On one approach to the optimization of low-thrust station keeping manoeuvres

Sukhanov, A. A.; Prado, A. F. B. A.

doi:10.1016/j.asr.2012.07.028

Cited by 20 publications

(10 citation statements)

References 28 publications

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“…We use the nominal orbit for disturbanceacceleration prediction in (15) due to the nonlinearity of the analytical expressions in (9). Since the nominal orbit is known in advance, a p,k can be predicted.…”

Section: A State Space Modelmentioning

confidence: 99%

“…To date, much of the research on low-thrust SK has been on openloop optimal maneuver design, see, e.g. [8], [9]. However, given the desire to place geostationary satellites in tight longitudinal windows as required for satellite co-location, the corresponding mission autonomy requirements, and the overall density of the GEO belt, developing the capability for fine closed-loop control is attractive.…”

Section: Introductionmentioning

confidence: 98%

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Model Predictive Control for simultaneous station keeping and momentum management of low-thrust satellites

Weiss

Kalabić

Cairano

2015

2015 American Control Conference (ACC)

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We propose a Model Predictive Control (MPC) policy for simultaneous station keeping and momentum management of a low-thrust nadir-pointing satellite in geostationary orbit around the Earth. The satellite is equipped with six electrically powered thrusters and three axisymmetric reaction wheels, which must be coordinated to control the satellite's orbital position and, concurrently, unload the wheels' stored angular momentum. The MPC policy enforces constraints that maintain the satellite in a tight latitude and longitude window and in a tight nadir-pointing attitude configuration, while minimizing the delta-v provided by the thrusters. The MPC policy exploits a prediction model of the environmental disturbance forces in order to significantly reduce the delta-v required for station keeping, and enforces constraints determined by the thruster configuration to select control forces and torques that can be generated by the propulsion system. We present numerical simulations of the control policy in closed-loop with the satellite nonlinear dynamics that validate the performance of the proposed design in terms of thruster usage and constraint enforcement.

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Section: A State Space Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 98%

Model Predictive Control for simultaneous station keeping and momentum management of low-thrust satellites

Weiss

Kalabić

Cairano

2015

2015 American Control Conference (ACC)

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“…The state constraints are handled by mean of the penalization term described by Equation (22) added to the objective function. The new objective function for the step (C) of the decomposition method reads thus: (39) with µ 3 a parameter that balance the objective function between the fuel consumption minimization and the stay in the SK window.…”

Section: Optimization Of the Commutation Times With The Switched Systmentioning

confidence: 99%

“…Several types of techniques for solving the resulting optimal sta-tion keeping control problem exist. When the thrust is considered as impulsive or when simple models are used to describe the disturbing forces, analytical solutions provide control laws, as in [22]. Otherwise, it is necessary to resort to numerical methods, such as direct collocation based methods as described in [23,24,25,26,27,28].…”

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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“…When simplifying assumptions are used, analytical control laws may be obtained, as in Sukhanov and Prado (2012). Otherwise, it is in general necessary to resort to numerical methods, such as direct collocation based methods as described in Hull (1997) and Betts (1998).…”

Section: Introductionmentioning

confidence: 99%

Integer Programming for Optimal Control of Geostationary Station Keeping of Low-Thrust Satellites

et al. 2017

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Abstract:A control scheme is elaborated to perform the station keeping of a geostationary satellite equipped with electric propulsion. The use of electric thrusters imposes to take into account some additional mutually exclusive constraints on the control function that can be reformulated as logical constraints. The resulting fuel optimal station keeping problem is thus not solved with classical methods, either direct or indirect, but is transformed into a linear integer programming problem. The linearised relative velocity of the satellite is computed and some linear constraints on this velocity are added to the original station keeping problem in order to perform the station kepping over one week after another. Simulation results validate the efficiency of the optimal control thrusts obtained by the solution of the overall linear integer programming problem.

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On one approach to the optimization of low-thrust station keeping manoeuvres

Cited by 20 publications

References 28 publications

Model Predictive Control for simultaneous station keeping and momentum management of low-thrust satellites

Model Predictive Control for simultaneous station keeping and momentum management of low-thrust satellites

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

Integer Programming for Optimal Control of Geostationary Station Keeping of Low-Thrust Satellites

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