Low Recurring Cost, Partially Reusable Heavy Lift Launch Vehicle

Abstract

This paper presents a partially reusable, two-stage-to-orbit launch vehicle concept for delivering 65 metric ton payloads to low Earth orbit. A winged booster and an expendable core stage each use identical main propulsion, thrust structure, and propellant feed systems. For both stages, four 745,000 lbf thrust, RS-68 oxygen/hydrogen rocket engines, presently used on the Delta-IV launch vehicle, are used. The booster, which does not require reentry thermal protection, ascends to aMach 2.4, 81,000 ft altitude condition, separates from the core stage, and glides back to a runway landing. Sixty-five metric tons in orbit would be enabling to a variety of exploration missions, including very large telescope emplacement missions, robust outer planet missions, and others requiring large payloadmasses or volumes. Use of a reusable booster, designed formaintainability and affordability, would, in combination with an expendable core using common propulsion, allow for significant reductions in recurring costs compared with a totally expendable vehicle with similar payload capabilities.