Angular drag-free control and fine satellite-to-satellite pointing for the Next Generation Gravity Missions

Canuto, Enrico; Colangelo, Luigi

doi:10.1109/ecc.2014.6862433

Cited by 6 publications

(15 citation statements)

References 10 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…  we (9) Extensive simulations [3,6], have shown the IFC model to be satisfyingly robust to the initial orbit perturbations envelope for the science phase of the NGGM mission. Indeed, given the very low thrust level constraining the NGGM control design (few milli-Newtons), stability and drift issues may affect some formation variable in case of a set of initial conditions non optimal for starting the NGGM mission science phase.…”

Section: Fig 2the Formation Triangle and The Formation Localmentioning

confidence: 97%

“…Let us define the state vector as: completing the state predictor, by adding to the embedded model a static noise estimator (described by (9)). Finally, the elements of the diagonal matrix 63 L   are scalar gains that can be tuned via pole placement, by fixing the closed-loop eigenvalues.…”

Section: Fig 2the Formation Triangle and The Formation Localmentioning

confidence: 99%

“…On the one hand, the position feedback operates at the orbital frequency and stabilizes the long-term perturbed dynamics of the formation triangle. Such feedback component leverages the state variables recovered by the state predictor (see (8) and (9) in Section 4) starting from the available measurements.…”

Section: Orbit and Formation Controlmentioning

confidence: 99%

“…The formation attitude rationale seeks an independent pointing control of each satellite [9]. Such a control action is made possible by disposing of proper optical sensors able to measure the satellite misalignment from the satellite-to-satellite line.…”

Section: Attitude and Pointing Rationalementioning

confidence: 99%

“…where J is the inertia tensor, Consequently, the control design requires a reliable estimation of FLOF quaternion, angular rate and acceleration [9]. According to the EMC methodology, the attitude control unit is based on a discrete-time version of (12) and (13).…”

Section: Attitude and Pointing Rationalementioning

confidence: 99%

See 4 more Smart Citations

Embedded model control GNC for the Next Generation Gravity Mission

et al. 2017

Self Cite

View full text Add to dashboard Cite

A Next Generation Gravity Mission (NGGM) concept for measuring the Earth's variable gravity field has been recently proposed by ESA. The mission objective consists in measuring the temporal variations of the Earth gravity field over a long time span, with very high spatial and temporal resolutions. This paper focuses on the guidance, navigation and control (GNC) design for the science phase of NGGM mission. NGGM will consist of a two-satellite long-distance formation like GRACE, where each satellite will be controlled to be drag-free like GOCE. Satellite-to-satellite distance variations, encoding gravity anomalies, will be measured by laser interferometry. The formation satellites, distant up to 200 km, will fly in a quasi-polar orbits at an Earth altitude between 300 and 450 km. Orbit and formation control counteract bias and drift of the residual drag-free accelerations, in order to reach orbit/formation long-term stability. Drag-free control allows the formation to fly counteracting the atmospheric drag, ideally subject only to gravity. Orbit and formation control, designed through the innovative Integrated Formation Control (IFC), have been integrated into a unique control system, aiming at stabilizing the formation triangle consisting of satellites and Earth Center of Masses. In addition, both spacecraft must align their control axis to the satellite-to-satellite line (SSL) with micro-radiant accuracy. This is made possible by specific optical sensors and the inter-satellite laser interferometer, capable of materializing the SSL. Such sensors allow each satellite to pursue an autonomous alignment after a suitable acquisition procedure. Pointing control is severely constrained by the angular drag-free control which must ideally zero the angular acceleration vector, in the science frequency band. The control unit has been designed according to the Embedded Model Control methodology and is organized in a hierarchical way, where drag-free control plays the role of a wide-band inner loop, and orbit/formation and attitude/pointing controls are narrow band outer loops. The relevant state equations are converted to discrete time providing the embedded model, part of the control unit. The state predictor, control law and reference generator are built on and interfaced to the embedded model. Simulated results, via a high-fidelity simulator, prove the concept validity and show that the control performances are in agreement with the defined mission requirements. Indeed, the presented control strategy has been shown capable of keeping the attitude and formation variables stable within the required boundaries, all over the 10-year mission, through a low-thrust authority in the order of few milli-Newton.

show abstract

Section: Fig 2the Formation Triangle and The Formation Localmentioning

confidence: 97%

Section: Fig 2the Formation Triangle and The Formation Localmentioning

confidence: 99%

Section: Orbit and Formation Controlmentioning

confidence: 99%

Section: Attitude and Pointing Rationalementioning

confidence: 99%

Section: Attitude and Pointing Rationalementioning

confidence: 99%

See 3 more Smart Citations

Embedded model control GNC for the Next Generation Gravity Mission

et al. 2017

Self Cite

View full text Add to dashboard Cite

show abstract

A review on DFACS (I): System design and dynamics modeling

JIAO,

LIU,

DANG

et al. 2024

Chinese Journal of Aeronautics

View full text Add to dashboard Cite

Satellite-to-satellite attitude control of a long-distance spacecraft formation for the Next Generation Gravity Mission

Canuto

Colangelo

Lotufo

et al. 2015

European Journal of Control

Self Cite

View full text Add to dashboard Cite

The paper presents the design and some simulated results of the attitude control of a satellite formation under study by the European Space Agency for the Next Generation Gravity Mission. The formation consists of two spacecraft which fly more than 200 km apart at an altitude from the Earth's ground of between 300 and 400 km. The attitude control must keep the optical axes of the two spacecraft aligned with a microradian accuracy (pointing control). This is made possible by specific optical sensors accompanying the inter-satellite laser interferometer, which is the main payload of the mission. These sensors allow each spacecraft to actuate autonomous alignment after a suitable acquisition procedure. Pointing control is constrained by the angular drag-free control, which is imposed by mission science (Earth gravimetry at a low Earth orbit), and must zero the angular acceleration vector below 0.

show abstract

Angular drag-free control and fine satellite-to-satellite pointing for the Next Generation Gravity Missions

Cited by 6 publications

References 10 publications

Embedded model control GNC for the Next Generation Gravity Mission

Embedded model control GNC for the Next Generation Gravity Mission

A review on DFACS (I): System design and dynamics modeling

Satellite-to-satellite attitude control of a long-distance spacecraft formation for the Next Generation Gravity Mission

Contact Info

Product

Resources

About