HP-981OA computer program with typewriter output so that yearly and total SPS program space transportation traffic models with associated costs could be derived more expediently as corresponding scenario data inputs evolved. Launch Site Consideration A 28.5° latitude due east launch was assumed for the HLLV's, requiring the OTV's to make the plane change for the equatorial orbit. This is a conservative assumption for performance, since an equatorial launch site offers the advantages of increased Earth rate, a slight increase in altitude because of the Earth's oblateness and, most importantly, the elimination of the plane change requirement which saves approximately 1500 fps of delta V. An additional operational benefit of an equatorial launch site is the opening of the launch window to almost "at will" launch instead of the total of about 3 hours daily available at a 28.5° KSC launch site. Future studies will investigate more thoroughly the technical and other trade-offs for various launch sites as well as the impacts of establishing the SPS in a Lagrangian metastable orbit inclined at approximately 7.3°. Transportation Fleet Description Vehicle characteristics for the space transportation fleet were synthesized for input to the scenario computer program. In-house and contractor studies served as background and reference data for developing the detailed vehicle data. Projected ranges of technology (performance, weights, and costs) were used in sizing the minimum cost (MIN), nominal cost (NOM), and maximum cost (MAX) vehicle derivative. Heavy Lift Launch Vehicle (HLLV) - The HLLV will be utilized for transport of all SPS hardware, OTV hardware and propellants, construction and support bases and consumables, and personnel consumables from Earth to LEO. Eleven candidate launch vehicles have been identified of these basic types: complete winged entry/recovery, complete ballistic entry/recovery, winged entry/recovery with large external hydrogen tank expended. The various costs of development, acquisition and operation are still under study. The minimum cost vehicle has been characterized as a two stage, series burn ballistic entry/recovery unmanned launch vehicle with Op/propane booster and Op/Hp second stage. The maximum cost vehicle has been characterized as a two stage, series burn winged entry/ recovery with Op/RP-l booster and Op/Hp second stage. The following HLLV input data was derived to provide tne extremes and is consistent with HLLV study data to date:
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