Minimum-fuel electric orbit-raising of telecommunication satellites subject to time and radiation damage constraints

Dutta, Atri; Libraro, Paola; Kasdin, N. Jeremy; Choueiri, Edgar Y.; Francken, Philippe

doi:10.1109/acc.2014.6859179

Cited by 5 publications

(4 citation statements)

References 14 publications

(17 reference statements)

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“…Let the power at the end of the k-th revolution is given by P k , where k ≥ 1. The degradation of the solar array is given by the following equation [47][48][49]:…”

Section: Solar Array Degradationmentioning

confidence: 99%

“…The neural network predicts the power degradation over a revolution, and updates the thrust availability for the next revolution. Prior efforts on capturing the radiation dose were an analytical model based on AP-8 data [47] and semi-analytical approach utilizing AP-9 data and the SCREAM software [48]; however, to the best of knowledge of the authors, there has not been any effort on utilizing a neural network based modeling of the solar array degradation. The paper is organized as follows: we first present the mathematical overview of the problem under consideration, then elaborate the two proposed extensions, and finally present numerical simulations to demonstrate our proposed methodology.…”

Section: Introductionmentioning

confidence: 99%

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

2020

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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.

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“…Let the power at the end of the k-th revolution is given by P k , where k ≥ 1. The degradation of the solar array is given by the following equation [47][48][49]:…”

Section: Solar Array Degradationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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

2020

Self Cite

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“…A satellite with a nominal shielding of 4mm of aliminium (Al) subject to additional radiation dose due to trapped electrons may be equivalent to up to 6.7 years of operations at GEO as shown in Figure 2 [4]. Orbit rising duration may be higher depending on the selected launch vehicle and launch strategy [5,6,7,8]. Figure 2 highlights the importance of additional radiation protection.…”

Section: Introductionmentioning

confidence: 99%

Design Tradeoffs in Full Electric, Hybrid and Full Chemical Propulsion Communication Satellite

Oz¹

2019

Sakarya University Journal of Computer and Information Sciences

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Full electric propulsion system becomes popular recently and getting more common in the communication satellite industry. Full electric or hybrid propulsion selection causes results in significant reduction in satellite propellant mass. Conventional full chemical satellite propellant mass is roughly 2/3 of launch mass so this huge reduction in propellant mass changes satellite design and preferences. Depending on satellite size and launch vehicle performance, full electric satellite requires 3-4 times less propellant compared to full chemical satellite and 1-2 times less propellant compared to the hybrid system. Satellite launch mass can be reduced by 40% for full electric propulsion and 15% for hybrid propulsion hence launch cost can be decreased by 40% and 15 % with the benefit of reducing propellant mass. It is possible to extend satellite communication capacity average 30 transponders for full electric and average 10 transponders for a hybrid system by using the benefit of propellant mass reduction. It takes 4-8 months to reach geostationary orbit for full electric satellite but in a chemical propulsion satellite, it takes a few days. Satellite subjects to additional radiation due to this long trip and hence additional aging. Expected revenue loss is another issue and conventional insurance policy needs an amendment to be in line with electric propulsion technology. The development of full electric satellite lowers the cost per transponder significantly.

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“…To resolve this problem, it is necessary to optimize satellite orbit and attitude control, into which substantial research has already been conducted [4][5][6], [9][10][11][12][13][14].…”

Section: Introductionmentioning

confidence: 99%

A Concept Study of the All-Electric Satellite’s Attitude and Orbit Control System in Orbit Raising

Sasaki¹

2017

JOACE

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All-electric satellite systems and electric propulsion are becoming increasingly well-known technologies, because they help in reducing the propellant weight by a significant amount and enable the mounting of an increased mission payload. Unfortunately, the systems suffer from a much longer Geostationary transfer orbit (GTO) to Geostationary equatorial orbit (GEO) transfer time. This means there is more delay inimp service-in times. Since the transfer orbit is in the Van Allen radiation belt, it is advisable to shorten the transfer time. To resolve this problem, significant progress has already been made to optimize the orbit and attitude control. These solutions require complex orbits and attitude control; relatively little research has studied the attitude control method. In this paper, the concept of a simple attitude control method that achieves orbit-raising time optimization and has little design effect on the subsystem, except for on the electric propulsion subsystem, is reported. 

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Minimum-fuel electric orbit-raising of telecommunication satellites subject to time and radiation damage constraints

Cited by 5 publications

References 14 publications

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

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

Design Tradeoffs in Full Electric, Hybrid and Full Chemical Propulsion Communication Satellite

A Concept Study of the All-Electric Satellite’s Attitude and Orbit Control System in Orbit Raising

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