J. Space Transportation This section provides a description of the space transportation system. Both launch and orbit transfer vehicles for cargo and personnel are included. In addition, launch facility requirements and operations/support are discussed. The space transportation system includes a heavy lift launch vehicle (HLLV), a modified shuttle personnel launch vehicle (PLV), a personnel and supplies high-thrust orbit transfer vehicle (OTV), and low-thrust cargo orbit transfer vehicle (COTV) installed on the SPS modules constructed at LEO. The low-thrust OTS modules are reusable and are returned to LEO by a vehicle similar to the personnel OTV. HLLV - The HLLV is a 2-stage, fully reusable winged launch vehicle. The launch configuration of the HLLV is shown in Figure B-22 with the overall geometry noted. This vehicle uses 16 LCH4/LO2 engines on the booster (first stage) and 14 standard SSME's on the orbiter (second stage). The LCH^/LO^ booster engines employ a gas generator cycle and provide a vacuum thrust of 9.79 X 10 newtons each. The SSME's on the orbiter provide a vacuum thrust of 2.09 X 10$ newtons (100% power level). The gross lift-off weight of an HLLV is 11,040 metric tons with a payload to low earth orbit of 424 metric tons. A return payload of 15% (63.5 metric tons) of the delivered payload was assumed for the orbiter entry and landing conditions. An airbreather propulsion system (aircraft jet engine) has been provided on the booster for flyback capability to simplify the booster operational mode. Its landing weight is 934 tons. The HLLV is launched vertically using an erection system as illustrated in figure B-23. The stack height of the vehicle is 164 meters. The booster has a wing span of 60.6 meters. The orbiter uses a glideback landing and has a landing weight of 439 metric tons.
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