In-Flight Results from the Drag-Free and Attitude Control of GOCE Satellite

Sechi, G.; Buonocore, M.; Cometto, Ferdinando; Saponara, M.; Tramutola, A.; Vinai, B.; André, Gaël; Fehringer, M.

doi:10.3182/20110828-6-it-1002.02966

Cited by 24 publications

(7 citation statements)

References 6 publications

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“…In GPB [9,10], LISA Pathfinder [11] or in LISA [12] missions, a combination of these two methods is used with a very small electrostatic control of the test-mass as no acceleration measurement is needed. MICROSCOPE uses the second method like the GOCE mission [13], the first mission implementing ONERA's space accelerometers in a drag-free system. It was also chosen because of the possibility to deliver acceleration measurement in a large range of 10 −5 m s −2 .…”

Section: Drag-free and Attitude Control System (Dfacs) Motivations An...mentioning

confidence: 99%

MICROSCOPE satellite and its drag-free and attitude control system

Rodrigues

Robert

Touboul

et al. 2022

Class. Quantum Grav.

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This paper focuses on the description of the design and performance of the MICROSCOPE satellite and its drag-free and attitude control system. The satellite is derived from CNES’ Myriade platform family, albeit with significant upgrades dictated by the unprecedented MICROSCOPE’s mission requirements. The 300 kg drag-free microsatellite has completed its 2 years flight with higher-than-expected performances. Its passive thermal concept allowed for temperature variations smaller than 1 μK at the frequency of the equivalence principle test f EP. The propulsion system provided a six-axis continuous and very low noise thrust from zero to some hundreds of micronewtons. Finally, the performance of its DFACS (aimed at compensating the disturbing forces and torques applied to the satellite) is the finest ever achieved in low Earth orbit, with residual accelerations along the three axes lower than 10−12 m s−2 at f EP over 8 days.

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Section: Drag-free and Attitude Control System (Dfacs) Motivations An...mentioning

confidence: 99%

MICROSCOPE satellite and its drag-free and attitude control system

Rodrigues

Robert

Touboul

et al. 2022

Class. Quantum Grav.

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“…In navigation, TRAID I realized DFC by its disturbance compensation system, which achieved 5 × 10 −11 m s −2 residual acceleration and thus improved the accuracy of ephemeris prediction [4]; in geophysics, the Gravity field and Steady-State Ocean Circulation Explorer (GOCE) employed a low altitude drag-free spacecraft to determine the Earth's gravity field with high accuracy and spatial resolution [5]. Its residual acceleration was better than 2 × 10 −9 m s −2 Hz −1/2 in the measurement bandwidth [6]; in fundamental physics, the Gravity Probe B performed in-orbit tests for geodesic effect with drag-free spacecraft, whose residual acceleration was 10 −10 m s −2 [7]. The LISA Pathfinder (LPF) achieved 1.74 × 10 −15 m s −2 Hz −1/2 acceleration noise above 2 mHz to validate drag-free performance for the Laser Interferometer Space Antenna (LISA) project [8,9].…”

Section: Introductionmentioning

confidence: 99%

Drag-free control design and in-orbit validation of TianQin-1 satellite

Xiao¹,

Bai²,

Li³

et al. 2022

Class. Quantum Grav.

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Drag-free control (DFC) is one of the key technologies for space-borne gravitational wave detectors. For the TianQin project, non-gravitational disturbances on the spacecraft must be suppressed by DFC. TianQin-1 is the first satellite for technology verification, whose main goal is to verify the disturbances reduction technologies. In this paper, the DFC requirement and preliminary analysis for the TianQin project are introduced, and then the design and the experimental validation with the TianQin-1 satellite is presented. In-orbit results show a successful validation of DFC and the residual acceleration of TianQin-1 satellite has been suppressed to 5×10-11 m/s2/Hz1/2 at 10 mHz versus 2×10-9 m/s2/Hz1/2 thruster noise.

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“…It was utilized in two small satellites with a mass in the range of 10 to 100 kg, ie, ORBCOMM, and Ørsted . GOCE of ESA was a nonsmall satellite with a mass over 1 ton that employs magnetic torquers as the sole attitude actuators . In a recent mission by ESA called Proba‐V, a small satellite weighing over 100 kg relies on purely magnetic actuation in the safe mode operation .…”

Section: Introductionmentioning

confidence: 99%

Robust stabilization of spacecraft attitude motion under magnetic control through time‐varying integral sliding mode

Sofyalı

Jafarov

2019

Intl J Robust & Nonlinear

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Magnetic spacecraft attitude control is suitable for missions with moderate pointing and stabilization requirements. It would be especially preferable if an implemented three-axis magnetic control law guarantees global and moreover robust stabilization. Motivated by this consideration, in this work, the integral sliding mode control method is successfully applied to the purely magnetic attitude control problem for the first time in literature. The resulting magnetic integral sliding mode control system, which is designed via Lyapunov's direct method by taking the four major environmental disturbance torques and the full inertia matrix uncertainty into account, has the expected insensitivity against environmental disturbances in the plane of continuous actuation. Along the instantaneous direction of underactuation, which continuously varies in control space as the satellite moves along the orbit, there is no counteraction to perturbations. However, as seen in the results of the high-fidelity simulation, state trajectories are ultimately bounded in the vicinity of the reference state independently from the initial state thanks to the proven robustness of the global stability. Performance robustness of the obtained control system against disturbances and model uncertainty is evaluated to be superior through a couple of comparisons with existing control laws even though it is partial due to the intrinsic underactuation in the system. KEYWORDSintegral sliding mode control, magnetic spacecraft attitude control, time-varying sliding manifold INTRODUCTIONSpacecraft's angular motion around their center of mass, namely, their attitude, is actively controlled by actuator triads, which basically consist of three orthogonally placed devices that produce torque by direct or indirect means. A failure of one of the three reaction wheels or reaction thrusters, which directly exerts control torque on the spacecraft body along the body axis it is aligned with, results in underactuation in the control system. Rigid spacecraft's attitude subject to such an underactuation cannot be asymptotically stabilized at the reference by continuous time-invariant control laws. 1 On the other hand, the case is different with the usage of a magnetic torquer triad. Each of them directly produces a magnetic moment along its axis, and the interaction of the resultant magnetic moment with the local geomagnetic field results in 3446

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In-Flight Results from the Drag-Free and Attitude Control of GOCE Satellite

Cited by 24 publications

References 6 publications

MICROSCOPE satellite and its drag-free and attitude control system

MICROSCOPE satellite and its drag-free and attitude control system

Drag-free control design and in-orbit validation of TianQin-1 satellite

Robust stabilization of spacecraft attitude motion under magnetic control through time‐varying integral sliding mode

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