Previous studies have investigated escape from aerospace vehicles in the general aspects of escape concepts, configurations, systems and performance for single crew compartments. At hand is the concept of two stage manned recoverable aerospace vehicles with a crew compartment in each state. In this study the detection, initiation and separation phases of escape were investigated to determine the unique problems, if any, in these phases resulting from the presence of two separated crew compartments. The basic mission was an orbital mission, and the basic configuration classes were vertical take-off and landing (VTOHL) and horizontal take-off and landing (HTOL). Generalized hazards analysis studies were made for each configuration class considering system hazards and mission effects. Escape concepts ranging from ejection seats to fully recoverable capsules were reviewed for applicability to the present problem with the fully recoverable capsule being selected. A combination manual/automatic escape initiation system was selected as the most promising for these advanced concept vehicles. A cockpit malfunction status display and emergency control console was conceptually designed. This system, called the Malfunction Warning Display, would be in each compartment and prior to staging each compartment would monitor boost performance, making the most use of the flexibility and decision making capability of the men in each crew compartment. Separation trajectory characteristics were investigated leading to the establishment of crew compartment location and ejection sequencing criteria. (Author)


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