|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64G-001/40 F42B-015/10 F02K-009/28 F02K-009/00|
|미국특허분류(USC)||244/172 ; 102/374 ; 102/377 ; 60/250 ; 60/253 ; 60/255 ; 60/257|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 16 인용 특허 : 16|
The disclosed launch systems are formed from mass producible elements that integrate propulsion, pneumatics and structural systems. In one embodiment, a launch system (10) includes multiple stages (12-16) where each stage includes a number of generally wedge-shaped segments (54). Alternating segments (54) form liquid fuel and oxidizer tanks. Each fuel and oxidizer tank pair is associated with a thruster (70). The resulting plurality of thrusters (70) are disposed about a common aerospike thrust structure (30-34). The segments (54) are connected to an int...
[ What is claimed is:] [1.] A launch system that has an elongate form with a central, longitudinal axis, comprising:at least a first propulsion element disposed within a first angular region on a first side of said longitudinal axis, including at least a first fuel tank for containing fuel in a fluid phase and a first combustion chamber in selective fluid communication with said first fuel tank;at least a second propulsion element disposed within a second angular region on a second side of said longitudinal axis opposite said first side, comprising at le...