Bi-metallic thermal compensator for mounting a solid propellant

Details Bi-metallic thermal compensator for mounting a solid propellant Bi-metallic thermal compensator for mounting a solid propellant

1978-03-13

1980-02-12

Garrett, Robert E.

Power plants

Reaction motor

Solid propellant

102 99, F02K 904

Patent

active

041876768

ABSTRACT:
A rocket assisted projectile is equipped with a bi-metallic disk which ches shape to compensate for propellant grain growth or shrinkage with change in ambient temperature for maintaining the propellant in a predetermined position within the combustion chamber of the rocket. The disk is located in the combustion chamber forward of the propellant grain and bears against the chamber forward wall and the forward end of the grain. The effective thickness of the disk increases with reduced temperature so that the grain is maintained in solid contact with the base of the projectile to prevent excessive energy absorption upon firing of the projectile.

REFERENCES:
patent: 1852543 (1932-04-01), Spencer
patent: 2937493 (1960-05-01), Adelman
patent: 3066481 (1962-12-01), George et al.
patent: 3144829 (1964-08-01), Fox
patent: 3201936 (1965-08-01), Bancelin
patent: 3238717 (1966-03-01), Aycock et al.
patent: 3327481 (1967-06-01), Horvath
patent: 3765846 (1973-10-01), Gottueb et al.
patent: 3786633 (1974-01-01), Worcester et al.
patent: 3916618 (1975-11-01), Araki et al.

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