Ordnance – Rocket launching – Having tubular guide means
Reexamination Certificate
1990-04-30
2001-11-06
Carone, Michael J. (Department: 3641)
Ordnance
Rocket launching
Having tubular guide means
Reexamination Certificate
active
06311604
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention relates to missile launchers and more particularly to protection for missile launch tubes.
2. Description of Related Art
Foreign matter can have a deleterious effect on a missile launch tube and the launching of missiles. Among the troublesome foreign matter are ice build up and debris which, if located within the missile launch tube, can result in damage to the tube, damage to the missile itself and undesirable launch characteristics for the missile.
Heretofore a number of techniques have been used to protect the missile launch tube and the missile. For example, the missile launch tube has been heated or pyrotechnic frangible covers have been provided. Moreover, plugs and retractable and unretractable caps have been utilized. In addition, diaphragms have been disposed across the face of the missile launch tube. All of these approaches have exhibited varying degrees of success.
Among the less than desirable characteristics exhibited by these types of devices were that they did not adequately prevent ice buildup, they tended to remain in the missile launch path too long and they created debris problems of their own which could impact on the missile, on adjacent missile launch tubes or on the launch vehicle itself. For example, a hollow foam plug was tried and it tended to ride on the nose of a launched missile. In addition, other plugs tended to ice up and freeze into a solid piece.
SUMMARY OF THE INVENTION
The present invention utilizes a missile launch tube cover comprising a hollow insert made of a light weight foam material which is divided into a plurality of “pie shaped” or radial segments. The cover is disposed in one end of an airborne or ground based missile launch tube such that when the missile is launched it tends to displace the cover and direct the segments in a radial direction because of positive air pressure imparted to the concave inside surfaces of the cover by the missile. A coating is formed on the outer surfaces of the cover to prevent icing and/or electromagnetic interference.
There are numerous advantages to this approach. For example, tile cover does not affect the missile exit. Moreover, it does not ride on the missile nose because its individual segments are each displaced in a radial direction away from the missile path. Thus, these segments do not then interfere with the missile's aerodynamics, control surfaces, or any guidance or control wire for wire guided missiles. Also, the individual segments are small and lightweight and do not create surface damage to the launch vehicle or damage to any adjacent launch tube covers. Additional advantages are that this missile cover is not withdrawn from the launch tube by negative air pressure created by launch of adjacent missiles and is not damaged or undesirably affected by the positive aerodynamic pressure or flash of adjacent launched missiles. Also the cover does not ice up and freeze into a unitary block.
REFERENCES:
patent: 3362291 (1968-01-01), De Luca
patent: 3456552 (1969-07-01), Nash
patent: 3754497 (1973-08-01), Rusbach
patent: 4301708 (1981-11-01), Mussey
patent: 4455917 (1984-06-01), Shook
patent: 4498368 (1985-02-01), Doane
patent: 4649795 (1987-03-01), Olander
patent: 2424480 (1974-12-01), None
Foris Victor G.
Tokiyama Takeshi
Alkov Leonard A.
Carone Michael J.
Lenzen, Jr. Glenn H.
Raytheon Company
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