Optimal Low Thrust Orbit Transfer from GTO to Geosynchronous Orbit and Stationkeeping using Electric Propulsion system

Gopinath, N. S.

doi:10.2514/6.iac-03-a.7.03

Cited by 11 publications

(3 citation statements)

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“…This reference also describes the advantages (complete control of the three orbit vectors, remaining diagonal pair of thruster for a complete control in case of failure of one thruster) of this specific propulsion system based on HS 702 satellite with a xenon ion propulsion system. It has been widely used as a typical configuration for electric propulsion in the literature [17], [18], [19] and more recently [20]. Nowadays the electric propulsion is a viable alternative to the chemical one, in particular in the case of SK of GEO satellite ( [21]), despite limiting thrust operations constraints (large on board power needs, mission requirements restricting the duration of use of the electric power system, impossibility to perform SK maneuvers at eclipse epochs, minimum elapsed time between two consecutive firing, on-off profile of the thrusters, thrust allocation).…”

Section: Introductionmentioning

confidence: 99%

A three-step decomposition method for solving the minimum-fuel geostationary station keeping of satellites equipped with electric propulsion

et al. 2019

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In this paper, a control scheme is elaborated in order to perform the station keeping of a geostationary satellite equipped with electric propulsion while minimizing the fuel consumption. The use of electric thrusters imposes to take into account some additional non linear and operational constraints that make the overall station keeping optimal control problem difficult to solve directly. That is why the station keeping problem is decomposed in three successive control problems. The first one consists in solving a classical optimal control problem with an indirect method initialized by a direct method without enforcing the thrusters operational constraints. Starting from this non feasible solution for the genuine problem, the thrusters operating constraints are incorporated in the second problem, whose solution produces a feasible but non optimal control profile via two different ways. Finally, the third optimizes the commutation times thanks to a method borrowed to the switched systems theory. Simulation results on a realistic example validate the benefit of this particular control scheme in the reduction of the fuel consumption for the geostationary station keeping problem.

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Section: Introductionmentioning

confidence: 99%

A three-step decomposition method for solving the minimum-fuel geostationary station keeping of satellites equipped with electric propulsion

et al. 2019

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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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“…Spacecraft rendezvous is an enabling technology for present and future space missions. In recent years, electric propulsion has been used and proposed for many space applications including orbit transfers and station keeping (see Anzel [1988Anzel [ , 1998, Gopinath and Srinivasamuthy [2003]), but also for interplanetary and deep space missions (see Rayman et al [1999], Gil-Fernndez et al [2006]). In this paper, we exploit direct methods that can easily handle linear and non linear path constraints on contrary to the Pontryagin's maximum principle methods,.…”

Section: Introductionmentioning

confidence: 99%

Collision avoidance in low thrust rendezvous guidance using flatness and positive B-splines

Louembet

Deaconu

2011

Proceedings of the 2011 American Control Conference

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The arising optimal control problem is solved by means of differential flatness in order to apply algebraic geometry tools. These tools based on B-splines parametrization and positive piecewise polynomial concept provide a certification of constraints satifaction continuously in time contrary to classical collocation techniques. The non convexity derived from the avoidance constraint is overcome by using time-varying convex approximation.

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Optimal Low Thrust Orbit Transfer from GTO to Geosynchronous Orbit and Stationkeeping using Electric Propulsion system

Cited by 11 publications

References 1 publication

A three-step decomposition method for solving the minimum-fuel geostationary station keeping of satellites equipped with electric propulsion

A three-step decomposition method for solving the minimum-fuel geostationary station keeping of satellites equipped with electric propulsion

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

Collision avoidance in low thrust rendezvous guidance using flatness and positive B-splines

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