Figure 8.9 Boeing Studies and Comparison with Existing Launchers. Figure 8.10 Rockwell Configuration. The ROCKWELL HLLV concept has a payload capability of 230 metric tons to LEO and is a winged, two-stage, parallel burn configuration designed for vertical take-off and horizontal landing. Both stages are fully reusable. The booster has 7 LOX/RP-1 (kerosene) engines that operate on a gas generator cycle (with high chamber pressure and relatively high Isp (352 sec)), and an air breather propulsion system for flyback to the launch site. The orbiter has 4 L0X/LH2 engines derived from the Space Shuttle Main Engine (SSME) technology but much larger and with a higher Isp (467 s versus 455 s).
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