Spacecraft attitude control with simultaneous unloading of the angular momentum of inertial actuators

DOI10.1134/S106423071503017XzbMath1338.93280MaRDI QIDQ295600

N. E. Zubov, V. N. Ryabchenko, E. A. Mikrin, M. Sh. Misrikhanov

Publication date: 13 June 2016

Published in: Journal of Computer and Systems Sciences International (Search for Journal in Brave)

Mathematics Subject Classification ID

Nonlinear systems in control theory (93C10) Application models in control theory (93C95) Variable mass, rockets (70P05) Control/observation systems governed by ordinary differential equations (93C15)

Related Items (5)

Selection of geometric parameters of an reaction wheel system positioning when controlling the angular motion of a spacecraft ⋮ LMI-based criteria of controllability and observability for a descriptor MIMO system ⋮ Output control of the spectrum of a descriptor dynamical system ⋮ Implementation of the orbital orientation mode of an artificial satellite of the Earth without accumulation of the angular momentum of the gyro system ⋮ Stabilization of the solar orientation mode of an artificial satellite of the Earth without accumulation of the angular momentum of the gyro system

Cites Work

• Synthesis of decoupling laws for attitude stabilization of a spacecraft
• Modification of the exact pole placement method and its application for the control of spacecraft motion
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