IJE TRANSACTIONS C: Aspects Vol. 32, No. 3 (March 2019) 430-437   

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A. Toloei and H. Asgari
( Received: October 07, 2018 – Accepted in Revised Form: January 03, 2019 )

Abstract    In this paper, a quaternion-based finite-time sliding mode attitude controller is designed for a spacecraft performing high-thrust orbital maneuvers, with cold gas thrusters as its actuators. The proposed controller results are compared with those of a quaternion feedback controller developed for the linearized spacecraft dynamics, in terms of settling time, steady-state error, number of thruster firings and their fuel usage. It is then proved that the sliding mode control has enough robustness against disturbances as well as a high accuracy in attitude tracking and also a low number of thruster firings. A 6 degree of freedom (DOF) total simulation, including spacecraft dynamics, guidance, navigation and control systems is also designed and the sliding mode controller performance in a sample transfer from an ecliptic orbit to a circular one is investigated. In order to solve the chattering problem caused mainly because of the discontinuity of sliding mode control algorithm and multiple switching on sliding surfaces, the sign function in the control input is replaced with a hyperbolic tangent function. Being aware of the advantages of sliding mode control method, using this algorithm in orbital transfers seems to be innovative and efficient.


Keywords    Attitude Control; Orbital Maneuver; Spacecraft; Sliding Mode; Quaternion



در این مقاله، سیستم کنترل ردیابی وضعیت زمان محدود بر پایه فیدبک کواترنیون‌های وضعیت برای فضاپیمای صلب در طول مانور مداری تراست بالا با استفاده از تراسترهای گاز سرد به عنوان عملگرهای کنترلی طراحی شده است. مدل دینامیکی غیرخطی فضاپیما معرفی شده و سطح لغزش و نهایتا کنترل مد لغزشی بر پایه این مدل دینامیکی توسعه داده شده است. همچنین نتایج کنترلر طراحی شده با نتایج حاصل از یک کنترلر فیدبک کواترنیون از نظر زمان نشست، خطای حالت ماندگار، تعداد روشن شدن عملگرها و همچنین مصرف سوخت آن‌ها مقایسه شده و برتری متد کنترلی مد لغزشی اثبات شده است. در پایان یک مانور مداری از مدار بیضوی به دایروی با کنترل وضعیت توسط سیستم کنترل معرفی شده انجام شده و نتایج حاصل از آن ارائه و بررسی شده است.


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