Solid propellant canister loaded multiple pulsed or staged rocket
AssigneeThiokol Corporation
InventorsBradley W. Smith, Dean C. Youngkeit
Life of this patent
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Abstract
A multi-pulse or multi-stage canister loaded solid propellant rocket motor. The canisters are prepared separately and loaded with solid propellant whereby the scrape rate may be reduced after which they are installed in a monolithic case which affords stiffness continuity over the length of the rocket motor to prevent guidance system upsetting free play. In order to reduce the complexity of installation of the membrane seal assembly for each pulse, the bulkhead therefor is manufactured integral with the case of the respective canister and becomes the forward closure thereof. For the multi-stage rocket motor, the monolithic case may be stepped and tapered, and the stages severable therefrom as they burn out by primer cord.
Claims16
A rocket motor comprising a monolithic elongate generally cylindrical case having means defining an aft aperture, at least two canisters each of which has an individual case and contains an individual grain of solid propellant material, said canisters disposed sequentially within said monolithic case in end to end relation with said individual canister cases attached to said monolithic case, each of said canisters has a closed forward end portion, an aft aperture means, and thrust nozzle means fixed to said respective canister case in flow communication with said respective canister aft aperture means, means for igniting each said grain of solid propellant material, and means for severing said monolithic case to release the aft one of said canisters after the solid propellant material therein is burned.
A rocket motor comprising a monolithic elongate generally cylindrical case having means defining an aft aperture, at least two canisters each of which has an individual case and contains an individual grain of solid propellant material, said canisters disposed sequentially within said monolithic case in end to end relation with said individual canister cases attached to said monolithic case, each of said canisters has a closed forward end portion, an aft aperture means, and thrust nozzle means fixed to said respective canister case in flow communication with said respective canister aft aperture means, means for igniting each said grain of solid propellant material, and means for severing said monolithic case to release the aft one of said canisters after the solid propellant material therein is burned, and wherein said monolithic case has at least two stepped portions to which said canister cases are attached respectively and a tapered portion between said stepped portions to have a larger diameter at the aft end than at the forward end thereof.
A method of making a rocket motor comprising the steps of:
- a. providing a monolithic elongate generally cylindrical case having an aft aperture;
- b. providing at least two canisters each having an individual case and containing an individual grain of solid propellant material and each having a closed forward end portion and an open aft end portion to which a nozzle is attached in flow communication therewith;
- c. inserting each of the canisters in the monolithic case in end to end relation;
- d. attaching said individual canister cases to the monolithic case;
- and
- e. providing means for severing the monolithic case and releasing the aft canister therefrom after the solid propellant material therein has burned.
Dependencies are inferred from the claim text.