Propulsion requirements for the HL-20 personnel launch system

A lifting-body approach to the design of an HL-20 personnel launch system spacecraft for SSF crew rotation missions is presented. The high hypersonic lift-to-drag ratio of the HL-20 provides significant advantages in reduced g-loads during entry, high crossrange capability, ability to fly to landing sites over an extensive part of the earth, and multiple landing opportunities per day at specific landing sites. The HL-20 is capable of performing a return-to-launch-site runaway landing anytime during the first minute of launch following activation of an enhanced launch escape system.