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MODELLING OF EARTH’S RADIATION FOR GPS SATELLITE ORBITS. Carlos Javier Rodriguez Solano Technische Universität München [email protected] 3 a Conferencia Al β an – Porto 2009. ESPACE. International Master‘s Program. ESPACE – Earth Oriented Space Science and Technology. - PowerPoint PPT Presentation
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ESPACEPorto, June 2009
MODELLING OF EARTH’S RADIATION FOR GPS SATELLITE ORBITS
Carlos Javier Rodriguez Solano
Technische Universität München [email protected]
3a Conferencia Alβan – Porto 2009
ESPACEPorto, June 2009
ESPACE
International Master‘s Program
ESPACE – Earth Oriented Space Science and Technology
www.espace-tum.de
ESPACEPorto, June 2009
ESPACE combines elements of engineering and science in one single interdisciplinary program
Remote Sensing
Satellite Technology
Navigation
Earth System
ESPACE
www.espace-tum.de
ESPACEPorto, June 2009
“The NAVSTAR GPS ( NAVigation System with Time And Ranging Global Positioning System) is a satellite-based radio navigation system providing precise three dimensional position, navigation and time information to suitably equipped users.”
Seeber (2003)
Introduction
Positions of at least 4 satellites
+
Travelled distance of the signal from the satellite’s antenna to the receiver
=Position on Earth and synchronization
of the receiver
ESPACEPorto, June 2009
The better the positions of the satellites are known
the higher precision that can be achieved on Earth for positioning
The International GNSS Service provides: Final Orbits with accuracy of 5 cm
Final Orbits are computed using:
1) Direct observations from the satellites to reference stations on Earth
2) Force models that include the principal perturbations to the orbit:
- Low terms of Geopotential
- Attraction of Sun and Moon
- Solar Radiation Pressure
- Solid Earth and Ocean Tides
- General Relativity
Introduction
ESPACEPorto, June 2009
An independent way to test the accuracy of Final Orbits is using:
Satellite Laser Ranging (SLR)
Accuracy of SLR measurements is 5 – 6 mm
NERC
This bias could come from the Earth radiation that arrives to the satellites
Not included in the modelling of Final Orbits
But there is a consistent bias of 4 – 5 cm
The GPS – SLR Orbit Anomaly.
Ziebart et al. (2007)
Introduction
ESPACEPorto, June 2009
Compute irradiance at satellite altitude due to emitted and reflected radiation, using:
- Albedo of the Earth (α ≈ 0.3)
- Satellite altitude (h ≈ 20000 km)
- Angle ψ, formed by satellite, Earth and Sun
Earth radiation model
ESPACEPorto, June 2009
After integration of and over the part of the sphere visible to the satellite,we get the total Earth´s irradiance model, which is plotted as function of ψ
emitId
reflId
Earth radiation model
ESPACEPorto, June 2009
GPS satellite model
The radiation coming from the Earth that impacts a satellite accelerates it due to the momentum transfer between the photons and the surface of the satellite.
GPS satellite model spherical bus + solar panel pointing to the Sun
100 times smaller as acceleration due to direct solar radiation
ESPACEPorto, June 2009
Numerical orbit integration
Numerical integration over one year of:
Unperturbed keplerian orbit + perturbing acceleration
Initial conditions for PRN06, one of the GPS satellites with laser retroreflectors
Semimajor axis [km] Eccentricity Inclination [deg] RAAN [deg] Argument of Perigee [deg]
26560.699 0.0062068 53.5060 155.9994 282.1291
Position in the RTN frame, perturbed – unperturbed (reference) orbit
RTN frame
ESPACEPorto, June 2009
Numerical orbit integration
Keplerian elements, perturbed – unperturbed (reference) orbit
Important drift in: Argument of Perigee + True Anomaly = T-component of position
ESPACEPorto, June 2009
Results and Discusion
Definition of different reference orbit:
- Mean keplerian elements over one revolution
- Same true anomaly as perturbed orbit
- Star of it at ∆u = 0
Possible to compare just in radial direction!
Position in the RTN frame, perturbed – reference orbit
Shift of 2 – 4 cm in radial direction, comparable with GPS – SLR Orbit Anomaly
ESPACEPorto, June 2009
Results and Discusion
Also very interesting, plot of radial residuals as a function of:
Sun elevation angle β0 and angle ∆u
Strong dependency with position of Sun
Twice per revolution and twice per year perturbation
ESPACEPorto, June 2009
Conclusions
- A not negligible effect of the Earth radiation on satellite orbits has been found
- Key factors for final results are
1) Earth radiation model with dependency on the relative position of satellite, Earth and Sun
2) Satellite model: bus, solar panel and orientation to the Sun
3) Reference orbit, suitable for the comparison in radial direction
Next steps of the Master Thesis:
- Include models in the computation of GPS orbits
- Use of real GPS and SLR data in the Bernese GPS Software
Better understanding of the GPS – SLR Orbit Anomaly,
a current limit of GPS orbits
ESPACEPorto, June 2009
THANK YOU!
ANY QUESTIONS?