VI-B-2 MODIFIED SINGLE STAGE TO ORBIT HEAVY LIFT LAUNCH VEHICLE JACK FUNK MISSION PLANNING AND ANALYSIS DIVISION I. GENERAL DESCRIPTION The single stage to orbit (SSTO) heavy lift launch vehicle configuration is shown in figure VI-B-2-1. The vehicle consists of a lifting body entry vehicle which contains the liquid oxygen propellant tank, main propulsion systems, guidance system and other support systems, and an external expendable liquid hydrogen fuel tank. The vehicle is operated single stage to orbit, that is, the hydrogen tank is carried all the way to orbit where it is staged for disposal with a technique similar to the disposal of the shuttle external propellant tank. Launches from KSC would use a disposal area in the Indian Ocean, the same as the shuttle. The entry vehicle and payload proceed to 185 KM (100 n.mi.) circular orbit using the on-orbit maneuvering system. The payload is separated and the heavy lift launch vehicle returns to the launch site for a horizontal landing. After separation the payload completes the orbit phase of the mission using an on-orbit maneuvering system. The heavy lift launch vehicle does not have a payload bay for launch and return of the payload. All payloads are carried external - piggy back. Manned payloads and payloads returned from orbit are carried in a modified shuttle orbiter. Since the shuttle orbiter no longer requires a main propulsion system, it can be modified to increase its payload, improve its landing characteristics, and safety of operation. Cargo for construction of the Solar Power Satellite Systems (SPS) is carried to orbit in a reusable cargo glider. Figure VI-B-2-2 shows the launch configuration with the cargo glider. The cargo glider is a light weight entry vehicle with a monocoque fuslage to carry cargo, light weight wings for entry and landing, an orbit maneuvering system, attitude control and guidance. The glider is unmanned and has no return payload capacity. Although the heavy lift launch vehicle is primarily being sized to support the Solar Power Satellites (SPS), this particular configuration is general purpose and can support all future space missions. This flexibility is obtained by carrying the modified orbiter as a payload. Since the vehicle is single stage to orbit, it also can operate from a variety of launch sites using the suborbital staging technique developed for disposal of the shuttle external tank. Suitable water disposal areas are available from many launch site locations. II. VEHICLE SIZING ANALYSIS The basic considerations in the sizing analysis are the weight of payloads to be carried, the systems and structure weight scaling factors
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