JP2000130992A - Shooting cylinder for guided flying body - Google Patents

Abstract

PROBLEM TO BE SOLVED: To reduce the aerodynamic drag of an aircraft while a guided flying body is mounted on the aircraft and after the guided flying body is shot and protect a driving device from a danger such as the breakage of a weather seal in the nozzle of the driving device due to the collision of ice or a bird in air in a shooting cylinder for the flying body shot backward the aircraft. SOLUTION: In a shooting cylinder for a flying body shot backward an aircraft, an 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 and reducing an aerodynamic drag in the rear end of a guided flying body 3.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a launch tube for a guided flying vehicle which is mounted on an aircraft (hereinafter referred to as a "base unit") and is fired toward a predetermined target located behind the base unit. In more detail, the state in which the guided vehicle is mounted on the base unit, and the aerodynamic resistance of the base unit after the guided vehicle is launched, are reduced, and at the same time, collisions with ice and birds in the atmosphere The present invention proposes a device for protecting the propulsion device.

[0002]

2. Description of the Related Art First, the use of such a guided flying object will be described with reference to FIG. FIG. 5 (a) is a diagram showing the state of launch of the guided flying vehicle 3 that is launched toward the rear of the base unit 1, in which the state change of the guided flying vehicle 3 after launch is shown in chronological order. Is shown. FIG.
(B) is a diagram showing a guided flying object attached to the base unit via a launcher, where 1 is the base unit, 2 is the launcher, 3
Reference numeral 4 denotes a propelling device, 4 denotes a propulsion device, 6 denotes a nozzle of the propulsion device, 15 denotes a hanger for suspending the guiding flying device on a launcher, 16 denotes a launcher rail, and 17 denotes a wing of the guiding flying device.

[0005] FIG. 5A shows a guided flying object 3 mounted on a base unit 1. The guided flying vehicle 3 is fired from the base unit 1 along the launcher rail 16, but immediately after being fired, the flight speed of the base unit 1 is opposite to the flying direction of the guided flying unit 3, so the speed is reduced accordingly. (), But with time, it accelerates in the direction of flight (), and continues to fly ().

In FIG. 5 (b), the guided flying object 3 is hung on a launcher rail 16 by a hanger 15, and at launch, the base unit 1 is moved along the launcher rail 16.
Let it fly in the opposite direction to the flight direction.

[0005]

The conventional guided flying vehicle has a large aerodynamic resistance due to wings and the like when mounted on the base unit, and the nozzle surface of the propulsion device having a large aerodynamic resistance faces directly in the flight direction. As a result, the flight performance of the aircraft was greatly affected. Also, during the flight, the impact of ice or birds in the air may damage the weather seal installed inside the nozzle of the propulsion device to maintain the airtightness inside the propulsion device, deteriorating the performance of the propulsion device. was there.

The present invention reduces the aerodynamic resistance of the base unit after the guided vehicle is mounted on the base unit and after the guided unit is fired, and propells the vehicle by collision with ice or birds in the atmosphere. An object of the present invention is to protect a propulsion device from dangers such as breakage of a weather seal inside a nozzle of the device.

[0007]

According to a first aspect of the present invention, there is provided a launching tube for a guided flying vehicle, wherein a deployable wing having a large aerodynamic resistance is folded and housed, and at the time of launching, the wing guides the wing until it comes out of the launching tube. It has a guide rail and a cover with a sharpened tip for protecting the nozzles and the like of the propulsion device and reducing aerodynamic resistance at the rear end of the flying object.

A second aspect of the invention provides a launch vehicle for a guided flying object in which a heat-resistant material is attached to an inner surface of the cover to thermally protect the cover when the propulsion device is blasted. It is.

A third aspect of the invention provides a launch vehicle for a guided flying object, wherein a backflow preventing device is provided at a rear portion of the launching tube in order to prevent a device of the guided flying device from being thermally destroyed by backflow of blast. It is provided with.

A fourth aspect of the invention provides a launch vehicle for a guided flying object, which includes a shock absorber connected to the hook in order to reduce a shock applied to the base unit by a thrust at the time of launching the guided flying object. Things.

[0011]

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 attached to the rear end of the launch tube, 9 is a seal material for blocking the inside of the launch tube from the outside air, 10 is a wing guide rail for folding and storing the deployed wings, and 11 is a suspender of the mother machine launcher. The lowering hook, A, indicates the blast ejected from the propulsion device.

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 prevented from colliding with ice or birds in the atmosphere.

FIG. 1B shows a state immediately after the guide flying object 3 has left the launching cylinder 7 and jumped out. Even in this state, the cover has the same shape as that of FIG. The aerodynamic resistance of 1 is the same as before launch.

Embodiment 2 FIG. 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 drawing, reference numeral 12 denotes a heat-resistant material attached to the inner surface of the cover.

In the present invention, a heat-resistant material 12 is adhered to the inner surface of the cover 8 in order to protect the cover 8 against the blast A of the propulsion device 4 thermally.

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 vehicle is mounted on a base unit, and FIG. 3 (b) shows a state immediately after a propulsion device is ignited. FIG. 3C shows a state immediately after the guided flying object is fired. In the figure, reference numeral 13 denotes a backflow prevention device attached to the rear part of the launch tube, and B denotes a blast which has flowed back by hitting a cover or the like.

In the present invention, a backflow prevention device 13 is provided at the rear of the launching cylinder 7 in order to prevent the equipment of the guidance flying vehicle 3 from being thermally destroyed by the blast backflow B.

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, reference numeral 14 denotes a shock absorber connected to a hook.

In the present invention, a shock absorber 14 connected to the hook 11 is provided in order to reduce the impact on the base unit 1 due to the thrust at the time of launch of the guidance flying object 3.

[0020]

According to the first aspect of the present invention, it is possible to reduce the aerodynamic resistance of the mother aircraft when the guided flying vehicle is mounted on the parent machine and after the guided flying vehicle is fired. Further, 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 ice, birds, or the like in the atmosphere.

According to the second aspect of the present invention, since the heat-resistant material is attached to the inner surface of the cover, the cover can be thermally protected when the blast of the propulsion device is received. Therefore, damage to the launch cylinder is small, and maintainability during reuse is good.

According to the third aspect of the present invention, since the backflow prevention device is provided at the rear portion of the launch tube, it is possible to prevent the equipment of the guided flying object from being thermally damaged by the backflow of the blast. Can be. Therefore, safety of the mother machine against explosion or the like of the propulsion device can be ensured.

According to the fourth aspect of the present invention, since the shock absorber connected to the hook is provided, it is possible to reduce the impact on the base unit due to the thrust at the time of launch of the guided flying object. Therefore, the influence on the flight of the mother machine at the time of launching the guided flying object can be reduced.

[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 diagram showing the operation of a conventional guided flying object.

[Explanation of symbols]

Reference Signs List 1 mother 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 heat resistant material, 13 backflow prevention device , 14 shock absorber, 15 hanger, 16 launcher rail, 17
Wings, A blast, B blast backflow.

Claims (4)

[Claims] 1. A launch tube for a guided flying vehicle that is launched toward the rear of an aircraft on which it is mounted, a cover attached to the rear end of the launch tube and having a sharp end, and a front portion of the launch tube. A wing guide rail provided on the inner wall of the launch tube along the axis of the guidance vehicle, and a hook attached to the upper portion of the launch tube for hanging on a launcher of the aircraft A launch vehicle for a guided flying object, comprising: 2. A launch vehicle for a guided flying object according to claim 1, further comprising a heat-resistant material attached to an inner surface of said cover. 3. The launch vehicle for a guided flying object according to claim 1, further comprising a backflow prevention device attached to a rear portion of the launching tube to prevent backflow of blast of the guided flying object. 4. The launch vehicle for a guided flying vehicle according to claim 1, further comprising a shock absorber connected to the hook and configured to reduce an impact applied to the aircraft by a thrust at the time of launching the guided flying vehicle.