Präzise Bahnbestimmung des GOCE- Satelliten mittels GPS. Heike Bock
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1 Präzise Bahnbestimmung des GOCE- Satelliten mittels GPS Redundante Antenne Hauptantenne Heike Bock
2 Entwicklung der LEO Bahnbestimmung am AIUB 1999: Gerhard Beutler initiiert die LEO Bahnbestimmung am AIUB im Hinblick auf die CHAMP-Mission 2003: Dissertation Heike Bock Efficient Methods for Determining Precise Orbits of Low Earth Orbiters Using the Global Positioning System 2006: Dissertation Adrian Jäggi Pseudo-Stochastic Orbit Modeling of Low Earth Satellites Using the Global Positioning System Diverse Projekte mit DLR, ESA, EUMETSAT, GFZ Seit 2004 ist das AIUB Mitglied des European GOCE Gravity Consortiums (EGG-C), welches die GOCE High-level Processing Facility (HPF) betreibt 2010: Dissertation Lars Prange Global Gravity Field Determination Using the GPS Measurements Made Onboard the Low Earth Orbiting Satellite CHAMP Weitere wichtige Arbeiten in der Gravitationsfeldbestimmung von Adrian Jäggi, Ulrich Meyer und Gerhard Beutler
3 Inhalt Übersicht über die GOCE Mission Status High-level Processing Facility Bahnbestimmung Allgemeines Precise Science Orbits (PSO) PSO-Prozedur Einfluss der PCVs (Phase Center Variations) Resultate und Validierung Datenqualität Zusammenfassung
4 Inhalt Übersicht über die GOCE Mission Status High-level Processing Facility Bahnbestimmung Allgemeines Precise Science Orbits (PSO) PSO-Prozedur Einfluss der PCVs (Phase Center Variations) Resultate und Validierung Datenqualität Zusammenfassung
5 GOCE satellite mission (1) Gravity and steady-state Ocean Circulation Explorer First Earth Explorer of the Living Planet Program of the European Space Agency Launch: 17 March 2009 from Plesetsk, Russia Sun-synchronous dusk-dawn orbit with inclination of 96.5 o Altitude: km Mass: 1050 kg at launch 5.3 m long, 1.1 m 2 cross section Courtesy:ESA
6 GOCE satellite mission (2) Three axes stabilised, nadir pointing, aerodynamically shaped satellite Drag free attitude control (DFAC) in flight direction (Xe electric propulsion system) Very rigid structure, no moving parts Attitude control by magnetorquers Courtesy:ESA
7 GOCE satellite mission (3) Core Payload: Electrostatic Gravity Gradiometer three pairs of accelerometers 0.5 m arm length Main mission goals: Determination of the Earth s gravity field with an accuracy of 1mGal (= 10-5 m/s 2 ) at a spatial resolution of 100 km Determination of the geoid on the 1 cm-level with a spatial resolution of 100 km Courtesy:ESA
8 GOCE satellite mission (4) Satellite to Satellite tracking instrument (SSTI) Dual frequency L1, L2 12 channel GPS receiver Real time position and velocity (3D, 3 sigma) < 100 m, < 0.3 m/s 1 Hz data rate Science and real time on board solution for navigation Hardly any data gaps Courtesy:ESA => Mission requirement for precise science orbits: 2 cm (1D)
9 GOCE satellite mission (5) Kuijper and Matatoros, 2011
10 GOCE satellite mission (5) Kuijper and Matatoros, 2011
11 GOCE satellite mission (5) Mission duration: Nominal mission has ended on March 2, 2011 Extended mission approved until end of 2012 Current altitude will be hold at least until (late) summer 2011 ESA, Fehringer, 2011
12 GOCE High-level Processing Facility (HPF)
13 GOCE High-level Processing Facility (HPF) Responsibilities for orbit generation: DEOS: => RSO (Rapid Science Orbit) AIUB: => PSO (Precise Science Orbit) IAPG: => Validation
14 Inhalt Übersicht über die GOCE Mission Status High-level Processing Facility Bahnbestimmung Allgemeines Precise Science Orbits (PSO) Einfluss der PCVs (Phase Center Variations) Resultate und Validierung Datenqualität Zusammenfassung
15 Kinematic orbit representation A kinematic orbit is an ephemeris at discrete measurement epochs Kinematic positions are fully independent of the force models used for LEO orbit determination Kinematic orbits are well suited for gravity field recovery of the longwavelength part
16 Dynamic orbit representation Satellite trajectory is a particular solution of the equation of motion defined by the force models used Dynamic orbits fully depend on the force models used, e.g., on the gravity field model The quality of dynamic orbits is fully dependent on the exact knowledge of the force models
17 Reduced-dynamic orbit representation Satellite trajectory is a particular solution of the equation of motion defined by the force models used. The strength of the force models is reduced, to some extent, by additional empirical parameters. Reduced-dynamic orbits heavily depend on the force models used, e.g., on the gravity field model (solving the equation of motion) Reduced-dynamic orbits are well suited to compute LEO orbits of highest quality
18 GOCE orbit generation Orbit solution Software GPS Observ. GPS products Sampling Data batches Latency reduceddynamic GEODYN triple-diff IGS rapid 10 sec 30 h 1 day RSO kinematic GHOST zero-diff CODE rapid 1 sec 24 h 1 day reduceddynamic BERNESE zero-diff CODE final 10 sec 30 h 7-10 days PSO kinematic BERNESE zero-diff CODE final 1 sec 30 h 7-10 days
19 GOCE orbit generation Orbit solution Software GPS Observ. GPS products Sampling Data batches Latency RSO GEODYN triple-diff kinematic GHOST zero-diff IGS rapid Accuracy requirement: 50 cm CODE rapid 10 sec 30 h 1 day 1 sec 24 h 1 day PSO reduceddynamic reduceddynamic BERNESE zero-diff kinematic BERNESE zero-diff CODE final Accuracy requirement: 2 cm CODE final 10 sec 30 h 1 sec 30 h 7-10 days 7-10 days
20 Inhalt Übersicht über die GOCE Mission Status High-level Processing Facility Bahnbestimmung Allgemeines Precise Science Orbits (PSO) PSO-Prozedur Einfluss der PCVs (Phase Center Variations) Resultate und Validierung Datenqualität Zusammenfassung
21 GOCE PSO procedure CODE products GOCE GPS data Data preprocessing Reduceddynamic orbit solution (iterative) Preparation of GPS orbits, clocks and ERPs (30 hours) Pseudorange: first a priori orbit Receiver clock synchronization Phase: Iterative data screening a priori 10 sec Piece-wise constant accelerations (6 min) Auxiliary data GOCE attitude data Kinematic orbit solution 1 sec Tailored version of Bernese GPS Software used Un-differenced processing Automated procedure 30 h batches => overlaps CODE final products Consequent use of antenna phase center variation (PCV) map Final kinematic positions are only accepted, if five or more simultaneous observations were available => on average only 0.7% positions missing (max.5.2%)
22 GOCE GPS data GOCE clock is not steered to integer seconds => no equidistant 1 Hz observations Switch to B-computer in Feb 2010 made clock more stable Behaviour of receiver clock changed during mission time Switch to redundant receiver can be noticed
23 GOCE PSO procedure: PCV map Antenna PCVs are the most important systematic error source in LEO GPS data processing. They have to be taken into account to achieve a high accuracy level for POD. Ground calibrations for the GOCE antenna are available but no improvement of the orbits could be achieved. Therefore, we decided to do an in-flight calibration of the GOCE antenna PCVs.
24 GOCE PSO procedure: PCV map Ground calibrations Chamber calibration Calibration on roboter (with part of the wing)
25 GOCE PSO procedure: PCV map 20 July 2010: Mean values of carrier phase observation residuals (ionosphere-free linear combination) Generation of the PCV map: 1. Mean values of 154 days of carrier phase observation residuals from reduced-dynamic orbit determination => first PCV map 2. Use of PCV map for reduced-dynamic orbit determination of 154 days 3. Mean values of observation residuals => add-on to previous PCV map 4. Back to 2. => 10 iterations
26 GOCE PSO procedure: PCV map PCV map from first iteration Generation of the PCV map: 1. Mean values of 154 days of carrier phase observation residuals from reduced-dynamic orbit determination => first PCV map 2. Use of PCV map for reduced-dynamic orbit determination of 154 days 3. Mean values of observation residuals => add-on to previous PCV map 4. Back to 2. => 10 iterations
27 GOCE PSO procedure: PCV map PCV map from last iteration Generation of the PCV map: 1. Mean values of 154 days of carrier phase observation residuals from reduced-dynamic orbit determination => first PCV map 2. Use of PCV map for reduced-dynamic orbit determination of 154 days 3. Mean values of observation residuals => add-on to previous PCV map 4. Back to 2. => 10 iterations
28 GOCE PSO: Impact of PCV map Orbit differences in cross-track direction between orbit generated without PCV map and the orbits from all iterations
29 GOCE PSO: Impact of PCV map Satellite Laser Ranging (SLR) residuals in laser retro reflector system PCVs not corrected PCVs corrected
30 PSO: Comparison reduced-dynamic kinematic orbits PCV map not used Orbit differences between reduced-dynamic and kinematic PSO solutions Orbit differences > 1 m removed (only 60 positions for the entire period)
31 PSO: Comparison reduced-dynamic kinematic orbits PCV map used Orbit differences between reduced-dynamic and kinematic PSO solutions Orbit differences > 1 m removed (only 60 positions for the entire period) Consistency of reduced-dynamic and kinematic PSO is at 2 cm level => mean 3D-RMS 1.82 cm
32 GOCE PSO: Overlaps reduced-dynamic orbits 5 h overlaps (21:30 02:30) PCV map not used Mean 3D-RMS: 2.54 cm PCV map used Mean 3D-RMS: 0.55 cm
33 GOCE PSO procedure: PCV map Main antenna Redundant antenna from 154 days from 58 days
34 GOCE PSO procedure: PCV map Redundant antenna Simulation of PCVs based on ray tracing from 58 days
35 PSO: Results from the entire mission Differences red.-dynamic kinematic mean 3D-RMS 2.07 cm Overlaps red.-dynamic orbits mean 3D-RMS 0.98 cm
36 Validation: SLR residuals for reduced-dynamic orbits Mean 0.45 cm RMS 1.71 cm
37 Validation: SLR residuals for kinematic orbits Mean 0.43 cm RMS 2.00 cm
38 Comparison RSO and PSO Differences red.-dynamic RSO PSO Start of PCV correction Differences kinematic RSO PSO
39 PSO: Data quality Orbit differences between reduceddynamic and kinematic PSO solution are more pronounced after the summerbreak Differences are noisier at regular intervals What is the reason for this?
40 PSO: Data quality
41 PSO: Data quality Observations of the second frquency are missing at begin/middle/end of GPS satellite passes Possible correlation with solar activity?
42 Data quality - Geographical distribution of L2 losses
43 Data quality - Geographical distribution of L2 losses
44 Data quality L2 losses Time differences of geometry-free linear combination (left) => changes in the ionosphere/ionospheric scintillations L2 losses mainly occur at time intervals with larger ionospheric scintillations
45 Data quality: RMS of phase residuals (red.-dyn orbits)
46 Inhalt Übersicht über die GOCE Mission Status High-level Processing Facility Bahnbestimmung Allgemeines Precise Science Orbits (PSO) PSO-Prozedur Einfluss der PCVs (Phase Center Variations) Resultate und Validierung Datenqualität Zusammenfassung
47 Zusammenfassung GOCE hat eine erfolgreiche nominelle Missionsdauer hinter sich und mindestens 18 weitere spannende Monate stehen bevor. Bahnbestimmung bildet einen wichtigen Teil der Datenverarbeitungskette. Genauigkeitsanforderungen von 2 cm werden sowohl für die reduziertdynamischen als auch für die kinematischen Bahnen erfüllt. Untersuchungen zur teilweise reduzierten Datenqualität sind im Gange.
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