Angular Position Determination of Spacecraft by Radio Interferometry

Lanyi, G. E.; Bagri, D. S.; Border, James S.

doi:10.1109/jproc.2007.905183

Cited by 64 publications

(28 citation statements)

References 14 publications

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“…The results of the current study in terms of achieved accuracy are compatible with those of the other recent well-established VLBI spacecraft tracking projects, such as the VLBA tracking of the Cassini spacecraft (Jones et al 2011) and NASA's Mars Exploration Rover B spacecraft during its final cruise phase (Lanyi et al 2007). …”

Section: Discussionsupporting

confidence: 89%

Spacecraft VLBI and Doppler tracking: algorithms and implementation

Duev

Calvés

Pogrebenko

et al. 2012

A&A

111

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Aims. We present the results of several multi-station Very Long Baseline Interferometry (VLBI) experiments conducted with the ESA spacecraft Venus Express as a target. To determine the true capabilities of VLBI tracking for future planetary missions in the solar system, it is necessary to demonstrate the accuracy of the method for existing operational spacecraft. Methods. We describe the software pipeline for the processing of phase referencing near-field VLBI observations and present results of the ESA Venus Express spacecraft observing campaign conducted in 2010−2011. Results. We show that a highly accurate determination of spacecraft state-vectors is achievable with our method. The consistency of the positions indicates that an internal rms accuracy of 0.1 mas has been achieved. However, systematic effects produce offsets up to 1 mas, but can be reduced by better modelling of the troposphere and ionosphere and closer target-calibrator configurations.

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Section: Discussionsupporting

confidence: 89%

Spacecraft VLBI and Doppler tracking: algorithms and implementation

Duev

Calvés

Pogrebenko

et al. 2012

A&A

111

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“…We expect, based on our previous experience with phase referenced VLBI (e.g., [9]), that an absolute accuracy of 0.1 mas with respect to the ICRF can be achieved for our calibration sources. Thus, the combined error of our Cassini positions with respect to the ICRF will be approximately 0.2 mas, consistent with the level of VLBI spacecraft tracking error predicted by [10].…”

Section: Pos(rts2012)046supporting

confidence: 83%

VLBI Astrometry of Planetary Orbiters

Jones¹,

Fomalont²,

Dhawan³

et al. 2012

Proceedings of Resolving the Sky - Radio Interferometry: Past, Present and Future — PoS(RTS2012)

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“…The various measurement uncertainty and frequency were varied for different sets of simulation runs. DSN ΔDOR measurement uncertainty was selected to be the stated 1 nrad capability of the system, processed once per day [30]. DSN range-only observations used a radial-only measurement accuracy of 1 m with observation frequency varied between once per day to once per 30 days.…”

Section: Glint Navigation Simulation and Performancementioning

confidence: 99%

Spacecraft Navigation Using Celestial Gamma-Ray Sources

Hisamoto

Sheikh

2015

Journal of Guidance, Control, and Dynamics

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As the future progresses for space exploration endeavors, spacecraft that are capable of autonomously determining their position and velocity will provide clear navigation advances to mission operations. Thus, new techniques for determining spacecraft navigation solutions using celestial gamma-ray sources have been developed. Most of these sources offer detectable, bright, high-energy events that provide well-defined characteristics conducive to accurate time alignment among spatially separated spacecraft. Using assemblages of photons from distant gamma-ray bursts, relative range between two spacecraft can be accurately computed along the direction to each burst's source based upon the difference in arrival time of the burst emission at each spacecraft's location. Correlation methods used to time-align the high-energy burst profiles are provided. A simulation of the newly devised navigation algorithms has been developed to assess the system's potential performance. Using predicted observation capabilities for this system, the analysis demonstrates position uncertainties comparable to the NASA Deep Space Network for deep-space trajectories. Nomenclature c = speed of light, m∕s f = nonlinear state vector function h = nonlinear simulated state vector function H = measurement matrix of partial derivatives with respect to states fi; j; kg = spacecraft coordinate system unit axis directionŝ n = line-of-sight vector, radians r SC = three-dimensional spacecraft position, m r Base = three-dimensional base station position, m S = fluence, erg∕cm 2 ∕T 90 t 0 = emission trigger time, s T 90 = burst emission time from 5 to 95% of total photon counts, s ν = simulated measurement noise vector v RSC = remote spacecraft velocity, m∕s x = extended Kalman filter (EKF) true state vector _ xt = nonlinear spacecraft orbital dynamics x = EKF estimated state vector y = observation (filter measurement) z = EKF measurement difference zt = measurement residual Δr = burst position offset, m Δt = burst arrival time offset, s δx = state vector errors ηt = measurement noise vector σ pos 0 = EKF initial position covariance estimate, m σ vel 0 = EKF initial velocity covariance estimate, m∕s

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Angular Position Determination of Spacecraft by Radio Interferometry

Cited by 64 publications

References 14 publications

Spacecraft VLBI and Doppler tracking: algorithms and implementation

Spacecraft VLBI and Doppler tracking: algorithms and implementation

VLBI Astrometry of Planetary Orbiters

Spacecraft Navigation Using Celestial Gamma-Ray Sources

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