Onboard and Real-Time Artificial Satellite Orbit Determination Using GPS

Chiaradia, Ana Paula Marins; Kuga, Helio Koiti; Prado, A. F. B. A.

doi:10.1155/2013/530516

Cited by 14 publications

(17 citation statements)

References 18 publications

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“…Orbital filters are widely used to improve the accuracy of the navigation solution provided by GNSS receivers. This is documented in Chiaradia et al (2000), Habib (2013), Pardal et al (2009) and many others. All of them use a Kalman Filter estimator for the positioning of a satellite in LEO.…”

Section: Introductionmentioning

confidence: 66%

GNSS-based Orbital Filter for Earth Moon Transfer Orbits

et al. 2015

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Numerous applications, not only Earth-based, but also space-based, have strengthened the interest of the international scientific community in using Global Navigation Satellite Systems (GNSSs) as navigation systems for space missions that require good accuracy and low operating costs. Indeed, already successfully used in Low Earth Orbits (LEOs), GNSSbased navigation systems can maximise the autonomy of a spacecraft while reducing the burden and the costs of ground operations. That is why GNSS is also attractive for applications in higher Earth orbits up to the Moon, such as in Moon Transfer Orbits (MTOs). However, the higher the altitude the receiver is above the GNSS constellations, the poorer and the weaker are the relative geometry and the received signal powers, respectively, leading to a significant navigation accuracy reduction. In order to improve the achievable GNSS performance in MTOs, we consider in this paper an adaptive orbital filter that fuses the GNSS observations with an orbital forces model. Simulation results show a navigation accuracy significantly higher than that attainable individually by a standalone GNSS receiver or by means of a pure orbital propagation.

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Section: Introductionmentioning

confidence: 66%

GNSS-based Orbital Filter for Earth Moon Transfer Orbits

et al. 2015

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“…The geometric distance from the GPS satellite to the receiver was calculated using

and

; we did not use

[ 13 ]. The GPS signal travels through space at the speed of light, and thus, the receiver does not instantly receive the signal emitted from the GPS satellite.…”

Section: Simulation and Resultsmentioning

confidence: 99%

“…Thus, an iteration technique was used to calculate the proper

. First,

was used instead of

to calculate the temporary

on the left side of the equation, Then, the temporary

was used on the right side of Equation (30) to update the temporary

, and the iterations continued until

converged [ 13 , 14 ].…”

Section: Simulation and Resultsmentioning

confidence: 99%

Coarse Initial Orbit Determination for a Geostationary Satellite Using Single-Epoch GPS Measurements

Kim

Kee

2015

Sensors

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A practical algorithm is proposed for determining the orbit of a geostationary orbit (GEO) satellite using single-epoch measurements from a Global Positioning System (GPS) receiver under the sparse visibility of the GPS satellites. The algorithm uses three components of a state vector to determine the satellite’s state, even when it is impossible to apply the classical single-point solutions (SPS). Through consideration of the characteristics of the GEO orbital elements and GPS measurements, the components of the state vector are reduced to three. However, the algorithm remains sufficiently accurate for a GEO satellite. The developed algorithm was tested on simulated measurements from two or three GPS satellites, and the calculated maximum position error was found to be less than approximately 40 km or even several kilometers within the geometric range, even when the classical SPS solution was unattainable. In addition, extended Kalman filter (EKF) tests of a GEO satellite with the estimated initial state were performed to validate the algorithm. In the EKF, a reliable dynamic model was adapted to reduce the probability of divergence that can be caused by large errors in the initial state.

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“…The applications of the EOSs require provisions of near real-time position information of LEO satellite platforms with high precision. Therefore, accurate, autonomous and real-time orbit determination (RTOD) using global, abundant, and low-cost GPS measurements onboard LEO satellites has been widely applied to many LEO missions [ 1 , 2 , 3 , 4 , 5 , 6 , 7 , 8 , 9 , 10 , 11 , 12 ].…”

Section: Introductionmentioning

confidence: 99%

A Novel Method for Precise Onboard Real-Time Orbit Determination with a Standalone GPS Receiver

Wang

Gong

Sang

et al. 2015

Sensors

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Satellite remote sensing systems require accurate, autonomous and real-time orbit determinations (RTOD) for geo-referencing. Onboard Global Positioning System (GPS) has widely been used to undertake such tasks. In this paper, a novel RTOD method achieving decimeter precision using GPS carrier phases, required by China’s HY2A and ZY3 missions, is presented. A key to the algorithm success is the introduction of a new parameter, termed pseudo-ambiguity. This parameter combines the phase ambiguity, the orbit, and clock offset errors of the GPS broadcast ephemeris together to absorb a large part of the combined error. Based on the analysis of the characteristics of the orbit and clock offset errors, the pseudo-ambiguity can be modeled as a random walk, and estimated in an extended Kalman filter. Experiments of processing real data from HY2A and ZY3, simulating onboard operational scenarios of these two missions, are performed using the developed software SATODS. Results have demonstrated that the position and velocity accuracy (3D RMS) of 0.2–0.4 m and 0.2–0.4 mm/s, respectively, are achieved using dual-frequency carrier phases for HY2A, and slightly worse results for ZY3. These results show it is feasible to obtain orbit accuracy at decimeter level of 3–5 dm for position and 0.3–0.5 mm/s for velocity with this RTOD method.

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Onboard and Real-Time Artificial Satellite Orbit Determination Using GPS

Cited by 14 publications

References 18 publications

GNSS-based Orbital Filter for Earth Moon Transfer Orbits

GNSS-based Orbital Filter for Earth Moon Transfer Orbits

Coarse Initial Orbit Determination for a Geostationary Satellite Using Single-Epoch GPS Measurements

A Novel Method for Precise Onboard Real-Time Orbit Determination with a Standalone GPS Receiver

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