As is well-known, accurate and reliable attitude stabilization is one of the most important issues and widely studied applications in the advanced spacecraft ACS design. For orbiting spacecraft, dynamics are strongly nonlinear in nature and are also affected by various external disturbances from the environment that influence the mission objectives significantly. In addition, actuator uncertainties induced by misalignment during installation and torque magnitude measurement errors further increase the design complexity and difficulty. In the practical aerospace engineering, the actuator saturation issue which is derived from the physical limitation on the actuator, should be also taken into consideration during the control law design. It may result in severe discrepancies or derivations between the desired control signals and the actual control output produced by the actuators, and the discrepancies or saturation phenomenon may reduce the control system performances and even cause the instability of the whole control system if it could be well handled and solved. All of the above mentioned problems cause considerable difficulties and challenges in the spacecraft ACS design, for meeting high-precision pointing requirements and desired control performance during the aerospace missions. In the last decades, there exist many results about the spacecraft ACS, such as nonlinear feedback control, robust control, adaptive control and so on [1–6]. Generally speaking, most or part of the previous works design by some advanced control techniques can handle external disturbances and uncertainties to a certain degree, but can hardly be applied to the practical engineering application. In view of its simplicity and good performance for practical applications, the PD or PD-like controls have been extensively studied and applied as well [7–9]. But, the actuator saturation problem can’t be considered in the above results. To solve this practical problem, some interesting methods and results were also presented by taken the actuators’ output magnitude constraints into account, such as an inverse tangent-based tracking function and backstepping method based nonlinear control law [10], explicit saturation function based robust attitude controller [11], standard hypertangent function based PD control scheme [12] and so on.


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    Titel :

    Nonlinear Proportional-Derivative Control Incorporating Closed-Loop Control Allocation for Spacecraft


    Beteiligte:
    Hu, Qinglei (Autor:in) / Li, Bo (Autor:in) / Xiao, Bing (Autor:in) / Zhang, Youmin (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2021-03-14


    Format / Umfang :

    27 pages




    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch