JPH08295295A - Aircraft housing airframe - Google Patents

Abstract

PURPOSE: To reduce parasite drag and a radio wave reflected area by lessening a frontal projected area of aircraft housing an airframe. CONSTITUTION: In this aircraft 1 housing an airframe 4 in an airframe mounting chamber 2 installed in the fuselage, it is equipped with two airframe mounting devices 3a and 3b being set up in this airframe mounting chamber 2 in parallel with a aircraft outer surface and having such linkage as shifting the airframe 4 to the outside of the chamber 2, and a door 5 of this chamber 2 to be opened at a time when the airframe 4 is shifted to the outside of the this mounting chamber 2, respectively.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an aircraft for accommodating a flying object which can minimize the frontal area.

[0002]

2. Description of the Related Art FIG. 4 shows an example of a conventional aircraft that houses a flying object. Inside the flying body mounting chamber 2 provided inside the body of the aircraft 1, a flying body 4 suspended by a flying body mounting device 3 mounted perpendicularly to the outer surface of the aircraft 1 is stored. It is separated from the outside by a door 5 provided in the flying body mounting chamber.

Since the flying vehicle mounting device 3 is arranged perpendicularly to the outer surface of the portion of the aircraft 1 to which it is mounted, the flying vehicle mounting chamber 2 has a width in which the flying vehicle 4 is suspended. It is determined from the height of the flying vehicle mounting device 3 in the state.

[0004]

In the conventional aircraft in which the projectile is housed, since the projectile mounting device is arranged perpendicularly to the outer surface of the aircraft, the in-flight projectile mounting chamber is provided. The width of is determined by the height of the flying vehicle mounting device with the flying vehicle suspended. For this reason, the front projection area of the aircraft becomes large, which has the following drawbacks. (1) Flight performance deteriorates because harmful resistance during flight increases. (2) Since the radio wave reflection area seen from the front becomes large, the risk of being caught by the threat radar increases.

The present invention is intended to provide an aircraft accommodating a flying vehicle capable of solving the above drawbacks.

[0006]

DISCLOSURE OF THE INVENTION The present invention relates to an aircraft in which a flying body is housed in a flying body mounting chamber provided in a fuselage, and the flying body is arranged in the flying body mounting chamber in parallel with the outer surface of the aircraft. Provided in the flying body mounting device having a link mechanism capable of moving to the outside of the flying body loading chamber, and in the flying body loading chamber that is opened when the flying body moves outside the flying body loading chamber to allow the flying body to pass. It is characterized by having a door.

[0007]

Since the flying vehicle mounting device provided in the flying vehicle mounting room has a link mechanism parallel to the outer surface of the aircraft, the width of the flying vehicle mounting room is The width of the flying object itself can be reduced without being restricted by the height of the flying object mounting device. Therefore, the front projection area of the aircraft can be made smaller than that of the conventional aircraft mounted on board the flying body, which contributes to reduction of harmful resistance and radio wave reflection area.

Further, when the projectile is fired, the link mechanism moves the projectile to a position outside the chamber for mounting the projectile, but the door provided in the chamber for mounting the projectile opens to smoothly fly. Let the body pass.

[0009]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described with reference to FIGS. A flying body mounting chamber 2 having a substantially rectangular cross-section in a direction perpendicular to the axis is provided so as to surround lower portions of the left and right main wings 1a of the aircraft 1 near the wing roots and the body 1b. The length of the projectile mounting chamber 2 in the machine axis direction is a length capable of accommodating the projectile 4, and the projectile mounting chamber 2 has a substantially rectangular parallelepiped shape.

In the flying body mounting chamber 2, left and right main wings 1
Two upper projectile mounting devices 3a, 3a, which are attached to the lower surface of a and are arranged so as to extend downward in parallel with the outer surface of the adjacent portion of the body 1b, Two lower projectile mounting devices 3b, 3b, which are attached to the parts and are arranged so as to extend horizontally in parallel with the outer surface of the adjacent part of the body 1b, are provided. , 3b has a flying body 4 suspended in the machine axis direction.

As shown in FIG. 2, each of the projectile mounting devices 3a and 3b is provided with a mounting portion 6 on the body side and a mounting portion 8 for the flying body 4, and the mounting portions 6 and 8 are mounted on the mounting portions 6 and 8. Are two link members 7 and 7 that are arranged parallel to each other in the vertical or horizontal direction and are parallel to the outer surface of the fuselage and are parallel to each other and have the same length.
Are connected to each other by the attachment part 6, the link members 7, 7
Further, the flying body mounting portion 8 constitutes a parallel link mechanism capable of moving the mounting portion 8 in parallel with the mounting portion 6, that is, the outer surface of the adjacent body portion. By means of a driving device (not shown), the mounting portion 8 can be moved in parallel from a position inside the flying carrier mounting chamber 2 shown by a solid line in FIG. 2 to a position outside the flying carrier mounting chamber 2 shown by a dotted line.

Doors 5, which can be opened and closed, are respectively provided at lower corners on both sides of the flight carrier mounting chamber 2 below the upper flight carrier mounting device 3a and on the sides of the lower flight carrier mounting device 3b. 5 are provided.

In this embodiment, the flying body mounting devices 3, 3
Since a and 3b are arranged inside the flying body mounting chamber 2 so as to be parallel to the outer surface of the aircraft in the adjacent portions of the aircraft 1, let's fly when the width of the flying body mounting chamber 2 is minimum. Only the lateral width of the body 4 is required, and the width of the flying body mounting chamber 2 can be reduced. Therefore, the front projection area of the aircraft can be reduced, and the harmful resistance and the radio wave reflection area can be reduced.

At the time of launching the flying body 4 mounted,
As shown by the arrow in FIG. 2, the flying body mounting device 3a or 3
3 (a) and 3 (b) while moving the link members 7, 7 of b to move the flying body 4 suspended on the mounting portion 8 in parallel with the outer surface of the body according to the mounting portion 6. As shown in, the door 5 on the moving path of the flying object 4 is opened. As a result, the flying body 4 moves through the opened door 5 to the outside of the flying body mounting chamber 2, and the flying body 4 is fired on it. In this way, in this embodiment, the flying object 4 can be reliably fired.

[0015]

As described above, according to the present invention, the front projection area of the aircraft that accommodates the flying object can be made smaller than before. As a result, the following effects can be obtained. (1) Flight performance is improved because harmful resistance during flight is reduced. (2) Since the radio wave reflection area of the aircraft seen from the front is reduced, the risk of being caught by the threat radar is reduced.

[Brief description of drawings]

FIG. 1 is a sectional view of an embodiment of the present invention.

FIG. 2 is a side view of the flying vehicle mounting apparatus according to the embodiment.

FIG. 3 (a) and FIG. 3 (b) are explanatory views of a projectile launching state in the embodiment.

FIG. 4 is a cross-sectional view of an aircraft that houses a conventional flying object.

[Explanation of symbols]

 1 Aircraft 1a Main wing 1b Fuselage 2 Flying body mounting room 3, 3a, 3b Flying body mounting device 4 Flying body 5 Door 6 Mounting part 7 Link member 8 Mounting part

Claims (1)

[Claims] 1. In an aircraft in which a flying body is stored in a flying body mounting chamber provided in the airframe, the flying body is placed inside the flying body mounting chamber in parallel with the outer surface of the aircraft, and the flying body moves to the outside of the flying body loading chamber. It is provided with a projectile mounting device having a possible link mechanism, and a door provided in the projectile mounting chamber that is opened when the projectile moves outside the projectile mounting chamber to allow the projectile to pass therethrough. An aircraft that stores the characteristic flying object.