the additional structural weight necessary to accommodate the increased up payload. REFERENCE CONFIGURATION DESCRIPTION (LRB W/4 F-l) Both series burn and parallel burn Shuttle/LRB configurations utilizing 4 and 3 F-Ts, respectively, were studied by the EDIN design sizing simulations. The series burn mode configuration designated EDINO5O5 achieved minimum GLOW in the design cases simulated and thus was selected as the PLV reference configuration. Launch vehicle configuration, weights summary, and comparison of this design point to the Baseline Shuttle are presented on Figure VI-C-2. A mission parameter summary by event is presented on Figure VI-C-3 with the mission altitude versus velocity profile. In minimizing the GLOW for the reference configuration, the ET was resized for a usable propellant loading of 1325 metric tons (2.920M pounds) at an average specific impulse of 281.93 seconds versus the baseline Shuttle two SRB combined propellant loading of 1007 metric tons (2.221M pounds) at an average specific impulse of 262.2 seconds. Preliminary cost estimated breakouts are given in Table VI-C-1 as provided by Ms. Debbie Webb of the Resources Management Office. DDT&E is estimated at $51OM with $460M attributed to the LRB; TFU is estimated at $376M with $73M attributed to the LRB and $300M for an Orbiter unit buy. ALTERNATE REFERENCE CONFIGURATION DESCRIPTION (LRB W/3 0? PROPANE ENGINES) An alternate series burn PLV design point utilized 3 new 02/propane "paper" engines in the LRB instead of the 4 F-l's as in the previous reference configuration--and was designated EDIN0511. The 02/propane engine characteristics, as provided by Mr. Merle Lausten of the Propulsion and Power Division, are compared to the F-l in Table VI-C-2. The EDIN0511 weights summary is compared to the EDIN0505 design point in Table VI-C-3. Both ET and LRB main propellant tankage is seen to be reduced with a reduction in GLOW from 2193 metric tons (EDIN0505) to 1779 metric tons (EDIN0511). A mission parameter summary by event is presented on Figure VI-C-4with mission altitude versus velocity profile. Preliminary cost estimate breakouts are given in Table VI-C-4, again provided by Ms. Webb. DDT&E is estimated at $1140 with $1090M attributed to the LRB. Approximately $500M of the $1090M is estimated for the development of the "new" Oo/propane booster engine, which may be available•from the HLLV program. TFU is estimated at $367M with $64M attributed to the LRB and $300M for an Orbiter unit buy. ORBITER PASSENGER TRANSPORT Concepts for a modified Orbiter for passenger transport have been devised by Rockwell International Corporation in an in-house effort and provided for inclusion in this report. The concepts vary in passenger capability from 80 to 68 to 50. The 80-passenger configuration has only
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