Ordnance – Rocket launching – Having means restraining rocket from movement in launching...
Reexamination Certificate
1999-04-22
2001-09-11
Carone, Michael J. (Department: 3641)
Ordnance
Rocket launching
Having means restraining rocket from movement in launching...
Reexamination Certificate
active
06286409
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
The present invention relates to an apparatus for restraining and releasing a missile using a rigid sphere, and in particular to an improved apparatus for restraining and releasing a missile using a rigid sphere which is capable of implementing a stable and accurate restraining of a missile and quickly releasing the missile without any impact or vibration when launching the missile.
2. Description of the Conventional Art
Generally, when moving a missile, the missile is inserted into a canister(launch tube) and supported thereby for protecting the missile from any external environment such as impact or vibration. When launching the missile, the missile is released from the restrained state. In this case, it is very important to stably insert the missile into the canister(launch tube), restrain the same and release the missile. When moving the missile, the missile is stably restrained by the canister with respect to an external force. When launching the missile, the missile restrained in the canister is quickly and accurately released for thereby enabling a reliability of the missile launching system.
In the conventional art, various missile restraining apparatuses are used. For example, an explosion type is directed to restraining a missile using an explosive bolt with an explosive therein and exploding the explosive bolt before launching the missile, and a tension or shear bolt type is directed to restraining a missile using a tension or shear bolt and releasing the missile by breaking the tension bolt or shear bolt using a launching force of the missile.
In the case of the launching type, an explosive force may damage a building or the interior of the missile. In the state the explosive bolt is not exploded, when a missile is launched, since the missile is launched with the canister being engaged, it is needed to check whether the explosive bolt is exploded before the missile is launched for preventing the above-described problems.
In the tension bolt or shear bolt type, the tension bolt or shear bolt is broken when the launching force exceeds the tension force of the tension bolt or the shearing force of the shear bolt. Since the tension force of the tension bolt or the shearing force of the shear bolt is affected by an initial acceleration of the launching force, in the case of the missile having a small launching force, the bolt having a small tension force or shear force is used, so that the reliability of the missile system is decreased the tension or shear bolt may be easily broken when handling the missile and the canister. On the contrary, in the case of the missile having a large launching force, since the bolt having a large tension force or shearing force is used, the bolts may not be broken when launching the missile, so that the impact force applied to the canister is increased for thereby causing a vibration of the canister and missile, and thus the missile may not be normally controlled.
The explosive type or the tension bolt or shear bolt type are all directed to a material exploding and breaking type, so that an exploding portion or breaking portion is broken by an over stress. Therefore, when fabricating the explosive, tension, or shear bolt, it is needed to maintain a uniformity in the quality of the material of the same and check a predetermined defect therein in order for the explosive, tension, or shear bolt to have a predetermined breaking force, tension or shearing force.
In addition, the conventional apparatus has a problem in that a predetermined error may occur when launching the missile due to the above-described problems.
SUMMARY OF THE INVENTION
Accordingly, it is an object of the present invention to provide an apparatus for restraining and releasing a missile using a rigid sphere which overcomes the aforementioned problems encountered in the conventional art.
It is another object of the present invention to provide an apparatus for restraining and releasing a missile using a rigid sphere which is capable of implementing a stable restraining of a missile, quickly and accurately restraining the missile from its restrained state using a combustion gas of a rocket motor of the missile for thereby preventing a vibration of a launching bed due to an external impact and increasing a launching stability and minimizing a launching error.
To achieve the above objects, there is provided an apparatus for restraining and releasing a missile using a rigid sphere which includes a pair of circular restraining protrusions formed at a rear end portion of a missile nozzle portion, a missile side restraining and releasing means having an operation cylinder engaged to a rear end surface of the restraining protrusion of the missile, an operation piston reciprocating within the operation cylinder, and a rigid sphere protruded from an outer surface of the operation cylinder when the operation piston is moved back and inserted into the outer surface of the operation cylinder when the operation piston is moved forwardly, a canister(launch tube) side restraining and releasing means having a missile restraining portion fixed to the inner surface of the rear end portion of the canister into which the missile is inserted, with the circular restraining protrusion being inserted into the missile restraining portion, a fixing cylinder fixing portion into which the rigid sphere protruded from the outer surface of the operation cylinder is inserted, and a piston guide portion for guiding the rear end portion of the operation piston, and a combustion gas guide means for guiding a part of a combustion gas generated when launching the missile toward the rear end portion of the operation piston for thereby moving the operation piston forwardly, so that the rigid sphere is escaped from the rigid sphere restraining groove for thereby releasing the restrained state of the missile.
Additional advantages, objects and features of the invention will become more apparent from the description which follows.
REFERENCES:
patent: 3444773 (1969-05-01), Ligne
patent: 4453449 (1984-06-01), Hollmann
patent: 4550640 (1985-11-01), Harter
patent: 5056407 (1991-10-01), Mathey
patent: 5714708 (1998-02-01), Shim et al.
patent: 5744745 (1998-04-01), Shim et al.
patent: 1428642 (1964-12-01), None
patent: 1340562 (1962-12-01), None
Lee Yeol Wha
Na Moon Soo
Park Heung Joon
Park Tae Hak
Agency for Defense Development
Carone Michael J.
Mun Kyonyaek K.
Scully Scott Murphy & Presser
LandOfFree
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