Zobrazeno 1 - 9
of 9
pro vyhledávání: '"Mohammed Arezki, Si Mohammed"'
Publikováno v:
Journal of Aerospace Technology and Management, Vol 11 (2019)
The moment of inertia parameters plays a critical role in assuring the spacecraft mission throughout its lifetime. However, determination of the moment of inertia is a key challenge in operating satellites. During satellite mission, those parameters
Externí odkaz:
https://doaj.org/article/dcf372cc32294b87accd1ac323788988
Autor:
Halima Boussadia, Mohammed Arezki Si Mohammed, Nabil Boughanmi, Abdelkrim Meche, Abdellatif Bellar
Publikováno v:
Aerospace Systems. 5:223-232
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::14b1ca6384159b4e348184f1d33388d1
https://doi.org/10.1007/s42401-021-00115-9
https://doi.org/10.1007/s42401-021-00115-9
Publikováno v:
In Comptes rendus - Géoscience April 2013 345(4):167-175
Publikováno v:
The Journal of the Astronautical Sciences. 67:1445-1469
This paper investigates a novel adaptive attitude controller design for rigid microsatellite based on feedback linearization approach, in which an accurate attitude pointing is required within a strict power limitation for space environment. The cont
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::c660fcc9fea96a93c6e6d83ed53a01bf
https://doi.org/10.1007/s40295-020-00227-y
https://doi.org/10.1007/s40295-020-00227-y
Autor:
Akram Adnane, Mohammed El-Amine Cheriet, Elhassen Benfriha, Abdellatif Bellar, Mohammed Arezki Si Mohammed, Youssef Kebbati
Publikováno v:
2022 5th International Conference on Advanced Systems and Emergent Technologies (IC_ASET).
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::fd3f3cb53b46cd2e945dff321e8eec02
https://doi.org/10.1109/ic_aset53395.2022.9765945
https://doi.org/10.1109/ic_aset53395.2022.9765945
Publikováno v:
Advances in Space Research. 61:1143-1157
Attitude estimation is a critical component of the Attitude Determination and Control System (ADCS) of any satellite. It is used to convert the sensor observation data to an estimated attitude using filtering algorithms. However, in the presence of s
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::1bfbb9a05a26c31a8b62549c38326a14
https://doi.org/10.1016/j.asr.2017.12.007
https://doi.org/10.1016/j.asr.2017.12.007
Autor:
A. Bellar, Mohammed Arezki Si Mohammed
Publikováno v:
Journal of Aerospace Technology and Management v.11 2019
Journal of Aerospace Technology and Management
Departamento de Ciência e Tecnologia Aeroespacial (DCTA)
instacron:DCTA
Journal of Aerospace Technology and Management, Vol 11, Iss 1, Pp 1619-1619 (2019)
Journal of Aerospace Technology and Management, Volume: 11, Article number: e1619, Published: 28 MAR 2019
Journal of Aerospace Technology and Management
Departamento de Ciência e Tecnologia Aeroespacial (DCTA)
instacron:DCTA
Journal of Aerospace Technology and Management, Vol 11, Iss 1, Pp 1619-1619 (2019)
Journal of Aerospace Technology and Management, Volume: 11, Article number: e1619, Published: 28 MAR 2019
The moment of inertia parameters play a critical role in assuring the spacecraft mission throughout its lifetime. However, determination of the moment of inertia is a key challenge in operating satellites. During satellite mission, those parameters c
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::cae0ac7985ce9862378c13ade7786464
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462019000100314
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462019000100314
Publikováno v:
2018 2nd IEEE Advanced Information Management,Communicates,Electronic and Automation Control Conference (IMCEC).
A147 estimation is one of the important aspects in Attitude Determination and Control System (ADCS) of a satellite. Under normal working conditions, it is possible to achieve sufficiently a good attitude estimation using regular Kalman filtering. How
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::3ede6f51d66d23de531456ee2b83852b
https://doi.org/10.1109/imcec.2018.8469422
https://doi.org/10.1109/imcec.2018.8469422
Publikováno v:
2016 8th International Conference on Modelling, Identification and Control (ICMIC).
The minimum power consumption is one of the criterion that can be used to choose the best tilt and rotation angles of pyramidal reaction wheel arrangement for attitude control system of microsatellite. In this paper, the simulation results show that
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::fe790f2b6aea61b1fcaf5699279147a0
https://doi.org/10.1109/icmic.2016.7804118
https://doi.org/10.1109/icmic.2016.7804118