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To meet the extreme design requirements for strength and erosion resistance of an advanced solid propellant rocket motor, a unique reinforced plastic fabrication process has been developed. An analysis of the process provides a state-of-the-art reference point from which trends for future design, material, fabrication, and quality control requirements are discussed.

THE GENERAL problem of non-air-breathing auxiliary power systems suitable for missiles and space vehicles is considered. On the basis of minimum weight it is shown that for powers less than a few kilowatts, systems such as batteries, fuel-cells, solar cells, and radioisotopes are preferred. The particular choice depends mainly upon the required duration. For powers larger than a few kilowatts, either chemical propellant-mechanical conversion systems or nuclear power systems must be used. Due to shielding considerations the nuclear auxiliary power systems are primarily restricted to satellites and space vehicles. The chemical propellant systems are required for durations of a few hours and less; the nuclear systems must be used for times greater than a few hours. Various types of chemical propellant-mechanical conversion systems are described.