This study investigated the adaptive fault-tolerant control (FTC) for a flexible variable structure spacecraft in presence of external disturbance, multiple actuator faults, and saturation. The attitude system model fault are first given. A sliding mode-based detection observer radial basis function-based estimation were designed to detect time occurrence estimate amplitude an unknown fault, re...

The vibration of flexible structures in spacecraft, such as large space deployable reflectors, solar panels and antenna structure, has a great impact on the normal operation spacecraft. Accurate control is necessary, angular displacement difficulty accurate control. In traditional method, mode good effect suppressing low-order modes, but there overflow. traveling wave modes worse than former, i...

Most past investigations of dual-spin spacecraft have assumed that the platform and rotor are symmetric and rigidly connected. Recently, Cretcher and Mingori, Wenglarz, Willems, and Bainum have considered the effects of flexibility in different parts of dual-spin spacecraft. Scher and FarrenkopP have considered the effects of an asymmetric rotor rigidly connected to the platform. However, the e...

Introduction: As spacecraft designs converge toward miniaturization and with the volumetric and mass constraints placed on avionics, programs will continue to advance the “state of the art” in spacecraft systems development with new challenges to reduce power, mass and volume. Although new technologies have improved packaging densities, a total system packaging architecture is required that not...

The main objective of this study is to propose a methodology to build a parametric linear model of Flexible Multibody Systems for control design. This approach uses a combined Finite Element State Space Approach based on component modes synthesis and double-port approach. The proposed scheme offers the advantage of automatic assembly of substructures, preserving the elastic dynamical behavior o...

With the development of space science and technology, on-orbit module replacement technology has been more and more attention. Accordance with the requirements of on-orbit spacecraft module replacement, this paper designs the flexible swap device, and analyses the working principle of the insert-pull process. Using Pro/E, the parametric geometry model is established, whose dynamics simulation a...

Abstract The solar array is a key part of spacecraft, which the main power supply. With trend spacecraft bus development, size panel attached to becomes larger and provide more load power. Large scale, low stiffness, flexibility affect attitude control directly. Monitoring analyzing dynamics behavior will be overall design spacecraft’s system. purpose monitoring verify dynamic modeling health d...