Long-distance, drag-free, low-thrust, LEO formation control for Earth gravity monitoring

Canuto, Enrico; Molano-Jimenez, Andres; Montenegro, Carlos Perez; Massotti, Luca

doi:10.1016/j.actaastro.2011.04.018

Cited by 18 publications

(14 citation statements)

References 10 publications

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“…The discrete-time equation of (20), sampled at the orbit period P nom and assuming zero-order interpolation (stepwise) along each orbit period, can be proved to have the form Equation (22), which also applies to HCW equation in Canuto et al, 13 can be referred to as a secular orbit dynamics. The frequency domain is upper bounded by the Nyquist frequency f max ¼ 0:5=P nom .…”

Section: Orbit Perturbation Dynamicsmentioning

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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Section: Orbit Perturbation Dynamicsmentioning

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 orbit tracking error is defined by the coordinate vector r of l r r . Unlike standard Clohessy-Wiltshire-Hill equations [8], r has coordinates in the true orbit LVLH frame L and not in the frame of the reference orbit.…”

Section: Models and Control Problems 21 Spacecraft Dynamicsmentioning

confidence: 99%

“…H F G I and s T is the least time unit of the attitude and orbit control system, which is mainly prescribed by thruster dynamics. The thruster noise, not reported in (8), is part of the overall disturbance D of (4).…”

Section: Models and Control Problems 21 Spacecraft Dynamicsmentioning

confidence: 99%

“…The angular portion of (15) is linear and time-invariant with zero eigenvalues and in a Jordan form. The linear portion of (15) can be approximated to be linear and time invariant and to possess the eigenvalues of the Clohessy-Wiltshire-Hill equations [8].…”

Section: Control Requirements and Control Lawmentioning

confidence: 99%

“…x accounts for the discrete-time thruster dynamics in (8) The spacecraft dynamics equation is very similar to (29) except for the thruster dynamics which is neglected because of the perturbation t s T . In addition, the filtered output Fig.…”

Section: Control Requirements and Control Lawmentioning

confidence: 99%

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Stochastic modelling and prediction for spacecraft drag-free control

Canuto

2016

Stochastic Systems Theory and its Applications (SSS)

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Spacecraft drag-free control is an effective way to make satellite orbit only shaped by gravity and to achieve accurate and quiet alignment of the spacecraft axes to their reference. Essential measurements come from fine accelerometers. Exploiting the experience of the GOCE satellite drag-free and attitude control, the paper provides an integrated modelling and control design procedure which encompasses accelerometer and spacecraft control. Essential to this framework is the stochastic modelling and prediction of the unknown disturbance class to be counteracted. Stochastic modelling of disturbance is the key asset of the Embedded Model Control methodology. Among other advantages it allows robust decoupling of state prediction and control for complex dynamic systems.

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