JP2000130993A - Shooting cylinder for guided flying body - Google Patents

Abstract

PROBLEM TO BE SOLVED: To reduce the aerodynamic drag of an aircraft, prevent a thermal effect to flying body due to the back flow of blast upon shooting the flying body and the transfer of load to a mother ship due to blast and protect a driving device from a danger such as the breakage of the nozzle of the driving device due to the collision of obstacles in air in a shooting cylinder for the induced flying body shot backward the aircraft. SOLUTION: In a shooting cylinder for a flying body shot backward an aircraft, expanded wings 5 large in aerodynamic drag are folded and housed therein. The shooting cylinder has a wing guide rail 10 for guiding the expanded wings 5 until the flying body passes through the shooting cylinder 7 upon shooting and a cover 8 with a sharp end for protecting the nozzle 6 of a driving device 4 to be broken by a blast A of the driving device 4.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a technology relating to a launch tube for a guided flying vehicle mounted on an aircraft (hereinafter referred to as a "base unit") and fired toward a target located behind the base unit. More specifically, the state in which the guided flying vehicle is mounted on the base unit, the aerodynamic resistance of the base unit after the guided flying unit is fired, and the rear of the guided flying unit in the state mounted on the base unit To protect the vehicle from collisions with obstacles such as birds and ice in the atmosphere.

[0002]

2. Description of the Related Art A technique related to a conventional projectile launcher will be described with reference to FIG. FIG. 7 (a) is a diagram showing the state of launch of the guided flying vehicle 3 that is launched toward the base unit 1, in which the change in state of the guided flying vehicle 3 after launch is shown in chronological order. Is shown. FIG. 7B is a view showing a guided flying object attached to the base unit via a launcher, wherein 1 is a base unit, 2 is a launcher, 3 is a guided flying unit, 4 is a propulsion device, and 6 is a propulsion device. Nozzle 19 is a hanger for suspending the guided flying object to the launcher,
Reference numeral 20 denotes a launcher rail, and reference numeral 21 denotes a wing of a guided flying object.

FIG. 7A shows a guided flying object 3 mounted on the base unit 1. The guided flying vehicle 3 is fired from the base unit 1 along the launcher rail 20, but immediately after being launched, the flight speed of the base unit 1 is opposite to the flying direction of the guided flying unit 3, so that the speed is reduced accordingly. (), But with time, it accelerates in the direction of flight (), and continues to fly ().

In FIG. 7 (b), the guided flying object 3 is hung on a launcher rail 20 by a hanger 19, and along the launcher rail 20 at the time of firing.
Fly in the opposite direction of your flight.

[0005]

The conventional guided flying object has a large aerodynamic resistance due to the wings 21 and the like when mounted on the base unit 1, and the nozzle 6 surface of the propulsion device 4 having a large aerodynamic resistance is directed in the flight direction. Therefore, the flight performance of the base unit 1 was greatly adversely affected. During flight, there is a danger that the weather seal inside the nozzle 6 of the propulsion device 4 is broken due to collision with obstacles such as birds and ice in the atmosphere, and the performance of the propulsion device 4 is deteriorated.

The present invention reduces the aerodynamic resistance of the mother aircraft after the guided flying vehicle is mounted on the mother aircraft and after the guided flying vehicle is fired, and reduces obstacles such as birds and ice in the atmosphere. An object of the present invention is to protect a propulsion device from a danger such as a weather seal inside a nozzle of the propulsion device being broken by collision of the propulsion device.

[0007]

According to a first aspect of the present invention, a launching tube for a guided flying object is provided with a deployable wing having a large aerodynamic resistance folded and housed, and at the time of launch, guides the deployable wing until it passes through the launching tube. Wing guide rails for protecting the nozzles and the like of the propulsion device, and a cover with a sharpened tip for reducing aerodynamic drag at the rear end of the flying object while being blasted and blasted. .

The launching tube for a guided flying object according to the second invention is a blade guide for folding and storing a deploying wing having a large aerodynamic resistance, and for guiding the deploying wing until it comes out of the launching tube at the time of launch. While protecting the rail and the nozzle of the propulsion device, etc.
A cover with a sharpened tip to reduce aerodynamic drag at the rear end of the flying object, and a lattice-shaped groove provided in the cover so that it can be easily broken by the blast of the propulsion device Things.

The launching tube for a guided flying vehicle according to the third invention is a blade guide for folding and storing a deploying wing having a large aerodynamic resistance, and for guiding the deploying wing at the time of launch until the deploying wing passes through the launching tube. Rail and a cover fixed to a polygonal pyramid shape with a sharp tip to reduce the aerodynamic drag of the rear end of the flying object while protecting and protecting the nozzle of the propulsion device while receiving the blast, and the cover It comprises a hinge that is openably and closably fixed to the launch tube, and an elastic body that fixes the cover in a polygonal pyramid shape and seals a gap.

A fourth aspect of the invention provides a launch vehicle for a guided flying object, wherein a deployment wing having a large aerodynamic resistance is folded and housed, and a wing guide for guiding the deployment wing at the time of launch until the deployment wing passes through the launch wing. A cover fixed in a polygonal pyramid shape with a sharpened tip to reduce the aerodynamic drag at the rear end of the flying object while protecting the rail and the nozzle of the propulsion device while receiving the blast while protecting it, and firing the cover It comprises a hinge which is fixed to the cylinder so as to be openable and closable, an elastic body which fixes the cover in a polygonal pyramid shape and closes a gap, and a stopper which restricts and fixes an opening angle of the cover.

The launching tube for a guided flying object according to a fifth aspect of the present invention is a wing guide for folding and storing a deploying wing having a large aerodynamic resistance, and for guiding the deploying wing at the time of firing until the deploying wing passes through the launching tube. A cover fixed to a polygonal pyramid with a pointed tip to protect the nozzles and the like of the propulsion device while receiving and opening the blast while reducing the aerodynamic resistance of the flying object rear end, and the cover A hinge for openably and closably fixed to a launch tube, an elastic body for fixing the cover in a polygonal pyramid shape and closing a gap, and a torsion bar attached to the hinge portion of the cover so that the opened cover closes instantly It is provided with.

A launching tube for a guided flying object according to a sixth aspect of the present invention is a wing guide for folding and storing a deploying wing having a large aerodynamic resistance, and for guiding the deploying wing until it passes through the launching tube at the time of firing. A cover fixed to a polygonal pyramid with a pointed tip to protect the nozzles and the like of the propulsion device while receiving and opening the blast while reducing the aerodynamic resistance of the flying object rear end, and the cover A hinge fixed to the launching tube so as to be openable and closable, an elastic body fixing the cover in a polygonal pyramid shape and sealing, a driving device attached to the hinge portion of the cover for opening and closing the cover, and the driving device. A control device that sends a control signal to control the opening / closing angle, speed, and timing of the cover.

[0013]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiment 1 FIG. 1 is a view showing Embodiment 1 of the present invention. FIG. 1A shows a state in which a guided flying object is mounted on a base unit, and FIG. 1B shows a state immediately after the guided flying object is fired. The state of is shown. In the figure, 1 is a mother machine, 2 is a launcher, 3 is a guided flying object, 4 is a propulsion device, 5 is a deployed wing housed in a launch tube in a folded state, 6 is a nozzle of the propulsion device, 7 is a launch tube, 8 is a cover with a sharp tip attached to the rear end of the launch tube, 9 is a sealing material for blocking the inside of the launch tube from outside air, 10 is a wing guide rail for folding and storing the deployed wings, and 11 is a launcher of the base unit. A indicates a blast ejected from the propulsion device 4.

In the present invention, when the guided flying object 3 is mounted on the base unit 1, the deploying wing 5 of the guided flying object 3 and the rear end of the propulsion device 4 have a cover 8 with a sharp tip. Since it is housed in the launching cylinder 7, the aerodynamic resistance of the parent machine can be reduced. At the same time, the nozzle 6 of the propulsion device 4 can be protected from collision with obstacles such as birds and ice in the atmosphere.

FIG. 1B shows a state immediately after the guidance flying object 3 has left the launching cylinder 7 and jumped out.
Is blown off by receiving the blast A ejected from the propulsion device 4, it is possible to prevent the blast A from flowing backward and thermally destroying the guidance flying object 3. Further, it is possible to prevent the load due to the blast A from being transmitted to the mother machine due to the breakage of the cover 8.

Embodiment 2 FIG. 2 is a view showing Embodiment 2 of the present invention. FIG. 2 (a) shows a state in which a guided flying object is mounted on a base unit, and FIG. 2 (b) shows a state immediately after the guided flying object is fired. The state of is shown. In the figure, 1 is a mother machine, 2
Is a launcher, 3 is a guided flying object, 4 is a propulsion device, 5 is a deployed wing housed in a launch tube in a folded state, 6 is a nozzle of the propulsion device, 7 is a launch tube, and 8 is a rear end of the launch tube. , A sealing material for cutting off the inside of the launch tube from outside air, 10 a wing guide rail for folding and storing the deployed wings, 11 a hook for hanging the launcher of the base unit, Reference numeral 12 denotes a lattice-shaped groove provided in the cover, and A denotes blast ejected from the propulsion device 4.

In the present invention, when the guide vehicle 3 is mounted on the base unit 1, the deploying wing 5 of the guide vehicle 3 and the rear end of the propulsion device 4 have a cover 8 with a sharp tip. Since it is housed in the launching cylinder 7, the aerodynamic resistance of the parent machine can be reduced. At the same time, the nozzle 6 of the propulsion device 4 can be protected from collision with obstacles such as birds and ice in the atmosphere.

FIG. 2B shows a state immediately after the guide flying object 3 has left the launching cylinder 7 and jumped out.
Receives the blast A ejected from the propulsion device 4 and is easily broken. Therefore, it is possible to prevent the blast A from flowing backward and thermally destroying the guidance flying object 3. Further, since the cover 8 is easily torn, the load due to the blast A can be prevented from being transmitted to the mother machine. further,
Since the fragments of the cover 8 are broken into small pieces by the lattice-shaped grooves 12, even if the fragments collide with the base unit 1, they are not damaged.

Embodiment 3 FIG. 3 is a view showing a third embodiment of the present invention. FIG. 3 (a) shows a state in which a guided flying object is mounted on a base unit, and FIG. 3 (b) shows a state immediately after the guided flying object is fired. The state of is shown. In the figure, 1 is a mother machine, 2
Is a launcher, 3 is a guided flying object, 4 is a propulsion device, 5 is a deployed wing housed in a launch tube in a folded state, 6 is a nozzle of the propulsion device, 7 is a launch tube, and 8 is a rear end of the launch tube. A cover fixed to a polygonal pyramid shape with a sharp tip
Reference numeral 9 denotes a seal material for blocking the inside of the launch tube from the outside air, 10 denotes a wing guide rail for folding and storing the deployed wings, 11 denotes a hook for hanging the launcher of the base unit, and 13 denotes a cover 8 which opens and closes the launch tube 7. A hinge 14 for fixing the cover 8 in a polygonal pyramid shape and an elastic body for closing the gap;
Indicates a blast ejected from the propulsion device 4.

According to the present invention, when the guide vehicle 3 is mounted on the base unit 1, the deploying wing 5 of the guide vehicle 3 and the rear end of the propulsion device 4 have a polygonal pyramid shape with a sharp tip. Since it is housed in the launching cylinder 7 having the fixed cover 8, the aerodynamic resistance of the parent machine can be reduced. At the same time, the nozzle 6 of the propulsion device 4 can be protected from collision with obstacles such as birds and ice in the atmosphere.

FIG. 3B shows a state immediately after the guiding flying object 3 has left the launching cylinder 7 and has jumped out.
Receives the blast A ejected from the propulsion device 4, so that it is possible to prevent the blast A from flowing backward and thermally destroying the guided flying object 3. Further, by opening the cover 8, it is possible to prevent the load due to the blast A from being transmitted to the parent machine. Further, since the fragments of the cover 8 do not scatter, the mother machine 1 is not damaged. In addition, the cover 8 can be reused by replacing the elastic body 14.

Embodiment 4 FIG. 4 is a view showing Embodiment 4 of the present invention. FIG. 4 (a) shows a state in which the guided flying object is mounted on the base unit, and FIG. 4 (b) shows a state immediately after the guided flying object is fired. The state of is shown. In the figure, 1 is a mother machine, 2
Is a launcher, 3 is a guided flying object, 4 is a propulsion device, 5 is a deployed wing housed in a launch tube in a folded state, 6 is a nozzle of the propulsion device, 7 is a launch tube, and 8 is a rear end of the launch tube. A cover fixed to a polygonal pyramid shape with a sharp tip
Reference numeral 9 denotes a seal material for blocking the inside of the launch tube from the outside air, 10 denotes a wing guide rail for folding and storing the deployed wings, 11 denotes a hook for hanging the launcher of the base unit, and 13 denotes a cover 8 which opens and closes the launch tube 7. A hinge 14 for fixing as much as possible is an elastic body that fixes the cover 8 in a polygonal pyramid shape and seals the gap.
Reference numeral 5 denotes a stopper for limiting the opening angle of the cover 8 and fixing the cover in that state, and A denotes blast ejected from the propulsion device 4.

According to the present invention, when the guide vehicle 3 is mounted on the base unit 1, the deploying wing 5 of the guide vehicle 3 and the rear end of the propulsion device 4 have a polygonal pyramid shape with a sharp tip. Since it is housed in the launching cylinder 7 having the fixed cover 8, the aerodynamic resistance of the parent machine can be reduced. At the same time, the nozzle 6 of the propulsion device 4 can be protected from collision with obstacles such as birds and ice in the atmosphere.

FIG. 4B shows a state immediately after the guiding flying object 3 has left the launching cylinder 7 and has jumped out.
Receives the blast A ejected from the propulsion device 4, so that it is possible to prevent the blast A from flowing backward and thermally destroying the guided flying object 3. Further, by opening the cover 8, it is possible to prevent the load due to the blast A from being transmitted to the parent machine. Further, since the cover 8 is fixed in an open state by the stopper 15, the base machine 1 is not damaged and the aerodynamic resistance is stabilized. In addition, the cover can be reused by replacing the elastic body 14.

Embodiment 5 FIG. 5 shows a fifth embodiment of the present invention. FIG. 5 (a) shows a state in which a guided flying object is mounted on a base unit, and FIG. 5 (b) shows a state immediately after the guided flying object is fired. The state of is shown. In the figure, 1 is a mother machine, 2
Is a launcher, 3 is a guided flying object, 4 is a propulsion device, 5 is a deployed wing housed in a launch tube in a folded state, 6 is a nozzle of the propulsion device, 7 is a launch tube, and 8 is a rear end of the launch tube. A cover fixed to a polygonal pyramid shape with a sharp tip
Reference numeral 9 denotes a seal material for blocking the inside of the launch tube from the outside air, 10 denotes a wing guide rail for folding and storing the deployed wings, 11 denotes a hook for hanging the launcher of the base unit, and 13 denotes a cover 8 which opens and closes the launch tube 7. A hinge 14 for fixing as much as possible is an elastic body that fixes the cover 8 in a polygonal pyramid shape and seals the gap.
Reference numeral 6 denotes a torsion bar which is attached to the hinge 13 and immediately closes the open cover 8, and A denotes a blast jetted from the propulsion device 4.

In the present invention, when the guided flying vehicle 3 is mounted on the base unit 1, the deploying wing 5 of the guided flying vehicle 3 and the rear end of the propulsion device 4 have a polygonal pyramid shape with a sharp tip. Since it is housed in the launching cylinder 7 having the fixed cover 8, the aerodynamic resistance of the parent machine can be reduced. At the same time, the nozzle 6 of the propulsion device 4 can be protected from collision with obstacles such as birds and ice in the atmosphere.

FIG. 5B shows a state immediately after the guiding flying object 3 has left the launching cylinder 7 and jumped out.
Receives the blast A ejected from the propulsion device 4, so that it is possible to prevent the blast A from flowing backward and thermally destroying the guided flying object 3. Further, by opening the cover 8, it is possible to prevent the load due to the blast A from being transmitted to the parent machine. Further, the cover 8 is instantly closed by the torsion bar 16, so that the base machine 1 is not damaged and the aerodynamic resistance can be maintained at the same level as before the launch. In addition, the cover can be reused by replacing the elastic body 14.

Embodiment 6 FIG. FIG. 6 is a view showing a sixth embodiment of the present invention. FIG. 6 (a) shows a state in which a guided flying object is mounted on a base unit, and FIG. 6 (b) shows a state immediately after the guided flying object is fired. The state of is shown. In the figure, 1 is a mother machine, 2
Is a launcher, 3 is a guided flying object, 4 is a propulsion device, 5 is a deployed wing housed in a launch tube in a folded state, 6 is a nozzle of the propulsion device, 7 is a launch tube, and 8 is a rear end of the launch tube. A cover fixed to a polygonal pyramid shape with a sharp tip
Reference numeral 9 denotes a seal material for blocking the inside of the launch tube from the outside air, 10 denotes a wing guide rail for folding and storing the deployed wings, 11 denotes a hook for hanging the launcher of the base unit, and 13 denotes a cover 8 which opens and closes the launch tube 7. A hinge 14 for fixing as much as possible is an elastic body that fixes the cover 8 in a polygonal pyramid shape and seals the gap.
Reference numeral 7 denotes a driving device for the cover 8 attached to the hinge 13, and reference numeral 18 denotes a control device that sends a control signal to the driving device to control the opening / closing angle, speed, and timing of the cover 8.

In the present invention, when the guided flying object 3 is mounted on the base unit 1, the deploying wing 5 of the guided flying object 3 and the rear end of the propulsion device 4 are formed in a polygonal pyramid shape with a sharp tip. Since it is housed in the launching cylinder 7 having the fixed cover 8, the aerodynamic resistance of the parent machine can be reduced. At the same time, the nozzle 6 of the propulsion device 4 can be protected from collision with obstacles such as birds and ice in the atmosphere.

FIG. 6B shows a state immediately after the guidance flying object 3 has left the launching cylinder 7 and jumped out.
Receives the blast A ejected from the propulsion device 4, so that it is possible to prevent the blast A from flowing backward and thermally destroying the guided flying object 3. Further, by opening the cover 8, it is possible to prevent the load due to the blast A from being transmitted to the parent machine. Further, the driving device 17 is operated by a control signal sent from the control device 18 and the cover 8 opens and closes at an arbitrary angle, speed, and timing, so that blast reverse flow immediately after firing, load transmission to the base machine, and Aerodynamic characteristics degradation can be prevented under optimal conditions. In addition, the cover can be reused by replacing the elastic body 14.

[0031]

According to the first aspect of the present invention, by providing a cover with a sharpened tip, the aerodynamic drag in a state where the guided flying object is mounted on the base unit is reduced, and birds and ice in the atmosphere are reduced. The propulsion device can be protected from dangers such as breakage of the weather seal inside the nozzle of the propulsion device due to the collision of the obstacle. Also, when launching a guided flying vehicle, the blast of the propulsion device breaks the cover, preventing the blast backflow of the propulsion device and reducing the thermal effect on the flying object, and blasting the base unit with the blast Load transmission can be prevented.

According to the second aspect of the present invention, by providing the cover with a sharpened tip, the aerodynamic drag in a state in which the guided flying object is mounted on the base unit is reduced, and birds and ice in the atmosphere are reduced. The propulsion device can be protected from dangers such as breakage of the weather seal inside the nozzle of the propulsion device due to the collision of the obstacle. Also, when launching a guided flying object, the blast of the propulsion device breaks the cover, preventing the blast backflow of the propulsion device and reducing the thermal effect on the flying object, as well as the blast Load transmission can be prevented. further,
By providing a lattice-shaped groove in the cover, the cover can be more easily broken and the pieces of the cover can be reduced into small pieces, so that even if the pieces collide with the mother machine, the mother machine can be prevented from being damaged. .

According to the third aspect of the present invention, by providing the cover fixed in a polygonal pyramid shape having a sharp pointed tip, the aerodynamic resistance in a state where the guided flying object is mounted on the base unit is reduced. The propulsion device can be protected from the danger that the weather seal inside the nozzle of the propulsion device is broken by collision of obstacles such as birds and ice in the atmosphere. Also,
The cover is opened by the blast of the propulsion device when launching the guided flying vehicle, preventing the blast backflow of the propulsion device to reduce the thermal effect on the flying vehicle and transmitting the load to the base unit by the blast. Can be prevented. Further, since the cover fragments are not scattered, the mother machine can be prevented from being damaged, and the cover can be reused.

According to the fourth aspect of the present invention, by providing a cover fixed in a polygonal pyramid shape having a sharp tip, the aerodynamic resistance in a state where the guidance flying object is mounted on the base unit is reduced. The propulsion device can be protected from the danger that the weather seal inside the nozzle of the propulsion device is broken by collision of obstacles such as birds and ice in the atmosphere. Also,
The cover is opened by the blast of the propulsion device when launching the guided flying object, preventing the blast backflow of the propulsion device to reduce the thermal effect on the flying object and transmitting the load to the base unit by the blast. Can be prevented. Further, since the fragments of the cover are not scattered, the mother machine can be prevented from being damaged, and the cover can be reused. In addition, the provision of the stopper limits the angle at which the cover opens and fixes the cover, so that aerodynamic resistance is stabilized.

According to the fifth aspect of the present invention, by providing the cover fixed in a polygonal pyramid shape having a sharp tip, the aerodynamic resistance in a state where the guidance flying object is mounted on the base unit is reduced. The propulsion device can be protected from the danger that the weather seal inside the nozzle of the propulsion device is broken by collision of obstacles such as birds and ice in the atmosphere. Also,
The cover is opened by the blast of the propulsion device when launching the guided flying vehicle, preventing the blast backflow of the propulsion device to reduce the thermal effect on the flying vehicle and transmitting the load to the base unit by the blast. Can be prevented. Further, since the fragments of the cover are not scattered, the mother machine can be prevented from being damaged, and the cover can be reused. In addition, since the open cover is instantly closed by providing the torsion bar in the hinge portion, the air resistance of the base unit after the launch of the guided flying object can be kept equal to the state before the launch.

According to the sixth aspect of the present invention, by providing the cover fixed in a polygonal pyramid shape having a sharp tip, the aerodynamic resistance in a state where the guidance flying object is mounted on the base unit is reduced. The propulsion device can be protected from the danger that the weather seal inside the nozzle of the propulsion device is broken by collision of obstacles such as birds and ice in the atmosphere. Also,
The cover is opened by the blast of the propulsion device when launching the guided flying object, preventing the blast backflow of the propulsion device to reduce the thermal effect on the flying object and transmitting the load to the base unit by the blast. Can be prevented. Further, since the fragments of the cover are not scattered, the mother machine can be prevented from being damaged, and the cover can be reused. In addition, by providing a drive device and a control device for opening and closing the cover, the opening angle, speed, and timing of the cover can be arbitrarily set, preventing blast backflow of the propulsion device during firing and transmitting load to the base unit by blast The prevention and the reduction of the aerodynamic drag of the mother machine after firing can be performed under optimum conditions.

[Brief description of the drawings]

FIG. 1 is a view showing a launch vehicle for a guided flying object according to a first embodiment of the present invention.

FIG. 2 is a view showing a launch vehicle for a guided flying object according to a second embodiment of the present invention.

FIG. 3 is a view showing a launch vehicle for a guided flying object according to a third embodiment of the present invention.

FIG. 4 is a view showing a launch vehicle for a guided flying object according to a fourth embodiment of the present invention.

FIG. 5 is a view showing a launch vehicle for a guided flying object according to a fifth embodiment of the present invention.

FIG. 6 is a view showing a launch vehicle for a guided flying object according to a sixth embodiment of the present invention.

FIG. 7 is a diagram showing the operation of a conventional guided flying object.

[Explanation of symbols]

Reference Signs List 1 base machine, 2 launcher, 3 guided flying object, 4 propulsion device, 5 deployment wing, 6 nozzle, 7 launch cylinder, 8 cover, 9 seal material, 10 wing guide rail, 11 hook, 12 groove, 13 hinge, 14 elasticity Body, 15
Stopper, 16 torsion bar, 17 drive, 18
Control device, 19 hanger, 20 launcher rail, 2
1 wing, A blast.

Claims (6)

[Claims] 1. A launching tube for a guided flying vehicle that is fired toward the rear of a mounted aircraft, attached to the rear end of the launching tube, receiving a blast of a propulsion device for the flying vehicle, A cover having a sharpened tip, a sealing material attached to a front portion of the launch tube to block the inside of the launch tube from the outside air, and an inner wall of the launch tube along the machine axis direction of the flying object And a hook attached to an upper part of the launch tube and suspended from a launcher of the aircraft. 2. A launch tube for a guided flying vehicle that is launched toward the rear of an aircraft on which it is mounted, a cover having a pointed tip attached to a rear end of the launch tube and having a lattice-like groove. A seal member attached to a front portion of the launch tube, for blocking the inside of the launch tube from outside air, and a wing guide rail provided on an inner wall of the launch tube along the machine axis direction of the flying object, Attached to the top of the launch tube,
A launching tube for a guided flying object, comprising: a hook for hanging the launcher of the aircraft. 3. A launching tube for a guided flying object that is launched toward the rear of an aircraft on which it is mounted, a triangular cover attached to the rear end of the launching tube, and the cover can be opened and closed with the launching tube. A hinge fixed to the cover, an elastic body that fixes the cover so that the tip shape becomes a polygonal pyramid, and seals a gap between the covers; and A seal material for blocking off, a wing guide rail provided on the inner wall of the launch tube along the machine axis direction of the flying object, and attached to the upper portion of the launch tube to hang on the launcher of the aircraft A launcher for a guided flying object, comprising: a hook; 4. A launching tube for a guided flying vehicle that is fired toward the rear of a mounted aircraft, a triangular cover attached to a rear end of the launching tube, and the cover can be opened and closed with the launching tube. A hinge fixed to the cover, an elastic body that fixes the cover so that the tip shape becomes a polygonal pyramid, and seals a gap between the covers; and A seal member for blocking the cover, a stopper attached to the hinge portion to limit and fix an opening angle of the cover, and a wing guide rail provided on an inner wall of the launch tube along an axial direction of the flying object. And a hook attached to an upper portion of the launch tube and suspended from a launcher of the aircraft. 5. A launching tube for a guided flying vehicle which is fired toward the rear of a mounted aircraft, a triangular cover attached to a rear end of the launching tube, and the cover can be opened and closed with the launching tube. A hinge fixed to the cover, an elastic body that fixes the cover so that the tip shape becomes a polygonal pyramid, and seals a gap between the covers; and A torsion bar attached to the hinge portion to limit the opening angle of the cover and enable instantaneous closing, and an inner wall of the launch tube along the machine axis direction of the flying object And a hook attached to an upper part of the launch tube and suspended from a launcher of the aircraft. 6. A launching tube for a guided flying vehicle which is fired toward the rear of a mounted aircraft, a triangular cover attached to a rear end of the launching tube, and the cover can be opened and closed with the launching tube. A hinge fixed to the cover, an elastic body that fixes the cover so that the tip shape becomes a polygonal pyramid, and seals a gap between the covers; and And a seal member for blocking, a driving device attached to the hinge portion, and opening and closing the cover, and a control device for controlling the driving device,
A wing guide rail provided on the inner wall of the launch tube along the axis direction of the flying object, and a hook attached to an upper portion of the launch tube and hanging from a launcher of the aircraft. A launcher for guided flying vehicles.