| bibtype |
J -
Journal Article
|
| ARLID |
0383283 |
| utime |
20240111140822.4 |
| mtime |
20121119235959.9 |
| title
(primary) (eng) |
Fault Diagnosis Scheme for Nonlinear Stochastic Systems with Time-Varying Fault: Application to the Rigid Spacecraft Control |
| specification |
| page_count |
8 s. |
| media_type |
Internet |
|
| serial |
| ARLID |
cav_un_epca*0373458 |
| ISSN |
2223-7038 |
| title
|
Cybernetics and Physics |
| volume_id |
1 |
| volume |
3 (2012) |
| page_num |
179-187 |
| publisher |
| name |
Rossiiskaya Akademiya Nauk |
|
|
| keyword |
Attitude control |
| keyword |
adaptive fault estimation |
| keyword |
LMI |
| keyword |
PDF |
| author
(primary) |
| ARLID |
cav_un_auth*0284758 |
| name1 |
Nguyen |
| name2 |
H.Q. |
| country |
CZ |
|
| author
|
| ARLID |
cav_un_auth*0101074 |
| name1 |
Čelikovský |
| name2 |
Sergej |
| full_dept (cz) |
Teorie řízení |
| full_dept |
Department of Control Theory |
| department (cz) |
TŘ |
| department |
TR |
| institution |
UTIA-B |
| full_dept |
Department of Control Theory |
| fullinstit |
Ústav teorie informace a automatizace AV ČR, v. v. i. |
|
| source |
|
| cas_special |
| project |
| project_id |
GAP103/12/1794 |
| agency |
GA ČR |
| country |
CZ |
| ARLID |
cav_un_auth*0283207 |
|
| abstract
(eng) |
This paper studies the problem of the fault estimation for a class of time-varying faults using output probability density function (PDF). In particular, the spacecraft control system is studied. First, the attitude control of the nonlinear model with uncertainties is given. Then, the measured output is viewed as a stochastic process and its PDF is modeled, which leads to a deterministic dynamical model including nonlinearities and uncertainties. A new adaptive fault diagnosis algorithm is proposed to improve the performance of the fault estimation. The proposed algorithm contains both the proportional and the integral term. The proportional term can improve the speed of the fault estimation, while the integral term can eliminate estimation error. Then, based on the linear matrix inequality (LMI) technique, a feasible algorithm is explored to find the designed parameters. Finally, simulation results of the spacecraft are given to show the efficiency of the proposed approach. |
| reportyear |
2013 |
| RIV |
BC |
| num_of_auth |
2 |
| inst_support |
RVO:67985556 |
| permalink |
http://hdl.handle.net/11104/0213271 |
| arlyear |
2012 |
| mrcbU56 |
dokument 255 kB |
| mrcbU63 |
cav_un_epca*0373458 Cybernetics and Physics 2223-7038 Roč. 1 č. 3 2012 179 187 Rossiiskaya Akademiya Nauk |
|