Integrated pulsed propulsion system for microsatellite

Details Integrated pulsed propulsion system for microsatellite Integrated pulsed propulsion system for microsatellite

1997-08-18

2000-10-17

Casaregola, Louis J.

Power plants

Reaction motor

Electric, nuclear, or radiated energy fluid heating means

137 6819, F03H 500

Patent

active

061313858

ABSTRACT:
A propulsion system and, in particular, a microthruster for a microsatellite. The microthruster may be formed as a resistojet type thruster formed with a chamber, closed by a diaphragm which acts as a blow-out disk. A fluid, such as an inert gas, is disposed within the chamber. Heating of the gas causes the gas pressure to increase until the diaphragm ruptures, which, in turn, causes the gas to flow out of the chamber, acting as a propellant, and providing a small unit force. The microthruster is adapted to be formed by known batch processing methods with 10.sup.4 -10.sup.6 microthrusters per wafer. The unit of force can be easily scaled by varying the number of microthruster 20 used for an application, the geometry of the chamber 22, as well as the type of fluid used within the chamber, to suit the microsatellite application.

REFERENCES:
patent: H795 (1990-07-01), Maykut et al.
patent: 3316719 (1967-05-01), Loprete
patent: 4399655 (1983-08-01), Fohl
patent: 5661970 (1997-09-01), Muller et al.
patent: 5857698 (1999-01-01), Fuerst et al.

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