A smooth attitude-stabilizing control law is derived from which known limits on the control authority of the system are rigorously enforced. Unknown disturbance torques, assumed to be of lesser magnitude than the control limits, are included in the formulation. A smooth control signal containing hyperbolic tangent functions that rigorously obeys a known maximum-torque constraint is introduced. The controller can be viewed as a smooth analog of the variable-structure approach, with the degree of sharpness of the control permitted to vary with time according to a set of user-defined parameters. Lyapunov analysis is employed to ensure global stability, and asymptotic convergence of the angular velocity is guaranteed via the Barbalat lemma. Attitude errors, expressed as Euler parameters, are shown via simulation to vanish whenever certain design parameters are selected appropriately, and guidelines for selection of those parameters are provided in depth.

Globally stabilizing saturated attitude control in the presence of bounded unknown disturbances

Appointed-time prescribed performance attitude tracking control via double performance functions

Fixed-time attitude tracking control for rigid spacecraft

This article considers the problem of velocity-free fixed-time attitude tracking control for rigid spacecraft. With the help of the homogeneity theorem, a semiglobal observer is introduced to estimate the unmeasured angular velocities within fixed time. Then, a velocity-free attitude tracking controller is designed to make the spacecraft attitude track a time-varying reference signal in finite time, which can be up bounded by a fixed number regardless of the initial conditions. Finally, numerical examples are provided to illustrate the efficiency of the present control scheme.

Fixed-Time Attitude Tracking Control for Rigid Spacecraft Without Angular Velocity Measurements

Review of advanced guidance and control algorithms for space/aerospace vehicles

Fixed-time attitude tracking control for spacecraft without unwinding

Adaptive prescribed performance tracking control for underactuated autonomous underwater vehicles with input quantization

Finite-time distributed formation control for multiple unmanned surface vehicles with input saturation

Robust Saturated Finite-Time Attitude Control for Spacecraft Using Integral Sliding Mode

This paper investigates the anti-unwinding finite-time attitude synchronization control problem for Spacecraft formation flying with external disturbances. Two finite-time controllers are designed based on rotation matrix and terminal sliding mode method. By designing a novel sliding mode surface, the first controller is developed when the upper bound of the external disturbances can be exactly known. However, this value is not always available in reality. In addition, the direct use of the upper bound of the external disturbances can result in the chattering problem. For the purpose of overcoming the disadvantage of the first controller, a modified control law is proposed, in which the adaptive law is applied to estimate the unknown value online. Theoretical analysis and numerical simulations are presented to demonstrate the validity of the proposed controllers.

Bing Huang

Papers

Fixed-time attitude tracking control for spacecraft without unwinding

Adaptive prescribed performance tracking control for underactuated autonomous underwater vehicles with input quantization

Finite-time distributed formation control for multiple unmanned surface vehicles with input saturation

Robust Saturated Finite-Time Attitude Control for Spacecraft Using Integral Sliding Mode

Rotation matrix based finite-time attitude synchronization control for spacecraft with external disturbances.