INTEGRAL LAUNCH AND REENTRY VEHICLE SYSTEMS – VOLUME 1 – BOOK 1- CONFIGURATION DESIGN AND SUBSYSTEMS

摘要

This study emphasized a two stage to orbit reusable spacecraft system for use in transporting cargo and passengers to and from a near earth orbital space station. A single conceptual "point" design was treated in detail and several alternate systems, corresponding to alternate payloads (size and weight), were examined based on parametric excursions from the "point" design. The overall design goal was to configure the carrier and orbiter vehicles to minimize operational and program recurring costs. This goal was achieved through high system reliability, vehicle recoverability, and rapid ground turnaround capability made possible through modular replaceable component design and use of an integrated onboard self test and check. out system. Launch and land landing of both stages at the ETR launch site was a study groundrule as was the nominal 25,000 lb payload delivered to and returned from orbit and packaged in a 15 ft, diameter by 30 ft. long cylindrical canister. The resulting system has a gross lift-off weight of 3.4 million pounds.