Journal of Guidance Control and Dynamics · 1989 · 136 citations · 18 references
EngineeringAerospace EngineeringAstrodynamicsFlight DynamicsFlight MechanicsAttitude ControlControl SystemsControl TheoryMotion ControlRoll DynamicsYaw DynamicsAttitude Control SystemsControl Of SpacecraftCoupled Attitude DynamicsGain SchedulingGain Scheduling ControlMomentum ManagementPitch Attitude DynamicsState Feedback Control
The coupled roll/yaw dynamics of the space station exhibit a transmission zero in a multivariable system. The paper proposes a new approach to CMG momentum management and attitude control for the space station. The method uses gravity‑gradient and gyroscopic torques with a state‑feedback controller that requires minimal storage for gain scheduling to achieve torque‑equilibrium attitude. The approach allows constant pitch attitude or pitch‑axis CMG momentum, enables simultaneous control of yaw attitude and roll‑axis CMG momentum (but not roll attitude with yaw‑axis CMG momentum), and reduces attitude and CMG momentum oscillations from cyclic aerodynamic disturbances.
A new approach to control moment gyro (CMG) momentum management and attitude control of the space station is presented. The control algorithm utilizes both the gravity-gradient and gyroscopic torques to seek torque equilibrium attitude in the presence of secular and cyclic disturbances. It is shown that, depending on mission requirements, either pitch attitude or pitch-axis CMG momentum can be held constant. It is also shown that a combination of yaw attitude and roll-axis CMG momentum can be held constant, whereas a combination of roll attitude and yaw-axis CMG momentum cannot. As a result, the overall attitude and CMG momentum oscillations caused by cyclic aerodynamic disturbances are minimized. A state feedback controller with minimal computer storage requirements for gain scheduling is also presented. An inherent physical property of the coupled roll/yaw dynamics is discussed in terms of a transmission zero of a multivariable system.
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