Patent ID: 6487844
Filing Date: 2002-12-03
Classification: B64G,F02K,F05D

Abstract:
A microthruster for use as a propellant device for a microsatellite, the microthruster comprising:a chamber for carrying a fluid which can be pressurised; a diaphragm in a wall of said chamber for closing said chamber, said diaphragm being rupturable when the fluid pressure in said chamber is increased to a rupture pressure of said diaphragm so that the fluid flows out of an exit section for fluid propellant from the chamber creating a thrust impulse over a blow-down time, the size of said microthruster being selected such that the blow-down time of said microthruster is <103 microseconds; and an aerospike formed integrally with the wall of the chamber of said microthruster in the center of said exit section of the chamber and extending outwardly beyond an outer face of the wall of said chamber in the vicinity of said diaphragm from a location inwardly of an inner face of the diaphragm so as to dynamically interact with the fluid being expelled from the chamber upon rupture of the diaphragm to provide an increased and more controllable impulse.