Particle filter using a new resampling approach applied to LEO satellite autonomous orbit determination with a magnetometer

Wu, Jiankang; Liu, Kun; Wei, Jingbo; Han, Dong; Xiang, Junhua

doi:10.1016/j.actaastro.2012.08.019

Cited by 14 publications

(7 citation statements)

References 13 publications

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“…On the other hand, relative states of two (or more) satellites can be utilized for an orbit estimation, independent of GPS satellites and/or ground stations [7,8,9,10,11]. Additionally, natural properties of a planet, like its magnetic field [12,13], atmosphere [14,15], or moons [16], can help to build an autonomous orbit estimation procedure. Spacecraft navigation and determination of Celestial Body (CB) characteristics can be autonomously accomplished using the planets geometric characteristics [17] or gravity field estimation [18].…”

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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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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“…11 In contrast to the Earth's magnetic field, the Earth's gravitational field is not affected by solar activities and only endures secular variations due to the its interior changes. 12,13 The typical position errors of orbit determination using magnetometer measurements range from a few to tens of kilometers, 7,14,15 whereas an orbital position accuracy of hundreds of meters has been achieved with GOCE gravity gradient measurements.…”

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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“…Particle filtering (PF) [19,20], a Monte Carlo (MC)based method that requires the propagation of a large number of state estimates called particles, is theoretically one of the most accurate and robust, yet computationally intensive, filtering algorithms. However, PFs may not always be the best filter for a problem [21] and are susceptible to divergence in certain cases because only a finite number of particles are used [22].…”

Section: Introductionmentioning

confidence: 99%

Parallel Computation of Trajectories Using Graphics Processing Units and Interpolated Gravity Models

Arora

Vittaldev

Russell

2015

Journal of Guidance, Control, and Dynamics

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Seeking improvements in speed and accuracy in multiobject trajectory simulations, a solution methodology is presented that takes advantage of 1) new high-fidelity geopotential and third-body perturbation models that efficiently trade memory for speed, and 2) a graphics processing unit based integrator to achieve parallelism across multiple objects. The two methods combined lead to multiplicative speedups, making the tool three orders of magnitude faster, in some cases, compared to the same simulation performed in serial on a single central processing unit. The tool is capable of Monte Carlo simulations of a single object or of propagating the mean and covariance of all the objects in a space catalog. The tool performance is demonstrated for 1) a five-day Monte Carlo simulation of the state uncertainty point cloud modeled with over one million objects, and 2) a seven-day simulation of position and velocity states of a full space catalog with over 250,000 objects. The simulations required approximately 1 and 3 h of runtime, respectively, on a single desktop workstation using a single-core central processing unit and a single graphics processing unit. The solution method is applicable to a variety of space situational awareness applications, including orbit determination, catalog maintenance, uncertainty propagation, and conjunction analysis.

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Particle filter using a new resampling approach applied to LEO satellite autonomous orbit determination with a magnetometer

Cited by 14 publications

References 13 publications

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

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

Parallel Computation of Trajectories Using Graphics Processing Units and Interpolated Gravity Models

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