Survey of Electric Propulsion Capability

Clark, K. E.

doi:10.2514/3.57030

Cited by 17 publications

(2 citation statements)

References 28 publications

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“…In particular,the electron-bombardment ion thruster introducedin 1960 [3,4] remainstoday the most likely choice for primaryand many auxiliary space propulsionneeds [5]. A discussionof the historical developmentand currenttechnologystatus of electron-bombardment ion thrusterscan be found in the literature [5,8].…”

Section: List Of Figuresmentioning

confidence: 99%

Cusped Magnetic Field Mercury Ion Thruster

Seattle

Wilburf

1977

Journal of Spacecraft and Rockets

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Section: List Of Figuresmentioning

confidence: 99%

Cusped Magnetic Field Mercury Ion Thruster

Seattle

Wilburf

1977

Journal of Spacecraft and Rockets

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“…Thus, in recent years, GEO satellite designers have begun to utilize electric propulsion systems in order to reduce the mass fraction of the satellite. While electric propulsion for satellite station keeping is not conceptually new [6], onboard power requirements and resistance in adopting the technology has hindered their implementation hitherto [7].…”

Section: Introductionmentioning

confidence: 99%

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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