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

Gazzino, Clément; Louembet, Christophe; Arzelier, Denis; Jozefowiez, Nicolas; Losa, Damiana; Pittet, Christelle; Cerri, Luca

doi:10.1016/j.ifacol.2017.08.1264

Cited by 10 publications

(6 citation statements)

References 15 publications

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“…From Equations (34) and (32) its effectiveness. Note that this state transition matrix can then be used in the framework of the linear GEO station keeping control problem, which is expressed as an optimal control problem whose objective is to minimize the fuel consumption while ensuring that the relative dynamic is respected and that the spacecraft does not fly out its station keeping window [48], [49] and [50].…”

Section: B Linearizationmentioning

confidence: 99%

Validated Semi-Analytical Transition Matrix for Linearized Relative Spacecraft Dynamics via Chebyshev Polynomials

Gilz

Bréhard

Gazzino

2018

2018 Space Flight Mechanics Meeting

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During guidance and control procedures of orbiting spacecraft, the respect of positioning and space constraints is decisive for successful missions achievement. The development of algorithms capable of fulfilling these constraints is directly related to how precisely the spacecraft trajectories are known. Since accuracy is essential for these procedures, the prevention and estimation of errors arising from approximations and numerical computations become critical. In this context, we consider solving linear ordinary differential equations via rigorous polynomial approximations in Chebyshev series. These are polynomials together with an error bound accounting for both approximation and rounding errors. Our method allows for the computation of validated approximations of the transition matrices describing the evolution of spacecraft trajectories. The proposed approach is employed in the following applications: first, we consider the linearized impulsive rendezvous framework, demonstrating how to use rigorous polynomials approximations to provide a validated propagation of the relative dynamics between spacecraft; this is then exploited for the hovering phases of the spacecraft rendezvous, where we conceive a validated model predictive control based on semi-definite programs. Finally, we propose a semi-analytical transition matrix for a simplified model of geostationary station keeping, linearizing the spacecraft dynamics which take into account the J2 Earth oblateness effect.

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Section: B Linearizationmentioning

confidence: 99%

Validated Semi-Analytical Transition Matrix for Linearized Relative Spacecraft Dynamics via Chebyshev Polynomials

Gilz

Bréhard

Gazzino

2018

2018 Space Flight Mechanics Meeting

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“…The above scheme of angular momentum unloading by EP mainly has the following problems [6][7][8][9][10][11][12][13][14][15]:…”

Section: Introductionmentioning

confidence: 99%

The Angular Momentum Unloading of the Asymmetric GEO Satellite by Using Electric Propulsion with a Mechanical Arm

Zhu,

Qin,

Zhu

et al. 2024

Aerospace

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A high-precision attitude control satellite uses an angular momentum exchange device such as a flywheel or a control moment gyro as the actuator for attitude stability control. Once the accumulation of angular momentum exceeds the upper limit of the angular momentum exchange device, the satellite will lose its attitude control ability. Therefore, it is necessary to unload the angular momentum exchange device to ensure the attitude control ability of the satellite platform. The angular momentum accumulation of GEO(Geosynchronous Orbit, GEO) satellites with asymmetric structure can reach 40 Nms per day, and the accumulation speed is more than 20 times that of GEO satellites with symmetrical structure. Therefore, it is necessary to carry out angular momentum unloading for GEO satellites with asymmetric structure every day. The previous method of angular momentum unloading using electric propulsion has weak unloading capacity, which is not suitable for angular momentum unloading of asymmetric satellites. This paper presents a method of angular momentum unloading using a four-joint mechanical arm plus an electric thruster. Large angular momentum unloading with near-zero burn-up can be achieved through the thrust generated by station keeping. In addition, the problem of attitude and orbit coupling control can be solved by controlling the thrust direction of the electric thruster with a mechanical arm.

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“…In that sense, the camera line-of-sight with the asteroid surface has to be maintained in order to recognize the landmarks. The guidance logic generates, by integration over the control horizon, a reference where only controlled states are prescribed by design [38]. Then, a continuous optimization problem to track this reference is posed.…”

Section: Introductionmentioning

confidence: 99%

Orbit-Attitude Predictive Control in the Vicinity of Asteroids with In Situ Gravity Estimation

Sanchez¹,

Vázquez²,

Biggs³

et al. 2022

Journal of Guidance, Control, and Dynamics

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This paper presents an integrated model-learning predictive control scheme for spacecraft orbit-attitude station-keeping in the vicinity of asteroids. The orbiting probe relies on optical and laser navigation while attitude measurements are provided by star trackers and gyroscopes. The asteroid gravity field inhomogeneities are assumed to be unkown a priori. The state and gravity model parameters are estimated simultaneously using an unscented Kalman filter. The proposed gravity model identification enables the application of a learning-based predictive control methodology. The predictive control allow for a high degree of accuracy since the

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

Cited by 10 publications

References 15 publications

Validated Semi-Analytical Transition Matrix for Linearized Relative Spacecraft Dynamics via Chebyshev Polynomials

Validated Semi-Analytical Transition Matrix for Linearized Relative Spacecraft Dynamics via Chebyshev Polynomials

The Angular Momentum Unloading of the Asymmetric GEO Satellite by Using Electric Propulsion with a Mechanical Arm

Orbit-Attitude Predictive Control in the Vicinity of Asteroids with In Situ Gravity Estimation

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