As part of a Provision of Services Agreement between Bristol Aerospace Ltd. and the Department of National Defence, the Defence Research Establishment, Valcartier was required to perform the structural integrity analysis of the grain of a solid propellant rocket motor , designated as the l7KS12000. Three load cases were considered for the final analysis: thermal contraction, launch acceleration, and ignition pressurization. The analyst used the finite element method and applied the Williams-Landel-Ferry technique of reduced variables to the propellant mechanical properties
17KS12000 Motor Grain Structural Integrity Analysis
1981
72 pages
Report
No indication
English