Engineering topics
Publications and source records attributed to Stang, D. A..
Three 71-cm-diameter boron/epoxy composite rocket motor chambers were filament wound. The first chamber was hydrostatically tested; the second failed in proof test as a result of fabrication deficiencies. The third chamber obtained a successful proof test, but deformed later in processing because of hydrolysis. In spite of the deformation, this chamber was test fired and then burst tested.
Method includes test device design and fabrication and standard Naval Ordnance Laboratory /NOL/ test ring as the test specimen. Technique provides accurate measurement of NOL ring elastic modulus, and adapts for use with fiber glass epoxy/rings.
Three 28-inch-diameter solid rocket motor cases were fabricated using 1/8 inch wide boron/epoxy tape. The cases had unequal end closures (4-1/8-inch-diameter forward flanges and 13-inch-diameter aft flanges) and metal attachment skirts. The flanges and skirts were titanium 6Al-4V alloy. The original design for the first case was patterned after the requirements of the Applications Technology Satellite apogee kick motor. The second and third cases were designed and fabricated to approximate the requirements of a small Applications Technology Satellite apogee kick motor. The program demonstrated the feasibility of designing and fabricating large-scale filament-wound solid propellant rocket motor cases with boron/epoxy tape.
In-plane stiffness matrices for composite cylinders of filament winding determined by internal pressure, axial tension and torsion tests
Buckling strengths of axially compressed filament wound cylinders determined by linear anisotropic shell theory