Figures 8 through 11. Figure 11 shows a time history of booster stage ballistic entry; the resulting total heat and heat rates were used to provide inputs to the sizing program for sizing aerosurfaces. The GLOW of the L0X/LH2 vehicle was 11,054 metric tons (24,370,200) pounds). Since the performance characteristics of the booster engines were closer to those of the upper stage than were the LOX/RP-1 booster engines, the ideal velocity for the stages was about equal. The LOX/ LH2 booster staging point was about 12,000 meters (41,000 feet) higher and the velocity about 230 meters per second (750 feet per second) greater than that of the LOX/RP-1 booster. A weight and performance summary for the L0X/LH2 vehicle is presented in Table 6, and the trajectory time histories for this vehicle are given in Figures 12 through 15. Figure 15 shows the resulting ballistic entry heating of the booster stage. After these vehicles had been sized, a L0X/C3H8 (propane) engine was proposed for the boost stage of an HLLV. Engine performance characteristics of this gas generator cycle engine are given in Table 7. Sizing studies and trajectory analysis defined the propane vehicle; its GLOW was 13,737.8 metric tons (30,286,651 pounds). As with the other vehicles, a growth allowance of twenty percent dry weight was maintained. A weight and performance summary of this vehicle is shown in Table 8 and trajectory time histories are given in Figures 16 through 19. The heat and heat ratings from the booster stage ballistic trajectory are shown in Figure 19. Table 9 lists the inert weight of each of the three candidate launch vehicles, and gives a brief summary of the geometric characteristics of each. Although the GLOW of the L0X/LH2 vehicle is about 2300 - 2800 metric tons ( 5-6 million pounds) less than the LOX/RP-1 or the L0X/C3H8 vehicles it is also by far the largest vehicle. The LOX/RP-1 and the L0X/C3H8 vehicles, however, are quite similar in both size and weight. Each of the candidate vehicles could meet the performance requirements of the SPSS. Ms. D. Webb of the Management Resources Office provided support to the HLLV sizing study by costing the candidate vehicles. Detailed cost statements are given in Tables 10 (L0X/LH2 vehicles), 11 (LOX/RP-1 vehicle), and 12 (L0X/C3H8 vehicle). A summary of the costs of these vehicles is presented in Table 13. Final evaluation of the winged two stage concept resulted in the selection of the L0X/C3H8 booster engines. A detailed weight statement for this vehicle is given in Tables 14, 15 (booster stage) 16, 17 (upper stage) and a geometry summary is shown in Tables 18 (booster stage) and 19 (upper stage). A reference trajectory is listed in Appendix A.
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