TY - JOUR
T1 - A simple orbit-attitude coupled modelling method for large solar power satellites
AU - Li, Qingjun
AU - Wang, Bo
AU - Deng, Zichen
AU - Ouyang, Huajiang
AU - Wei, Yi
N1 - Publisher Copyright:
© 2018 IAA
PY - 2018/4
Y1 - 2018/4
N2 - A simple modelling method is proposed to study the orbit-attitude coupled dynamics of large solar power satellites based on natural coordinate formulation. The generalized coordinates are composed of Cartesian coordinates of two points and Cartesian components of two unitary vectors instead of Euler angles and angular velocities, which is the reason for its simplicity. Firstly, in order to develop natural coordinate formulation to take gravitational force and gravity gradient torque of a rigid body into account, Taylor series expansion is adopted to approximate the gravitational potential energy. The equations of motion are constructed through constrained Hamilton's equations. Then, an energy- and constraint-conserving algorithm is presented to solve the differential-algebraic equations. Finally, the proposed method is applied to simulate the orbit-attitude coupled dynamics and control of a large solar power satellite considering gravity gradient torque and solar radiation pressure. This method is also applicable to dynamic modelling of other rigid multibody aerospace systems.
AB - A simple modelling method is proposed to study the orbit-attitude coupled dynamics of large solar power satellites based on natural coordinate formulation. The generalized coordinates are composed of Cartesian coordinates of two points and Cartesian components of two unitary vectors instead of Euler angles and angular velocities, which is the reason for its simplicity. Firstly, in order to develop natural coordinate formulation to take gravitational force and gravity gradient torque of a rigid body into account, Taylor series expansion is adopted to approximate the gravitational potential energy. The equations of motion are constructed through constrained Hamilton's equations. Then, an energy- and constraint-conserving algorithm is presented to solve the differential-algebraic equations. Finally, the proposed method is applied to simulate the orbit-attitude coupled dynamics and control of a large solar power satellite considering gravity gradient torque and solar radiation pressure. This method is also applicable to dynamic modelling of other rigid multibody aerospace systems.
KW - Differential-algebraic equations
KW - Gravity gradient torque
KW - Natural coordinate formulation
KW - Solar power satellite
KW - Solar radiation pressure
UR - http://www.scopus.com/inward/record.url?scp=85041393820&partnerID=8YFLogxK
U2 - 10.1016/j.actaastro.2017.12.037
DO - 10.1016/j.actaastro.2017.12.037
M3 - 文章
AN - SCOPUS:85041393820
SN - 0094-5765
VL - 145
SP - 83
EP - 92
JO - Acta Astronautica
JF - Acta Astronautica
ER -