JP2013040744A - Missile - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a missile that can achieve simplification of the structure, reliably deploy a deceleration umbrella, and reliably prevent a propelling part from colliding to a separated payload during inertial flight or both from interfering with each other.SOLUTION: The missile includes: a rocket motor 2 generating thrust force by combustion of a solid propellant 21; a payload part 3 detachably coupled with the rocket motor 2 and separated from the rocket motor 2 after completion of the combustion; and the deceleration umbrella 4 for decelerating the rocket motor 2 by deploying at a state separated from the payload 3. In the rocket motor 2, a deceleration umbrella storage space 25 is formed, wherein the deceleration umbrella storage space 25 has a front opening 25f blocked by the payload part 3 at the stage before separated from the payload 3, and released in front of the flying direction of the rocket motor 2 at the state separated from the payload 3, and a rear opening 25r discharging the deceleration umbrella 4 to the rear side of the flying direction by air A introduced from the front opening 25f.

Description

  The present invention relates to a flying object that carries a payload and flies by thrust obtained from a propulsion unit such as a rocket motor, and in particular, during inertial flight after combustion of the propulsion unit is finished, the payload and the propulsion unit are separated. This is related to a flying object in which flying is continued only in the payload.

Conventionally, as a flying object as described above, there is one described in Patent Document 1, for example.
This flying object is formed by detachably coupling a payload and a rocket motor as a propulsion unit, and the payload and the rocket motor are separated by a separation mechanism using a pyrotechnic such as a gas generator, for example. It has become.

  The rocket motor is provided with a plurality of aerodynamic stabilization plates and an umbrella storage portion that opens toward the flight direction of the rocket motor. In this umbrella storage section, the speed reduction umbrella is stored in a folded state, and the rope of the speed reduction umbrella is connected to the rocket motor side. The speed reduction umbrella housed in the umbrella housing part of the rocket motor is connected to the payload by a wire, and this wire is cut with a predetermined tension by a cutting mechanism.

  In this flying object, when this rocket motor is disconnected from the payload during inertial flight after the completion of combustion of the rocket motor, the payload that intends to continue inertial flight stores the speed reduction umbrella via the wire in the rocket motor umbrella The rocket motor is pulled out from the part in the flight direction, and the rocket motor is decelerated by the deployment of the pulled-out reduction umbrella, so that the rocket motor collides with the payload and the two interfere with each other. .

Japanese Patent Laid-Open No. 2003-185398

  However, in the conventional flying body described above, after the rocket motor and the payload are separated, the wire connecting the speed reduction umbrella and the payload, which has been pulled out from the umbrella housing portion of the rocket motor and deployed, is cut by a cutting mechanism. However, since this cutting mechanism is required to reliably pull out the speed reduction umbrella from the umbrella housing part of the rocket motor and to quickly cut the wire after the speed reduction umbrella is deployed, its structure is precise and complicated. In addition, since the cutting operation is performed based on the tension applied to the wire, there is a problem that it cannot be denied that there is instability.

  In addition, in the conventional flying object, the position relationship between the rocket motor and the deployed speed reducing umbrella is reversed when the speed reducing umbrella pulled out from the umbrella housing part of the rocket motor is deployed. There is a problem that it cannot be said that there is no risk that the umbrella is entangled with the aerodynamic stabilization plate, and it has been a conventional problem to solve these problems.

  The present invention has been made by paying attention to the above-described conventional problems, and can realize the simplification of the structure and reliably deploy the speed reduction umbrella. As a result, the propulsion separated during the inertial flight. An object of the present invention is to provide a flying object capable of reliably preventing a part from colliding with a payload and mutually interfering with each other.

  The invention according to claim 1 of the present invention includes a propulsion unit that generates thrust by combustion of a propellant, a payload unit that is separably coupled to the propulsion unit and that separates from the propulsion unit after completion of combustion during flight, A flying body including a speed reduction umbrella that is coupled to the propulsion part and is deployed at a stage separated from the payload part and decelerates the propulsion part. The propulsion part has a speed reduction umbrella storage space for storing the speed reduction umbrella. And the speed reduction umbrella housing space has a front opening that is closed by the payload portion before being separated from the payload portion and opened at the front side in the flight direction of the propulsion portion when separated from the payload portion. And having a rear opening for releasing the speed reduction umbrella stored in the speed reduction umbrella storage space to the rear side in the flight direction by air introduced from the front opening. And which has a projectile of this configuration as a means for solving the conventional problems described above.

  In the flying body according to claim 2 of the present invention, the payload section includes a payload and an outer cylinder that can be divided in a radial direction covering the payload, and the payload section is itself separated from the propulsion section by a separating means. In addition to the separation, the outer cylinder is divided in the radial direction by the dividing means and separated from the payload.

  In the flying body according to claim 3 of the present invention, the flying body includes a closing body that closes a rear opening in the speed reduction umbrella housing space of the propulsion unit, and the closing body is closed when the propulsion unit is separated from the payload portion. It is set as the structure isolate | separated from this propulsion part by the isolation | separation means.

  In the flying body according to the present invention, as the propulsion unit, a rocket motor using a solid propellant as a fuel or a rocket engine using a liquid propellant as a fuel can be employed, and there is no particular limitation.

  Further, in the flying body according to the present invention, the size and quantity of the decelerating umbrella that expands and decelerates the propulsion unit when it is separated from the payload part is the flying speed or mass of the propulsion part at the time of separation from the payload part. Depending on the conditions, the size and number of the speed reduction umbrella storage space for storing the speed reduction umbrella is also determined, but in order to stabilize the behavior of the propulsion part after separation from the payload part, the propulsion part However, for example, in the case of a rocket motor, it is desirable to arrange a plurality of speed reduction umbrellas and speed reduction umbrella storage spaces at equal intervals around the nozzle.

  Furthermore, in the flying body according to the present invention, when the payload portion that is separably coupled to the propulsion portion by welding or the like includes a payload and a split outer cylinder that covers the payload, the payload portion As the separating means for separating the propelling part from the outer cylinder and the dividing means for the outer cylinder, for example, linear pyrotechnics that can be arranged respectively in the coupling part and the dividing part with the propelling part in the outer cylinder can be used. For example, a linear pyrotechnic can be used as the closing means separating means for the closing body, as in the case of the separating means and dividing means for the outer cylinder. Can be used.

The flying object according to the present invention is launched from a launcher on the ground or the sea and flies while accelerating by obtaining thrust generated in the propulsion unit.
In this flying object, when the propulsion unit is separated from the payload unit by the remote command or timer operation after the completion of the combustion of the propulsion unit during the flight, the front opening of the speed reduction umbrella storage space that has been blocked by the payload unit is opened. Thus, air is introduced from the opened front opening.

  In this way, when air is introduced from the front opening of the opened deceleration umbrella storage space, the reduction umbrella is released from the rear opening to the rear side in the flight direction by this air, and the released reduction umbrella is immediately deployed. The propulsion unit is decelerated, so that the separated propulsion unit collides with the payload unit and the two interfere with each other.

  Therefore, the flying object according to the present invention does not need to be equipped with a wire for pulling out a reduction umbrella, which has been necessary in the past, or a cutting mechanism for this wire, so that the structure relating to the deployment of the reduction umbrella can be simplified. It becomes.

  In addition, since the speed reduction umbrella is released from the rear opening of the speed reduction umbrella storage space to the rear side in the flight direction, and deployed, for example, when the flying body has an aerodynamic stabilization plate, the speed reduction umbrella has the aerodynamic stabilization plate. As a result, it is possible to reliably prevent the propulsion part from colliding with the payload part and the mutual interference with each other.

  At this time, when the payload portion is formed by covering the payload with an outer cylinder that can be divided in the radial direction, for example, the linear pyrotechnics and the outer cylinder dividing means as separating means for separating the propulsion section from the payload section. When the linear pyrotechnics are operated, the payload part itself is separated from the propulsion part, and the outer cylinder is cracked in the radial direction so as to be separated from the payload. As the separation mechanism using the work is not required, the structure of the airframe is simplified and the cost of the airframe is reduced.

  Furthermore, if the rear opening in the propelling unit storage space of the propulsion unit is closed with a closing body until the payload unit and the propulsion unit are separated, inadvertent release of the decelerating umbrella will be prevented. Reliability will be improved.

  Since the flying body according to claim 1 of the present invention has the above-described configuration, the speed reduction umbrella can be reliably deployed after realizing the simplification of the structure, and as a result, combustion of the propulsion unit is finished. A very excellent effect is obtained in that it is possible to surely prevent the propulsion unit separated during the subsequent inertial flight from colliding with the payload unit and interfering with each other.

  In addition, since the flying object according to claim 2 of the present invention has the above-described configuration, the structure of the aircraft can be simplified and the cost of the aircraft can be reduced, and the flying object according to claim 3 of the present invention can be realized as described above. Since the structure is adopted, it is possible to reliably prevent the reduction umbrella from being released before the propulsion unit is separated from the payload unit.

It is sectional explanatory drawing (a) along the axis direction of the flying body by one Example of this invention, and P direction arrow explanatory drawing (b) of Fig.1 (a). FIG. 2 is an explanatory cross-sectional view illustrating a situation where a payload portion and a propulsion portion are separated from each other during inertial flight of the flying object in FIG. 1. FIG. 2 is a partial cross-sectional explanatory view showing a situation where a flying umbrella in FIG. 1 is released and deployed.

Hereinafter, a flying object according to the present invention will be described with reference to the drawings.
1 to 3 show an embodiment of a flying object according to the present invention.

  As shown in FIG. 1 (a), the flying object 1 includes a rocket motor (propulsion unit) 2 that generates thrust, and a rocket motor 2 that is separably coupled to the rocket motor 2 after the completion of combustion in flight. A payload part 3 to be separated and a speed reducing umbrella 4 that is connected to the rocket motor 2 and is deployed when the rocket motor 2 is separated from the payload part 3 to decelerate the rocket motor 2 are provided.

  The rocket motor 2 has a cylindrical shape, and includes a combustion chamber 22 filled with a solid propellant 21 and a nozzle 23 that ejects high-temperature and high-pressure combustion gas generated by the combustion of the solid propellant 21 in the combustion chamber 22. A plurality of aerodynamic stabilization plates 24 are provided on the outer peripheral surface as well as on the axis.

  Further, as shown in FIG. 1B, the rocket motor 2 has four speed reduction umbrella storage spaces 25 arranged at intervals of 90 ° around the combustion chamber 22, and these speed reduction umbrellas are stored. One reduction umbrella 4 in a folded state is stored in each of the spaces 25.

  Each of these deceleration umbrella storage spaces 25 has a front opening 25f located on the front side in the flight direction of the rocket motor 2 and a rear opening 25r located on the rear side in the flight direction. The front opening 25f is blocked by the payload portion 3 before being separated from the payload portion 3, while the rear opening 25r is blocked by the closing body 26 until being separated from the payload portion 3. It has become so.

  Then, as shown in FIG. 2, each front opening 25f of the speed reduction umbrella housing space 25 is opened when separated from the payload portion 3, and each rear opening 25r is closed by a closing body 26 that closes the opening 25r. By separating from the rocket motor 2 by the operation of the linear pyrotechnic 27 as the body separating means, each is opened like the front opening 25f.

  After the speed reduction umbrellas 4 respectively stored in these speed reduction umbrella storage spaces 25 are pushed by the air A indicated by the white arrows introduced from the front opening 25f and discharged from the rear opening 25r to the rear side in the flight direction, The rocket motor 2 is decelerated as shown in FIG. The rope 4 a of the speed reduction umbrella 4 is connected to the vicinity of the rear opening 25 r of the speed reduction umbrella storage space 25.

  In this case, the payload portion 3 includes a payload 31 and an outer cylinder 32 that covers the payload 31, and the payload portion 3 is fixed to the rocket motor 2 by welding or the like, Coupled to the rocket motor 2. The outer cylinder 32 is composed of a plurality of outer cylinder pieces 33 that are divided in the radial direction, and each coupling portion and each divided portion of the outer cylinder pieces 33 are separated as separating means. A linear pyrotechnic 34 and a linear pyrotechnic 35 as a dividing means are arranged. That is, the payload portion 3 is separated from the rocket motor 2 by operating these linear pyrotechnics 34 and 35, respectively, and the outer cylinder 32 is divided into a plurality of outer cylinder pieces 33 to thereby generate the payload 31. It is supposed to be separated from.

  The flying object 1 is accelerated by jetting high-temperature and high-pressure combustion gas generated from combustion of the solid propellant 21 in the combustion chamber 22 of the rocket motor 2 from the nozzle 23 while being launched from a ground or sea launcher. While flying toward the target.

  The flying object 1 continues to fly at high speed even after the solid propellant 21 burns in the rocket motor 2, and when a predetermined time elapses from the launch, the linear pyrotechnics of the payload section 3 by remote command or timer operation. When each of the products 34 and 35 is activated, the payload portion 3 itself is separated from the rocket motor 2, and the outer cylinder 32 of the payload portion 3 is separated into a plurality of outer cylinder pieces 33 and scattered in the radial direction to be separated from the payload 31. To do.

  When the rocket motor 2 is disconnected from the payload part 3, all the front openings 25f of the four deceleration umbrella storage spaces 25 that have been blocked by the payload part 3 are opened, and at the same time, by remote command or timer operation When the linear pyrotechnics 27 are activated and the closing body 26 is separated from the rocket motor 2, the rear openings 25r of the four speed reduction umbrella storage spaces 25 are also opened.

  As described above, when the front openings 25f and the rear openings 25r of the four speed reduction umbrella storage spaces 25 are opened, air A is introduced from the front openings 25f of the speed reduction umbrella storage space 25. The speed-reducing umbrella 4 is pushed by the introduced air A and discharged from the rear opening 25r to the rear side in the flight direction, and the released four speed-reducing umbrellas 4 are immediately deployed, whereby the rocket motor 2 is decelerated and the payload portion 3 In this case, the rear-end collision of the rocket motor 2 and the mutual interference between the two are avoided.

  Therefore, in the flying object 1 according to the above-described embodiment, the wire for pulling out the reduction umbrella, which has been conventionally required, and the cutting mechanism of this wire become unnecessary, and the structure related to the development of the reduction umbrella 4 can be simplified. It becomes.

  Further, since the speed reduction umbrella 4 is released from the rear opening 25r of the speed reduction umbrella storage space 25 to the rear side in the flight direction and is deployed, the speed reduction umbrella 4 is reliably deployed without being entangled with the aerodynamic stabilization plate 24. Thus, it is possible to reliably prevent the rocket motor 2 from colliding with the payload section 3 and the mutual interference between the two.

  Furthermore, in the flying object 1 according to the above-described embodiment, the payload portion 3 is formed by covering the payload 31 with the outer cylinder 32 that can be divided in the radial direction, and the outer cylinder 32 is welded to the rocket motor 2 by welding or the like. Since it is coupled to the rocket motor 2 by fixing, if each of the linear pyrotechnics 34 and 35 as the separating means and the dividing means is operated, the payload portion 3 itself is separated from the rocket motor 2, The outer cylinder is cracked in the radial direction and separated from the payload. Therefore, the structure of the fuselage is simplified and the cost of the fuselage is reduced to the extent that a separation mechanism using pyrotechnics such as a gas generator becomes unnecessary. Will be illustrated.

  Furthermore, in the flying body 1 according to the above-described embodiment, the rear opening 25r in the speed reduction umbrella housing space 25 of the rocket motor 2 is closed by the closing body 26 until the rocket motor 2 is separated from the payload portion 3. Therefore, inadvertent release of the deceleration umbrella 4 is prevented, and the reliability is improved.

  The configuration of the flying object according to the present invention is not limited to the above-described embodiment, and for example, a rocket engine using a liquid propellant as fuel as the propulsion unit can be adopted as another configuration.

1 Flying object 2 Rocket motor (propulsion unit)
3 Payload part 4 Reduction umbrella 21 Solid propellant 25 Reduction umbrella storage space 25f Front opening 25r of reduction umbrella storage space Rear opening 26 of reduction umbrella storage space Closure body 27 Linear pyrotechnic (blocking body separating means)
31 Payload 32 Outer cylinder 34 Linear pyrotechnic (separation means)
35 Linear pyrotechnics (division means)
A Air

Claims (3)

A propulsion unit that generates thrust by combustion of the propellant;
A payload unit that is separably coupled to the propulsion unit and is separated from the propulsion unit after completion of combustion during flight,
In a flying body comprising a speed reduction umbrella that is coupled to the propulsion unit and deployed at a stage separated from the payload unit to decelerate the propulsion unit,
The propulsion unit is formed with a reduction umbrella storage space for storing the reduction umbrella,
The deceleration umbrella storage space has a front opening that is closed by the payload portion before being separated from the payload portion and opened at the front side in the flight direction of the propulsion portion when separated from the payload portion. And a rear opening that discharges the speed reduction umbrella stored in the speed reduction umbrella storage space to the rear side in the flight direction by air introduced from the front opening.   The payload portion includes a payload and an outer cylinder that can be divided in a radial direction to cover the payload. The payload portion is separated from the propulsion unit by a separation unit, and the outer cylinder is diametrically separated by the division unit. The flying object according to claim 1, wherein the flying object is divided in a direction and separated from the payload.   2. A closure body for closing a rear opening of the propulsion unit in the speed reduction umbrella housing space is provided, and the closure body is separated from the propulsion section by a closure body separating unit when the propulsion section is separated from the payload section. Or the flying object of 2.

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