TY - GEN
T1 - A Time-Varying Subspace Method for Shape Estimation of a Flexible Spacecraft Membrane
AU - Brownell, Matthew
AU - Sinclair, Andrew
AU - Singla, Puneet
N1 - Publisher Copyright:
© 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2023
Y1 - 2023
N2 - The focus of this work is to develop a reduced-order model to capture the motion of a large, flexible spacecraft from distributed sensor measurements. The spacecraft structure is motivated by a concept for capturing solar energy and accurately directing it to desired locations on the Earth’s surface. A previously developed analytical model is utilized to simulate data of the fullycoupled attitude-orbital-flexible dynamics of a large spacecraft in orbit. Utilizing this simulation in place of an experimental test-bed, local acceleration sensor measurements, distributed across the surface of the spacecraft, are obtained. This data is then used to find a reduced-order model to estimate the shape of the spacecraft in real-time with lower computational complexity. Rather than finding a global model between input and output space, system theory concepts are utilized to find a subspace over which the unknown dynamics evolve. This paper utilizes the Eigensystem Realization Algorithm (ERA) to obtain said reduced-order model. The derived reduced-order model is guaranteed to capture controllable and observable modes of the spacecraft motion. The reduced-order model’s validity is tested by attempting to replicate the analytical model’s output data and dynamic characteristics such as modal frequency and damping. The resultant reduced-order model accurately reproduced the output data and dynamic characteristics of the analytical model. This provides a basis for optimism in identifying flexible-body dynamics from input-output data while in an orbit.
AB - The focus of this work is to develop a reduced-order model to capture the motion of a large, flexible spacecraft from distributed sensor measurements. The spacecraft structure is motivated by a concept for capturing solar energy and accurately directing it to desired locations on the Earth’s surface. A previously developed analytical model is utilized to simulate data of the fullycoupled attitude-orbital-flexible dynamics of a large spacecraft in orbit. Utilizing this simulation in place of an experimental test-bed, local acceleration sensor measurements, distributed across the surface of the spacecraft, are obtained. This data is then used to find a reduced-order model to estimate the shape of the spacecraft in real-time with lower computational complexity. Rather than finding a global model between input and output space, system theory concepts are utilized to find a subspace over which the unknown dynamics evolve. This paper utilizes the Eigensystem Realization Algorithm (ERA) to obtain said reduced-order model. The derived reduced-order model is guaranteed to capture controllable and observable modes of the spacecraft motion. The reduced-order model’s validity is tested by attempting to replicate the analytical model’s output data and dynamic characteristics such as modal frequency and damping. The resultant reduced-order model accurately reproduced the output data and dynamic characteristics of the analytical model. This provides a basis for optimism in identifying flexible-body dynamics from input-output data while in an orbit.
UR - http://www.scopus.com/inward/record.url?scp=85200347497&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85200347497&partnerID=8YFLogxK
U2 - 10.2514/6.2023-2068
DO - 10.2514/6.2023-2068
M3 - Conference contribution
AN - SCOPUS:85200347497
SN - 9781624106996
T3 - AIAA SciTech Forum and Exposition, 2023
BT - AIAA SciTech Forum and Exposition, 2023
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA SciTech Forum and Exposition, 2023
Y2 - 23 January 2023 through 27 January 2023
ER -