TY - GEN
T1 - System modeling and control of a heliogyro solar sail
AU - Pimienta-Peñalver, Adonis
AU - Tsai, Liwei
AU - Juang, Jer Nan
AU - Crassidis, John L.
N1 - Publisher Copyright: © 2018 by the American Institute of Aeronautics and Astronautics, Inc.
PY - 2018/1/1
Y1 - 2018/1/1
N2 - A heliogyro solar sail concept has recently been proposed as an alternative to deep space missions without the need for on-board propellant. Although this type of solar sail has existed conceptually for several decades, and some previous studies have investigated certain aspects of its operation, a significant amount of research is still needed to analyze the dynamic and control characteristics of the structure under the projected range of orbital conditions. This research effort provides an improvement upon the existing discrete-mass models of the heliogyro blade, and the extension of its application from a single membrane blade to a fully-coupled approximation of the dynamics of the structure with multiple spinning membrane blades around a central hub. Additionally, this work investigates the implementation of a control algorithm at each blade root to impose structural integrity and attitude control by coordinating well-known helicopter blade pitching profiles.
AB - A heliogyro solar sail concept has recently been proposed as an alternative to deep space missions without the need for on-board propellant. Although this type of solar sail has existed conceptually for several decades, and some previous studies have investigated certain aspects of its operation, a significant amount of research is still needed to analyze the dynamic and control characteristics of the structure under the projected range of orbital conditions. This research effort provides an improvement upon the existing discrete-mass models of the heliogyro blade, and the extension of its application from a single membrane blade to a fully-coupled approximation of the dynamics of the structure with multiple spinning membrane blades around a central hub. Additionally, this work investigates the implementation of a control algorithm at each blade root to impose structural integrity and attitude control by coordinating well-known helicopter blade pitching profiles.
UR - https://www.scopus.com/pages/publications/85141589176
U2 - 10.2514/6.2018-1311
DO - 10.2514/6.2018-1311
M3 - Conference contribution
SN - 9781624105265
T3 - AIAA Guidance, Navigation, and Control Conference, 2018
BT - AIAA Guidance, Navigation, and Control
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Guidance, Navigation, and Control Conference, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -