JP3050025B2 - Projectile launcher - Google Patents

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 a flying object fired by a rocket motor.

[0002]

2. Description of the Related Art FIG. 12 is a view showing a conventional projectile launching apparatus, in which 1 is a launcher, 2 is a canister, 3 is a flying object stored in a canister 2, 4
Is a rocket motor, which is a propulsion device serving as a driving force for detaching the flying object 3 from the canister 2 and flying in the air, 5 is a rocket motor nozzle, and A is a rocket. It is a rocket motor jet injected from the motor.

Next, the operation of the launching device will be described. FIG. 12A shows a restricted combustion state in the canister 2 in which the rocket motor 5 is ignited immediately after the rocket motor 5 is ignited or due to some failure factor but the flying object 3 does not move. FIG. 12B shows a state in which the rocket motor 5 is ignited and the flying object 3 starts to separate from the launcher 1 and the canister 2 with sufficient thrust.

A rocket motor for propelling a flying object utilizes gas energy in which a chemical fuel burns, and ejects a high-temperature, high-pressure gas at a higher speed than a rocket motor nozzle. The relationship between the cross-sectional area ratio and the gas pressure ratio at the combustion chamber and the nozzle outlet is represented by the following equation.

[0005]

(Equation 1)

Here, P0 and A0 are the pressure and cross-sectional area at the nozzle throat, PS1 and AS1 are the pressure and cross-sectional area at the nozzle outlet, and K is the specific heat ratio. Further, as shown in Expression 1, the static pressure at the nozzle outlet depends on the relationship between the throat cross-sectional area of the nozzle and the cross-sectional area of the nozzle. Generally, in the case of a flying object, the static pressure at the nozzle outlet becomes higher than the atmospheric pressure due to restrictions on the fuselage diameter, thrust pattern, combustion time, and the like. For this reason, most of the gas ejected from the nozzle 6, that is, the rocket motor jet A flows in the nozzle ejection direction, but a part of the gas also flows in the opposite direction, that is, the aircraft body side of the flying object.

[0007]

It is desired that the launching device composed of the launcher, the canister, and the flying object be reduced in size and weight especially for those mounted on ships and vehicles. At the same time, a physical energy processing method for the rocket jet ejected from the rocket motor becomes a major problem.

In a launch vehicle for a flying object, the energy of the rocket motor jet is very large, and the total pressure of the jet is 10
Exceeding 0 atm, the temperature rises to around 2500 ° C. Therefore, even a small amount of jet has enough heat to raise the airframe temperature of the flying object, and it is necessary to take appropriate heat protection measures. Especially, the flying object is lightened because it flies in the air, and is vulnerable to the thermal environment. In addition, the projectile has a warhead that is pyrotechnic in nature, and an excessive temperature rise can cause explosion in the launcher and be very dangerous. For such a flying object, it is first necessary to ensure the safety at the time of restraint combustion in which the rocket motor is burned while being held by the canister due to some failure factor.

Further, even if the influence of the rocket motor jet during restraint combustion is eliminated by other means, the effect of the rocket motor jet will occur until the launched flying object leaves the canister. The flying object is wrapped in the rocket motor jet in the narrow space inside the canister. Even if the effect is short,
In recent years, the weight of components has been advanced in flying objects, and this is a major problem.

The present invention has been made to solve such a problem, and an object of the present invention is to prevent a rocket motor jet injected from a nozzle from flowing forward of the fuselage and increasing the fuselage temperature.

[0011]

A flying object launching device according to the present invention is provided with a shielding plate fixed to the inside of the canister and divided into two spaces in the canister at the tail of the flying body. is there.

Further, a partition plate having a hole having the maximum cross-sectional shape of the flying object and surrounding the body of the flying object and dividing the space in the canister into three or more is provided inside the canister.

Further, the shielding plate is movable together with the flying object, and a stopper is provided at an outlet of the canister for separating the shielding plate from the flying object when the flying object is separated from the canister.

An aircraft flare is provided at the tail of the fuselage in place of the stable wing of the flying body.

Further, on the nozzle outlet side of the rocket motor,
An extension nozzle held by a canister was provided.

Further, the extension nozzle is made movable with the flying object, and a stopper for separating the flying object from the extension nozzle when the flying object separates from the canister is provided at an outlet of the canister.

The canister has an airtight structure, and the inside is pressurized with gas.

In addition, a gas nozzle for jetting high-pressure gas provided in the launcher downward from the upper part of the projectile warhead is provided inside the canister.

Further, a gas nozzle is provided inside the canister for injecting the cooling gas provided in the launcher upward from the lower side of the warhead of the flying object along the body surface of the flying object.

Further, a cooling gas source provided on the flying object and a gas nozzle for jetting the gas upward from the lower part of the warhead are attached to the lower part of the flying object.

[0021]

In the projectile launching device constructed as described above, the rocket motor jet ignited by the rocket motor is ejected and flows forward by the shielding plate provided at the tail of the aircraft. And prevent explosion of flying objects in the launcher.

Further, by applying pressure to the interior of the canister or by jetting high-pressure gas from the gas nozzle toward the lower part of the flying object, it is possible to prevent the rocket motor jet flowing toward the upper part of the aircraft.

Further, by injecting the high-pressure gas for cooling provided in the canister onto the surface of the body, the rise in the body temperature can be reduced.

[0024]

【Example】

Embodiment 1 FIG. FIG. 1 is a sectional view showing an embodiment of the present invention, and reference numerals 1 to 7 are exactly the same as those of the above-mentioned conventional apparatus.
The interior of the canister 2 before the projectile is fired is divided into two near the tail of the projectile 3 by the shielding plate 8. During the restricted combustion, the shielding plate 8 shields the rocket motor jet A into the space behind the canister 2 on the rear side of the fuselage. The shield plate 8 can prevent a high-temperature gas flow from flowing into the forward side of the fuselage, and can suppress the rise of the warhead 4.

Embodiment 2 FIG. FIG. 2 is a sectional view showing one embodiment of the present invention. A shield plate 8 is provided on the tail of the flying object 3 as in the first embodiment. The partition plate No. 9 is as shown in FIG. 3 when viewed from above the canister before taking a cross section. The partition plate 9 has a hole having a shape of a projection from the front end direction of the flying object 3, and a plurality of the partition plates 9 are provided to divide the space in the canister 2 into three or more. When the flying object is normally fired, a part of the rocket motor jet A tends to flow toward the front of the fuselage. However, since the flow is reduced by the partition plate 9 and does not reach the warhead, Explosion of the warhead 4 can be prevented.

Embodiment 3 FIG. FIG. 4 is a sectional view showing an embodiment of the present invention. The shield plate 8 at the tail of the flying object 3 is attached to the flying object 3 and moves in the canister together with the flying object. During restraint combustion of the flying object,
As in the first embodiment, the jet of the rocket motor is shielded in the space behind the canister, so that the temperature rise of the warhead can be suppressed. When the flying object is normally fired, the shield plate 8 that has moved together with the flying object 3 is separated from the flying object by the stopper 10 provided at the canister outlet and is left in the canister, leaving only the flying object. Detach the canister and jump out. Due to the movable shield plate 8, the rocket motor jet A does not flow forward of the flying object together with the restraint combustion and the normal firing.

Embodiment 4 FIG. FIG. 5 is a sectional view showing an embodiment of the present invention. In the present invention, the stable wing of the flying object 3 is removed, and an airframe flare 11 fixed to the tail of the flying object is provided. The flare 11 produces an effect equivalent to that of a stable wing due to the air resistance of that portion. The outer shape of the fuselage flare 11 conforms to the inner shape of the canister 2 and can prevent the rocket motor jet A from flowing forward of the fuselage. The airframe flare 11 does not separate even when the flying object 3 leaves the canister 2, and stabilizes the aircraft when flying.

Embodiment 5 FIG. FIG. 6 is a sectional view showing an embodiment of the present invention. An extension nozzle 12 is joined to the rocket motor nozzle outlet of the flying object according to the present invention, and the rocket motor nozzle 6 is used before ignition and during restraint combustion.
And the extension nozzle 12 are integrated. At the time of constrained combustion, the nozzle outlet pressure of the rocket motor jet A can be reduced by the extension nozzle 12, so that the flow rate of the rocket motor jet A flowing forward of the flying object 3 can be reduced. In addition, this extension nozzle 12
Is fixed to the canister 2 and separates from the flying object when the flying object 3 moves forward, so that when the flying object normally fires, the original thrust of the flying object can be obtained.

Embodiment 6 FIG. FIG. 7 is a sectional view showing an embodiment of the present invention. The rocket motor nozzle 6 of the flying object 3 is provided with an extension nozzle 12 similarly to the fifth embodiment.
Move in the canister with the flying object. At the time of restraint combustion of the flying object, the backflow of the rocket motor jet to the flying object side can be reduced and the temperature rise of the warhead can be suppressed, as in the fifth embodiment. When the flying object is normally fired, the extension nozzle 12 that has moved together with the flying object 3 is separated from the flying object by the stopper 10 provided at the canister outlet, and is left behind in the canister. The movable extension nozzle 12 can lower the nozzle exit pressure of the rocket motor even during normal firing, and makes it difficult for the jet A to flow backward in front of the flying object. Thereby, the temperature rise of the warhead can be suppressed.

Embodiment 7 FIG. FIG. 8 is a sectional view showing an embodiment of the present invention. The canister 2 of the present embodiment is sealed, and is applied with a pressure higher than the nozzle outlet pressure of the rocket motor jet. When the flying object 3 is ignited in this state, the lid at the rear of the aircraft is broken by the pressure of the rocket motor jet A, and the jet flows toward the rear of the aircraft. At this time, since the pressure in the canister 2 is high, the gas in the canister flows backward to the body. Due to this gas flow B, the rocket motor jet A hardly flows to the front of the fuselage, so that the temperature rise of the warhead can be prevented.

Embodiment 8 FIG. FIG. 9 is a sectional view showing an embodiment of the present invention. The launcher 1 of this embodiment is provided with a high-pressure gas source 13, and a gas nozzle 14 for ejecting the high-pressure gas from the upper side to the lower side of the warhead of the flying object 3 is provided on the inner wall of the canister 2. . When the rocket motor 5 is ignited, the rocket motor jet A also tends to flow toward the front of the fuselage.
By flowing the high-pressure gas in the direction in which it is pushed back into the rocket motor jet A, the temperature rise of the warhead can be prevented.

Embodiment 9 FIG. FIG. 10 is a sectional view showing an embodiment of the present invention. The launcher 1 of this embodiment is provided with a cooling gas source 15. A plurality of gas nozzles 14 are provided on the inner wall of the canister 2, and the cooling gas is ejected upward from the lower side of the warhead of the flying object 3 along the body surface of the flying object. Even if the entire projectile is wrapped in the rocket motor jet by the blown cooling gas, it is possible to locally prevent the temperature of the warhead of the projectile from rising.

Embodiment 10 FIG. FIG. 11 is a sectional view showing an embodiment of the present invention. The flying object 3 of this embodiment has a cooling gas source 15 inside, and a plurality of gas nozzles 14 are provided around the warhead 4. The cooling gas is jetted from the gas nozzle 14 upward from the lower part of the warhead of the flying object 3 along the body surface of the flying object. Thereby, the same effect as that of the ninth embodiment can be obtained.

[0034]

Since the present invention is configured as described above, the following effects can be obtained.

In the projectile launching device, the inside of the canister is divided into two by a shielding plate at the tail of the projectile, and the rocket motor jet is shielded into the space behind the canister at the time of restrained combustion. In addition, even during normal firing, the partition plate provided inside the canister mitigates the rocket motor jet from flowing forward. As described above, the temperature rise of the warhead can be suppressed.

The shield plate is attached to the tail of the flying object and is separated from the flying object by a stopper provided at the outlet of the canister at the canister outlet. The jet can be prevented from flowing at all in front of the flying object, and the temperature rise of the warhead can be suppressed.

Further, by providing an airframe flare fixed to the tail of the flying body and having an outer shape adapted to the inner shape of the canister, it is possible to prevent the rocket motor jet from flowing forward.

In addition, by joining the extension nozzle to the exit of the rocket motor nozzle of the flying object and increasing the exit diameter of the nozzle, the nozzle exit pressure of the rocket motor jet can be reduced at the time of restrained combustion. The flow rate of the rocket motor jet flowing toward the front of the body can be reduced.

Further, by applying a pressure to the canister or jetting high-pressure gas downward from above the canister, it is possible to prevent the rocket motor jet from flowing above the canister.

Further, by blowing a cooling gas around the warhead, the temperature rise of the warhead can be suppressed.

[Brief description of the drawings]

FIG. 1 is a sectional view showing Embodiment 1 of the present invention.

FIG. 2 is a sectional view showing a second embodiment of the present invention.

FIG. 3 is an explanatory view showing a partition plate according to a second embodiment of the present invention.

FIG. 4 is a sectional view showing a third embodiment of the present invention.

FIG. 5 is a sectional view showing a fourth embodiment of the present invention.

FIG. 6 is a sectional view showing a fifth embodiment of the present invention.

FIG. 7 is a sectional view showing Embodiment 6 of the present invention.

FIG. 8 is a sectional view showing a seventh embodiment of the present invention.

FIG. 9 is a sectional view showing an eighth embodiment of the present invention.

FIG. 10 is a sectional view showing a ninth embodiment of the present invention.

FIG. 11 is a sectional view showing a tenth embodiment of the present invention.

FIG. 12 is a sectional view showing a conventional projectile launching device.

[Explanation of symbols]

 Reference Signs List 1 launcher 2 canister 3 flying object 4 warhead 5 rocket motor 6 rocket motor nozzle 7 wing 8 shielding plate 9 partition plate 10 stopper 11 flare 12 extension nozzle 13 high pressure gas source 14 gas nozzle 15 cooling gas source 16 pressurized gas A rocket motor jet B Gas flow

──────────────────────────────────────────────────続 き Continuation of the front page (56) References JP-A-5-272899 (JP, A) JP-A-3-204597 (JP, A) JP-A-5-34486 (JP, U) 11798 (JP, B2) JP 5-26120 (JP, B2) JP 50-14079 (JP, B1) US Patent 4,324,167 (US, A) US Patent 3,811,703 (US, A) US Patent 3,745,926 (US, A) U.S. Pat. No. 2,998,780 (US, A) U.S. Pat. No. 3,319,522 (US, A) (58) Fields investigated (Int. Cl. ⁷ , DB name) F41F 3/04-3/077 F42B 15/00 F42B 15/34 F42B 10/02-10/06

Claims (5)

(57) [Claims] 1. A flying object comprising a projectile equipped with a warhead and a rocket motor, a canister that wraps the entire flying object and holds the flying object, and a launcher that stores the canister. The launching device of the above, adapted to the internal cross-sectional shape of the canister , and
Around the torso of the body
Shield plate divided into two parts and the upper side of the canister
Attached, with flying object when flying object detaches
The shielding plate that has moved to the flying object is separated from the flying object.
A projectile launching device characterized in that it has a stopper to make it fly. 2. A flying object comprising a flying object having a warhead and a rocket motor, a canister wrapping the entire flying object and holding the flying object, and a launcher for storing the canister. The launcher of the rocket motor, the outlet of the nozzle of the rocket motor, the cap
A projectile launching device characterized by having an extension nozzle held by a nysta. 3. A flying object comprising a projectile equipped with a warhead and a rocket motor, a canister that wraps the entire projectile and holds the flying object, and a launcher that houses the canister. In the launching device, the rocket motor was joined to the outlet side of the nozzle
An extension nozzle attached to the upper side of the canister
With the flying object nozzle when the flying object separates
Separate the extended nozzle that has moved from the flying object
A launching device for a flying object characterized by a stopper provided. 4. A flying object comprising a projectile equipped with a warhead and a rocket motor, a canister that wraps the entire projectile and holds the flying object, and a launcher that houses the canister. The launching device, the high pressure gas source provided in the launcher, and the canister
The bullet of the high-pressure gas flying body attached inside the star
A projectile launching device characterized by having a gas nozzle which blows downward from above the head . 5. A flying device having a warhead and a rocket motor.
Wrap and fly the flying body and the whole flying body
A canister for holding a body and storing the canister
Launcher and launch vehicle launcher
A cooling gas source provided in the launcher;
A bullet of a flying object that is installed inside the star
Along the surface of the flying object from the lower part of the head upward
With multiple gas nozzles
Flying object launcher.