Patent Number: 6,332,592

Title: Method for velocity precision pointing in spin-stabilized spacecraft or rockets

Abstract: A method of velocity precision pointing of spin-stabilized spacecraft or rockets is disclosed. This method involves softening the ignition transient of the ramp up phase of thrust, which may be achieved by modification of the solid propellant, applying a coating of slow burning material upon the solid propellant varying the grain density of the solid propellant over an exposed surface area or as a function of propellant depth, where depth is defined in the direction of the burn surface area regression, pre-pressurizing the combustion chamber with a gas having a molecular mass smaller than that of the combustion products and which is unreactive with the propellant, installing one or more relief valves in the combustion chamber to regulate the pressure, forming a ring of an ablative material on the throat section of the nozzle, having a rubber fitting at a throat section of the nozzle to regulate the pressure of the combustion chamber, pulsing the engine, or using a pyrogen igniter to soften the ignition transient.

Inventors: Longuski; James M. (Lafayette, IN), Javorsek, II; Daniel (West Lafayette, IN)

Assignee: Townsend; Donald E.

International Classification: B64G 1/22 (20060101); B64G 1/28 (20060101); B64G 1/40 (20060101); B64G 1/24 (20060101); B64G 1/26 (20060101); F02K 009/72 ()

Expiration Date: 12/25/2018