Sequential Low-Thrust Orbit-Raising of All-Electric Satellites

Pardhasai Chadalavada,Tanzimul Farabi,Atri Dutta

doi:10.3390/aerospace7060074

Pardhasai Chadalavada, Tanzimul Farabi + Show 1 more

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https://doi.org/10.3390/aerospace7060074

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Journal: Aerospace	Publication Date: Jun 4, 2020
Citations: 6	License type: CC BY 4.0

Affiliation: Wichita State University

Abstract

In this paper, we consider a recently developed formulation of the electric orbit-raising problem that utilizes a novel dynamic model and a sequence of optimal control sub-problems to yield fast and robust computations of low-thrust trajectories. This paper proposes two enhancements of the computational framework. First, we use thruster efficiency in order to determine the trajectory segments over which the spacecraft coasts. Second, we propose the use of a neural network to compute the solar array degradation in the Van Allen radiation belts. The neural network is trained on AP-9 data and SPENVIS in order to compute the associated power loss. The proposed methodology is demonstrated by considering transfers from different geosynchronous transfer orbits. Numerical simulations analyzing the effect of thruster efficiency and average power degradation indicate the suitability of starting the maneuver from super-geosynchronous transfer orbits in order to limit fuel expenditure and radiation damage. Furthermore, numerical simulations demonstrate that proposed enhancements are achieved with only marginal increase in computational runtime, thereby still facilitating rapid exploration of all-electric mission scenarios.

Highlights

In recent years, enhancements to solar-electric propulsion technology [1,2,3] have seen their greater usage in Earth-orbiting satellites [1,4,5], for both station-keeping as well as orbital transfer purposes [5].These applications have largely been for relatively larger satellites, and a variety of electric propulsion technologies are currently being miniaturized for future incorporation in nano-satellites as well [6,7].The primary focus of this paper is the electric orbit-raising maneuver during the deployment of satellites operating in the geosynchronous equatorial orbit (GEO)
We consider geocentric electric orbit-raising problem, modeled as a sequence of orbit-raising sub-problems, with the goal of the minimizing the deviation from the geosynchronous equatorial orbit in each revolution
This paper extended the mathematical formulation in two different ways: allowance for coasting beyond the shadow of the Earth and provision of computation of power loss of the solar arrays and thereby the available thrust for the remaining part of the transfer

Summary

Introduction

Enhancements to solar-electric propulsion technology [1,2,3] have seen their greater usage in Earth-orbiting satellites [1,4,5], for both station-keeping as well as orbital transfer purposes [5].These applications have largely been for relatively larger satellites, and a variety of electric propulsion technologies are currently being miniaturized for future incorporation in nano-satellites as well [6,7].The primary focus of this paper is the electric orbit-raising maneuver during the deployment of satellites operating in the geosynchronous equatorial orbit (GEO). Enhancements to solar-electric propulsion technology [1,2,3] have seen their greater usage in Earth-orbiting satellites [1,4,5], for both station-keeping as well as orbital transfer purposes [5]. These applications have largely been for relatively larger satellites, and a variety of electric propulsion technologies are currently being miniaturized for future incorporation in nano-satellites as well [6,7]. We are interested in tools that facilitate fast and robust analysis of numerous electric orbit-raising scenarios to help identify best technology selections for the satellite bus

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