نوع مقاله : مقاله پژوهشی
نویسندگان
1 دکتری تخصصی / دانشگاه صنعتی مالک اشتر
2 دانشیار مجتمع برق دانشگاه صنعتی مالک اشتر
3 دانشیار دانشگاه صنعتی مالک اشتر
چکیده
کلیدواژهها
موضوعات
عنوان مقاله [English]
نویسندگان [English]
In this paper, the Trajectory optimization of a typical three-stage satellite launch vehicle is presented. The results of this optimization can be used as a preset guidance law in the launch vehicles. In this optimization, the dynamic constraints of the Trajectory and the conditions of the insertion point are considered. The results obtained from the optimization algorithm are based on the model of a typical example. Due to the nonlinear and constrained model, the use of numerical optimization method for this problem is inevitable. The optimization program uses a non-linear and constrained algorithm to extract the optimal sub-optimal program from the sequential quadratic programming method. To run the flight program, a time function of the desired flight angle of the launch vehicle is applied as an input to the program at each stage of the optimization operation. The trajectory and mass optimization algorithm is designed in such a way that in addition to optimizing the payload for a three-stage carrier rocket, it considers the path parameters and the final insertion conditions as optimization constraints. The results of various simulations of the prepared program show its efficiency in optimizing the payload mass and fulfilling the orbital insertion conditions and determining the accessible Trajectories.
کلیدواژهها [English]
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