TY - GEN
T1 - Analysis of ambiguous orbits for elliptic chief relative orbit estimation with range-only measurements
AU - Wang, Jingwei
AU - Butcher, Eric A.
AU - Alan Lovell, T.
N1 - Publisher Copyright:
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2016
Y1 - 2016
N2 - Ambiguous spacecraft relative orbits based on linear dynamics and elliptic chief orbit are studied for the purpose of sequential relative orbit estimation with range-only measurements. Using a geometric solution of the Tschauner-Hempel equation, mirror ambiguous orbits, which conserve the shape and size of the true relative orbit, are proven to exist. However, deformed ambiguous orbits, which distort the shape and size of the true relative orbit are shown to vanish due to the non-zero chief orbit eccentricity although they persist in Kaiman filtering simulations. This persistent phenomenon is explained through a perturbation analysis using variation of the geometric ambiguous states. Furthermore, it is shown that the inclusion of chief orbit eccentricity and nonlinearities in the filter model can help resist the tendency of an extended Kaiman filter to converge to the ambiguous orbits.
AB - Ambiguous spacecraft relative orbits based on linear dynamics and elliptic chief orbit are studied for the purpose of sequential relative orbit estimation with range-only measurements. Using a geometric solution of the Tschauner-Hempel equation, mirror ambiguous orbits, which conserve the shape and size of the true relative orbit, are proven to exist. However, deformed ambiguous orbits, which distort the shape and size of the true relative orbit are shown to vanish due to the non-zero chief orbit eccentricity although they persist in Kaiman filtering simulations. This persistent phenomenon is explained through a perturbation analysis using variation of the geometric ambiguous states. Furthermore, it is shown that the inclusion of chief orbit eccentricity and nonlinearities in the filter model can help resist the tendency of an extended Kaiman filter to converge to the ambiguous orbits.
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U2 - 10.2514/6.2016-5634
DO - 10.2514/6.2016-5634
M3 - Conference contribution
AN - SCOPUS:85089160595
SN - 9781624104459
T3 - AIAA/AAS Astrodynamics Specialist Conference, 2016
BT - AIAA/AAS Astrodynamics Specialist Conference, 2016
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA/AAS Astrodynamics Specialist Conference, 2016
Y2 - 13 September 2016 through 16 September 2016
ER -