| 摘要 |
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 internal, hollow structural spine (26) that can also interface with an internal umbilical tower (46). The segments (54) together with their associated thrusters and related components can be mass produced, thereby increasing competition among suppliers, reducing design costs and timeframes.
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