The Tobit-Unscented-Kalman-Filter-Based Attitude Estimation Algorithm Using the Star Sensor and Inertial Gyro Combination

For the orbit operation of spacecraft, due to environmental factors, a star sensor installed on the spacecraft must have data censoring, which greatly reduces the attitude determination ability of the traditional combined-attitude-determination algorithm. To address this problem, this paper proposes...

Descripción completa

Detalles Bibliográficos
Autores principales: Wang, Xinmei, Zhang, Hui, Gao, Xiaodong, Zhao, Rujin
Formato: Online Artículo Texto
Lenguaje:English
Publicado: MDPI 2023
Materias:
Article
Acceso en línea:https://www.ncbi.nlm.nih.gov/pmc/articles/PMC10305351/
https://www.ncbi.nlm.nih.gov/pubmed/37374828
http://dx.doi.org/10.3390/mi14061243

Internet

https://www.ncbi.nlm.nih.gov/pmc/articles/PMC10305351/
https://www.ncbi.nlm.nih.gov/pubmed/37374828
http://dx.doi.org/10.3390/mi14061243

Ejemplares similares