Document Details

Document Type : Article In Journal 
Document Title :
Stabilization of Underactuated Spacecraft Dynamics via Singularly Perturbed Feedback Linearization
الموازنة الألية لديناميكا مركبة الفضاء تحت المشغلة بواسطة الخطية المشوشة الشاذة الناتجة عن التغذية الارتجاعية
 
Subject : Mechanical Engineering 
Document Language : English 
Abstract : The concept of control by feedback linearization is extended to underactuated spacecrafts, by singularly perturbing the nonrealizable linear system resulting from the feedback linearizing transformation, and by utilizing the control coefficient pseudoinverse design methodology that has been recently developed. The underactuated Euler’s system of dynamical equations for the spacecraft is partitioned into actuated and unactuated subsystems, and a function of the angular velocities about the unactuated body axes is used to prescribe a desired second-order dynamics for the unactuated subsystem. The evaluation of this dynamics along the trajectories defined by the underactuated Euler’s dynamical equations results in a relation that is pointwise-linear in the control variables, and a condition is derived based on this relation to assess the realizability of the desired unactuated dynamics by checking the rank of the involved control coefficient Jacobian. The control variables are solved by utilizing the Moore-Penrose pseudoinverse of the control coefficient, resulting in a control law that is composed of particular and auxiliary parts. The particular part works to realize the desired linear unactuated dynamics, and the pseudo-control vector in the auxiliary part is chosen to yield a singularly perturbed feedback linearization for the actuated subsystem. The singularity avoidance problem that is related to using the control coefficient pseudoinverse is solved by modifying the pseudoinverse definition in the vicinity of the singularity, and the large control effort reduction problem is solved by deactivating the particular part of the control law whenever the angular velocities about the actuated axes become high. The control law yields a global asymptotic stability of the origin for the closed loop system when the spacecraft is equipped with two independent gas jet actuators. We show that perturbed feedback linearization is not applicable when the degree of actuation is one. 
ISSN : 1319-1047 
Journal Name : Engineering Sciences Journal 
Volume : 16 
Issue Number : 2 
Publishing Year : 1426 AH
2005 AD 
Number Of Pages : 15 
Article Type : Article 
Added Date : Sunday, October 11, 2009 

Researchers

Researcher Name (Arabic)Researcher Name (English)Researcher TypeDr GradeEmail
عبدالرحمن حسن باجودةAbdulrahman H. BajodahResearcher  

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