Savings of 50 percent can be achieved in ablative nozzles for 260-in.-dia solid rocket motors using present state-of-the-art materials. An optimum nozzle design with respect to cost and performance results from the use of a standard carbon-phenolic tape grade for the throat insert and canvas, carbon-silica and silica materials throughout the remainder of the nozzle.
LOW-COST FABRICATION TECHNIQUES FOR SOLID ROCKET NOZZLES
Sae Technical Papers
National Aeronautic and Space Engineering and Manufacturing Meeting ; 1970
1970-02-01
Conference paper
English