United Technologies Corporation

Eduardo D Casillas

Claude R Joyner

Andrew S Perrucci

Glenn F Sander

Randy C Parsley

Charlie W Shaeffer

Scott E Lowther

The present invention relates to a reusable space access launch vehicle system which comprises a reusable vehicle, at least one expendable boost propulsion device attached to the reusable vehicle, and an oxidizer system onboard the vehicle. The oxidizer system supplies an oxidizer, preferably in a gaseous state, to the at least on expendable boost propulsion device. In a preferred embodiment, the at least one boost propulsion device comprises a hybrid rocket combustor.

Reusable space access launch vehicle system

The present invention relates to a propulsion system for transporting a crew transfer vehicle. The propulsion system has a casing which defines a chamber, a solid propellant system positioned within the chamber for generating one of emergency escape propulsion during an emergency portion of an ascent flight and orbital injection propulsion during normal flight operations, and a sustain propulsion system communicating with the chamber for sustaining one of the emergency escape propulsion during the emergency portion of the ascent flight and orbital injection propulsion during the normal flight operations. In one embodiment of the present invention, the sustain propulsion system comprises a hybrid solid fuel grain and liquid oxidizer system. In a second embodiment of the present invention, the secondary propulsion system comprises a liquid fuel and liquid oxidizer system.

Adaptable solid-hybrid rocket for crew escape and orbital injection propulsion

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San Jose, CA, United States of America

Eduardo D Casillas