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Not Available Virtually every user of launch services is seeking methods to reduce launch costs. A reusable conventional launch vehicle configuration shows the potential to achieve this goal. The LOX/LNG propellant combination shows the potential to enhance both propulsion system reusability and launch system mass-to-orbit capability. This propellant combination also has the performance margins necessary to offset the increased mass required to achieve practical vehicle reusability. Integrating LOX/LNG propulsion into a reusable conventional vehicle system can positively address both of the competing goals of increasing launch system performance and lowering costs. One of the most likely sources of increased system performance comes from upper stage performance. An upper-stage thrust chamber performance of 360s Isp will be targeted in this investigation. Recovery system operations and vehicle and propulsion system reuse criteria will be investigated to establish overall vehicle feasibility and cost structure. A specific vehicle concept will be defined that will have the potential to offer useful mass-to-orbit capability and low costs. The L-curve cost structure of reusable launch vehicles will be investigated and defined including a comparison to expendable vehicle configurations.