کد مقاله کد نشریه سال انتشار مقاله انگلیسی نسخه تمام متن
487487 703573 2015 7 صفحه PDF دانلود رایگان
عنوان انگلیسی مقاله ISI
Particle Swarm Optimization Applied to Ascent Phase Launch Vehicle Trajectory Optimization Problem
ترجمه فارسی عنوان
بهینه سازی ذرات به روش بهینه سازی مسافت راه اندازی خودرو در فاز بالا مورد استفاده قرار می گیرد؟
موضوعات مرتبط
مهندسی و علوم پایه مهندسی کامپیوتر علوم کامپیوتر (عمومی)
چکیده انگلیسی

The ascent phase trajectory optimization of a single stage liquid propellant hypersonic launch vehicle is considered in this paper. Trajectory optimization is done to achieve desired terminal conditions using angle of attack as a control variable. The formulation entails nonlinear 2-dimensional launch vehicle flight dynamics with mixed boundary conditions and multi-constraints. The burning time of the liquid rocket engine is fixed, leading to fixed time problem. By studying the behavior of the problem with boundary constraints, the non-linear problem is solved using the PSO method and the optimal trajectory is obtained. The effect of two types of dynamic inertia weight and constant inertia weight in PSO algorithm is examined. The influence of controlling parameters is also investigated.

ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Procedia Computer Science - Volume 54, 2015, Pages 516-522