Advanced designs for high pressure, high performance solid propellant rocket motors
AssigneeCordant Technologies Inc.
InventorsDavid K. Hawkins, Carol J. Campbell
Life of this patent
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Abstract
A solid rocket propellant formulation with a burn rate slope of less than about 0.15 ips/psi over a substantial portion of a pressure range of about 1,000 psi to about 7,000 psi and a temperature sensitivity of less than about 0.15%/.degree. F. is provided. A high performance solid propellant rocket motor including the solid rocket propellant formulation is also provided. The rocket motor is encased in a high strength low weight motor casing which is further equipped with a nozzle throat constructed of material that has an erosion rate not more than about 2 to about 3 mils per second during motor operation. The solid rocket propellant formulation can be cast in a grain pattern such that an all-boost thrust profile is achieved.
Claims14
A solid propellant formulation comprising:
- from about 25% to about 55% by weight ammonium perchlorate particles having an average size of about 200 .mu.m;
- from about 25% to about 40% by weight ammonium perchlorate particles having an average size in a range of from about 2 .mu.m to about 50 .mu.m;
- from about 7% to about 15% by weight of at least one energetic polymeric binder, which further comprises a polymeric binder and an energetic plasticizer;
- and
- from about 1% to about 4% by weight of at least one ballistic modifier;
- wherein said propellant formulation has a burn rate slope of less than about 0.15 ips/psi over a substantial portion of a pressure range of from about 1,000 psi to about 7,000 psi and a temperature sensitivity of less than about 0.15%/.degree. F.,
- wherein said burn rate slope is equal to:
- ##EQU5##
A solid propellant formulation comprising at least one oxidizer, at least one energetic polymeric binder, which further comprises a polymeric binder and an energetic plasticizer, and at least one ballistic modifier, said solid propellant formulation exhibits a burn rate slope of less than 0.15 ips/psi extending over at least a substantial portion of a pressure range between 1000 psi and 7000 psi, the burn rate slope being equal to:
Dependencies are inferred from the claim text.