Real time orbit determination using GPS navigation solution

Gomes, Vivian Martins; Kuga, Helio Koiti; Chiaradia, Ana Paula Marins

doi:10.1590/s1678-58782007000300006

Cited by 8 publications

(5 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The state transition matrix (߶ ǡିଵ ) is used to propagate covariance matrix is given by Eq. (21), (Grewal et al, 2007, Gomes et al, 2007;…”

Section: Least Square Implementationmentioning

confidence: 99%

“…Each GPS satellite transmits the Navigation Message through C/A code. The C/A codes from at least four GPS satellites are required to calculate the user receiver position in Earth Centered Earth Fixed (ECEF) coordinate system (Gomes et al, 2007).…”

Section: Gps Data Processingmentioning

confidence: 99%

“…Therefore, to solve for user position and time, we need to solve the following simultaneous equations Eq. (29) (Amaral et al, 2007, Gomes et al, 2007.…”

Section: Gps Navigation Solutionmentioning

confidence: 99%

See 2 more Smart Citations

Simplified Orbit Determination Algorithm for Low Earth Orbit Satellites Using Spaceborne GPS Navigation Sensor

Aghav

Gangal

2014

Artificial Satellites

View full text Add to dashboard Cite

In this paper, the main work is focused on designing and simplifying the orbit determination algorithm which will be used for Low Earth Orbit (LEO) navigation. The various data processing algorithms, state estimation algorithms and modeling forces were studied in detail, and simplified algorithm is selected to reduce hardware burden and computational cost. This is done by using raw navigation solution provided by GPS Navigation sensor. A fixed step-size Runge-Kutta 4th order numerical integration method is selected for orbit propagation. Both, the least square and Extended Kalman Filter (EKF) orbit estimation algorithms are developed and the results of the same are compared with each other. EKF algorithm converges faster than least square algorithm. EKF algorithm satisfies the criterions of low computation burden which is required for autonomous orbit determination. Simple static force models also feasible to reduce the hardware burden and computational cost.

show abstract

“…The state transition matrix (߶ ǡିଵ ) is used to propagate covariance matrix is given by Eq. (21), (Grewal et al, 2007, Gomes et al, 2007;…”

Section: Least Square Implementationmentioning

confidence: 99%

Section: Gps Data Processingmentioning

confidence: 99%

See 1 more Smart Citation

Simplified Orbit Determination Algorithm for Low Earth Orbit Satellites Using Spaceborne GPS Navigation Sensor

Aghav

Gangal

2014

Artificial Satellites

View full text Add to dashboard Cite

show abstract

“…Gomes et al [14] analyzed a real-time orbit estimator using the raw navigation solution provided by GPS receivers. The estimation algorithm considers a Kalman filter with a rather simple orbit dynamic model and random walk modeling of the receiver clock bias and drift.…”

Section: Introductionmentioning

confidence: 99%

Onboard and Real-Time Artificial Satellite Orbit Determination Using GPS

Chiaradia

Kuga

Prado

2013

Mathematical Problems in Engineering

View full text Add to dashboard Cite

An algorithm for real-time and onboard orbit determination applying the Extended Kalman Filter (EKF) method is developed. Aiming at a very simple and still fairly accurate orbit determination, an analysis is performed to ascertain an adequacy of modeling complexity versus accuracy. The minimum set of to-be-estimated states to reach the level of accuracy of tens of meters is found to have at least the position, velocity, and user clock offset components. The dynamical model is assessed through several tests, covering force model, numerical integration scheme and step size, and simplified variational equations. The measurement model includes only relevant effects to the order of meters. The EKF method is chosen to be the simplest real-time estimation algorithm with adequate tuning of its parameters. In the developed procedure, the obtained position and velocity errors along a day vary from 15 to 20 m and from 0.014 to 0.018 m/s, respectively, with standard deviation from 6 to 10 m and from 0.006 to 0.008 m/s, respectively, with the SA either on or off. The results, as well as analysis of the final adopted models used, are presented in this work.

show abstract

“…Then, it goes to orbital maneuvers based in low thrust (Casalino and Colasurdo 2002;Casalino et al 1999;Brophy and Noca 1998;Zee 1963;Lion and Handelsman 1968;Prado 2007, 2008;Macau 2000;Macau and Grebogi 2006), swing-by techniques (Flandro 1966;Marsh 1988;Farquhard and Dunham 1981;Prado and Broucke 1995;Prado 2007;Gomes et al 2013;DeMelo et al 2009), and even gravitational capture (Belbruno and Miller 1993;Pierson and Kluever 1994;Neto and Prado 1998). It covers also some more applied concepts, like searches for specific orbits (Chiaradia et al 2003;Carvalho et al 2010;Araujo et al 2012;Domingos et al 2008;D'Amario et al 1982;Farquhar et al 1985;Gomes and Domingos 2015;Salazar et al 2015aSalazar et al , b, 2014Salazar et al , 2012Gomes et al 2007).…”

mentioning

confidence: 99%

Applications of celestial mechanics in natural objects and spacecrafts

Gomes

Mello²,

Macau³

et al. 2017

Comp. Appl. Math.

View full text Add to dashboard Cite

Studies related to Celestial Mechanics started long ago, and it is one of the oldest fields in Astronomy. It started to try to explain the motions of the stars in the sky, in particular the irregular motion of some of those of then, which were really the planets of the Solar System. In the 20th century, with the arrival of the "Space Age", many applications related to the motion of artificial spacecrafts appeared. This new field was called "Astrodynamics", to designate the use of Celestial Mechanics in man-made objects. Several aspects, like orbit determination, maneuvers to change the orbit of the spacecraft, etc., are covered by this topic. The present Focus Issue in Celestial Mechanics publishes a list of papers in topics related to applications in Celestial Mechanics to both situations: natural and artificial satellites. Keywords Celestial mechanics • Astrodynamics • Orbital dynamics Mathematics Subject Classification 37N05 The science of "Celestial Mechanics" was born to study the motion of the celestial bodies. It started with the observation of the motion of the stars in the night sky, which has been made probable, since the first form of humans was able to understand what they could see in the sky. The time and the evolution of technology improved our knowledge in Celestial Mechanics. A major series of steps were made in the years near 1600. Tycho Brahe (1546-1601) made accurate observations of the motion of the stars which moved against the fixed ones. Those data were than studied by Johannes Kepler (1571-1630), which made the important "Three Laws of Kepler" of the orbital motion: 1. The orbit of each planet is an ellipse with the Sun occupying one of the focus.

show abstract

Real time orbit determination using GPS navigation solution

Cited by 8 publications

References 5 publications

Simplified Orbit Determination Algorithm for Low Earth Orbit Satellites Using Spaceborne GPS Navigation Sensor

Simplified Orbit Determination Algorithm for Low Earth Orbit Satellites Using Spaceborne GPS Navigation Sensor

Onboard and Real-Time Artificial Satellite Orbit Determination Using GPS

Applications of celestial mechanics in natural objects and spacecrafts

Contact Info

Product

Resources

About