JP2001116497A - Missile - Google Patents

Abstract

PROBLEM TO BE SOLVED: To obtain a missile which is released from an aircraft to an aimed target without being equipped with a propelsive device to sufficiently reach the target even being released in the outside of the range of an antiaircraft firearm while a sufficient quantity of mountable missible is secured on the aircraft. SOLUTION: A bomb 1 is equipped with main wings 4 of a high aspect ratio which increase the lift-drag ratio of the bomb 1 while the bomb 1 being in the flight, an expanding mechanism 5 which folds the left and right main wings 4 along the left and right side of the fuselage before the bomb 1 is released from the aircraft, and expands the main wings 4 in the pitching direction and then in the rolling direction of the fuselage after being released from the aircraft, and a restraint wire 11 which is provided between the left and right main wings 4, and restrains expanding operation of the main wings 4 in the pitching direction while the bomb 1 is mounted on the aircraft.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flying object such as a bomb having no propulsion device which is dropped from an aircraft and falls toward a predetermined target.

[0002]

2. Description of the Related Art FIG. 6 is a configuration diagram of a conventional bomb which is a flying object having no propulsion device for generating a thrust toward an axle forward. 1 is a bomb, 2 is a fuselage of the bomb 1, 3 is a stabilizer of the bomb 1, a is an air current, and a is a fuselage 2 and a stabilizer 3
Is the drag between the fuselage 2 and the stable wing 3. FIG. 7 is an explanatory view of a conventional bomb, FIG. 7 (a) is an explanatory view showing a relationship between a lift-drag ratio of the bomb and a flying distance, and FIG. 7 (b) is a bomb dropping mother machine and a target body. It is an explanatory diagram showing a relative positional relationship with an attack target, where d is the lift-drag ratio of a conventional bomb, o is the flight distance of the conventional bomb, and mosquito is mounted during flight. It is a dropping mother machine that drops bomb 1,
K is an attack target having an anti-aircraft weapon, and K is the range of the anti-aircraft weapon of the attack target K.

In FIG. 6, when a bomb 1 flies, a stable wing 3 provided at the rear of the fuselage generates a moment acting in the direction of head-down around the center of gravity, for example, so that the bomb 1 moves in the vertical and horizontal directions. In each case, fly to the target in a statically stable posture. At that time, the bomb 1 receives the air current A and generates lift and drag U on the entire body. The lift / drag ratio k ₀ of the bomb 1 is expressed by Expression 1 using the lift and drag U.

[0004]

(Equation 1)

[0005] The lift-drag ratio k ₀ shown in Equation 1 is one of the parameters for determining the flying distance of the bomb 1, and qualitatively, as shown in FIG. Since a relationship such as a) is established, when the lift-drag ratio of the bomb 1 is determined, the flight distance of the bomb 1 is set accordingly.
There is a close relationship between the flight distance of the bomb 1 and the survivability of the bomb 1 dropper, and in FIG. 7 (b) showing the relative positional relationship between the bomb dropper and the attack target, If the flight distance of 1 is not enough, the dropping machine of bomb 1 will drop the bomb 1 enough to reach the target
It is necessary to fly within the range of the target's anti-aircraft weapons, especially for facilities and military ships where the target is important, such as air defense radar and anti-aircraft guns and short-range anti-aircraft missiles. Since an anti-aircraft weapon is provided, there has been a problem that as a result, the dropping base unit of the bomb 1 is intercepted by the anti-aircraft weapon provided in the attack target.

[0006] In the conventional bomb 1, if an expensive guidance device is not provided, it is inevitable that the bomb 1 must be dropped at a short distance in order to cause great damage to the attack target key. As a result, it was inevitable that the base unit of the bomb 1 would be exposed to the threat of anti-aircraft weapons provided for the target.

[0007]

SUMMARY OF THE INVENTION In order to prevent a bomb dropping base unit from being intercepted by an anti-aircraft weapon provided on the attack target, even if the attack target is dropped from outside the range of the anti-aircraft weapon of the attack target. You need to increase the flight distance so that you can get enough. However, in order to increase the flight distance, the bomb's airlift surface must be increased,
It is necessary to increase the lift-drag ratio k ₀ shown in the above, but this involves an increase in the external dimensions of the bomb. Conflicting problems such as a decrease in the number occur. In other words, the present invention suppresses the resistance of the bomb's load while the bomb is mounted on the aircraft, while reducing the number of available bombs. On the other hand, it proposes a long-range bomb that can sufficiently reach the target even if the bomb is dropped from the outside of the range of the anti-aircraft weapon of the target.

[0008]

According to a first aspect of the present invention, there is provided a flying object having no propulsion device in which an aircraft is dropped from an aircraft and falls toward a predetermined target. Stabilizing wings provided at the rear to secure aerodynamic static stability in the vertical and horizontal directions of the flying object, and two left and right sides of a high aspect ratio provided at the center of the fuselage to increase the lift-drag ratio A main wing composed of wings, and before the aircraft is dropped from the aircraft, the left and right wings of the main wing are folded along the left and right side surfaces of the fuselage, respectively, and after the aircraft is dropped from the aircraft, the main wing is And a deployment mechanism for deploying in the order from the pitch direction to the roll direction.

A flying object according to a second aspect of the present invention is a wound spring provided in the deployment mechanism of the flying object, for providing a deployment axis in a pitch direction to the fuselage and applying a rotational force to the deployment wing about the deployment axis. And a deployment axis in the roll direction with respect to the aircraft,
A locking mechanism for fixing the positions of the main wings in the pitch direction and the roll direction after the main wing has completed the deployment operation, and the flying body provided between the left and right wing tips of the main wing while the flying object is mounted on the aircraft. A restraining wire for restraining the deployment operation of the main wing in the pitch direction, and an explosion bolt provided on the restraining wire and controlling the deployment timing of deploying the main wing by cutting the restraining wire are provided.

A flying object according to a third aspect of the present invention includes a servo mechanism provided in the deploying mechanism of the flying object for controlling a deployment movement in a pitch direction with respect to the aircraft, and a deployment axis in a roll direction with respect to the aircraft. And a lock mechanism for fixing the position of the main wing in the roll direction after the main wing has completed the deployment operation.

A flying object according to a fourth aspect of the present invention is a helical spring provided on the deploying mechanism of the flying object, for providing a deployment axis in a pitch direction to the fuselage and applying a rotational force to the deployment wing about the deployment axis. A servo mechanism for controlling the deployment movement in the roll direction relative to the fuselage, a lock mechanism for fixing the position of the main wing in the pitch direction after the main wing has completed the deployment operation, and a mechanism provided between the left and right wing tips of the main wing. A restraining wire for restraining the main wing in a pitch direction while the flying object is mounted on the aircraft, and a deployment timing provided for the restraining wire to cut the restraining wire and control the deployment timing of deploying the main wing. And an explosion bolt that performs.

[0012]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiment 1 FIG. 1 is a block diagram showing Embodiment 1 of the present invention, in which 1 is a bomb, 2 is a fuselage of the bomb 1, 3 is a stabilizer provided on a fuselage 2, and 4 is a high aspect ratio. Reference numeral 5 denotes a deployment mechanism of the main wing 4 provided in the center of the fuselage 2, reference numeral 6 denotes a deployment axis in a pitch direction with respect to the fuselage provided in the deployment mechanism 5, and reference numeral 7 denotes a deployment axis in the pitch direction. Reference numeral 8 denotes a winding spring provided around the circumference, reference numeral 8 denotes a deployment axis in a roll direction with respect to the body provided in the deployment mechanism 5, reference numeral 9 denotes a lock mechanism for fixing the position of the main wing 4 in the pitch direction, and reference numeral 10 denotes a lock mechanism. Reference numeral 11 denotes a lock mechanism for fixing the position of the main wing 4 in the roll direction. Reference numeral 11 denotes a restraining wire provided between the left and right wing ends of the main wing 4.
Reference numeral 2 denotes an explosion bolt provided on the restraining wire 11, A denotes airflow, A denotes lift of the fuselage 2 and the stable wing 3, C denotes drag of the fuselage 2 and the stable wing 3, C denotes lift of the main wing 4, and U denotes a main wing. 4 drag,
“Sa” is the development direction in the pitch direction of the main wing 4, and
In the roll direction. FIG. 2 is an explanatory diagram showing Embodiment 1 of the present invention, and FIG. 2 (a) is an explanatory diagram showing a relationship between a lift-drag ratio of a bomb and a flying distance, and FIG.
FIG. 7 is an explanatory view showing a relative positional relationship between a bomb dropping base unit and an attack target which is a target body. In the figure, d is the same bomb lift-drag ratio as in FIG. 7, and o is the same as in FIG. Is the flight distance of the bomb, mosquito is the same bomb dropping base unit as in FIG. 7, ki is the attack target with the same anti-aircraft weapon as in FIG. 7, and ku is the anti-aircraft weapon with the same attack target as in FIG. The range is the range, s is the lift-drag ratio of the increased bomb 1, and c is the increased range of the bomb 1.

First, a mechanism according to a first embodiment of the present invention will be described with reference to FIG. In the figure, a bomb 1 has a fuselage 2 which is a component similar to a conventional bomb, and a stabilizer wing 3 for the bomb 1 to fly in a statically stable posture in each of a vertical direction and a horizontal direction. The main wing 4 has a high aspect ratio. The main wing 4 is subjected to a pitching and a rolling direction deployment motion with respect to the fuselage by the divided left and right wings and a deployment mechanism 5 of each wing root. The structure can be deployed in the direction in which the span becomes longer. The deployment mechanism 5 is provided with a helical spring 7 that applies the kinetic energy of deployment of the main wing 4 in the pitch direction, but is provided between the left and right wing tips of the main wing 4 while the bomb 1 is mounted on the aircraft. The deployment movement of the main wing 4 is restrained by the restrained wire 11 that has been dropped, and after the bomb 1 is dropped from the aircraft, the restraining wire 11 is cut by the explosion bolt 12 to start the deployment movement of the main wing 4. It is a mechanism that can control timing.

1 (a), 1 (b) and 1 (c), a flying state of the first embodiment of the present invention will be described. Before the bomb 1 was dropped from the onboard carrier,
As shown in (a), the deployment movement of the main wing 4 in the pitch direction is restrained by the restraining wire 11 to have a compact external shape, but when the bomb 1 is dropped from the mounting base machine, the restraining wire 11 The wing 4 is cut by the explosion of the wing 12 and the wing 4 is expanded by the kinetic energy stored in the winding spring 7 so that the wing 4 is arranged in a pitch direction with respect to the fuselage around the deployment axis 6 as shown in FIGS. When the main wing 4 reaches a predetermined position in the developing direction, the position of the main wing 4 in the pitch direction is fixed by the lock mechanism 9. Subsequently, the main wing 4 receives a large pressure on the lower surface of the wing due to the air flow a, and deploys around the deployment axis 8 in the roll direction with respect to the fuselage as shown in FIG. 1 (b) to FIG. 1 (c).
When the main wing 4 reaches a predetermined position in the developing direction, the position of the main wing 4 in the roll direction is fixed by the lock mechanism 10, and thereafter the main wing 4 keeps flying while maintaining a high aspect ratio as shown in FIG. . When the wing 4 of the bomb 1 expands and flies while maintaining a high aspect ratio, the bomb 1 receives an air current, and in addition to the lift and drag generated by the fuselage 2 and the stable wing 3, a new wing 4 is formed. Since lift force and drag force are generated, all of the bombs 1 have lift L 'as shown in Equation 2;
A drag D 'as shown in Equation 3 is generated.

[0015]

(Equation 2)

[0016]

(Equation 3)

Accordingly, the lift-drag ratio k ′ of the bomb 1 is expressed as shown in the following equation (4).
Is increased compared to the conventional bomb lift-drag ratio k ₀ .

[0018]

(Equation 4)

The lift-drag ratio k 'shown in Equation 4 is one of the parameters for determining the flight distance of the bomb 1. The qualitatively shown in FIG. Since the relationship as in a) is established, if the lift-drag ratio of the bomb 1 increases from d to s, the flying distance of the bomb 1 will increase from o to c. By sufficiently increasing the flying distance of the bomb 1, the dropping base unit of the bomb 1 drops the bomb 1 from the outside of the range of the anti-aircraft weapon of the attack target as shown in FIG. The attack target can be reached. That is, the dropping base unit of the bomb 1 can attack the target without being intercepted by an anti-aircraft gun or an anti-aircraft missile provided for the target. In the case where accuracy with respect to the attack target is required, the stabilizing wing 3 may be used as the steering wing, and the bomb may be guided and controlled using a required guiding device.

Further, according to the first embodiment of the present invention, while the bomb is mounted on the aircraft, the wing can be folded to have a compact outer shape, so that the bomb-dropping base unit can be used. In addition to suppressing the load resistance, the number of bombs that can be mounted can be secured by the amount equivalent to the conventional product.

Embodiment 2 FIG. FIG. 3 is a block diagram showing a second embodiment of the present invention, in which 1 denotes a bomb, 2 denotes a fuselage of the bomb 1, 3 denotes a stabilizer provided on the fuselage 2, and 4 denotes a high aspect ratio. Reference numeral 5 denotes a deployment mechanism of the main wing 4 provided at the center of the fuselage 2, reference numeral 6 denotes a deployment axis in a pitch direction with respect to the fuselage provided in the deployment mechanism 5, and reference numeral 13 denotes a deployment axis in the pitch direction. Reference numeral 6 denotes a servo mechanism provided around, 8 denotes a roll axis in the roll direction with respect to the airframe provided in the deploy mechanism 5, 10 denotes a lock mechanism for fixing the position of the main wing 4 in the roll direction, and Is the air current, a is the lift of the fuselage 2 and the stable wing 3, c is the drag of the fuselage 2 and the stable wing 3, C is the lift of the main wing 4, K is the drag of the main wing 4, and S is the wing 4
Is the deployment direction in the roll direction of the main wing 4, S is the mounting angle setting direction of the main wing 4, T is the lift of the changed main wing 4, and H is the changed main wing 4 4 is the drag of the modified fuselage 2 and the stable wing 3
Is the drag. FIG. 4 is an explanatory view showing Embodiment 2 of the present invention. FIG. 4 (a) is an explanatory view showing the relationship between the lift-drag ratio of the bomb and the flying distance, and FIG. It is explanatory drawing which shows the relative positional relationship of a dropping mother machine and an attack target which is a target body, In the figure, d is the lift-drag ratio of the conventional bomb same as FIG. 7, and o is the same conventional bomb as FIG. The flight distance is shown. The mosquito is the same bomb release mother machine as in FIG.
2 is the range of the anti-aircraft weapon of the same attack target as in FIG. 7, ス is the increased lift-to-drag ratio of bomb 1 as in FIG. Is the increased bomb 1 flight distance, te is the increased bomb 1 lift-drag ratio, and g is the further increased bomb 1 flight distance.

First, a mechanism according to a second embodiment of the present invention will be described with reference to FIG. In the figure, a bomb 1 has a fuselage 2 which is a component similar to a conventional bomb, and a stabilizer wing 3 for the bomb 1 to fly in a statically stable posture in each of a vertical direction and a horizontal direction. The main wing 4 has a high aspect ratio. The main wing 4 is subjected to a pitching and a rolling direction deployment motion with respect to the fuselage by the divided left and right wings and a deployment mechanism 5 of each wing root. The structure can be deployed in the direction in which the span becomes longer.

3 (a), 3 (b), and 3 (c), a description will be given of a flying state of the second embodiment of the present invention. Before the bomb 1 was dropped from the carrier,
As shown in FIG. 3A, when the bomb 1 is dropped from the mounting base machine, the main wing 4 is moved around the deployment axis 6 by the servo mechanism 13 from FIG. 3A to FIG. As shown in FIG. 3B, the main wing 4 is subjected to a large pressure on the lower surface of the wing by the airflow a, so that the main wing 4 is subjected to a large pressure on the lower surface of the wing.
As shown in (c), when the main wing 4 is deployed to the predetermined position in the roll direction with respect to the fuselage and reaches the predetermined position in the roll direction, the roll position of the main wing 4 is fixed by the lock mechanism 10, and thereafter. The main wing 4 keeps flying while maintaining a high aspect ratio as shown in FIG. When the wing 4 of the bomb 1 expands and flies while maintaining a high aspect ratio, the bomb 1 receives an air current, and in addition to the lift and drag generated by the fuselage 2 and the stable wing 3, a new wing 4 is formed. Since lift force and drag force are generated, all the bombs 1 generate a lift L 'as shown in Equation 2 and a drag D' as shown in Equation 3. Therefore lift-drag ratio k bomb 1 'is expressed as the number 4, by attaching the wing 4, the lift-drag ratio k' magnitude of increases compared to the lift-drag ratio k ₀ of a conventional bomb.

Further, as shown in FIG. 3 (d), the required mounting angle of the main wing 4 is set by the servo mechanism 13 so that the angle of attack of the fuselage 2 with respect to the air current A becomes zero, and the trimming occurs when flying. By eliminating the large induced resistance of the fuselage 2, the bomb 1 receives the air current A, and the drag tsu having reduced the induced resistance of the fuselage in the fuselage 2 and the stable wing 3, and the lift generated in the fuselage 2 in the main wing 4. As a result of the lifting of the bomb 1 due to the increase in the lift of the bomb 1 and the drag H due to the increase in the induced resistance of the wing 4 caused by the lift compensated,
A lift L ' ₂ as shown in Equation 5 and a drag D' ₂ as shown in Equation 6 are generated.

[0025]

(Equation 5)

[0026]

(Equation 6)

Therefore, the lift-drag ratio k ′ ₂ of the bomb 1 is expressed as shown in Expression 7, and the mounting angle of the main wing 4 is optimized by the servo mechanism 13 as compared with the case where the mounting angle of the main wing 4 is not optimized. Further increase.

[0028]

(Equation 7)

The lift-drag ratio k ′ ₂ shown in Equation 7 is one of the parameters for determining the flying distance of the bomb 1, and the qualitative relationship between the lift-drag ratio and the flying distance is shown in FIG. Since the relationship shown in (a) is established, when the lift-drag ratio of the bomb 1 increases from d to te, the flying distance of the bomb 1 increases from o to o. By sufficiently increasing the flying distance of the bomb 1, the dropping mother machine of the bomb 1 drops the bomb 1 from outside the range of the anti-aircraft weapon of the attack target as shown in FIG. The attack target can be reached. That is, the dropping base unit of the bomb 1 can attack the target without being intercepted by an anti-aircraft gun or an anti-aircraft missile provided for the target. In the case where accuracy with respect to the attack target is required, the stabilizing wing 3 may be used as the steering wing, and the bomb may be guided and controlled using a required guiding device.

Further, in Embodiment 2 of the present invention, while the bomb is mounted on the aircraft, the main wings can be folded into a compact external shape, so that the bomb-dropping base unit can be used. In addition to suppressing the load resistance, the number of bombs that can be mounted can be secured by the amount equivalent to the conventional product.

Further, in the second embodiment of the present invention, the mounting angle of the main wing 4 can be optimized by the servo mechanism 13, so that the lift-drag ratio of the bomb can be increased as shown by the following equation (7). It is superior to form 1 in flight distance extension.

Embodiment 3 FIG. FIG. 5 is a block diagram showing Embodiment 3 of the present invention. In the drawing, reference numeral 1 denotes a bomb, 2 denotes a fuselage of the bomb 1, 3 denotes a stabilizer provided on the fuselage 2, and 4 denotes a high aspect ratio. Reference numeral 5 denotes a deployment mechanism of the main wing 4 provided in the center of the fuselage 2, reference numeral 6 denotes a deployment axis in a pitch direction with respect to the fuselage provided in the deployment mechanism 5, and reference numeral 7 denotes a deployment axis in the pitch direction. Reference numeral 8 denotes a winding spring provided around the circumference, 8 denotes a deployment axis in the roll direction with respect to the body provided in the deployment mechanism 5, and 14 denotes a deployment axis 8 in the roll direction.
9 is a lock mechanism for fixing the position of the main wing 4 in the pitch direction, 11 is a restraining wire provided between the left and right wing ends of the main wing 4, and 12 is a restraining wire 11. It is an explosion bolt provided,
A is the lift of the fuselage 2 and the stable wing 3, C is the drag of the fuselage 2 and the stable wing 3, C is the lift of the main wing 4, U is the drag of the main wing 4, and S is the development direction of the main wing 4 in the pitch direction. Is the deployment direction of the main wing 4 in the roll direction, and na is the dihedral angle setting direction of the main wing 4.

First, a mechanism according to a third embodiment of the present invention will be described with reference to FIG. In the figure, a bomb 1 has a fuselage 2 which is a component similar to a conventional bomb, and a stabilizer wing 3 for the bomb 1 to fly in a statically stable posture in each of a vertical direction and a horizontal direction. The main wing 4 has a high aspect ratio. The main wing 4 is subjected to a pitching and a rolling direction deployment motion with respect to the fuselage by the divided left and right wings and a deployment mechanism 5 of each wing root. The structure can be deployed in the direction in which the span becomes longer. The deployment mechanism 5 is provided with a helical spring 7 that applies the kinetic energy of deployment of the main wing 4 in the pitch direction, but is provided between the left and right wing tips of the main wing 4 while the bomb 1 is mounted on the aircraft. The deployment movement of the main wing 4 is restrained by the restrained wire 11 that has been dropped, and after the bomb 1 is dropped from the aircraft, the restraining wire 11 is cut by the explosion bolt 12 to start the deployment movement of the main wing 4. It is a mechanism that can control timing.

Next, FIGS. 5 (a), 5 (b) and 5 (c) show a flying state of the third embodiment of the present invention. Before the bomb 1 was dropped from the carrier,
As shown in (a), the deployment movement of the main wing 4 in the pitch direction is restrained by the restraining wire 11 to have a compact external shape, but when the bomb 1 is dropped from the mounting base machine, the restraining wire 11 The wing 4 is cut by the explosion of the wing 12 and the wing 4 is expanded by the kinetic energy stored in the winding spring 7 so that the wing 4 is arranged in a pitch direction with respect to the fuselage around the expansion axis 6 with respect to the airframe as shown in FIGS. 5 (a) to 5 (b). When the main wing 4 reaches a predetermined position in the developing direction, the position of the main wing 4 in the pitch direction is fixed by the lock mechanism 9. Subsequently, the main wing 4 is deployed by the servo mechanism 14 around the deployment axis 8 in the deployment direction of the roll with respect to the fuselage as shown in FIGS. 5 (b) to 5 (c). Keep flying with high aspect ratio like). When the wing 4 of the bomb 1 expands and flies while maintaining a high aspect ratio, the bomb 1 receives air currents, and in addition to the lift and drag generated by the fuselage 2 and the stable wing 3, a new wing 4 Due to lifting and dragging, all bomb 1 units are
, And a drag D ′, such as Equation (3). Therefore lift-drag ratio k bomb 1 'is expressed as the number 4, by attaching the wing 4, the lift-drag ratio k' magnitude of increases compared to the lift-drag ratio k ₀ of a conventional bomb. Number 4
The lift-drag ratio k 'shown in Fig. 2 is one of the parameters that determine the flight distance of the bomb 1. The lift-drag ratio and the flight distance are qualitatively related to each other as shown in Fig. 2 (a). Therefore, when the lift-drag ratio of the bomb 1 increases from d to s, the flying distance of the bomb 1 increases from o to c. Bomb 1
By sufficiently increasing the flight distance of the bomb 1, the dropper of the bomb 1 will drop the bomb 1 from outside the range of the anti-aircraft weapon of the attack target as shown in FIG. Can be reached. That is, the dropping base unit of the bomb 1 can attack the target without being intercepted by an anti-aircraft gun or an anti-aircraft missile provided for the target. In the case where accuracy with respect to the attack target is required, the stabilizing wing 3 may be used as the steering wing, and the bomb may be guided and controlled using a required guiding device.

In the third embodiment of the present invention, while the bomb is mounted on the aircraft, the main wing can be folded to have a compact outer shape. In addition to suppressing the load resistance, the number of bombs that can be mounted can be secured by the amount equivalent to the conventional product.

In Embodiment 3 of the present invention, FIG.
As shown in (d), the dihedral angle of the wing 4 can be adjusted with the set direction by the deployment servo mechanism 13, so that when the bomb is used as a guided bomb, in the first and middle stages of guidance where stable flying characteristics are required. Set the dihedral angle to 0 to secure the roll stability of the fuselage, and at the end of guidance where responsiveness of the fuselage is required, set a predetermined dihedral angle and make a turn instead of sacrificing some of the roll stability of the fuselage. Embodiment 2 is superior to Embodiment 1 or Embodiment 2 in terms of guidance control performance in that an optimum body roll characteristic can be set according to the flying situation of the bomb 1, such as reducing the constant.

[0037]

According to the first aspect of the present invention, a flying object such as a bomb having no propulsion device for flying from an aircraft to a predetermined target body has the flying object mounted on the aircraft. In the meantime, in addition to suppressing the load resistance of the flying object, while securing the number of vehicles that can be mounted equivalent to the conventional product, on the other hand, the range of the range of the anti-aircraft weapon of the attack target where the flying object is the target is Even if dropped from the outside, the target body can be sufficiently reached, and as a result, the target body can be attacked without damaging itself.

Further, according to the second aspect, the range of the flying object can be further extended as compared with the first aspect.

Further, according to the third aspect, the guidance control performance is superior to the first and second aspects.

[Brief description of the drawings]

FIG. 1 is a configuration diagram showing a first embodiment of the present invention.

FIG. 2 is an explanatory diagram showing the first embodiment of the present invention.

FIG. 3 is a configuration diagram showing a second embodiment of the present invention.

FIG. 4 is an explanatory diagram showing Embodiment 2 of the present invention.

FIG. 5 is a configuration diagram showing a third embodiment of the present invention.

FIG. 6 is a configuration diagram of a conventional bomb.

FIG. 7 is an explanatory view of a conventional bomb.

[Explanation of symbols]

 Reference Signs List 1 bomb 2 fuselage 3 stable wing 4 main wing with high aspect ratio 5 deployment mechanism of main wing 4 6 deployment axis in pitch direction winding spring roll axis in deployment direction locking mechanism in pitch direction locking mechanism in roll direction constraint wire explosion bolt servo in pitch direction Mechanism Servo mechanism in the roll direction a Airflow b Lift of fuselage 2 and stabilizers 3 c Drag of fuselage 2 and stabilizers 3 d Lift / drag ratio of conventional bombs e Conventional bomb flying distance f Bomb-dropping base unit A Anti-aircraft firearm Attack target with hull Attack target's range of anti-aircraft weapons KE Lift of main wing 4 Drag of main wing 4 Deployment direction in pitch direction Deployment direction in roll direction Increased lift-drag ratio of bomb 1 Increased flight distance of bomb 1 Setting angle setting direction of wing 4 Changed lift of wing 4 Changed resistance of wing 4 Changed resistance of fuselage 2 and stable wing 3 Increased lift / drag ratio of bomb 1 further increased Flying distance of bomb 1

Claims (4)

[Claims] 1. A flying object having no propulsion device in which an aircraft is dropped from an aircraft and falls toward a predetermined target object, wherein the flying object is provided at the rear of the fuselage with respect to the longitudinal direction and the lateral direction of the flying object. A stable wing that ensures aerodynamic stability,
A main wing comprising two left and right wings having a high aspect ratio, which is provided at a center portion of the fuselage of the flying object and increases a lift-drag ratio;
Before the aircraft is dropped from the aircraft, the left and right wings of the main wing are respectively folded along the left and right sides of the fuselage, and after the aircraft is dropped from the aircraft, the main wings are moved from the pitch direction to the roll direction with respect to the aircraft. A flying object having a deployment mechanism for deploying in order. 2. A deployment axis provided on the flying body deployment mechanism in a pitch direction with respect to the fuselage, a winding spring for applying a rotational force to the deployment wing about the deployment axis, and deployment in a roll direction with respect to the aircraft. A shaft, a lock mechanism for fixing the positions of the main wing in the pitch direction and the roll direction after the main wing has completed the deployment operation, and while the flying object provided between the left and right wing tips of the main wing is mounted on the aircraft Comprises a restraining wire for restraining a deployment operation of the main wing in a pitch direction, and an explosion bolt provided on the restraining wire and controlling a deployment timing of deploying the main wing by cutting the restraining wire. The flying object according to claim 1. 3. A servo mechanism provided in the deploying mechanism of the flying object for controlling a deploying movement in a pitch direction with respect to the fuselage, a deploying axis in a roll direction with respect to the fuselage, and the main wing has completed the deploying operation. The flying object according to claim 1, further comprising a lock mechanism for fixing a position of the main wing in the roll direction later. 4. A deploying axis provided in the deploying mechanism of the flying object in a pitch direction with respect to the fuselage, a winding spring for applying a rotational force to the deploying wing about the deploying axis, and deploying in a roll direction with respect to the fuselage. A servo mechanism for controlling the movement, a lock mechanism for fixing the position of the main wing in the pitch direction after the main wing has completed the deployment operation, and a flying object provided between the left and right wing tips of the main wing are mounted on the aircraft. A restraining wire for restraining a deployment operation of the main wing in a pitch direction is provided, and an explosion bolt provided on the restraining wire and controlling a deployment timing of deploying the main wing by cutting the restraining wire is provided. The flying object according to item 1.