Explosive Forming of Solid Propellant Rocket Motor End Closures
Technical rept. 1 Feb 1969-30 Apr 1970
MORTON THIOKOL INC BRIGHAM CITY UT WASATCH OPERATIONS
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This report describes the manufacturing processes developed as a preliminary step in establishing a lower cost production capability for large solid rocket motor end closures. The objective of the program was to evaluate two new approaches to the use of explosive energy for forming large, high strength steel hemispheres suitable for fabrication into SRM end closures and subsequently to analyze the overall processing costs. The two approaches, which are complementary in nature, consist of a die developed from ring segments suitable for production use after successful demonstration, and use of welded truncated conical preforms in place of flat blanks as starting material. The data derived from the program provide an insufficient basis upon which to base definite conclusions. However, despite numerous unexpected difficulties in preform fabrication and limited success in explosively forming them, it is concluded that the segmented subscale die could be scaled to full size without undue difficulty. Strain calculations verified by limited experimental results indicate that the target configuration is within the formability limits of a properly fabricated, thermally conditioned, and suitably restrained preform.
- Fabrication Metallurgy
- Solid Propellant Rocket Engines