JPH0784999B2 - Stable wing folding and deploying structure - Google Patents

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a stable wing folding and deploying structure for folding and deploying and stabilizing a stable wing for stabilizing the flight attitude of a flying object which is mounted on the aircraft and is launched from a flying aircraft. BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a stable wing folding and unfolding structure for a flying body, in which the mechanism for folding and unfolding the wing can be simplified and downsized, and the deployed stable wing can be firmly fixed to increase the degree of freedom in the launching posture of the flying body.

[0002]

2. Description of the Related Art In order to stabilize the flight attitude of a projectile mounted on an aircraft and launched from the aircraft in flight, a plurality of stabilizing wings are generally attached to the rear portion of the fuselage of the projectile. This stabilizer wing is attached to the rear of the fuselage by projecting radially and fixed, and while the flight vehicle is mounted on the aircraft, it is stored or folded along the inside of the fuselage or along the outer periphery of the fuselage and is launched from the aircraft. After that, there is a form that spreads radially from the outer peripheral surface of the body.

In the type in which the stabilizer wing is fixed to the rear of the fuselage, the stabilizer wing always projects radially from the fuselage, so that a large storage space is required when the projectile is mounted inside the aircraft. Mounting efficiency decreases.

On the other hand, in the type in which the stabilizing wing is folded and unfolded with respect to the fuselage, the stabilizing wing can be folded, so that the storage space on the aircraft side can be reduced. Therefore, it is mainly applied to the case where the flying object is mounted inside the aircraft to move to the destination. In addition, as described in Japanese Patent Publication No. 63-64720, the conventional structure for folding and deploying a stable wing of such a flying body is as described in Japanese Patent Publication No. 63-64720. In addition to this, the foldable and stable wing with the nesting front and rear struts and the cloth cover of the wing between them is stored in this vacant space, and the outer peripheral surface of the fuselage is stored. A plurality of slots extending parallel to the central axis were formed in the core, and the stabilizer blades were radially extended outward from the slots.

[0005]

[Problems to be Solved by the Invention] However, the above Japanese Patent Publication No. 63
In the stable wing folding and unfolding structure described in Japanese Patent Publication No. 64720, since the stabilizing wing must be folded and stored inside the fuselage of the flying vehicle, the stabilizing wing folding and unfolding mechanism must be equipped. The space was taken up by the stabilizing wings and its folding and unfolding mechanism, which sometimes reduced the space for loading other equipment. Further, in such a stable blade folding and deploying structure, since the deploying operation of the stabilizing blade and the holding and fixing in the deployed state are usually constituted by different mechanisms, the number of parts increases and the structure becomes complicated, It was a big one. For these reasons, the fold-out type stabilizing wing was applicable only to relatively large flying objects such as missiles or bombs.

Further, in the above-mentioned folding and deploying type stabilizer blade, it is generally difficult to sufficiently increase the structural strength in the deployed state, and therefore, the direction of launching the projectile from the aircraft during flight is in the above stabilizer blade. In order to reduce the aerodynamic force applied to the aircraft, it was necessary to make the angle of attack to the airflow smaller, that is, the direction parallel to the flight direction of the aircraft.
Therefore, the launching posture of the projectile, such as launching in a direction perpendicular to the flight direction of the aircraft, cannot be taken, and the degree of freedom thereof is limited. In addition, as described above, when launching projectiles in a direction parallel to the flight direction of the aircraft, a transport mechanism that sequentially sends the projectiles stacked vertically inside the aircraft to the launch position is required. The device became complicated and large in size. 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, makes it possible to simplify and miniaturize the mechanism for folding and unfolding the stabilizing blade, and to firmly fix the deployed stabilizing blade so that the launching posture of the projectile is free. It is an object of the present invention to provide a stable wing folding and deploying structure for a flying object that can increase the degree of flight.

[0008]

In order to achieve the above-mentioned object, the structure for folding and unfolding a stable wing of a flying vehicle according to the present invention has a plurality of stabilizing wings mounted on the rear portion of the fuselage of the flying vehicle on the outer peripheral surface of the rear portion of the fuselage. And a hinge connection having a hinge axis parallel to the center axis of the fuselage, and the end face shapes of the body side hinge and the stable wing side hinge in contact with each other are formed into an inclined surface inclined at a predetermined angle with respect to the hinge rotation surface, and the stable wing side hinge is also provided. Is provided with a spring that constantly urges the body toward the hinge on the fuselage side, and the stabilizer wings are folded while the projectile is mounted on the aircraft, and after being launched from the aircraft, expand radially from the outer peripheral surface of the fuselage. It is designed to be fixed.

In addition, it is effective to provide a fixing stopper at one end of the stabilizer-side hinge in the hinge connection of the stabilizer blade, which holds the hinge so that the hinge does not separate from the fuselage-side hinge when the stabilizer blade is deployed. is there.

[0010]

In the structure for folding and expanding the stable wings of the flying vehicle constructed as described above, a plurality of stabilizing wings mounted on the outer peripheral surface of the rear part of the fuselage of the flying object are hinge-coupled with a hinge axis parallel to the central axis of the fuselage. The projectile is mounted inside an aircraft in a state of being folded by, and the projectile is launched from the aircraft so that the fuselage-side hinge and the stabilizer-wing-side hinge in the hinge connection of the stable wing have a sloped shape in contact with each other. With the end face shape and the biasing force of the spring that constantly biases the stable wing side hinge toward the fuselage side hinge, the stable wing rotates about the hinge axis of the hinge connection and the end faces of both hinges come into contact with each other. Thus, the stabilizing wings automatically operate to radially expand from the outer peripheral surface of the fuselage and be fixed at that position.

[0011]

Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. FIG. 1 is a partially exploded perspective view showing an embodiment of a structure for folding and expanding a stable wing of a flying vehicle according to the present invention. This projectile is a missile or bomb launched from an aircraft that is mounted on an aircraft, or an electron (E)
CM) is a small aircraft, and its stable wing folding and deploying structure is for folding and deploying the stable wing for stabilizing the flight attitude of the above-mentioned flying body. As shown in FIG. A plurality of, for example, four stabilizing wings 4, 4, ... Are radially attached to the rear portion of the cylindrical body 3. The stabilizing wings 4, 4, ... Are folded while the flying body 1 is mounted on an aircraft (not shown),
After being launched from the aircraft, it is deployed radially from the outer peripheral surface of the body 3. As shown in FIG. 1 and FIG. 2, the specific mounting structure is as shown in FIG. 1 and FIG.
Is a hinge connection having hinge axes 6, 6, ... In parallel with each other, and the shape of the end faces of the front and rear two body-side hinges 7 and the stable wing-side hinges 8 which are connected to each other by the hinge axis 6 is a hinge rotation surface (see FIG. 2). In the direction perpendicular to the plane of FIG. 2), the front body side hinge 7 is coaxial with the hinge shaft 6 and is inclined at an angle of, for example, 45 degrees.
And a rear stable blade 8 on the stable wing side, for example, a compression spring 9 is installed to attach the stable wing side hinge 8 to the body side hinge 7 at all times.

Here, since the end face shape of the fuselage side hinge 7 and the end face shape of the stable wing side hinge 8 are formed in a slanted shape so as to be in contact with each other, as shown in FIG.
By rotating the stable-wing-side hinge 8 about the hinge shaft 6 at an angle of, for example, 90 degrees or more (actually, about 143 degrees), the slope of the end face shape of the fuselage-side hinge 7 is as if a screw lead. As a result, the contact with the lead moves the stable wing-side hinge 8 back and forth. That is, when the stable wing side hinge 8 is in contact with the fuselage side hinge 7 as shown in FIG. 3B, when the stable wing side hinge 8 is rotated about 143 degrees, the stable wing side hinge 8 advances in the direction of arrow A as shown in FIG. Then, when rotating from this state in the opposite direction to 143 degrees,
As shown in FIG. 7B, the stable wing side hinge 8 retracts in the direction of arrow B. At this time, as shown in FIG. 2, since the compression spring 9 is interposed between the front body-side hinge 7 and the rear stabilizer-side hinge 8, as shown in FIG. 4 is folded and the stable wing side hinge 8 is rotated 143 degrees, the compression spring 9 is compressed and the arrow C
A biasing force always acts in the direction, and the deploying torque of the stabilizing blade 4 can be obtained by the principle of "a screw having a large lead angle" due to the slope of the body side hinge 7. When the stabilizing blade 4 is released from the folded state, the stabilizing blade side hinge 8 is retracted in the arrow B direction as shown in FIG. 3 (b) by the expansion torque due to the biasing force of the compression spring 9 in the arrow C direction. The stabilizing wing 4 automatically deploys, rotates about 143 degrees, and the stabilizing wing-side hinge 8 comes into full contact with the slope of the body-side hinge 7 to stop the deploying operation. Further, the compression spring 9 presses the stabilizing-wing-side hinge 8 against the slope of the body-side hinge 7, so that the expanded stabilizing-wing 4 is fixed.

At this time, as shown in FIGS. 4 and 5, the stabilizer blades 4 are radially expanded from the outer peripheral surface of the body 3 (for example, in a cross shape) and fixed. In order to secure the fixation of the stable blade 4 in the deployed state, as shown in FIG. 2, the hinge 8 is provided at the front end portion of the stable blade-side hinge 8 in the hinge connection of the stable blade 4 and the fuselage-side hinge 7. It is also possible to provide a fixing stopper 10 for holding the fixing stopper 10 so as not to separate from it.
The fixing stopper 10 is provided with a screw 1 on the outer peripheral surface of the body 3.
It consists of a leaf spring attached at 0 ', etc., and as shown in FIG. 3 (a), when the stabilizing wing 4 is folded and the stabilizing wing side hinge 8 is advanced in the direction of arrow A, along the outer peripheral surface of the body 3 It is in the gap on the lower surface of the hinge 8 on the front side of the stable blade,
As shown in FIG. 3 (b), with the stabilizer blades 4 deployed and the stabilizer-wing side hinges 8 retracted in the direction of arrow B, as shown in FIG. It is adapted to be locked to the front end of the hinge 8. As a result, the stable wing-side hinge 8 cannot be rotated by being sandwiched between the front and rear by the body-side hinge 7 and the fixing stopper 10, and the stable wing 4 is firmly fixed in the deployed state.

In the structure for folding and expanding the stable blade constructed as described above, when the stabilizing blade 4 is folded, the compression spring 9 always exerts a biasing force in the expanding direction. Since the stabilizer wing 4 is held in the folded state while the vehicle is mounted on the aircraft,
It is stored in the cartridge 11 as shown in FIG. This cartridge 11 has the stabilizing wings 4, 4, ... As described above.
Is stored and fired in a state in which the stable wings 4 are folded and hinged by the hinge connection, and the projectile 1 is stored therein, as shown in FIG. It is formed in a prismatic tubular shape.
The inner diameter is slightly larger than the outer diameter of the cylindrical body 3 shown in FIG. 1, and the hinge shafts 6 provided at the respective apexes formed at the rear portion of the body 3 in the shape of a square tube are inside the tube. The flying body 1 is housed in the four corners of the vehicle. An explosive chamber 12 is provided at the rear end of the cartridge 11, and a piston 14 is fitted in front of the explosive chamber 12 via a spacer 13. Further, a cap 15 is attached to the tip of the cartridge 11. This cap 15 is, as shown in FIG.
With the flying body 1 housed inside, a lid is provided to prevent the flying body 1 from being pulled out. As shown in FIG. 7, one shear pin 16 made of, for example, a synthetic resin is provided on each side surface of the cartridge. It is designed to be driven in from the tubular plate 17 of 11 and temporarily fixed.

Next, the operation of the structure for folding and deploying the stable wings of the flying object will be described. First, FIG.
In FIG. 3, the cap 15 at the tip of the cartridge 11 is removed, and the flying vehicle 1 is housed inside the cartridge 11. At this time, the stabilizer wings 4, 4, ... At the rear part of the fuselage 3 of the flying body 1 have the hinge shaft 6 as shown by the chain line in FIG.
Is rotated about 143 degrees in a predetermined direction, and is folded along the outer peripheral surface of the body formed into a square shape. This stable wing 4,
In a state where 4, ... Are folded, the flying body 1 is inserted into the cartridge 11 from the rear side of the body. And FIG.
As shown in FIG. 7, the cap 15 is fitted to the tip of the cartridge 11, and as shown in FIG. 7, the shear pin 16 is driven from the cylindrical plate 17 of the cartridge 11 to temporarily fix the cap 15. As a result, the flying body 1 is housed inside the cartridge 11. Similarly, the required number of flying bodies 1 are housed in the cartridges 11, respectively.

Next, the required number of the cartridges 11 accommodating the flying objects 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 12 at the rear end of the cartridge 11 shown in FIG. Ignite with an electric fuse. Then, the explosive burns to generate expanded gas, and the pressure in the space 18 surrounded by the spacer 13 on the front side of the piston 14 increases. The high pressure pushes the piston 14 to the left in FIG. 6, and the movement of the piston 14 causes the flying body 1 to move.
The rear end of the flying body 1 is pushed, and the flying body 1 is pushed out to the left inside the cartridge 11. At this time, the cap 15 attached to the tip of the cartridge 11 is pushed by the nose of the flying body 1 and temporarily attached to the shear pin 1 for temporary fixing.
6 is cut and falls off from the tip of the cartridge 11.
In this state, the projectile 1 is pushed to the left inside the cartridge 11 by the pressure of the expansion gas in the space 18, and is ejected from the cartridge 11 to the outside.

The flying body 1 is mounted on the cartridge 11
When it is driven outward from the tip of the, the restraint by the tubular plate 17 on the stabilizing wings 4, 4, ... Folded around the hinge shaft 6 is released. At this time, the stabilizing wing side hinge 8 is pushed by the urging force of the compression spring 9 shown in FIG. 3A in the direction of arrow C, and the stabilizing wing 4 is moved by the principle of “a screw with a large lead angle” due to the slope of the body side hinge 7. As the deployment torque is generated, the stable wing-side hinge 8 retracts in the direction of arrow B as shown in FIG. 3 (b), and as shown in FIGS. 4 and 5,
Each of the four stabilizing wings 4 automatically expands in the direction of the arrow. Thereafter, the stable wing-side hinge 8 is rotated about 143 degrees and comes into full contact with the slope of the body-side hinge 7 as shown in FIG. Stabilizes the wing side hinge 8 and the fuselage side hinge 7
The stabilizing blade 4 is fixed in the deployed state by pressing it against the slope surface of. In such a state, the flying body 1 flies according to a preset target motion. It should be noted that during the period from the time when the stabilizer blade 4 starts to be expanded to the time when the stabilizer blade 4 is fixed, even if an aerodynamic force such as a side wind is applied to the stabilizer blade 4, the stabilizer blade 4 will escape to the leeward side by waving. The hinge connection part is not overloaded.

As shown in FIGS. 4 and 6, on the outer peripheral surface of the front half of the body 3 of the flying body 1, a large number of ridges 19, 19, ... Along the longitudinal direction of the body 3 are arranged at substantially equal intervals. This is because the airflow is made to flow along the longitudinal direction of the body 3.

Further, in FIGS. 1 and 5, the rear portion of the body 3 is shown to be formed into a square tube shape and four stabilizing wings 4 are attached, but the present invention is not limited to this, and the body 3 is not limited to this. The rear part may have a polygonal or circular cross section, and the number of stabilizing blades 4 may be two or more. Further, the strength of the compression spring 9 may be appropriately determined in consideration of the folding and unfolding operation of the stabilizing blade 4 and the fixed strength at the time of unfolding.

[0020]

Since the present invention is constructed as described above,
A plurality of stabilizing wings 4 mounted on the outer peripheral surface of the rear portion of the fuselage 3 of the flying body 1 are folded by a hinge connection having a hinge axis 6 parallel to the central axis 5 of the fuselage, and the flying body 1 is inside the aircraft. Mounted on a vehicle, and the projectile 1 is only launched from the aircraft, the end faces of the fuselage side hinge 7 and the stabilizer wing side hinge 8 in contact with each other in the hinge connection of the stable wing 4 and the stable wing side hinge 8 With the urging force of the spring (9) that constantly urges the
The stabilizer blade 4 rotates about the hinge shaft 6 of the hinge joint, and the end surfaces of both the hinges come into contact with each other, so that the stabilizer blade 4
Can be automatically expanded radially from the outer peripheral surface of the body and fixed at that position.

Therefore, unlike the conventional case, it is not necessary to fold and store the stabilizing wings inside the fuselage of the flying body itself or to equip the folding and unfolding mechanism, and the space in the fuselage 3 of the flying body 1 can be effectively used. Can be used. Further, since the structure for expanding and fixing the stabilizing blade 4 is realized by the same mechanism, the number of parts is small and the mechanism for folding and expanding can be simplified and downsized. Therefore, the folding expansion type stabilizing wing can be applied to a small flying body.

Further, since the stabilizing wing 4 in the deployed state is firmly fixed by the inclined end surface shapes of the fuselage side hinge 7 and the stabilizing wing side hinge 8 and the urging force of the spring (9), it can be fixed from the aircraft in flight. The degree of freedom of the attitude of the flying projectile 1 can be increased. 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]

1 is a partially exploded perspective view showing an embodiment of a structure for folding and deploying a stable wing of a flying vehicle according to the present invention;

FIG. 2 is a partial cross-sectional explanatory view showing a structure for attaching a stabilizer wing to a flying object,

FIG. 3 is an enlarged explanatory view of a main portion showing a state in which a stable blade is connected to a hinge;

FIG. 4 is a front view of the flying object in FIG. 2 seen from the nose side;

5 is a sectional view taken along line VV of FIG.

FIG. 6 is a partial cross-sectional explanatory view showing a state in which a flying object is stored inside a cartridge;

7 is a sectional view taken along line VII-VII of FIG.

[Explanation of Codes] 1 ... Flying body, 3 ... Fuselage, 4 ... Stabilizing wing, 5 ... Fuselage center axis, 6 ... Hinge axis, 7 ... Fuselage side hinge, 8 ... Stabilizing wing side hinge, 9 ... Compression spring, 10 ... Fixed Stopper, 11 ... Cartridge.

Front page continuation (72) Inventor Hiroshi Furui Shinnobu 1015 Kamiodanaka, Nakahara-ku, Kawasaki City, Kanagawa Prefecture Fujitsu Limited (72) Inventor Toshio Sato, 3175, Showa-machi, Kanazawa-ku, Yokohama, Kanagawa In-company (72) Inventor Yukio Otsuka 3175 Showa-cho, Kanazawa-ku, Yokohama-shi, Kanagawa Japan Airplane Co., Ltd.

Claims (2)

[Claims] 1. A plurality of stabilizing blades attached to a rear portion of a fuselage of a flying body are hinged to each other on an outer peripheral surface of the rear portion of the fuselage having a hinge axis parallel to a central axis of the fuselage. The contacting end face is formed into a slant face inclined at a predetermined angle with respect to the hinge rotation face, and
The stabilizer wings are provided with springs that constantly urge the hinges toward the fuselage side hinges, and the stabilizer wings are folded while the projectile is mounted on the aircraft, and the fuselage outer peripheral surface after being launched from the aircraft. A structure for folding and deploying a stable wing of a flying vehicle, which is characterized in that it is radially deployed and fixed. 2. A fixing stopper is provided at one end of the stable wing side hinge in the hinge connection of the stable wing to hold the stable wing so as not to separate from the fuselage side hinge when the stable wing is deployed. A structure for folding and deploying a stable wing of a flying body according to claim 1.