|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||060/251; 060/253; 244/171.1|
|§371/§102 date||20051101 (20051101)|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 4 인용 특허 : 20|
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 ...
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 c...