TY  - CONF
Y1  - 2016///
PB  - Institute of Electrical and Electronics Engineers Inc.
SN  - 9784907764531
A1  - Parman, S.
UR  - https://www.scopus.com/inward/record.uri?eid=2-s2.0-84973662066&doi=10.1109%2fSICEISCS.2016.7470156&partnerID=40&md5=02883953b7e1dc14c94d2630bb58959d
EP  - 6
AV  - none
N2  - The paper investigates structural deflection of flexible satellite during attitude maneuvers. The satellite is consisted of a rigid main body and two flexible solar panels. Elastic motions of the flexible panels are discretized adhering the finite element method. The attitude maneuvers are equipped with feed-forward inputs in constant amplitude. The inputs are utilized to the satellite complying the fuel-efficient input shaper method. Several cases are investigated in the simulation in order to conclude the influence of fuelling duration with respect to the solar panel deflection, especially in the transient response. © 2016 The Society of Instrument and Control Engineers-SICE.
N1  - cited By 2; Conference of 2nd SICE International Symposium on Control Systems, ISCS 2016 ; Conference Date: 7 March 2016 Through 10 March 2016; Conference Code:121644
SP  - 1
ID  - scholars7039
TI  - Study on structural deflection of flexible satellite during attitude maneuver using fuel-efficient input shaper
KW  - Computer control systems; Control systems; Deflection (structures); Flexible structures; Fuels; Satellites; Solar cell arrays; Solar concentrators; Transient analysis
KW  -  Attitude maneuver; Constant amplitude; Elastic motions; Flexible panels; Flexible satellites; Flexible solar panels; Input shapers; Solar panels
KW  -  Finite element method
ER  -