JPH06281394A - Aircraft placing launcher - Google Patents

Abstract

PURPOSE:To direct an airframe etc. to a target without altering a direction of an aircraft to a target of a side or a rear of the aircraft and to perform a lock-on by controlling a direction and a position of a launcher provided on a lower body of the aircraft from a cockpit. CONSTITUTION:A hydraulic oil supply unit 6 is mounted at an aircraft 1 to supply hydraulic oil to a driver 4 of a launcher body 3 through a hydraulic tube 5. The body 3 is rotated by the driver 4 and vertically moved perpendicularly. A post 7 of the body 3 is vertically movable by a hydraulic actuator 8, and rotated by an upper gear 10 of the actuator 8 and a gear 11 of a hydraulic motor 9. With this structure, a pilot controls the body 3 on a lower body of the aircraft 1 to direct an airframe 2 to a target in all directions such as forward, side, rearward, etc., and to lock-on to launch it.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION The present invention relates to a flying object, a flare,
The present invention relates to an aircraft-mounted launcher applied to launch sub-munitions.

[0002]

2. Description of the Related Art FIG. 4 is an explanatory view of a conventional airborne launcher used for launching an air-to-air flying body or the like. In the figure, the launcher has a launcher body 14 attached to both sides of the aircraft 1, and each of the launcher bodies 14 is equipped with one flying body 2. The launcher body 14 is attached with its direction fixed in the flight direction of the aircraft 1.

[0003]

As described above, in the conventional launcher for an aircraft, the launcher main body 14 is fixedly mounted in the flight direction of the aircraft 1, and the launcher is provided only in front of the aircraft 1. 2 can not be fired, so when the pilot locks on the flying body 2 to the target, it is necessary to steer the aircraft 1 so that the target is in front of the aircraft 1 and change the direction. In the meantime, there is a high risk of overlooking the target flying at high speed or being easily targeted by the other aircraft.

[0004]

The launcher for an aircraft according to the present invention is intended to solve the above-mentioned problems, and is a launcher body provided under the torso of an aircraft and capable of rotating in the lateral direction and moving in the vertical direction. And means for controlling the orientation and position of the launcher body from the cockpit of the aircraft.

[0005]

In other words, in the aircraft launcher according to the present invention, the direction and position of the launcher body, which is provided under the body of the aircraft and is capable of rotating in the lateral direction and moving in the vertical direction, are controlled from the cockpit of the aircraft. It is designed so that the pilot can control the direction of the launcher body without changing the direction of the aircraft for the targets on the side and the back of the aircraft and point the flight object etc. to the target and lock it on. In addition, the launcher body position can be controlled in the vertical direction to avoid interference between the launched projectile and the external components of the aircraft, and mutual interference between the projectiles.

[0006]

1 to 3 are explanatory views of an aircraft launcher according to an embodiment of the present invention. In the figure, the air vehicle launcher according to the present embodiment is used for launching an air-to-air flying object, and as shown in FIG.
A launcher body 3 having a mechanism capable of rotating in the yaw direction by 360 ° and vertically moving up and down is attached to the lower part of the body, and the launchers 2 are provided on both sides of each launcher body 3.
It is designed to equip one by one. The movement of the launcher main body 3 is controlled by the pilot from the cockpit, and the pilot controls the launcher main body 3 provided below the body of the aircraft 1 for the targets on the side and the rear of the aircraft 1. The flying body 2 can be aimed and locked on.

As shown in FIG. 2, a hydraulic pressure supply device 6 is installed in the aircraft 1 and supplies hydraulic pressure to a drive device 4 of the launcher body 3 through a hydraulic pipe 5. The launcher main body 3 is configured to make a rotary motion of 360 ° in the yaw direction and a vertical motion in the vertical direction by the drive device 4. The column 7 of the launcher body 3 can be moved up and down by a hydraulic actuator 8 and can be rotated by a combination of a gear 10 above the hydraulic actuator 8 and a gear 11 of a hydraulic motor 9. With this mechanism, the pilot controls the launcher body 3 under the body of the aircraft 1 to direct the flying body 2 to the target in all directions such as the front, side, and rear of the aircraft 1,
It can be locked on and fired. At this time, the flying body 2 launched to the side interferes with the external load below the aircraft 1, or the flying body 2 launched to the front and the rear and the launcher body 3 fly In order to avoid interference with the body 2, the launcher body 3 is designed to move up and down.

Incidentally, as shown in FIG. 3, the launcher body 3 is provided with a launcher cover in case the aerodynamic resistance becomes large when the launcher 3 is rotated and directed to the side, which causes a great hindrance to the motion performance of the aircraft 1. 12 can also be attached. This launcher cover 12 is detachably attached when the flying body 2 is mounted and suspended in consideration of maintainability, but it is attached to the front part of the launcher cover 12 so that the flying body 2 can be launched even in the mounted state. Is the passage 1 of the flying body 2
3 and the exhaust ports 14 for the gas ejected from the propulsion device of the flying body 2 are opened at the rear, respectively, and these opening portions of the launcher cover 12 allow the launcher cover 12 to be attached even when the launcher cover 12 is attached. It is possible to fire. The material of the launcher cover 12 is a light alloy, such as a titanium alloy, which is excellent in strength, rigidity and heat resistance.

In the conventional airborne launcher,
Since the launcher main body 14 is attached with the direction fixed to the flight direction of the aircraft 1, and the projectile 2 can be launched only in front of the aircraft 1, the pilot locks the projectile 2 on the target. In this case, it is necessary to steer the aircraft so that the target is in front of the aircraft and change its direction.During the change of direction, the target flying at high speed may be overlooked or the target may be easily targeted by the other aircraft. However, in the launcher equipped with this aircraft, the pilot controls the launcher main body 3 to aim the flying body 2 at the target without changing the attitude of the aircraft 1 for the target on the side and the rear of the aircraft 1. Since it can be locked on, the response to the target becomes faster, and it is possible to take an overwhelming advantage over the other aircraft.

[0010]

The launcher for mounting on an aircraft according to the present invention is configured as described above, and is aimed at a target such as a flying body without changing the direction of the aircraft with respect to the side and rear targets of the aircraft. Since it can be locked on, the risk of missing the target flying at high speed and being easily targeted by the other aircraft is low.

[Brief description of drawings]

FIG. 1 (a) is a front view of an aircraft launcher according to an embodiment of the present invention, and FIG. 1 (b) is a bottom view.

FIG. 2A is a front view of the hydraulic pressure supply device, and FIG. 2B is a perspective view of a drive device.

FIG. 3 (a) is a front view of a launcher cover of an aircraft-mounted launcher according to an application example of the above embodiment, and FIG. 3 (b) is a bottom view thereof.

FIG. 4 (a) is a front view of a conventional aircraft launcher, and FIG. 4 (b) is a bottom view thereof.

[Explanation of symbols]

 1 Aircraft 2 Flying Body 3 Launcher Main Body 4 Drive Device for Launcher Main Body 5 Hydraulic Pipe 6 Hydraulic Supply Device 7 Support 8 Hydraulic Actuator 9 Hydraulic Motor 10 Gear 11 Gear 12 Launcher Cover 13 Passage Port 14 Exhaust Port

Claims (1)

[Claims] 1. A launcher main body, which is provided under the torso of an aircraft and is rotatable laterally and vertically movable, and means for controlling the orientation and position of the launcher main body from the cockpit of the aircraft. A launcher equipped with an aircraft.