کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
5028784 | 1470641 | 2017 | 7 صفحه PDF | دانلود رایگان |
![عکس صفحه اول مقاله: Optimizing Ballistic Schemes for Transfer to Geostationary Orbits by Electric Propulsion Optimizing Ballistic Schemes for Transfer to Geostationary Orbits by Electric Propulsion](/preview/png/5028784.png)
The problem of the choice of optimal ballistic schemes for a transfer to a geostationary orbit (GEO) with low and high thrust propulsion is considered. A bi-criteria optimization problem is solved by outputting a set of Pareto-optimal solutions. Results of the numerical modeling of combined insertion schemes, their ballistic optimization, and calculations of design parameters for a spacecraft with a combined propulsion unit are given. To insert a satellite into a given orbital plane, semi-major axis and eccentricity deviations are reduced by solving a terminal control problem. An approximately-optimal control and an expression for characteristic velocity expense as a function of initial boundary conditions with insertion of an electric propulsion (EP) powered spacecraft into a given station with the control are obtained.
Journal: Procedia Engineering - Volume 185, 2017, Pages 345-351