Fuel Optimal Reorientation of Axisymmetric Spacecraft
Fuel Optimal Reorientation of Axisymmetric Spacecraft

Author: M. V. Dixon

Publisher:

Published: 1970

Total Pages: 48

ISBN-13:

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The problem of reorienting axisymmetric spacecraft by using reaction control jets and at the same time minimizing fuel expenditure is analyzed. The reorientations considered are not limited to small angle rotations, and axial cross-coupling is not neglected. However, only rest-to-rest maneuvers are studied and the vehicle is modeled as a rigid body free from disturbance torques. It is assumed that the attitude control thrustors can provide large enough torques for the thrust durations to be negligible compared to the maneuver periods. The Pontryagin Maximum Principle is used to determine the optimality of control profiles involving only two thrustor firings - an initial and a terminating thrust. These maneuvers are found to be optimal for a large class of reorientations and this method appears to have great practical potential, typically offering an average spacecraft fuel saving of 10 to 25 percent over current techniques. (Author).

Fast Satellite Attitude Maneuver and Control
Fast Satellite Attitude Maneuver and Control

Author: Dong Ye

Publisher: Academic Press

Published: 2022-08-02

Total Pages: 280

ISBN-13: 0323954561

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Fast Satellite Attitude Maneuver and Control introduces the concept of agile satellites and corresponding fast maneuver attitude control systems, systematically and comprehensively presenting recent research results of fast maneuver attitude control for agile satellites by using advanced nonlinear control techniques. This reference book focuses on modeling and attitude control, considering different actuator combinations, actuator installation deviation, actuator fault, and flexible appendage coupling effect for agile satellites. The book provides a unified platform for understanding and applicability of agile satellites fast maneuverer and stabilization control for different purposes. It will be an excellent resource for researchers working on spacecraft design, nonlinear control systems, vehicle systems and complex control systems. Unifies existing and emerging concepts concerning nonlinear control theory, fault tolerant, and attitude control for agile satellites Provides a series of the latest results, including, but not limited to, fast maneuverer and stabilization control, hybrid actuator control, nonlinear attitude control, fault tolerant control, and active vibration suppression towards agile satellites Comprehensively captures recent advances of theory, technological aspects and applications of fast maneuverer and stabilization control in agile satellites Addresses research problems in each chapter, along with numerical and simulation results that reflect engineering practice and demonstrate the focus of developed analysis and synthesis approaches Contains comprehensive, up-to-date references, which play an indicative role for further study

Minimum Time Spacecraft Reorientation with Hybrid Heuristic/Gradient Optimization Methods
Minimum Time Spacecraft Reorientation with Hybrid Heuristic/Gradient Optimization Methods

Author: Luke Guyer

Publisher:

Published: 2021

Total Pages:

ISBN-13:

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Spacecraft often need to be reoriented in a time-optimal manner to satisfy mission requirements. By formulating a maneuver as a mathematical optimization problem, reorientation has been studied extensively in the past in search of fast yet sufficiently optimal solutions. Attitude constraints may also be necessary to avoid the damaging of optical sensors by bright celestial bodies. This research considers a hybrid heuristic/gradient optimization algorithm applied to an inverse dynamics formulation of spacecraft reorientation as a fast approach at finding a sufficiently optimal reorientation time in constrained space. Two heuristic algorithms, Particle Swarm Optimization (PSO) and the Continuous Interacting Ant Colony (CIAC) algorithm, were paired with a gradient-based optimizer to make up two different versions of the hybrid solver. For the constrained case in which 500 or more heuristic iterations were used, the algorithm found a feasible solution 90% of the time and a quasi-optimal solution 82% of the time, requiring 1.5 minutes of runtime in MATLAB. The gradient-based optimizer provided a significant improvement to a purely heuristic solution, decreasing a CIAC maneuver time by 40% and a PSO maneuver time by as much as 60%. For the case of unconstrained reorientation, the optimizer exhibited out-of-plane motion and control torques approaching bang-bang structures. The CIAC version of the hybrid algorithm consistently performed faster and found lower average maneuver times than PSO in less heuristic iterations.