JPH0682197A - Trunk extension structure of missile - Google Patents

Abstract

PURPOSE:To miniaturize a stable wing fixed to a trunk rear part, and extend the trunk from a shrinked state and fix the same in a missile mounted on an aeroplane and shot from the flying aeroplane. CONSTITUTION:A trunk 3 of a missile 1 is formed into a cylindrical configuration and is divided into a plurality of portions longitudinally, and is assembled into a telescopic system of a plurality of stages. Tapers 7, 8 are formed in a front end inner peripheral surface of an outside cylindrical structure 5 and in a rear end outer peripheral surface of an inside cylindrical structure 6, each taper having a slanting angle ranging from about 3-10 and making contact with each other. The trunk 3 is extended into a plurality of stages and is fixed utilizing an engagement of the tapers 7, 8. Hereby, when the missile 1 is mounted on the aeroplane, the trunk 3 is shrinked into a plurality of stages in a telescopic manner, while when the flying structure is shot from the aeroplane, the trunk is extended to a plurality of stages for fixation thereof.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention reduces the size of a stabilizing wing fixed to the rear part of a fuselage and expands and fixes the fuselage from a contracted state in a projectile mounted on the aircraft and launched from the aircraft in flight. The present invention relates to a fuselage extension structure of a flying object.

[0002]

2. Description of the Related Art Conventionally, in this type of flying body, in order to stabilize its flight attitude, a plurality of stabilizing wings are radially fixed to the rear portion of the body of the flying body and fixed. Since this stabilizing wing utilizes the restoring force due to the aerodynamic force during flight, that is, the effect of stabilizing the weather vane, in order to ensure the flight attitude stability of the above-mentioned flying object, its wing area is increased or the center of gravity is increased. It is a requirement that it be installed further back from the position. In the conventional general flying body, the stabilizer blade is attached to the rear portion of the fuselage, and the entire length of the fuselage is constant. Therefore, the blade area of the stabilizer blade is increased in order to obtain sufficient stability.

[0003]

However, in such a conventional flying body, since the comparatively large stabilizing wings constantly project radially from the fuselage, the entire shape of the flying body becomes large, and the flying body becomes large. A large storage space is required when the is installed inside an aircraft, and the installation efficiency is reduced. Therefore, usually, a suspension device is provided on the lower surface of the main wing outside the aircraft or under the fuselage, and a plurality of projectiles are mounted using this suspension device. In this case, a large number of flying objects cannot be mounted, and the maximum speed and cruising performance of the aircraft are reduced due to the increase in air resistance due to the presence of the protrusions outside the aircraft body.

Further, in order to reduce the aerodynamic force applied to a relatively large stabilizer, the direction in which a flying object is launched from a flying aircraft is parallel to the direction in which the angle of attack with respect to the air flow can be reduced, that is, the flight direction of the aircraft. Had to take direction. In this case, when the above-mentioned projectiles are mounted inside an aircraft, a transport mechanism that sequentially stacks the mounted projectiles to the launch position is required, which makes the launcher complicated and large. It was Therefore, space is taken up by the above-mentioned launching device, and the loading efficiency of the aircraft is reduced.

Therefore, the present invention solves such a problem, downsizes the stabilizing wing fixed to the rear part of the fuselage, and expands and fixes the fuselage from a contracted state. The purpose is to provide.

[0006]

In order to achieve the above object, the structure for expanding the fuselage of a flying body according to the present invention is such that a fuselage body of a flying body having a plurality of stabilizing wings fixed to a rear portion thereof is formed in a tubular shape. It is divided into a plurality of parts in the longitudinal direction and combined in a nesting manner of a plurality of stages. Furthermore, the front end inner peripheral surface of the outer tubular body and the rear end outer peripheral surface of the inner tubular body each have an inclination angle of 3 °. Form a taper that is about 10 ° and is in contact with each other,
The fuselage is expanded in multiple stages and can be fixed by biting the taper, and while the flying body is mounted on the aircraft, the fuselage is contracted in multiple stages in a nested manner and is launched from the aircraft. By doing so, it is expanded and fixed in multiple stages.

[0007]

In the fuselage extension structure for a flying vehicle constructed as described above, a plurality of stabilizing wings are fixed to the rear portion, and the fuselage is formed in a tubular shape and divided into a plurality of sections in the longitudinal direction thereof in a plurality of stages. When the projectile is loaded inside the aircraft in a telescopically contracted state, and the projectile is launched from this aircraft, the inner tubular body becomes the piston and the outer tubular body becomes the cylinder. The inner cylindrical body is punched out, and the forward acceleration of this inner cylindrical body forms on the inner peripheral surface of the front end of the outer cylindrical body and the outer peripheral surface of the rear end of the inner cylindrical body, respectively. The loosely tapered tapers come into contact with each other and bite into each other, and as a result, the body operates so as to be extended and fixed in multiple stages.

[0008]

Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. FIG. 1 is a partial cross-sectional explanatory view showing a state in which a fuselage is stretched in a fuselage stretching structure for a flying vehicle according to the present invention. This projectile is a small aircraft for missiles or bombs launched from an aircraft that is mounted and flying in an aircraft, or for anti-electron (ECM), and its fuselage extension structure is After the fuselage is contracted and is launched from the aircraft, the fuselage is expanded and fixed. As shown in FIG. 1, a plurality of, for example, four stabilizer wings 4, 4, are provided at the rear of the fuselage 3. ... are fixed radially. The body 3 is contracted while the flying body 1 is mounted on an aircraft (not shown), and is stretched and fixed after being launched from the aircraft. As shown in FIGS. 1 and 2, the specific structure is that the body 3 is formed into a cylindrical shape having an appropriate diameter, and is divided into a plurality of parts in the longitudinal direction, for example, two front and rear parts, The rear portion has a slightly larger diameter to form an outer cylinder 5, and the front portion has a smaller diameter than the outer cylinder 5 to form an inner cylinder 6. Then, as shown in FIG. 2, the entire inner cylinder 6 is inserted into the outer cylinder 5 to be combined, for example, in a two-stage nested manner. Further, the inner peripheral surface of the front end portion of the outer cylinder 5 and the outer peripheral surface of the rear end portion of the inner cylinder 6 are formed with tapers 7 and 8 which are in contact with each other. When the outer cylinder 5 and the inner cylinder 6 combined in the above-mentioned nesting type are expanded by the firing, the taper 8 of the inner cylinder 6 and the taper 7 of the outer cylinder 5 are caused by the acceleration of the firing. They collide with each other and bite each other to fix them in a stretched state, and the inclination angles of the respective inclinations are, for example, about 3 ° to 10 °. This is to absorb the impact caused by the collision between the outer cylinder 5 and the inner cylinder 6 during the expansion as the plastic strain energy of the material of the outer cylinder 5 and the inner cylinder 6, and the taper inclination angle is smaller as shown in FIG. This is because a large plastic strain area A can be obtained as shown in (4). According to experiments conducted at the research and development stage of the present invention, the taper inclination angle of about 3 ° to 10 ° is favorable in terms of shock absorption and bite fixing.

In the fuselage extension structure constructed as described above, the fuselage 3 is contracted in a plurality of stages in a telescopic manner and mounted on the aircraft. Therefore, the fuselage 3 is mounted while the flying body 1 is mounted on the aircraft. In order to maintain the contracted state, the cartridge is stored in the cartridge 9 as shown in FIG. As shown in FIG. 2, the cartridge 9 is housed in a state in which the body 3 of the flying vehicle 1 (see FIG. 1) is contracted by the outer cylinder 5 and the inner cylinder 6, for example, in a two-stage nesting system, and gas is stored. It is fired by pressure, and as shown in FIG. 5, it is formed to be slightly longer than the length of the outer cylinder 5 and is formed in a rectangular tube shape capable of accommodating the outer cylinder 5 inside. The inner diameter thereof is set to be slightly larger than the outer diameter of the cylindrical outer cylinder 5 shown in FIG. 2, and as shown in FIG. Are positioned at the four corners of the rectangular tubular shape to accommodate the outer cylinder 5 and the inner cylinder 6 that are combined in the nesting manner. An explosive chamber 10 is provided at the rear end of the cartridge 9, and a retainer 10 'is attached to the front thereof. This retainer 1
0'holds the rear end of the outer cylinder 5 by friction when the projectile 1 is launched from the cartridge 9 by the gas pressure, and prevents the gas pressure from being directly applied to the outer cylinder 5, Since the gas pressure is applied only to the bottom surface 15 of the cartridge 6, it is formed into a short tubular shape that can fit into the inner diameter of the cartridge 9, and the cylindrical concave step portion 11 is provided on the outer peripheral side of the front half portion thereof. The outer cylinder 5 is formed so that the rear end portion of the outer cylinder 5 is fitted therein. Further, a cap 12 is attached to the tip of the cartridge 9. As shown in FIG. 5, the cap 12 includes an outer cylinder 5 of the projectile 1 in the cartridge 9.
Also, with the inner cylinder 6 housed, the flying body 1 is capped so as not to be pulled out. As shown in FIG. 6, each of the two side faces has a shear pin 13 made of, for example, a synthetic resin. It is driven from the cylindrical plate 14 and temporarily fixed.

Next, the operation of the fuselage extension structure of the flying object thus constructed will be described. First, in FIG. 5, the cap 12 at the tip of the cartridge 9 is removed, and the flying vehicle 1 is housed inside the cartridge 9. At this time, the body 3 of the flying body 1 is contracted by nesting the inner cylinder 6 inside the outer cylinder 5 as shown in FIG. 2, and the flying body 1 in this contracted state is retracted from the rear side of the body. Insert into the cartridge 9. At this time, the rear end portion of the outer cylinder 5 is securely fitted into the concave step portion 11 formed on the outer peripheral side of the front half portion of the retainer 10 '. Then, as shown in FIG. 5, the cap 12 is fitted to the tip of the cartridge 9, and as shown in FIG. 6, the shear pin 13 is driven from the cylindrical plate 14 of the cartridge 9 to temporarily fix the cap 12. As a result, the flying body 1 is housed in the cartridge 9 in a contracted state. Similarly, the required number of flying bodies 1 are housed in the cartridges 9, respectively.

Next, the required number of the cartridges 9 containing the flying bodies 1 are mounted horizontally or vertically in the aircraft, for example, at appropriate places on the bottom of the fuselage. When the aircraft flies in this state and the projectile 1 is launched during the flight, the explosive filled in the explosive chamber 10 at the rear end of the cartridge 9 shown in FIG. Ignite with an electric fuse. Then, the explosive is burned to generate expanded gas, and the pressure in the space 16 surrounded by the retainer 10 'on the front side of the bottom surface 15 of the inner cylinder 6 increases. Due to this gas pressure, the bottom surface 15 of the inner cylinder 6 is pushed leftward in FIG. At this time, since the rear end portion of the outer cylinder 5 is covered by the front half portion of the retainer 10 ', the above gas pressure is not directly applied, and the outer cylinder 5 remains stationary and acts as a cylinder. The bottom surface 15 of the piston acts as a piston. Therefore, the inner cylinder 6 slides in the outer cylinder 5 and is pushed to the left. At this time, the cap 12 attached to the tip of the cartridge 9 is pushed by the nose of the inner cylinder 6, the shear pin 13 for temporary fixing is cut, and falls off from the tip of the cartridge 9. In this state, the pressure of the expansion gas in the space 16 causes the inner cylinder 6 to be pushed out to the left while being accelerated inside the outer cylinder 5, and at the rear end portion of the inner cylinder 6 where it exits from the front end portion of the outer cylinder 5. The taper 8 formed on the outer peripheral surface and the taper 7 formed on the inner peripheral surface of the front end portion of the outer cylinder 5 collide with each other. At this time, the outer cylinder 5 is rapidly accelerated by being pulled by the inner cylinder 6, but due to the contact of the tapers 7 and 8 having a gentle inclination, the contact portion is plastically deformed to absorb the impact force due to the collision. , Bite into each other. As a result, as shown in FIG. 1, the outer cylinder 5 and the inner cylinder 6 are fixed in a stretched state, and the body 3 becomes the flying body 1 extended to a predetermined length.

In the flying body 1 with the body 3 stretched and fixed in this way, the portion of the outer cylinder 5 is slid in the cartridge 9 shown in FIG. The cartridge 9 is fired to the outside from the tip.
After that, the flying body 1 flies in accordance with a preset target motion. At this time, as shown in FIG. 1, by expanding the body 3, the distance between the center of gravity 17 and the stabilizing wing 4 can be increased, and the wing area required to secure flight attitude stability can be reduced. .

As shown in FIG. 1, on the outer peripheral surface of the body 3 of the flying body 1, a large number of ridges 18, 18, ... Are formed at substantially equal intervals along the longitudinal direction of the body 3. However, this is to allow the airflow to flow along the longitudinal direction of the body 3.

In addition, in FIG.
Although it is shown that one stabilizing blade 4 is attached, the present invention is not limited to this, and any number of two or more may be used.
In addition, in FIGS. 1 and 2, the body 3 is shown as being combined in a two-stage nesting type, but the present invention is not limited to this, and may be combined in a three-stage or more nesting type.

[0015]

Since the present invention is constructed as described above,
A cylindrical body 3 having a plurality of stabilizing wings 4 fixed to the rear part,
With the outer tubular body (5) and the inner tubular body (6) contracted in multiple stages in a telescopic manner, the projectile 1 is mounted inside the aircraft, and the flight is performed from the aircraft. The inner tubular body (6) is ejected by firing the body 1 with gas pressure or the like, and the forward acceleration of the inner tubular body (6) accelerates the inner peripheral surface of the front end portion of the outer tubular body (5). And the taper 7 and 8 formed on the rear end of the inner cylindrical body 6 and having a gentle slope, respectively, come into contact with and bite into each other, and as a result, the body 3 is expanded and fixed in multiple stages. be able to. Therefore, the distance between the center of gravity 17 of the flying object 1 and the stabilizing wing 4 can be increased, and the wing area required to ensure flight attitude stability can be reduced. For this reason, the projecting body 1 can be miniaturized by minimizing the protruding amount of the stabilizing wings 4 from the body 3. Further, when the fuselage 3 is contracted, the length of the fuselage 3 can be shortened to almost half, so that the member for accommodating the flying vehicle 1 can be downsized, and when it is mounted inside the aircraft. The storage space can be reduced. For these reasons, it is possible to mount a large number of flying bodies 1 inside the aircraft.

Further, since the amount of protrusion of the stabilizing wing 4 can be minimized to reduce the wing area, the aerodynamic force applied to the stabilizing wing 4 can be reduced, the structural strength of the wing itself can be improved, and the aircraft in flight. It is possible to increase the degree of freedom of the attitude of the flying body 1 that is launched from the. For example, it is possible to fire vertically downward at a right angle to the flight direction of the aircraft. In this case, the projectiles 1 can be mounted on an aircraft simply by arranging them vertically downward, the launching device can be simplified, and the mounting space can be efficiently used by effectively utilizing the internal space of the aircraft. Can be improved.

[Brief description of drawings]

FIG. 1 is a partial cross-sectional explanatory view showing a state in which a fuselage is expanded in a fuselage expansion structure for a flying vehicle according to the present invention;

FIG. 2 is a cross-sectional view showing a state in which a body divided into a plurality of parts is telescopically combined and contracted,

FIG. 3 is a side view of the flying object in FIG. 2 viewed from the tail side;

FIG. 4 is a graph for explaining a shock absorbing effect by a taper formed on the inner peripheral surface of the front end portion of the outer cylinder and the outer peripheral surface of the rear end portion of the inner cylinder;

FIG. 5 is a cross-sectional view showing a state in which the projectile is contracted and stored inside the cartridge,

6 is a sectional view taken along line VI-VI of FIG.

[Explanation of symbols]

1 ... Flying body, 3 ... Fuselage, 4 ... Stable wings, 5 ... Outer cylinder,
6 ... Inner cylinder, 7, 8 ... Taper, 9 ... Cartridge,
10 ... Explosive chamber, 10 '... Retainer, 15 ... Bottom surface of inner cylinder.

 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Haruichi Kazuhide 682-24-21, Imakawa City, Chiba Prefecture 678-24−211 (72) Inventor Hironobu Furui 1015 Kamiodanaka, Nakahara-ku, Kawasaki City, Kanagawa Prefecture Fujitsu Limited ( 72) Inventor Toshio Sato, 3175 Showa-cho, Kanazawa-ku, Yokohama, Kanagawa Japan Airplane Co., Ltd. (72) Inventor Kiyotaka Tachikawa, 3175, Showa-machi, Kanazawa-ku, Yokohama City, Kanagawa Japan Airplane Co., Ltd.

Claims (1)

[Claims] 1. A fuselage body of a flying body having a plurality of stabilizing wings fixed to a rear portion thereof is formed into a tubular shape, divided into a plurality of parts in a longitudinal direction thereof, and combined in a nesting manner of a plurality of stages, and an outer cylinder. The inner peripheral surface of the front end of the cylindrical body and the outer peripheral surface of the rear end of the inner cylindrical body are formed with a taper in contact with each other with an inclination angle of about 3 ° to 10 °. It is possible to fix it by biting, and while the flying body is mounted on the aircraft, the above fuselage is contracted in multiple stages of nesting type, and it is expanded and fixed in multiple stages by being launched from the aircraft. The structure to expand the fuselage of the flying body.