Linearization method for optimization of low thrust spacecraft trajectories. Theoretical aspects
The Article deals with theoretical aspects of the modified linearization method (MLM) which allows solving of wide class of nonlinear optimization tasks arising during optimization of low thrust spacecraft trajectories (Ефанов B.B. и dp., 2009; Хартов B.B. и dp., 2010). Main modifications of the linearization method are connected with its refinement aimed at optimization of compound dynamic systems and design parameters of a spacecraft.