Construction and investigation of ballistic diagrams of flight of a manned space vehicle to mars

This work is devoted to the problems of ballistic substantiation of the concept of a manned expedition to Mars adopted at present which should answer the following questions: how can this project be realized in the framework of the imposed requirements and constraints from the point of view of space ballistics and technical capabilities of propulsion systems, and what is the cost of this flight from the point of view of energy and time consumption criterions. The ballistic design constructions carried out were based on initial data reflecting the latest results of corresponding engineering, technological, and scientific studies and were aimed at the search of most optimal ballistic diagrams capable of providing realization of this expedition under the given conditions. Versions of ballistic diagrams with application of “strong propulsion” systems operating on chemical fuel and “weak propulsion” electric propulsions engines were considered. The construction of ballistic diagrams and the choice of optimal trajectories for different sections of the flight of the manned interplanetary space vehicle were carried out using methodical and program-algorithmic tools developed at TsNIIMASH Mission Control Center (MCC). The obtained results of ballistic design and analysis of the flight diagrams of the manned interplanetary space vehicle (MISV) presented in this paper can serve as initial data for further activity concerning the project of the expedition to Mars in different directions, including space object control problems and realization of its flight as a whole.