TY - GEN
T1 - Solar radiation pressure model for attitude motion of Hayabusa in return cruising
AU - Mimasu, Yuya
AU - Van Der Ha, Jozef C.
AU - Funase, Ryu
AU - Mori, Osamu
AU - Kawaguchi, Jun'ichiro
AU - Shirakawa, Ken'ichi
PY - 2009
Y1 - 2009
N2 - The Hayabusa spacecraft embarked on its return trajectory to Earth, after its touchdown on the asteroid Itokawa. During the cruise phase Sun-pointing mode, the spin-axis of the Hayabusa performs a coning motion under the solar radiation pressure effects. The effect mainly originates from the diffuse reflection of the solar radiation pressure on the solar array panels. In the simple analysis of this coning motion, however, the diffuse reflection coefficient is inconsistent in comparison to the typical diffusive parameter of the solar array panel. This discrepancy must be clarified by constructing a more accurate model of the solar radiation pressure in order to be able to dissolve the uncertainty during the return phase of the Hayabusa spacecraft. The accurate model should also be able to support the extremely precise navigation during the return phase to the Earth. This paper presents the precise model of the solar radiation pressure of the Hayabusa spacecraft and the estimation method for obtaining the optical parameters of the solar radiation pressure model.
AB - The Hayabusa spacecraft embarked on its return trajectory to Earth, after its touchdown on the asteroid Itokawa. During the cruise phase Sun-pointing mode, the spin-axis of the Hayabusa performs a coning motion under the solar radiation pressure effects. The effect mainly originates from the diffuse reflection of the solar radiation pressure on the solar array panels. In the simple analysis of this coning motion, however, the diffuse reflection coefficient is inconsistent in comparison to the typical diffusive parameter of the solar array panel. This discrepancy must be clarified by constructing a more accurate model of the solar radiation pressure in order to be able to dissolve the uncertainty during the return phase of the Hayabusa spacecraft. The accurate model should also be able to support the extremely precise navigation during the return phase to the Earth. This paper presents the precise model of the solar radiation pressure of the Hayabusa spacecraft and the estimation method for obtaining the optical parameters of the solar radiation pressure model.
UR - http://www.scopus.com/inward/record.url?scp=77953548272&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:77953548272
SN - 9781615679089
T3 - 60th International Astronautical Congress 2009, IAC 2009
SP - 5115
EP - 5124
BT - 60th International Astronautical Congress 2009, IAC 2009
T2 - 60th International Astronautical Congress 2009, IAC 2009
Y2 - 12 October 2009 through 16 October 2009
ER -