Trw Limited

Peter D Lohn

David H Lewis, Jr

James E Eninger

H Wilhelm Behrens

Wingsiu R Chan

Robert A Schlichting

A spacecraft component ( ) includes a plurality of parts, e.g., a first part ( ) and a second part ( ) connected to one another, at least the first part ( ) being mounted for movement with respect to another of the parts, e.g., the second part ( ). At least one microthruster ( ) is provided on the first part for actuation thereof and includes a chamber ( ), a fluid provided in the chamber and a diaphragm ( ) covering an opening in the chamber ( ).

Spacecraft component with microthruster actuation and operation thereof

A microthruster ( ) provides a small unit force. The microthruster is useful, for example, as a propellant for a microsatellite. The microthruster includes an aerospike ( ) extending outwardly beyond the face of an outer wall of the chamber ( ) of the microthruster in the vicinity of an outlet nozzle thereof formed by two diaphragms or burst disks ( ), closing the chamber on respective sides of the aerospike. The aerospike is preferably formed integrally with the chamber by batch microelectronic fabrication methods. Higher thrust efficiency and more controllable and uniform impulse characteristics are attainable with the microthruster and with an array ( ) comprising a plurality of the microthrusters.

Aerospike augmentation of microthruster impulse

There is provided a cylindrical valve 20 for placement in the flow path of a singlet-delta oxygen generator 12 that feeds O.sub.2.sup.* to a chemical laser gain medium 14. The feed path 22 includes a sharp 90.degree. bend 24 that causes fluid velocity variations in O.sub.2.sup.* entering the gain medium 14. Integral with the valve 20 is a tubular structure 12 having a partial circumferential radially extending surface 44 fitted with 'O' ring for sealing and opening the feed path between the 'O.sub.2.sup.* ' generator 12 and gain generator 14. A series of vanes 32, 34, 36 disposed in velocity control zones 50, 52, 54 and 56 are integral with the valve 20 for leveling out the velocity variations and controlling the wake formation 58, 59 and 60 in the O.sub.2.sup.* entering the gain generator 14.

Integrated valve and flow control apparatus and method for chemical

A missile defense system generates a change in density in the air path of a missile. The density change is created by a high-pressure water system which can be generated by a water jet or a body of water explosively created from a water surface. When operating against a waterborne missile, the density of the water medium is changed. The change in density creates an effective barrier against an incoming missile.

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Torrance, CA, United States of America

Peter D Lohn