A new approach to on-board stationkeeping of GEO-satellites

Park, Bong-Kyu; Tahk, Min-Jea; Bang, Hyochoong; Park, Chang-Su; Jin, Jaehyun

doi:10.1016/j.ast.2005.08.004

Cited by 14 publications

(4 citation statements)

References 8 publications

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“…With the increasing number of GEO spacecraft in the same orbital window [14][15][16], the station-keeping control of GEO spacecraft requires more autonomy. However, the station-keeping control technology by ground stations for GEO spacecraft is relatively mature for the present [17], but how to realize autonomous station-keeping control especially when two or more orbital elements need to be controlled is still a problem to be solved. Guelman [18] proposed a novel approach based on the use of a closed loop control law, which threw high demand on the thrusters and consumed more fuel because of frequent control.…”

Section: Introductionmentioning

confidence: 99%

A station-keeping control method for GEO spacecraft based on autonomous control architecture

Yang

2015

Aerospace Science and Technology

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Section: Introductionmentioning

confidence: 99%

A station-keeping control method for GEO spacecraft based on autonomous control architecture

Yang

2015

Aerospace Science and Technology

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“…Yang and Li studied the autonomous station-keeping control method for GEO satellites and developed the corresponding software [25]. Park et al also proposed an autonomous station-keeping system based on the real-time determination [26].…”

Section: Introductionmentioning

confidence: 99%

Geostationary Station-Keeping of Electric-Propulsion Satellite Equipped with Robotic Arms

Xu²,

Zhou

et al. 2022

Aerospace

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We propose two approaches based on feedforward control and model-predictive control, respectively, to solve the station-keeping problem of an electric-propulsion geostationary Earth orbit (GEO) satellite, whose thrusters are mounted on two robotic arms on its anti-nadir face. This novel configuration enables a wider range of thrust direction, making it possible to regard the thrust direction as control variables. To solve this control problem, we present the quick feedforward controller (QFFC) and the fuel-optimal model predictive controller (FOMPC). The QFFC is developed based on the analysis of GEO dynamics and the thruster configuration. The FOMPC applies an optimization algorithm to solve the nonlinear model predictive control (NLMPC) problem with the initial value given by the QFFC. Numerical simulations suggest that both controllers could achieve stable station-keeping over multiple objective elements with fewer thrusters and fewer maneuvers. The QFFC has higher control accuracy and lower computational requirements than the FOMPC, whereas the FOMPC could significantly save fuel consumption. The robustness assessment and other discussions of the controllers are also presented.

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“…They provide coverage to a specific area. GEO satellites are subjected to various non-Keplerian forces and disturbance torques constantly, resulting in a deviation from the satellite's desired orbital position (Bong-Kyu Park et al, 2005). For satellites in GEO, the main perturbations are solar and lunar gravitational attractions that induce drift in orbital inclination, solar radiation pressure that affects orbit eccentricity (Losa, 2007).…”

Section: Introductionmentioning

confidence: 99%

Control Allocation of a GEO Satellite for Station-Keeping and Momentum Management by Using Thrusters and Reaction Wheels

Emri¹,

Cihan²

2021

European Journal of Science and Technology

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This paper presents a control allocation method for simultaneous station-keeping and momentum management maneuvers. The considered satellite model is equipped with internal and external actuators to control the satellite's orbit and attitude and, concurrently, unload the angular momentum stored in the reaction wheels. Our method allocates the external and internal actuators to achieve the control objectives. Internal actuators such as reaction wheels generate torque based on the conservation of the momentum. In this study, two different controllers are utilized to control satellite attitude and reaction wheel speeds. To manage the satellite attitude in three axes, at least three reaction wheels are needed. In this study, four reaction wheels are used to ensure control in case of failure of a reaction wheel. In addition, with six chemical thrusters, east-west and north-south orbit correction maneuvers are performed. For the satellite to serve throughout its service life, fuel optimization of the satellite is required. The proposed control allocation method will enforce constraints that maintain orbital accuracy and the satellite in a nadir pointing attitude configuration while minimizing the use of thrusters, significantly reducing fuel consumption. The method combines the two generally separated objectives of orbital and attitude control through constraints determined by the propulsion system. Numerical simulations are performed to validate the proposed method. The simulations show that using the proposed control allocation method can significantly increase the service life of geostationary satellites.

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A new approach to on-board stationkeeping of GEO-satellites

Cited by 14 publications

References 8 publications

A station-keeping control method for GEO spacecraft based on autonomous control architecture

A station-keeping control method for GEO spacecraft based on autonomous control architecture

Geostationary Station-Keeping of Electric-Propulsion Satellite Equipped with Robotic Arms

Control Allocation of a GEO Satellite for Station-Keeping and Momentum Management by Using Thrusters and Reaction Wheels

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