on the front page (72) Atsushi Ikegame, 216 Totsuka-cho, Totsuka-ku, Yokohama-shi, Kanagawa Prefecture Inside the Communication Systems Division of Hitachi, Ltd. Address Communication Systems Division, Hitachi, Ltd. (72) Inventor Takeshi Iwata 4-6 Kanda Surugadai, Chiyoda-ku, Tokyo Inside Hitachi, Ltd. (72) Kenichi Nagashima 216 Totsukacho, Totsuka-ku, Yokohama-shi, Kanagawa Prefecture Hitachi, Ltd. Communication Systems Division

Claims (11)

[Claims] 1. A launcher that stores a curved wing so as to be wound around a flying body and that launches a flying object having a wrap-around wing formed so as to be deployed at the time of launch, wherein the wrap-around wing is flying. An inner cylinder containing the flying object housed in the body and the body, and a guide formed along the axial direction of the inner cylinder and guiding the inner cylinder into the launcher;
A structure having a first electric signal line externally connected to the flying object; a structure installed in the launcher, which is formed so as to fit with a guide portion of the structure loaded in the launcher. Rail part,
A launch port formed at an exit end face of the flying object in a launch direction, a second electrical signal line for transmitting a launch control signal of the flying object, and an electrical connector for connecting the electrical wiring and the electrical signal line. A launcher characterized by comprising: 2. A launcher which stores a curved wing so as to be wound around a flying body and fires a flying body having a wrap-around wing formed so as to be deployed at the time of firing, wherein the wrap-around wing is capable of flying. An inner cylinder enclosing the flying object housed in the body and trunk, a guide portion formed along the axial direction of the inner cylinder, for guiding the inner cylinder into the launcher, and one end side of the guide portion A first electric signal line disposed on the rear side of the inner cylinder, the other end of which is inserted into the launcher, and the other end of which is installed in the launcher; A rail portion formed to fit with a guide portion of the structure to be loaded in the machine;
A launch port formed at the exit end face of the projectile in the launch direction, a second electric signal line transmitting a launch control signal of the projectile, and a launcher on the rear side with respect to the launch direction of the projectile A launcher, comprising: an electrical connector to be installed for connecting the second electrical signal line and the first electrical signal line. 3. The launcher according to claim 1, wherein a guide portion formed in the inner cylinder is formed at a position lower than the launcher to be inserted. A flying object fixing tool that fixes the flying object by moving a fixing tool in and out of the inner surface, a fixing device driving device that drives the flying object fixing device,
The fixing device driving device is provided with a fixing device having electric wiring for supplying electricity from the outside, and the flying object is pressed by pressing the flying object against the inner surface of the inner cylinder by operating the flying object fixing device. The projectile launcher according to claim 1, wherein the launcher is fixed. 4. The projectile, wherein the guide portion is mounted at a position above the inner cylinder, wherein the projectile fixing tool which moves in and out of the inner surface of the inner cylinder from the guide portion, and the projectile A fixing device having a fixing device driving device for driving the fixing device and an electric wiring for supplying electricity to the fixing device driving device from outside is installed, and the flying object fixing device is provided inside the inner cylinder from the guide portion. The projectile according to claim 1 or 2, wherein the projectile is fixed to the inner cylinder by pressing the projectile in the direction of gravity. 5. The launcher has an opening formed in a body of the projectile, and the projectile is moved into the inner cylinder by inserting the projectile fixing device into the opening. The launch vehicle according to claim 3, wherein the launch vehicle is fixed. 6. The launcher according to claim 1, wherein the rail portion is provided on a bottom surface of the launcher, and a guide portion fixing device for fixing the guide portion to the rail portion is provided at a rear portion of the rail portion. The launch vehicle according to claim 1, wherein the launch vehicle is provided. 7. The launcher according to claim 1, wherein the launcher is provided with an opening / closing door which can be remotely operated electrically in front of or behind the launch direction of the launcher. 8. The launcher has a photoelectric conversion device installed on the flying object and the flying object connection connector, and guides a power supply for driving the photoelectric conversion device installed on the flying object side from outside the flying object. The launcher according to claim 1, wherein signals are exchanged at the time of adjustment in a non-contact manner. 9. The launcher has a structure in which the guide portion is attached to one of two half cylinders divided by a plane including the center axis of the cylinder, and the other cylinder is detachable from the half cylinder. The launch vehicle according to claim 1 or 2, wherein the launch vehicle is formed. 10. The launcher according to claim 4, wherein the guide portion is attached to one of two half-cylindrical bodies divided by a plane including the central axis of the cylinder, and the other cylinder is further divided by a plane including an axis.
3. A structure in which a divided cylinder is formed, and the two four-divided cylinders are double door-opening doors, and a structure is formed by being attached to the half cylinder to which a guide portion is attached. The launcher described in. 11. The launcher is characterized in that the inner cylinder and the guide portion of the structure are detachably assembled so that the inner cylinder is formed of a plastic material or a thin cylindrical structure. The launch vehicle according to claim 1.