The hybrid rocket system of this invention is characterized by use of an oxidizer tank having a cylindrical midsection surrounded by a skirt and bonded thereto by a layer of elastomeric adhesive. The skirt outer surface is in turn adhesively secured to a spacecraft inner surface. An elongated solid
The hybrid rocket system of this invention is characterized by use of an oxidizer tank having a cylindrical midsection surrounded by a skirt and bonded thereto by a layer of elastomeric adhesive. The skirt outer surface is in turn adhesively secured to a spacecraft inner surface. An elongated solid-fuel motor case is mechanically rigidly secured to a central rear surface of the tank, and the case terminates in a throat and nozzle. The elastomeric-adhesive bonding of tank to skirt, and rigid adhesion of skirt to spacecraft forms the sole support for the rocket system, and separate support for the motor case is not required.
대표청구항▼
What is claimed is: 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 i
What is claimed is: 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. 2. The propulsion system of claim 1, wherein the tank has an inner liner of an epoxy-fiberglass composite material, the inner liner being overwound with an outer layer of graphite-fiber tow and an epoxy matrix. 3. The propulsion system of claim 2, wherein the skirt is fiberglass. 4. The propulsion system of claim 3, wherein the elastomeric means is a layer of an elastomeric adhesive bonding the skirt to the tank. 5. The propulsion system of claim 4 wherein the elastomeric adhesive has a thickness of about 0.1 inch. 6. The propulsion system of claim 2, wherein the tank inner liner and outer layer are wound around and secured to forward and rear flanges, the flanges in turn being secured to forward and rear bulkheads respective, the bulkheads sealing the tank. 7. The propulsion system of claim 6, wherein the motor case is rigidly secured to the rear bulkhead by releasable fasteners, enabling replacement of a fired motor case. 8. The propulsion system of claim 1 wherein the elastomeric means and an adhesive adhesively securing the skirt to the fuselage form the sole support of the propulsion system to the fuselage. 9. The propulsion system of claim 1 wherein said motor case is cantilevered from said oxidizer tank and is free from other attachment to the fuselage. 10. The propulsion system of claim 1 wherein said motor case is only secured to said oxidizer tank. 11. 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 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; a solid-fuel motor case secured to a rear surface of the oxidizer tank, the case having a rear end defining a throat, and a nozzle; the case being cantilevered behind the tank, wherein said oxidizer tank provides sufficient support to said motor case for entirely supporting said motor case. 12. The propulsion system of claim 11, wherein the elastomeric means is a layer of an elastomeric adhesive bonding the skirt to the tank. 13. The propulsion system of claim 12 wherein the elastomeric adhesive has a thickness of about 0.1 inch. 14. The propulsion system of claim 11, wherein the tank has an inner liner of an epoxy-fiberglass composite material, the inner liner being overwound with an outer layer of graphite-fiber tow and an epoxy matrix. 15. The propulsion system of claim 14, wherein the skirt is fiberglass. 16. The propulsion system of claim 14, wherein the tank inner liner and outer layer are wound around and secured to forward and rear flanges, the flanges in turn being secured to forward and rear bulkheads respective, the bulkheads sealing the tank. 17. The propulsion system of claim 11, wherein the motor case is rigidly secured to the rear bulkhead by releasable fasteners, enabling replacement of a fired motor case. 18. The propulsion system of claim 11 wherein the elastomeric means and an adhesive adhesively securing the skirt to the fuselage form the sole support of the propulsion system to the fuselage. 19. The propulsion system of claim 11 wherein said motor case is entirely supported through said oxidizer tank.
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