NONLINEAR ROTATIONAL MANEUVER AND VIBRATION DAMPING OF NASA SCOLE SYSTEM

被引：4
作者：
AZAM, M
SINGH, SN
IYER, A
KAKAD, YP
机构：
[1] Department of Electrical and Computer Engineering, University of Nevada Las Vegas, Las Vegas
[2] Department of Electrical Engineering, University of North Carolina Charlotte, Charlotte
来源：
ACTA ASTRONAUTICA | 1994年 / 32卷 / 03期
关键词：
D O I：
10.1016/0094-5765(94)90054-X
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
We treat the question of large rotational maneuver and vibration stabilization of NASA Spacecraft Control Laboratory Experiment (SCOLE) system. The mathematical model of SCOLE system includes the dynamical equations for rigid body slew maneuver and three-dimensional vibration of the flexible beam and the reflector with an offset mass. The design approach taken here is to decompose the rigid mode control from vibration stabilization. Feedback input (Shuttle torque)-output (attitude angles) map linearization technique is used for designing attitude control system for large-angle slewing. Linearization of the input-output (i-o) map is accomplished by nonlinear inversion theory. It is shown that attitude control system asymptotically decouples the flexible dynamics and a linear feedback law is easily designed for vibration suppression. For the synthesis of the control law an observer is designed. Simulation results are presented to show that in the closed-loop system large angle maneuvers can be accomplished using only the measured state variables.
引用
收藏
页码：211 / 220
页数：10
相关论文
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