A novel autonomous orbit determination system using Earth sensors (scanner)

Nagarajan, N.; Bhat, M. Seetharama; Kasturirangan, K.

doi:10.1016/0094-5765(91)90063-b

Cited by 10 publications

(5 citation statements)

References 4 publications

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“…To this end, one of the foremost suggestions is to exploit the attitude sensors for orbit determination. Nagarajan et al [2] are among those who pioneered this method. They used a pair of conical Earth scanners, enhancing the orbit determination accuracy with least square method.…”

Section: Introductionmentioning

confidence: 98%

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Integrated magnetometer–horizon sensor low-earth orbit determination using UKF

Farahanifar

Assadian

2015

Acta Astronautica

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Section: Introductionmentioning

confidence: 98%

“…The GPS-based orbit determination is highly accurate and applicable for the majority of modern satellites [2,3]. However, it is not an autonomous orbit determination because the satellite receives the GPS signal from outside.…”

Section: Introductionmentioning

confidence: 99%

Integrated magnetometer–horizon sensor low-earth orbit determination using UKF

Farahanifar

Assadian

2015

Acta Astronautica

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“…Furthermore, the nadir vector can be used to estimate the satellite orbit as well. For Earth orbiting satellites, horizon detectors have been used for orbit determination purpose assuming spherical [20,21,22,23,24] and non-spherical Earth models [25]. Moreover, horizon sensors can be employed for finding the solar direction as discussed in [26].…”

Section: Introductionmentioning

confidence: 99%

Orbit estimation using a horizon detector in the presence of uncertain celestial body rotation and geometry

2018

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This paper presents an orbit estimation using non-simultaneous horizon detector measurements in the presence of uncertainties in the celestial body rotational velocity and its geometrical characteristics. The celestial body is modelled as a tri-axial ellipsoid with a three-dimensional force field. The non-simultaneous modelling provides the possibility to consider the time gap between horizon measurements. An unscented Kalman filter is used to estimate the spacecraft motion states and estimate the geometric characteristics as well as the rotational velocity of the celestial body. A Monte-Carlo simulation is implemented to verify the results. Simulations showed that using non-simultaneous horizon vector measurements, the spacecraft state errors converge to zero even in the presence of an uncertain geometry and rotational velocity of the celestial body.

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“…Recent years have witnessed a series of studies on autonomous orbit determination for low-Earth-orbiting (LEO) satellites. Nagarajan et al 1 investigated the use of low-cost Earth scanners combined with known attitude information for orbit estimation. The development of Global Positioning System (GPS) has contributed to the progress of satellite navigation using onboard GPS receivers.…”

Section: Introductionmentioning

confidence: 99%

Autonomous orbit determination using epoch-differenced gravity gradients and starlight refraction

Chen

Sun

2017

Chinese Journal of Aeronautics

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Autonomous orbit determination via integration of epoch-differenced gravity gradients and starlight refraction is proposed in this paper for low-Earth-orbiting satellites operating in GPS-denied environments. The starlight refraction can compensate for the significant along-track position error using solely gravity gradients and benefit from the integration in view of accuracy improvement in radial and cross-track position estimates. The betweenepoch differencing of gravity gradients is employed to eliminate slowly varying measurement biases and noises near the orbit revolution frequency. The refraction angle is directly used as measurement and its Jacobian matrix is derived from an implicit observation equation. An information fusion filter based on sequential extended Kalman filter is developed for the orbit determination. Truth-model simulations are used to test the performance of the algorithm and the effects of differencing intervals and orbital heights are analyzed. A semi-simulation study using actual gravity gradient data from the Gravity field and steady-state Ocean Circulation Explorer (GOCE) combined with simulated starlight refraction measurements is further conducted and a three-dimensional position accuracy of better than 100 m is achieved.

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A novel autonomous orbit determination system using Earth sensors (scanner)

Cited by 10 publications

References 4 publications

Integrated magnetometer–horizon sensor low-earth orbit determination using UKF

Integrated magnetometer–horizon sensor low-earth orbit determination using UKF

Orbit estimation using a horizon detector in the presence of uncertain celestial body rotation and geometry

Autonomous orbit determination using epoch-differenced gravity gradients and starlight refraction

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