JP2000130991A - Launcher of missile - Google Patents

Abstract

PROBLEM TO BE SOLVED: To safely launch a missile, and to secure the safety around a launcher by substituting a cover being provided at the injection port of the tip of a canister for weak two-stage covers and a pre-loading part that is pinched by the covers and is boosted. SOLUTION: An injection port 2 at the tip of a canister 1 is exposed to the jet of a rocket motor with high temperature and pressure being jetted from the rocket motor of a missile being launched from an adjacent canister. Then, in the injection port 2, an outside cover 8, a pre-loading part 9 where inside pressure is boosted, and an inside cover 10 are provided. When the missile is launched, a nose part 5 of the missile is allowed to collide with the inside and then outside covers 10 and 8 for breaking a film. The inside and outside covers 10 and 8 are weak, and time difference exists between the two collisions, thus preventing large impact force from being generated, and hence avoiding an abnormal situation such as the damage of the nose part 5 of the missile.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a launching device for launching a plurality of flying objects propelled by a rocket motor.

[0002]

2. Description of the Related Art A conventional technique relating to a flying object launching apparatus will be described with reference to the drawings. FIG. 4 is a diagram showing a configuration of a launching device according to a conventional technique. FIG. 4A is a diagram illustrating a state at the moment when the flying object is fired, and FIG. 4B is a diagram illustrating a state immediately after the flying object is fired. In the figure, 1 is a canister, 2 is an ejection port at the tip of the canister 1, 3 is a cover for closing the ejection port 2, 4 is a canister 1
A flying object 5 is stored in each of the flying objects, 5 is a nose portion of the flying object 4, 6 is a rocket motor for generating a propulsive force of the flying object 4, and 7 is a jet from the rocket motor 6. When the flying object 4 is fired, the flying object 4 is ejected from the canister 1 by the nose portion 5 colliding with the cover 3 and breaking the cover 3 as shown in FIG. At this time, as shown in FIG. 4 (b), the external pressure is applied to the cover 3 of the adjacent canister 1 by being exposed to the rocket motor jet 7, which is a high-temperature and high-pressure gas from the flying object 4 protruding from the canister 1. Is done. The flying object nose portion 5 has a very sharp shape to reduce aerodynamic drag. In addition, the material of the nose part 5 is a ceramic material that is vulnerable to impact force due to the requirement of heat resistance for aerodynamic heating at high speed flight and the improvement of radio wave transmission when mounting a target capture radar inside. There are many examples to use. In order to reduce the impact force applied to the flying object nose portion 5 when the cover 3 is ruptured, it is desirable that the strength of the cover 3 be as low as possible. Conversely, in order to protect the inside of the canister 1 from the high-temperature and high-pressure rocket motor jet 7 from which the flying object 4 ejected from the adjacent canister 1 is ejected, it is desirable that the strength of the cover 3 is as high as possible.
Due to the above-mentioned conflicting strength requirements, the allowable range of the strength of the cover 3 is significantly narrowed.

[0003]

In the prior art projectile launching apparatus, the cover 3 is provided to reduce the impact force applied to the projectile nose portion 5 when the cover 3 is broken by collision. Low strength was required.
On the other hand, the cover 3 is required to have high strength in order to shut off heat and pressure applied from the outside. The range of the strength of the cover 3 that simultaneously satisfies these contradictory requirements is narrow, and there is a problem that the actual strength of the cover 3 is out of this range. If the strength of the cover 3 is insufficient, as shown in FIG. 4B, the cover 3 cannot withstand the external pressure of the rocket motor jet 7 of the flying object fired from the adjacent canister 1 and the cover 3 is ruptured. Therefore, when the high-temperature and high-pressure rocket motor jet 7 enters the interior of the canister 1, the flying object 4 stored in the canister 1 may be directly exposed to the high-temperature and high-pressure rocket motor jet 7, causing a failure or ignition. was there.
On the other hand, when the strength of the cover 3 is excessively high, FIG.
It is said that the flying nose 5 may be damaged by the impact force when the cover 3 collides and ruptures as described above, and the flying vehicle 4 may become uncontrollable due to a failure of the internal radar or a change in aerodynamic characteristics. There was a problem.

SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems. In a flying object launching apparatus, a cover conventionally provided at an outlet at the tip of a canister is replaced with a two-stage cover having low strength. By replacing it with a pressurized pressurized section sandwiched between the covers, the heat and pressure of the rocket motor jet of the projectile launched from the adjacent canister are cut off, and the projectile breaks the cover An object of the present invention is to alleviate the impact force applied to the flying object nose portion when ejecting the flying object, to launch the flying object safely, and to ensure the safety around the launching device.

[0005]

According to a first aspect of the present invention, there is provided a flying object launching apparatus which stores a flying object and which stores the flying object until immediately before launching. A plurality of canisters arranged adjacent to each other, an outer cover provided at the injection port of the canister to close the injection port, a pressurizing section provided inside the outer cover and having an increased internal pressure, An inner cover for separating the pressurizing section from the flying object storage portion of the canister.

A flying object launching device according to a second aspect of the present invention is a launching device for storing a flying object and launching the flying object, wherein the flying object is stored until immediately before launching, A plurality of canisters, an outer cover provided at the injection port of the canister and closing the injection port, a pressurizing section provided inside the outer cover, and a pressurizing section provided between the pressurizing section and the canister. It has an inner cover for separating the casing storage portion, and a vent provided at the injection port for ventilating the outside of the injection port and the pressurizing section.

A flying object launching device according to a third aspect of the present invention is a launching device for storing a flying object and firing the flying object, wherein the flying object is stored until immediately before launching, A plurality of canisters, a movable frame provided at the injection port of the canister and movable back and forth in the direction of the injection port, an outer cover provided at the movable frame to close the injection port, and an outer cover And a pressurizing portion whose volume changes by movement of the movable frame, and an inner cover separating the pressurizing portion and the flying object storage portion of the canister.

[0008]

DESCRIPTION OF THE PREFERRED EMBODIMENTS First Embodiment FIG. 1 is a partial configuration diagram showing a first embodiment of the present invention. In the figure, 1 is a canister, 2 is an outlet at the tip of the canister, 5 is a nose of a flying object, 8 is an outer cover,
9 is a pressurizing section, and 10 is an inner cover.

FIG. 1A shows the state of the projectile launching device before the projectile is launched. In the figure, an injection port 2 at the tip of a canister 1 is exposed to a high-temperature, high-pressure rocket motor jet ejected from a rocket motor of a flying object fired from an adjacent canister. The injection port 2 is provided with an outer cover 8, a pressurizing section 9 whose internal pressure has been increased, and an inner cover 10. High pressure is applied to the outer surface of the outer cover 8 by the rocket motor jet, but the pressure difference between the inner and outer surfaces is small because the pressurizing portion 9 on the inner surface is pressurized to a pressure intermediate between the high pressure on the outer surface and the atmospheric pressure. The load applied to the outer cover 8 is small. Therefore, the high pressure applied from the rocket motor jet can be cut off by the outer cover 8 having low strength. Further, the differential pressure between the inside of the pressurizing section 9 and the inside of the canister 1 is small, and the load applied to the inner cover 10 separating them is small. Therefore, it is possible to withstand the load by the inner cover 10 having low strength.

FIG. 1B shows the state of the projectile launching device when the projectile is launched. In the drawing, the flying object nose portion 5 first breaks the inner cover 10 by collision, and then breaks the outer cover 8 by collision. The inner cover 10 and the outer cover 8 have low strength, and there is a time difference between two collisions, so that a synergistic effect of these collisions does not generate a large impact force. As a result, the impact force applied to the flying object nose portion 5 is small, and an abnormal situation such as damage to the nose portion 5 can be avoided.

Embodiment 2 FIG. 2 is a partial configuration view showing Embodiment 2 of the present invention. In FIG. 2, 1 is a canister, 2 is an outlet at the tip of the canister, 5 is a nose portion of a flying object, and 8 is Outer cover,
9 is a pressurizing section, 10 is an inner cover, and 11 is a vent.

FIG. 2A shows a state of the projectile launching device before launching the projectile. In the figure, an injection port 2 at the tip of a canister 1 is exposed to a high-temperature, high-pressure rocket motor jet ejected from a rocket motor of a flying object fired from an adjacent canister. The outlet 2 is provided with an outer cover 8, a pressurized section 9, an inner cover 10, and a vent 11 for ventilating the outside of the outlet 2 and the pressurized section 9. A high pressure is applied to the outer surface of the outer cover 8 by the rocket motor jet, but the pressurizing portion 9 on the inner surface is pressed by the external high-pressure gas gradually flowing from the vent 11 to a pressure approximately intermediate between the external high-pressure gas and the atmospheric pressure. Therefore, the pressure difference between the inner and outer surfaces is small, and the load applied to the outer cover 8 is small. Therefore, the high pressure applied from the rocket motor jet can be cut off by the outer cover 8 having low strength. In addition, the flying object launched from the adjacent canister flies away in a short time, and it takes time to flow from the ventilation port 11.
Is lower than the pressure on the outer surface of the outer cover 8, and as a result, the load applied to the inner cover 10 is small. Therefore, it is possible to withstand the load by the inner cover 10 having low strength.

FIG. 2B shows a state of the launching device of the flying object when the flying object is fired. In the drawing, the flying object nose portion 5 first breaks the inner cover 10 by collision, and then breaks the outer cover 8 by collision. The inner cover 10 and the outer cover 8 have low strength, there is a time difference between two collisions, and a large impact force is not generated due to a synergistic effect of these collisions. As a result, the impact force applied to the flying object nose portion 5 is small, and an abnormal situation such as damage to the nose portion 5 can be avoided.

Embodiment 3 FIG. 3 is a partial configuration view showing Embodiment 3 of the present invention. In FIG. 3, reference numeral 1 denotes a canister, 2 denotes an outlet at the tip of the canister, 5 denotes a nose portion of a flying object, and 8 denotes Outer cover,
9 is a pressurizing section, 10 is an inner cover, and 12 is a movable frame.

FIG. 3A shows a state of the projectile launching device before the projectile is launched. In the figure, an outlet 2 at the tip of a canister 1 is exposed to a high-temperature and high-pressure rocket motor jet ejected from a rocket motor 6 of a flying object fired from an adjacent canister. The injection port 2 is provided with a movable frame 12, an outer cover 8 fixed to the movable frame 12, a pressurizing section 9, and an inner cover 10. A high pressure is applied to the outer surface of the outer cover 8 by the rocket motor jet, but the movable frame moves due to the differential pressure between the inner and outer surfaces of the outer cover 8, and the pressurizing portion 9 on the inner surface is compressed to increase the inner pressure. The differential pressure is small, and the load applied to the outer cover 8 is small. Therefore, the high pressure applied from the rocket motor jet can be cut off by the outer cover 8 having low strength. In addition, the movable range of the movable frame 12 is limited, and the pressure inside the pressurizing portion 9 which is increased by the compression is lower than the pressure on the outer surface of the outer cover 8, and as a result, the load applied to the inner cover 10 is small. . Therefore, it is possible to withstand the load by the inner cover 10 having low strength.

FIG. 3B shows a state of the launching device of the flying object when the flying object is fired. In the drawing, the flying object nose portion 5 first breaks the inner cover 10 by collision, and then breaks the outer cover 8 by collision. The inner cover 10 and the outer cover 8 have low strength, there is a time difference between two collisions, and a large impact force is not generated due to a synergistic effect of these collisions. As a result, the impact force applied to the flying object nose portion 5 is small, and an abnormal situation such as damage to the nose portion 5 can be avoided.

[0017]

The present invention is configured as described above and has the following effects.

According to the first aspect of the present invention, in the projectile launching apparatus, the pressure and heat from the outside of the projectile launched from the adjacent canister by the rocket motor jet are cut off and the projectile is launched. By breaking through the cover that seals the launch port of the projectile launching device, the impact force received by the projectile nose can be reduced and the nose of the projectile can be prevented from being damaged. .

According to the second invention, in addition to the effects of the first invention, maintenance and maintenance can be facilitated because there is no need to pressurize the pressurizing section before use.

According to the third invention, in addition to the effect of the second invention, maintenance and maintenance can be facilitated by the hermetically sealed pressurizing section.

[Brief description of the drawings]

FIG. 1 is a partial configuration diagram showing Embodiment 1 of the present invention.

FIG. 2 is a partial configuration diagram showing Embodiment 2 of the present invention.

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

FIG. 4 is a diagram showing a configuration of a conventional projectile launching device.

[Explanation of symbols]

Reference Signs List 1 canister, 2 injection port, 3 cover, 4 flying object, 5 flying object nose, 6 rocket motor, 7 rocket motor jet, 8 outer cover, 9 pressurized section, 10 inner cover, 11 vent, 12 Movable frame.

Claims (3)

[Claims] 1. A launching device for storing a flying object and launching the flying object, wherein the canister stores the flying object until immediately before launching, and a plurality of canisters arranged adjacent to each other; An outer cover provided at the injection port to close the injection port, a pressurized section provided inside the outer cover and having an increased internal pressure, and an inner side separating the pressurized section and the flying object storage portion of the canister. A projectile launching device comprising a cover. 2. A launching device for storing a flying object and launching the flying object, wherein the projecting device stores the flying object until immediately before launching, and a plurality of canisters arranged adjacent to each other; An outer cover provided at the injection port to close the injection port, a pressurized portion provided inside the outer cover, an inner cover separating the pressurized portion from the flying object storage portion of the canister, A launching device for a flying object, comprising: a vent provided at an outlet for ventilating the outside of the injection port and the pressurizing section. 3. A launching device for storing a flying object and firing the flying object, wherein the canister stores the flying object until immediately before launching, and a plurality of canisters arranged adjacent to each other; A movable frame provided at the injection port and movable back and forth in the direction of the injection port, an outer cover provided on the movable frame to close the injection port, and a volume provided by movement of the movable frame provided inside the outer cover. A projectile launching device comprising: a pressurizing portion that changes; and an inner cover that separates the pressurizing portion from the projectile storage portion of the canister.