A preliminary design study was conducted to determine the feasibility of performing space rescue, resupply, and reconnaissance with a glide-type reentry vehicle. It was assumed the 15,000 pound rescue vehicle could be boosted to a 100nm circular orbit by a Titan 3-D launch vehicle. From this parking orbit, orbital transfer, rendezvous, and deorbit capability were determined. A reentry trajectory analysis was performed and showed that a crossrange of 2,000 nm could be attained. Heating analysis indicated that the reentry problem could be overcome with currently available engineering materials. Due to a relatively small onboard incremental velocity capability, only limited use as a rescue vehicle is planned. (Author).