In this paper, the preferred region of design parameters for quasi-normalized equations of single-axis attitude control of rigid spacecraft using pulse-width pulse-frequency modulator (PWPFM) is presented for rest-to-rest maneuvers. Using the quasi-normalized equations for attitude control reduces the system parameters, that is, the moment of inertia, the filter gain, and the maximum torque of ...

Generally, underwater unmanned vehicle (UUV) have adopted an inertial navigation system (INS), dead reckoning (DR), acoustic navigation and geophysical navigation techniques as the navigation method because GPS does not work in deep underwater environment. Although the tactical inertial sensor has been usually used at UUV for precise control during long operation time because the sensor can pro...

A spin stabilized satellite reorientation maneuver in the inertial space is investigated. Spin axis pointing and nutation damping magnetic attitude control algorithms are utilized. Evolutionary equations for oscillations of a symmetrical near required position derived. The exact solution wobble amplitude obtained averaged motion. angles relative to direction analyzed. Optimal gain found maneuve...

Based on active disturbance rejection control (ADRC) and fuzzy logic control, a control scheme for attitude maneuver control of spacecraft is proposed. In which a maneuver path is planned to reduce overshoot and improve rapidity, and an extended state observer is designed to cope with unknown disturbances and parameter uncertainties. Furthermore, in order to improve dynamic performance of the c...

In this paper, we consider the problem of three-axis robust attitude stabilization of a rigid spacecraft using minimal, three-dimensional kinematic parameters. New nonlinear control laws having a class of relaxed feedback gain structures are proposed, and are shown to provide a robustness with respect to inertia uncertainties of a rigid body. A numerical example is given to illustrate the theor...

We present a novel method for integrating GPS position estimates with position and attitude estimates derived from visual odometry using a scheme similar to a classic loosely-coupled GPS/INS integration. Under such an arrangement, we derive the error dynamics of the system and develop a Kalman Filter for estimating the errors in position and attitude. Using a control-based approach to observabi...

An efficient Kalman filter based algorithm has been proposed for the spacecraft attitude estimation problem using a novel split-field-of-view star camera and three-axis rate gyros. The conventional spacecraft attitude algorithm has been modified for on-orbit estimation of interlock angles between the two fields of view of star camera, gyro axis, and the spacecraft body frame. Real time estimati...

INTRODUCTION The Attitude and Orbit Control System (AOCS) plays an essential role in the flight control of a spacecraft. This system usually contains a minimum of three reaction wheels (often 4-5 wheels are used for optimization and redundancy [1]). By accelerating the appropriate wheels, the system can produce a zero-mean reaction torque about any axis to the spacecraft, which enables the spac...

Multi-axis hydraulic rigs are widely used in industrial testing applications but still represent a challenging area for control system design. The current paper considers the control of a six-degrees-of-freedom multi-axis shaking table driven by six hydraulic actuators. The strategy adopted employs adaptive decentralized position control, i.e. each axis has its own adaptive controller. The sche...