Method for binding solid propellant to rocket motor case
AssigneeHer Majesty the Queen in right of Canada, as represented by the Minister of National Defense
InventorsJacques Ratte, Jean Bigras
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Abstract
A method of bonding a solid rocket propellant to a motor casing using a flexible sheet insulant. The flexible sheet insulant is easily installed without intermediate adhesive on the metal or propellant side, retains its self-adhesive properties for long periods when stored at temperatures lower than 40.degree.F before installation and has improved resistance to erosion. The flexible sheet insulant comprises an elastomeric polymer binder in particular a carboxyl-terminated polybutadiene having dispersed therein from 50-80% preferably 65-75% by weight of a siliceous filler reinforcing material at least 50% of which is in the form of fibers. Preferably the filler consists of 50 to 80% asbestos fibers and 20% to 50% asbestos floats.
Claims2
A method comprising preparing a partially cured composition in the form of a sheet for use as a flexible insulant in a rocket motor containing a case-bonded solid rocket propellant which comprises admixing a curable elastomeric polymer binder, a curing agent and a curing catalyst with from 50-80% by weight of the total composition of a siliceous heat-resistant reinforcing filler, at least 50% of said filler being in the form of fibers and the remainder in the form of floats, partially curing the dough obtained to allow curing thereof to the consistency required for subsequent rolling, rolling said partially cured dough into said sheet, pressing said sheet around the inside walls of a rocket motor casing to effect bonding between said sheet and the inside of said wall, introducing a castable rocket propellant that has the same binder as said partially cured composition into the casing and fully curing the propellant and insulant to bond the insulant and propellant together.
The process comprising mixing in a preheated mixer that is preheated to a temperature of about 140.degree.F a carboxyl-terminated polybutadiene binder, a curing agent of tri-functional epoxide and an iron octasol curing catalyst, admixing the mixture with a siliceous filler comprising from 50-80% by weight of asbestos fibers and 20-50% by weight of asbestos floats, partially curing to a dough of the required consistency for subsequent rolling by heating for about two hours at a temperature of 160.degree.F, rolling the partially cured dough, placing said rolled dough around the inside wall of a rocket motor casing, casting a carboxyl-terminated polybutadiene castable propellant into said casing and fully curing the composite so obtained to effect bonding between the propellant and the insulant and the insulant and the casing.
Dependencies are inferred from the claim text.