Pointing control system for the Eclipse mission

Brugarolas, Paul; Kia, T.; Li, Diane; Alexander, James W.

doi:10.1117/12.671068

Cited by 3 publications

(2 citation statements)

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“…The requirement can be met with a multi-layer pointing control system. 25 The first layer is comprised of two phases, both employing the spacecraft Attitude Control System (ACS) actuators. The normal phase uses the spacecraft star tracker as the primary control input and is characterized by multi-degree acquisition ranges and 10 arcsec pointing uncertainties..…”

Section: Technical Approach Summarymentioning

confidence: 99%

THESIS: terrestrial and habitable zone infrared spectroscopy spacecraft

Vasisht

Swain

Akeson

et al. 2008

Space Telescopes and Instrumentation 2008: Optical, Infrared, and Millimeter

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THESIS is a concept for a medium class mission designed for spectroscopic characterization of extrasolar planets between 2-14 microns. The concept leverages off the recent first-steps made by Spitzer and Hubble in characterizing the atmospheres of alien gas giants. Under favourable circumstances, THESIS is capable of identifying biogenic molecules in habitable-zone planets, thereby determining conditions on worlds where life might exist. By systematically characterizing many worlds, from rocky planets to gas-giants, THESIS would deliver transformational science of profound interest to astronomers and the general public.

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Section: Technical Approach Summarymentioning

confidence: 99%

THESIS: terrestrial and habitable zone infrared spectroscopy spacecraft

Vasisht

Swain

Akeson

et al. 2008

Space Telescopes and Instrumentation 2008: Optical, Infrared, and Millimeter

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“…To satisfy high performance requirements relating to line-of-sight pointing accuracy of space observatory, remote sensing, laser communications and other high precision spacecrafts, an ultra-quiet spacecraft bus is imperative (Brugarolas et al, 2006;Doyle, 2007;Lee et al, 2011). However, the microvibrations induced by mechanical moving devices onboard spacecrafts, such as flywheels, solar array drive motors and cryo-coolers could undermine the stability of the bus seriously, causing deleterious effects on the pointing performance (Brugarolas et al, 2010;Oh et al, 2013).…”

Section: Introductionmentioning

confidence: 99%

Modeling and analysis of a flywheel microvibration isolation system for spacecrafts

Wei

Luo

et al. 2015

Advances in Space Research

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High‐Precision Three‐Axis Pointing and Control

Bayard

2010

Encyclopedia of Aerospace Engineering

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This chapter discusses spacecraft precision three‐axis attitude control based on reaction wheel actuation and star tracker and gyro sensing. The nonlinear dynamics and kinematics associated with a rigid body with n reaction wheels are presented. A linearized controller using n reaction wheels is designed that stabilizes the three‐axis attitude dynamics, while commanding desired spacecraft attitude, rate, and acceleration. Properties of the attitude controller are discussed including its stability, command tracking, and disturbance rejection properties. Sensor errors and reaction wheel disturbances are discussed as the two main sources of pointing error. Methods are presented to model these errors and to deal with their effects.

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Pointing control system for the Eclipse mission

Cited by 3 publications

References 0 publications

THESIS: terrestrial and habitable zone infrared spectroscopy spacecraft

THESIS: terrestrial and habitable zone infrared spectroscopy spacecraft

Modeling and analysis of a flywheel microvibration isolation system for spacecrafts

High‐Precision Three‐Axis Pointing and Control

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