Dynamics of Earth Orbiting Formations

Ploen, Scott R.; Scharf, Daniel P.; Hadaegh, Fred Y.; Açıkmeşe, A. Behçet

doi:10.2514/6.2004-5134

Cited by 15 publications

(9 citation statements)

References 11 publications

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“…The spacecraft models presented in this section are similar to the ones derived in (Ploen et al, 2004). All coordinates, both for the leader and the follower spacecraft, are expressed in an orbital frame, which origin relative to the center of Earth is given by r o , and satisfies Newton's gravitational laẅ Note that this assumption is naturally satisfied when the reference frame is following a Keplerian orbit, but it also holds for any sufficiently smooth reference trajectory.…”

Section: Spacecraft Modelsmentioning

confidence: 90%

Robustness of Iss Systems to Inputs With Limited Moving Average, With Application to Spacecraft Formations

Grøtli¹,

Chaillet

Panteley

et al. 2010

Proceedings of the 7th International Conference on Informatics in Control, Automation and Robotics

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Abstract:We provide a theoretical framework that fits realistic challenges related to spacecraft formation with disturbances. We show that the input-to-state stability of such systems guarantees some robustness with respect to a class of signals with bounded average-energy, which encompasses the typical disturbances acting on spacecraft formations. Solutions are shown to converge to the desired formation, up to an offset which is somewhat proportional to the considered moving average of disturbances. The approach provides a tighter evaluation of the disturbances' influence, which allows for the use of more parsimonious control gains.

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Section: Spacecraft Modelsmentioning

confidence: 90%

Robustness of Iss Systems to Inputs With Limited Moving Average, With Application to Spacecraft Formations

Grøtli¹,

Chaillet

Panteley

et al. 2010

Proceedings of the 7th International Conference on Informatics in Control, Automation and Robotics

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“…Under such assumptions, that may be referred to as 'ideal' or 'model-based', the altitude control must asymptotically stabilize the radial dynamics, 'exactly' cancel the disturbance d x in equation (22), and track the reference perturbation r ref given by equation (40). To this end, the 'ideal' control law writes as…”

Section: Orbit Altitude Controlmentioning

confidence: 99%

Orbit and formation control for low-earth-orbit gravimetry drag-free satellites

Canuto

Colangelo

Buonocore

et al. 2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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The paper outlines orbit and formation control of a long-distance (>100 km) two-satellite formation for the monitoring of the Earth gravity. Orbit control applies to a single satellite and performs altitude control. Here, formation control is formulated as a control capable of altitude and distance control at the same time. The satellites being placed in a low Earth orbit, orbit, and formation control employ the measurements of a global navigation system. Formation control is imposed by long-distance laser interferometry, which is the key instrument for gravity measurement. Orbit and formation control are low-frequency control systems in charge of canceling bias and drift of the residual drag-free accelerations. Drag-free control is the core of the orbit/formation control since it allows the formation to fly drag-free only subject to gravity. Drag-free control being required to have a bandwidth close to 1 Hz, is designed as the inner loop of the formation control. In turn, formation control must not destroy drag-free performance, in which objective demands that formation control be effective only below the 0.2 mHz orbital frequency. Control design is based on a new orbit and formation dynamics, which are compared with the classical Hill-Clohessy-Wiltshire equations. The new dynamic equations are the first step in building the embedded model, which is the core of the control unit. Embedded model derivation is explained only for the orbit control, and briefly mentioned for the formation control. Simulated results are provided. Drag-free results are compared with GOCE experimental data.

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“…The spacecraft model that we use is similar to the one derived in , with some small modifications to the representation; see for details. Similar models have been used in , and .…”

Section: Application To Spacecraft Formation Controlmentioning

confidence: 99%

Robustness of ISS systems to inputs with limited moving average: Application to spacecraft formations

Grøtli

Panteley

Chaillet

et al. 2015

Intl J Robust & Nonlinear

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Summary We provide a theoretical framework that fits realistic challenges related to spacecraft formation with disturbances. We show that the input‐to‐state stability of such systems guarantees some robustness with respect to a class of signals with bounded average‐energy, which encompasses the typical disturbances acting on spacecraft formations. Solutions are shown to converge to the desired formation, up to an offset, which is somewhat proportional to the considered moving average of disturbances. In the presence of fast peaking perturbations, the approach provides a tighter evaluation of the disturbances' influence, which allows for the use of more parsimonious control gains. Copyright © 2015 John Wiley & Sons, Ltd.

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Dynamics of Earth Orbiting Formations

Cited by 15 publications

References 11 publications

Robustness of Iss Systems to Inputs With Limited Moving Average, With Application to Spacecraft Formations

Robustness of Iss Systems to Inputs With Limited Moving Average, With Application to Spacecraft Formations

Orbit and formation control for low-earth-orbit gravimetry drag-free satellites

Robustness of ISS systems to inputs with limited moving average: Application to spacecraft formations

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