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专利名称：Composite propellant with differentially
cured area at initial burn surface
发明人：Donald E. Elrick,Harry Gilbert申请号：US04/781282申请日：19681204公开号：US04337103A公开日：19820629
摘要：Composite rocket propellants, in which the base component is a functionallyterminated rubber, and case-bonded rocket motors containing same, are provided,wherein cross-link density at, and adjacent at least a portion of the initial propellantburning surface is lower than that throughout the remainder of the propellant to providegreater strain capability at the initial burning surface together with greater propellantstrength 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 oras a rocket motor component, to the initial low cross-link density and thereafter applyingto said initial burning surface, an interferent capable of interfering with the cure processto substantially stop same, and then again subjecting the entire propellant to curingconditions to cure the remaining curable propellant portion to the higher cross-linkdensity.
申请人：HERCULES INCORPORATED
代理人：Michael B. Keehan
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