All-propulsion design of the drag-free and attitude control of the European satellite GOCE

Canuto, Enrico; Massotti, Luca

doi:10.1016/j.actaastro.2008.07.017

Cited by 59 publications

(27 citation statements)

References 14 publications

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“…Simulation results indicate that the thrust needed to continuously counteract the drag force, for the considered mission scenario, is in the throttling range of such kind of thruster, and comparable to that required in similar missions, like GOCE (see, e.g., [7]). A 30 W Xenon resistojet [17] provides out of plane impulsive burns to compensate for the cross-track component of drag, which is due to the co-rotation of the atmosphere with the Earth, and the sun-synchronous resonance effects on the orbit inclination and right ascension of the ascending node.…”

Section: A Orbit and Attitudementioning

confidence: 83%

“…Nevertheless, the EP capability of providing continuous thrust over several thousands of hours, together with the reduced propellant mass consumption, allows for accurate LEO station-keeping operations over sufficiently long duration missions. In this regard, the GOCE mission represents a breakthrough in space technology [6,7]. Some recent studies have been focused on drag free spacecraft operations [8,9].…”

mentioning

confidence: 99%

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Autonomous Low-Earth-Orbit Station-Keeping with Electric Propulsion

Garulli

Giannitrapani

Leomanni³

et al. 2011

Journal of Guidance, Control, and Dynamics

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This paper studies the application of an electric propulsion system for autonomous station-keeping of a remote sensing spacecraft flying at low altitude. The considered propulsion system exploits a Xenon propellant bus, which operates both a low power Hall effect thruster and a resistojet. The former is used for continuous in-track control, while the latter provides the impulsive thrusts necessary for cross-track maneuvers. The adopted navigation solution is based on an extended Kalman filter, employing gyro, star-tracker and GPS measurements. Lyapunov-based and proportionalderivative feedback laws are used for orbit and attitude control, respectively. The performance of the proposed electric propulsion system and guidance, navigation and control solution is evaluated on a low Earth orbit mission.

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Section: A Orbit and Attitudementioning

confidence: 83%

mentioning

confidence: 99%

Autonomous Low-Earth-Orbit Station-Keeping with Electric Propulsion

Garulli

Giannitrapani

Leomanni³

et al. 2011

Journal of Guidance, Control, and Dynamics

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“…This sort of information has been used in the development of models of practical engineering systems such as satellites [5] and ships [16] and for process control [18] for example (where typically the disturbances are assumed to be low frequency in character). Insight from the underlying physics is usually employed to decide on the meaningful frequency range of the disturbance.…”

Section: The Robust Fault Reconstruction Schemementioning

confidence: 99%

“…Consequently all the frequency content of ξ 1 will be below 10rad/s. In some situations where the disturbance ξ 1 represents a physical quantity, engineering judgement and practical experience can be used to define suitable bounds on the frequency content of the disturbances: see for example [5], [16], [18]. Hence the filter matrices that appropriately describe the characteristics of ξ 1 are chosen as A …”

Section: A Design Of Observersmentioning

confidence: 99%

Robust Fault Reconstruction in Uncertain Linear Systems Using Multiple Sliding Mode Observers in Cascade

Tan

Edwards

2010

IEEE Trans. Automat. Contr.

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Abstract-In observer-based fault reconstruction, one of the necessary conditions is that the first Markov parameter from the fault to the output must be full rank. This paper seeks to relax that requirement by using multiple sliding mode observers in cascade. Signals from an observer are used as the output of a fictitious system whose input is the fault. Another observer is then designed and implemented for the fictitious system. This process is repeated until the first Markov parameter of the fictitious system with respect to the fault is full rank. The result is that robust fault reconstruction can be carried out for a wider class of systems compared to other works that also seek to relax the requirement of a full rank first Markov parameter. In addition, this paper has also investigated and presented the necessary and sufficient conditions as easily testable conditions and also the precise number of observers required. A simulation example verifies the effectiveness of the scheme.

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“…Recent developments in miniaturized ion engines make use of RF ioniziation, obviating the need for an internal electron emitter [36]- [38]. Ion engines have been employed in notable mission such as Deep Space-1 [10] , Dawn [39] and GOCE [40] , typically achieve specific impulse between I sp = 2000 − 3000s.…”

Section: ) Electrothermal Accelerationmentioning

confidence: 99%

Space Propulsion Technology for Small Spacecraft

2018

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Abstract-As small satellites become more popular and capable, strategies to provide in-space propulsion increase in importance. Applications range from orbital changes and maintenance, attitude control and desaturation of reaction wheels to drag compensation and de-orbit at spacecraft end-of-life. Space propulsion can be enabled by chemical or electric means, each having different performance and scalability properties. The purpose of this review is to describe the working principles of space propulsion technologies proposed so far for small spacecraft. Given the size, mass, power and operational constraints of small satellites, not all types of propulsion can be used and very few have seen actual implementation in space. Emphasis is given in those strategies that have the potential of miniaturization to be used in all classes of vehicles, down to the popular 1-liter, 1 kg CubeSats and smaller.

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All-propulsion design of the drag-free and attitude control of the European satellite GOCE

Cited by 59 publications

References 14 publications

Autonomous Low-Earth-Orbit Station-Keeping with Electric Propulsion

Autonomous Low-Earth-Orbit Station-Keeping with Electric Propulsion

Robust Fault Reconstruction in Uncertain Linear Systems Using Multiple Sliding Mode Observers in Cascade

Space Propulsion Technology for Small Spacecraft

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