Spacecraft Maneuver With Performance Guaranteed

Spacecraft Maneuver with Performance Guaranteed

Facing future-oriented aerospace applications, large-scale space construction and on-orbit services have rapidly developed. In such emerging and increasingly complex spacecraft maneuvering and control tasks, more precise control accuracy and higher performance guarantees need to be fully considered due to the need for safe close rendezvous movements. This book is dedicated to solving the aerospace system’s performance guaranteed and precise control challenges with the expected transient and strict steady-state constraints. It is designed so that the aerospace closed-loop system can theoretically meet the pre-defined or prescribed performance requirements with the simple parameter selection. Furthermore, the expected performance constraints or indicators of the aerospace system time-domain performance response, such as settling time, overshoot, steady-state error, and state amplitude, will be directly guaranteed in the control design. Moreover, this book systematically proposes a series of spacecraft performance guaranteed control algorithms based on the practical situation of the aerospace system. For individual spacecraft, control algorithms that consider practical problems such as control task requirements, settling time constraints, transient performance normalization, input command constraints, and optimization faced by the on-orbit spacecraft are proposed to achieve the precise control objectives of the system under constraints and various complex situations. For the pre-combination and post-combination control of multiple spacecraft, game algorithms based on performance guarantees are proposed and thoroughly discussed. For spacecraft formations, control algorithms that consider full-state constraints, nonlinear uncertainties, output feedback, and collision avoidance are proposed. This book provides the theoretical basis and simulation experience for scholars and engineers to develop high-performance, high-precision spacecraft control algorithms. Furthermore, it hopes that these will contribute to the development of the world’s aerospace technology.

Fundamentals and Aerospace Applications of Prescribed Performance Control

Spacecraft Dynamics and Control

Spacecraft Dynamics and Control: The Embedded Model Control Approach provides a uniform and systematic way of approaching space engineering control problems from the standpoint of model-based control, using state-space equations as the key paradigm for simulation, design and implementation. The book introduces the Embedded Model Control methodology for the design and implementation of attitude and orbit control systems. The logic architecture is organized around the embedded model of the spacecraft and its surrounding environment. The model is compelled to include disturbance dynamics as a repository of the uncertainty that the control law must reject to meet attitude and orbit requirements within the uncertainty class. The source of the real-time uncertainty estimation/prediction is the model error signal, as it encodes the residual discrepancies between spacecraft measurements and model output. The embedded model and the uncertainty estimation feedback (noise estimator in the book) constitute the state predictor feeding the control law. Asymptotic pole placement (exploiting the asymptotes of closed-loop transfer functions) is the way to design and tune feedback loops around the embedded model (state predictor, control law, reference generator). The design versus the uncertainty class is driven by analytic stability and performance inequalities. The method is applied to several attitude and orbit control problems. - The book begins with an extensive introduction to attitude geometry and algebra and ends with the core themes: state-space dynamics and Embedded Model Control - Fundamentals of orbit, attitude and environment dynamics are treated giving emphasis to state-space formulation, disturbance dynamics, state feedback and prediction, closed-loop stability - Sensors and actuators are treated giving emphasis to their dynamics and modelling of measurement errors. Numerical tables are included and their data employed for numerical simulations - Orbit and attitude control problems of the European GOCE mission are the inspiration of numerical exercises and simulations - The suite of the attitude control modes of a GOCE-like mission is designed and simulated around the so-called mission state predictor - Solved and unsolved exercises are included within the text - and not separated at the end of chapters - for better understanding, training and application - Simulated results and their graphical plots are developed through MATLAB/Simulink code