The momentum management controller is used for large spacecrafts with orbit maintenance of long life which only have small difference in three-axis main inertia. It should be guaranteed that one inertia axis of spacecraft is strictly perpendicular to the orbital plane. Then, an inertial reference coordinate system for momentum management is established. It is observed that the drift of long-period orbit factors has an approximate linear relation to time, which leads to a linear increase of output offset of the momentum control. Therefore, the failed reasons in the design of the optimal control law are analyzed, and the state equation is augmented with internal model principle to compensate the perturbation, then the optimal quadratic regulators with pole placement method is used to design the controller according to the state space equation. Finally, semi-physical simulation validates the controller. The results show that the design of the compensation method is feasible, and the long term stability of attitude and angular momentum are achieved.

Effect analysis and compensation for orbit perturbation in spacecraft used momentum management

This study investigates the application of gravity gradient and aerodynamic torques in the attitude control and momentum management (ACMM) of the space station. Due to the large inertia and solar panels, environmental torque is significant enough in the ACMM in order to save fuel costs. Towards this end, the gravity gradient and the solar panels' aerodynamic models are established. The weighted-state H∞ controller is designed since the attitude control sub-system is much slower than the momentum management sub-system. Numerical results are shown to demonstrate the practicability of the environmental torque application and the effectiveness of the weighted-state H∞ technique.

Attitude control and momentum management of space station via weighted-state H ∞ method

http://ieeexplore.ieee.org/iel7/6882077/6895198/06896350.pdf

Application of Characteristic Model-Based Controller to momentum management of Space Station

This paper uses inertial momentum management control method for long-term on-orbit working stability of large spacecraft which only has small difference in three-axis main inertia. To avoid the accumulation of gravity gradient torque, it should be guaranteed that one inertia axis of spacecraft is strictly perpendicular to its orbital plane. Then, an inertial reference coordinate system for momentum management is established. It is observed that the drift of ascending node right ascension and along-track angle of orbit caused by orbit perturbation has an approximate linear relation to time. This leads to a linear increase of the momentum and causes divergences of attitude and angular momentum. We render analysis to the problem and augment the long-period orbit factors in state equation on the basis of internal model principle in order to compensate the perturbation. Finally, semi-physical simulations are setup to validate the approach. It shows that the compensation method is feasible and long-term stability of attitude and momentum is achieved.

Effect analysis and compensation for orbit perturbation of spacecraft using momentum management control

For saturation of control moment gyros because of accumulation of constant component of gravitational torque and aero torque,a dynamics model of space station is established and linearized in inertial reference,then the state space equation is augmented by the filter states,and the linear quadratic regulator(LQR) method is used to design the feedback gain matrix for the momentum management controller of space station in inertial reference.In inertial reference the gravitational torque and aero dynamical torque are composed by multiples of frequency of orbit angular velocity,so the augmented filters can be selected according to the actual disturbance frequency to reduce the influence of different disturbing torgues on attitude of space station or momentum of control moment gyros,thus the space station can maintain attitude control without disaturation for long time.Simulation validats the controller.

HE Yingzi

Papers

Momentum Management Control of Space Station Complex in Inertial Reference