The method of design-ballistic optimization developed by authors assumes the solution of a task on a self-optimizing control. The Pontryagin's maximum principle is applied to transition to a boundary-value problem. Runge-Kutta-4 method is used for direct modeling of operated movement. Optimization of parameters is carried out by means of downhill simplex method. Solutions of a boundary-value problem on a self-optimizing control for flight of the minimum duration and the minimum expenses of a propellant are received with the fixed duration. Change of an expense of a gas working fluid on flight Earth Mars is analyzed at various parameters of the spacecraft.
Features of optimization of interplanetary flights with low-thrust engines
2013-06-01
712661 byte
Conference paper
Electronic Resource
English
Low-Thrust Engines for Interplanetary Flights
NTIS | 1974
|Optimization of interplanetary flights with vehicles of low thrust acceleration
Engineering Index Backfile | 1964
|Optimization of interplanetary flights with vehicles of low thrust acceleration
Engineering Index Backfile | 1963
|