Optimal direct trajectories to the jupiter with nuclear electric propulsion

Аuthors

Konstantinov M. S.^*, Min T. ^**

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: mkonst@bk.ru
**e-mail: minnntheino@gmail.com

Abstract

Subject
The interplanetary trajectory of spacecrafts Article Optimal direct trajectories to the Jupiter with nuclear electric propulsion
Purpose
The analysis of optimal direct trajectories of spacecraft with nuclear electric propulsion during the flight to the Jupiter.
The analysis of the possible types of extremals.Using the transversality conditions to choose the optimal date of start and magnitude of hyperbolic excess velocity from the Earth
Design/methodology/approach
The trajectory optimization problem of spacecraft with nuclear electric propulsion to the Jupiter carried out by using the Pontryagins maximum principle.
Ensuring compliance with transversality conditions in solving the boundary value problem in order to choose the optimal date of start and magnitude of hyperbolic excess velocity from Earth.
Originality/value
The analysis of the possible types of extremals of the optimal direct trajectory to the Jupiter with nuclear electric propulsion
The transversality conditions in solution to the boundary value problem in order to choose the optimal date of start and magnitude of hyperbolic excess velocity from Earth.
Results
There are 8 types of extremals in rendezvous with Jupiter problem. The detail trajectory and mass characteristics of these extremals are presented. The analysis of choosing optimal date of start and magnitude of hyperbolic excess velocity from Earth is presented as well.
Practical implications
Space mission to the Jupiter with nuclear electric propulsion.
Conclusions
The comparative analysis between results of the using optimality conditions with the results of iterated date of start and magnitude of the hyperbolic excess velocity is presented. The coincidence of the results proves the correctness of used transversality conditions.
Analyzed space transportation system based on the heavy launch vehicle «Angara-5», the chemical upper stage KVTK and nuclear electric propulsion system with an input power of 100 kW can deliver a spacecraft with final mass 6246 kg in direct flight to Jupiter.

Keywords:

spacecraft, Jupiter, optimal trajectory, transversality conditions, extremal solutions

References

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