Autonomous orbit determination and observability analysis for formation satellites

Ouyang, Wei; Zhang, Hongbo; Xing, Jian-jun

doi:10.1109/chicc.2016.7554179

Cited by 5 publications

(2 citation statements)

References 10 publications

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“…The Keplerian elements are defined as the semi-major axis a , eccentricity e , inclination i , right ascension of ascending node Ω, argument of perigee ω, and mean argument of latitude u . In Equation (1), five description parameters are used to determine the relative motion in the LVLH frame (Zeng et al, 2012; Hu et al, 2013; Ou et al, 2016). Based on the orbit elements of the chief, the relative orbit elements are obtained with these parameters.…”

Section: Formation Configuration Designmentioning

confidence: 99%

Observability-based Mars Autonomous Navigation Using Formation Flying Spacecraft

Ouyang

Hongbo

2017

J. Navigation

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This paper concentrates on designing an autonomous navigation scheme for Mars exploration. In this scheme, formation flying spacecraft are used to realise absolute orbit determination when orbiting around Mars. Inertial Line-Of-Sight (LOS) vectors from “deputy” spacecraft to the “chief” are measured using radio cross-link, optical devices and attitude sensors. Since the system's observability is closely related to the navigation performance, an analytical approach is proposed to optimise the observability. In this method, the gravity gradient tensor difference is chosen as the performance index to optimise two navigation scenarios. When there is one deputy flying around the chief, optimal parameters are obtained by solving the constrained optimisation problem. When a second deputy is added into the formation, the optimal configuration is also obtained. These results reveal that the observability is mainly determined by the magnitude of the in-track and cross-track distances in the configuration. An Extended Kalman Filter (EKF) is used to estimate the position and velocity of the chief. The results of a navigation simulation confirms that adding more deputies can significantly improve the navigational performance.

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Section: Formation Configuration Designmentioning

confidence: 99%

Observability-based Mars Autonomous Navigation Using Formation Flying Spacecraft

Ouyang

Hongbo

2017

J. Navigation

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“…Spacecraft cooperation, taking the advantage of inter-satellite measurements, has been widely used to aid navigation performance [1][2][3][4] . Usually, cooperative navigation relies on a main satellite which processes all measurements collected by other spacecraft and estimates the states of all spacecraft [5][6][7] . This centralized system introduces notable challenges, such as the single-point failure of that one spacecraft on constellation navigation, coupled with an increasing computation burden as the amount of satellites increases.…”

Section: Introductionmentioning

confidence: 99%

Fully Decentralized Cooperative Navigation for Spacecraft Constellations

Qin

Macdonald

Dong

2021

IEEE Trans. Aerosp. Electron. Syst.

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This paper proposes a method to decentralize the navigation burden, and improve the fault tolerance for a spacecraft constellation. The constellation body reference system is introduced, which is the perifocal frame of one satellite in the constellation. The structure of the proposed navigation method is constructed to enable each spacecraft to estimate its own orbit in this body reference system. This step is essentially the relative orbit determination based on inter-satellite range measurements. Thereafter, the approach to transfer an orbit from the constellation body reference system to inertial reference system is developed. The essential requirements on absolute

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Absolute orbit determination using line-of-sight vector measurements between formation flying spacecraft

Ouyang

2018

Astrophys Space Sci

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Autonomous orbit determination and observability analysis for formation satellites

Cited by 5 publications

References 10 publications

Observability-based Mars Autonomous Navigation Using Formation Flying Spacecraft

Observability-based Mars Autonomous Navigation Using Formation Flying Spacecraft

Fully Decentralized Cooperative Navigation for Spacecraft Constellations

Absolute orbit determination using line-of-sight vector measurements between formation flying spacecraft

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