the disclosed launch systems are formed from mass producible elements that integrate propulsion , pneumatics and structural systems . in one embodiment , a launch system includes multiple stages where each stage includes a number of generally wedge - shaped segments . alternating segments form liquid fuel and oxidizer tanks . each fuel and oxidizer tank pair is associated with a thruster . the resulting plurality of thrusters are disposed about a common aerospike thrust structure . the segments are connected to an internal , hollow structural spine that can also interface with an internal umbilical tower . the segments together with their associated thrusters and related components can be mass produced , thereby increasing competition among suppliers , reducing design costs and timeframes .