Patent ID: 7540145
Filing Date: 2009-06-02
Classification: B64G,F02K

Abstract:
1. In a suborbital spacecraft having a fuselage with a generally central and open interior cylindrical surface, a hybrid-rocket propulsion system, comprising an oxidizer tank having an outer and central cylindrical surface covered by a skirt, and insertable within the fuselage interior surface, the skirt and tank being secured together by an elastomeric means, and an outer surface of the skirt being adhesively secured to the fuselage interior surface; an elongated and generally cylindrical solid-fuel motor case rigidly secured to a central rear surface of the oxidizer tank, the case having a rear end defining a throat, and a nozzle extending behind the fuselage; the case being cantilevered behind the tank, said oxidizer tank providing sufficient support to said motor case for entirely supporting said motor case.