| Abstract: | The problem of using an energy storage device in spacecraft low-thrust propulsion systems with a constant-power thruster is
considered and solved for optimal quasi-circular maneuvers in the near-Earth space. The maximum payload is the optimality
criterion. The optimal control as a function of time and the optimal mass parameters of the spacecraft were determined. Domains
of the mass parameters where the use of an energy storage device makes sense are shown.
T. G. Shevchenko University, Kiev, Ukraine. Translated from Prikladnaya Mekhanika, Vol. 35, No. 10, pp. 93–100, October, 1999. |
