![]() Dissertation, Mechanical Engineering Dept., Middle East Technical Univ., Ankara, Turkey, 2010. Acik S., “ Internal Ballistic Design Optimization of a Solid Rocket Motor,” M.S. and Guozhu L., “ A Hybrid Optimization Approach for SRM FINOCYL Grain Design,” Chinese Journal of Aeronautics, Vol. 21, No. 6, 2008, pp. 481–487. and Guozhu L., “ A Hybrid Approach for Design Optimization of Wagon Wheel Grain for SRM,” 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, AIAA Paper 2008-4893, July 2008. and Foster W., “ A Review of Analytical Methods for Solid Rocket Motor Grain Analysis,” 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA Paper 2003-4506, July 2003. G., “ Generalized Coordinate Grain Design and Internal Ballistics Evaluation Program,” 3rd Solid Propulsion Conference, AIAA Paper 1968-0490, 1968. Finally, the optimum geometrical parameters for a slotted grain subjected to both structural and internal ballistic performance constraints are investigated through multidisciplinary optimization techniques. The structural analysis results are evaluated by using a deterministic approach based on the margin of safety with respect to the stress and strain criteria. Within a coupled analysis approach, the pressure data obtained from the internal ballistic performance analysis are used for the ignition step of the linear viscoelastic analysis. To enable an efficient optimization process, a surrogate heat transfer model that predicts the cooldown time of the system by eliminating expensive iterations is also implemented and validated. The transient temperature distribution data derived from the cooldown process are required inputs for the material properties to be used in the viscoelastic structural analysis. Structural analysis of the solid propellant is achieved by using a parametric linear viscoelastic model and a parametric cooldown heat transfer model, both of which are based on the finite element method. In-house codes such as a zero-dimensional internal ballistic solver and an analytical burnback solver are implemented to compute the variation of chamber pressure and the rocket thrust transiently. ![]() This research aims to optimize the geometric design of slotted propellant grains for solid rocket motors with respect to coupled internal ballistic performance and structural strength criteria. ![]()
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