MANUFACTURING TECHNOLOGY FOR LARGE MONOLITHIC FIBERGLASS REINFORCED PLASTIC ROCKET MOTOR CASE. VOLUME II. APPENDIXES.
Final technical documentary rept. 1 May 63-7 Sep 65,
AEROJET-GENERAL CORP AZUSA CA
Pagination or Media Count:
The final report is presented in two volumes. Volume I presents the program objective, plan of accomplishment, performance and results. Volume II presents information supplementary to the program in the form of appendices. Information in Volume II is in the form of specifications to design, fabricate, and test major items of tooling and equipment, inspection reports of the 260-inch-diameter segmented mandrel, and detailed fabrication instructions for the major chamber fabrication processes. The program objective was the development of fabrication processes, manufacturing methods technology and controls, tooling, and equipment required to fabricate very large rocket motor cases using the filament-winding process. Demonstration of the manufacturing methods development was to be accomplished by the hydrotest of a prototype filament-wound case 260 in. in diameter by 54.5 ft long. Laboratory investigations were conducted to determine, investigate and resolve deviations from standard fabrication procedures and case design resulting from the increase in thickness associated with the very large filament-wound rocket case. The glass composite wall thickness ranges from 1.25 in. in the cylindrical section to 6.5 in. around the boss openings. Selected case design parameters and fabrication processes were evaluated by the fabrication and test of two 54-in.-diameter by 11.5-ft-long subscale cases. The largest known horizontal-track-type winding machine was designed and fabricated to filament-wind a chamber 22 ft in diameter by 55 ft long.
- Solid Propellant Rocket Engines