JP2001116493A - Guided missile launcher - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a launcher which is used for launching a guided missile from an aircraft in the backwards and can prevent the maneuverability and flying safety of the aircraft from being impaired by preventing a large asymmetric load from being applied to the wings of the aircraft due to the thrust which is generated when the missile is launched. SOLUTION: A launcher for launching a guided missile from an aircraft in the backwards is provided with a shock absorber which absorbs the dynamic load which is transmitted between the launcher of the aircraft and the launcher when the missile is launched so as to suppress the transmission of the thrust transmitted to the aircraft when the missile is launched.

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 that is mounted on an aircraft (hereinafter referred to as a "base unit") and fires toward a predetermined target located behind the base unit. .

[0002]

2. Description of the Related Art The use of a guided flying object mounted on an aircraft and capable of flying toward the rear of a base unit will be described with reference to FIG. FIG. 5A is a diagram showing a launching situation of the guided flying object 3 launched toward the rear of the base unit 1,
,... Indicate, in chronological order, changes in the state of the guided flying object 3 after the launch. FIG. 5 (b) is a view showing a launch vehicle for a guided flying object attached to a base unit via a launcher, where 1 is a base unit, 2 is a launcher, 3 is a guided flying unit, 4 is a propulsion device, 5 is a nozzle of a propulsion device, 6 is a launch tube for accommodating a guided flying object, 14 is a hook for suspending the launch tube on the launcher of the base unit, 15 is a hanger,
16 is a cover A attached to the rear end of the launch tube, 17 is a cover F attached to the front end of the launch tube, 18 is a deployed wing of a guided flying object stored in the launch tube in a folded state.
A, 19 are deployment wings F of the guided flying object stored in the launch tube in a folded state, 20 are hanger rails for sliding the guided flying object in the launching direction inside the launch tube,
Reference numeral 21 denotes a radome, and reference numeral 22 denotes a wing guide rail for folding and storing the deployed wing.

[0005] FIG. 5A shows a state in which a guided flying object 3 is housed in a launch cylinder 6 attached to a base unit 1 via a launcher 2. The guided flying vehicle 3 is fired from the launch tube 6 toward the rear of the base unit 1, 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 Although it is decelerating (state), it accelerates in the flying direction over time (state) and continues flying (state).

[0004] In FIG.
Is housed inside a launching cylinder 6 having a cover A16 and a cover F17 to prevent the nozzle 5 of the propulsion device 4 of the guided flying object 3 being carried by the motherboard from collision with ice, birds, and the like in the atmosphere. , The radome 21 is protected from the external environment such as aerodynamic heating, aerodynamic load and rain. At the time of firing, the guided flying object 3 is ejected along the hanger rail 20 in a direction opposite to the flight direction of the base unit 1 to fly.

[0005]

In the conventional launch vehicle for guided flying vehicles, a large asymmetric load is applied to the wings of the base aircraft due to the thrust when the guided flying vehicle is launched, and the kinematic performance and flight safety of the base aircraft are increased. There was a problem that was damaged.

According to the present invention, the effect of the thrust generated when the guided flying object accommodated in the launch tube is fired to reduce the load applied to the mother device via the launch tube and affect the kinematic performance and flight safety of the mother device. An object of the present invention is to obtain a reduced launch vehicle for a guided flying vehicle.

[0007]

According to a first aspect of the present invention, there is provided a launching tube for a guided flying object, which stores a guided flying object to be fired toward the rear of a mounted aircraft before launching. Covers respectively attached to both ends of the launch tube, hooks for suspending the launch tube from the aircraft, and disposed between the aircraft and the launch tube and transmitted from the launch tube to the aircraft Means for buffering a dynamic load during firing.

The launching tube for a guided flying object according to a second aspect of the present invention includes an openable / closable cover attached to an end of the launching tube on the front side of the aircraft (a rear end of the launching tube), and the openable / closable cover. And a drive mechanism for opening and closing the.

A third aspect of the invention provides a launch vehicle for a guided flying object, comprising: an openable / closable cover attached to an end (front end of the launching tube) of the launching tube on the rear side of the aircraft; And a drive mechanism for opening and closing.

In a fourth aspect of the invention, a cover mounted on the front end of the aircraft has a pointed tip.

[0011]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiment 1 FIG. 1 is a view showing Embodiment 1 of the present invention. FIG. 1 (a) shows a state in which a guided flying object is mounted on a base unit, and FIG. 1 (b) shows a state immediately after the guided flying object is fired. The state of is shown. In the figure, 1 is a base machine, 2 is a launcher, 3 is a guided flying object, 4 is a propulsion device, 5 is a nozzle of a propulsion device, 6 is a launching cylinder, 7 is disposed between the launcher and the launching cylinder, and A buffer device 14 for buffering a dynamic load at the time of launching transmitted between the launcher and the launching tube. 14 is a hook for suspending the launching tube 6 on the launcher of the mother machine at two support portions spaced apart from each other. Is a hanger, 16 is a cover A attached to the rear end of the launch tube,
Reference numeral 17 denotes a cover F attached to the front end of the launch tube, and reference numeral 18 denotes deployment wings A and 19 stored in the launch tube 6 in a folded state.
Is the deployed wing F stored in the launch tube 6 in a folded state,
Reference numeral 20 denotes a hanger rail for sliding the guided flying object in the firing direction, 21 denotes a radome, 22 denotes a wing guide rail for storing the deployed wings in a folded state, and 23 denotes a blast ejected from the propulsion device. The shock absorber 7 inserts, for example, a damping elastic rubber or a shock absorber constituted by an elastic member and a viscous member at two places (particularly near the hook) between the launcher 2 and the launch cylinder 6. And install it.

In this embodiment, since the launch tube 6 is covered by the covers A and F, when the guided flying object 3 is launched, it receives a thrust for launch and is added to the launch tube 6. A shocking load is applied to the launch cylinder 6 via the hook 14.
To the launcher 2. In this process, the shock absorber 7
The transmission of this load is suppressed by the action of. Therefore, a large asymmetric load is not applied to the wings of the base unit 1, and the kinetic performance and flight safety of the base unit 1 can be maintained. When the launch vehicle 3 is launched, the radome 21 has a cover F1.
By breaking through 0, it is separated from the launching cylinder 6. In this case, the shock absorber 7 also effectively acts on the load applied to the firing cylinder 6 when the radome 21 pierces the cover F10.

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. FIG. 2 (c) shows a state after the guided flying object has been fired and separated from the base unit. In the figure, reference numeral 8 denotes a cover A that can be opened and closed, and 9 denotes a drive mechanism for opening and closing the cover A. Other configurations are the same as those of the first embodiment.

In this embodiment, the propulsion device 4 is ignited by opening the cover A8 attached to the rear end of the firing cylinder 6 by using the drive mechanism 9 immediately before firing the guidance flying object 3. Since the blast 23 that is ejected rearward is discharged to the rear of the launch cylinder 6, a load due to thrust is not transmitted from the launch cylinder 6 to the base unit 1, so that the kinetic performance and flight safety of the base unit 1 are maintained. Further, after the guided flying object 3 has been fired and separated from the parent machine, by closing the cover A8, the aerodynamic resistance can be maintained at the same level as before the firing.

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. FIG. 3 (c) shows a state after the guided flying object has been fired and separated from the base unit. In the figure, reference numeral 10 denotes a cover F which can be opened and closed, and 9 denotes a drive mechanism for opening and closing the cover F. Other configurations are the same as those of the first embodiment.

In this embodiment, the cover F10 is opened by the drive mechanism 9 immediately before launching the guided flying object 3, so that the radome 21 does not break through the cover F10 and the guided flying object 3 is launched. , The radome 21 made of a brittle material such as ceramics is not damaged, and there is no possibility that the cover F10 is broken and scattered in the air to damage the mother device 1, thereby maintaining the flight safety of the mother device 1. it can. After the guided flying object 3 has been fired and separated from the base unit 1, the cover F10
By closing, the aerodynamic resistance can be kept equal to that before the launch.

Embodiment 4 FIG. 4 is a view showing a fourth embodiment of the present invention. FIG. 4 (a) shows a state in which a guided flying object is mounted on a 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 11 denotes a cover A having a sharpened tip. Other configurations are the same as those of the first embodiment.

In this embodiment, the aerodynamic resistance is reduced by providing the cover A11 having a sharpened tip at the rear end side of the launch cylinder 6, and the aerodynamic force and aerodynamic vibration received by the launch cylinder 6 are reduced. As a result, vibration and deformation are reduced, and there is no fear that the vibration and deformation of the wings of the base unit 1 are coupled to influence the flight characteristics, and the flight safety of the base unit 1 can be maintained.

[0019]

According to the first aspect of the present invention, when a guided flying object is fired, the impact load applied to the mother machine through the launch tube due to thrust is suppressed, and the kinetic performance and flight of the mother aircraft are reduced. Safety can be maintained.

According to the second aspect of the invention, when the guided flying object is fired, the thrust is not transmitted from the launch cylinder to the base machine by opening the cover attached to the rear end of the launch cylinder immediately before the launch. Kinetic performance and flight safety can be maintained. Also, after the guided flying object has been fired and separated from the base unit, the cover attached to the rear end of the launch cylinder can be closed to keep the aerodynamic resistance equal to that before the launch.

According to the third aspect of the invention, when the guided flying object is fired, the cover attached to the front end of the launch tube is opened immediately before the launch, so that the radome does not break through the cover. Will leave the launcher,
The radome made of a brittle material such as ceramics is not damaged, and there is no possibility that the cover is broken and scattered in the air to damage the mother machine, and the flight safety of the mother machine can be maintained. Also, after the guided flying object has been fired and separated from the parent machine, the cover attached to the front end of the launch cylinder can be closed to keep the aerodynamic resistance equal to that before the launch.

According to the fourth aspect of the present invention, the aerodynamic drag is provided by providing the cover having a pointed tip at the rear end side of the launch cylinder when the launch vehicle for the guided flying vehicle is mounted on the base unit. As the aerodynamic and aerodynamic vibrations received by the launch tube are reduced, vibration and deformation are reduced, so it is possible to maintain the flight safety of the mother aircraft without fear of affecting the flight characteristics by coupling with the vibration of the wings of the mother aircraft. it can.

[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 a conventional launch vehicle for a guided flying object.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Base machine 2 Launcher 3 Guide flying object 4 Propulsion device 5 Nozzle 6 Launch cylinder 7 Shock absorber 8 Cover A 9 Drive mechanism 10 Cover F 11 Cover A 14 Hook 15 Hanger 16 Cover A 17 Cover F 18 Deployment wing A 19 Deployment wing F Reference Signs List 20 hanger rail 21 radome 22 wing guide rail 23 blast

Claims (4)

[Claims] 1. A launch tube for accommodating a guided flying object to be fired toward the rear of a mounted aircraft before launch, a cover attached to both ends of the launch tube, and the launch from the aircraft. Guided flying equipped with a hook for suspending a tube and a means disposed between the aircraft and the launching tube to buffer a dynamic load during launch transmitted from the launching tube to the aircraft. Launcher for body. 2. An openable / closable cover attached to an end (front end of the launching cylinder) of the launching cylinder on the front side of the aircraft, and a drive mechanism for opening and closing the openable / closing cover. A launch vehicle for a guided flying object according to claim 1. 3. An openable / closable cover attached to an end (front end of the launching cylinder) of the launching cylinder on the rear side of the aircraft, and a drive mechanism for opening and closing the openable / closing cover. A launch vehicle for guided flying vehicles according to item 1. 4. A launch vehicle for a guided flying vehicle according to claim 1, wherein the cover attached to the front end of the aircraft has a pointed tip.