Composite propellant with differentially cured area at initial b

Details Composite propellant with differentially cured area at initial b Composite propellant with differentially cured area at initial b

1968-12-04

1982-06-29

Miller, Edward A.

Explosive and thermic compositions or charges

Structure or arrangement of component or product

Solid particles dispersed in solid solution or matrix

149 2, 149 196, 149 1992, 149 20, C06B 4510

Patent

active

043371035

ABSTRACT:
Composite rocket propellants, in which the base component is a functionally terminated rubber, and case-bonded rocket motors containing same, are provided, wherein cross-link density at, and adjacent at least a portion of the initial propellant burning surface is lower than that throughout the remainder of the propellant to provide greater strain capability at the initial burning surface together with greater propellant strength for higher mass ratio and improved case bonding than possible utilizing a single "compromise" propellant cross-link density of the prior art.
Method is provided which involves initially curing the entire propellant mass, alone or as a rocket motor component, to the initial low cross-link density and thereafter applying to said initial burning surface, an interferent capable of interfering with the cure process to substantially stop same, and then again subjecting the entire propellant to curing conditions to cure the remaining curable propellant portion to the higher cross-link density.

REFERENCES:
patent: 3147161 (1964-09-01), Abere et al.
patent: 3177190 (1965-04-01), Hsieh
patent: 3305523 (1967-02-01), Burnside
patent: 3417059 (1968-12-01), Hoffman

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