Gravity Field and Steady-State Ocean Circulation Explorer
Artist's view of GOCE. Its sleek, aerodynamic design led it to be dubbed the 'Ferrari of space'
|Mission type||Gravitational research|
|Mission duration||Planned: 20 months
Final: 4 years, 7 months, 24 days
|Manufacturer||Thales Alenia Space
|Launch mass||1,077 kg (2,374 lb)|
|Dry mass||872 kg (1,922 lb)|
|Dimensions||5.3 m × 2.3 m (17.4 ft × 7.5 ft)|
|Start of mission|
|Launch date||17 March 2009, 14:21:00UTC|
|Launch site||Plesetsk 133/3|
|End of mission|
|Last contact||10 November 2013, 22:42UTC|
|Decay date||11 November 2013, 00:16 UTC|
|Perigee||254.9 km (158.4 mi)|
|Apogee||254.9 km (158.4 mi)|
|Epoch||29 June 2010|
|Bandwidth||up to 1.2 Mbit/s download
up to 4 kbit/s upload
The Gravity Field and Steady-State Ocean Circulation Explorer (GOCE) was the first of ESA's Living Planet Programme satellites intended to map in unprecedented detail the Earth's gravity field. The spacecraft's primary instrumentation was a highly sensitive gravity gradiometer consisting of three pairs of accelerometers which measured gravitational gradients along three orthogonal axes.
GOCE mapped the deep structure of the Earth's mantle and probed hazardous volcanic regions. It brought new insight into ocean behaviour; this in particular, was a major driver for the mission. By combining the gravity data with information about sea surface height gathered by other satellite altimeters, scientists were able to track the direction and speed of geostrophic ocean currents. The low orbit and high accuracy of the system greatly improved the known accuracy and spatial resolution of the geoid (the theoretical surface of equal gravitational potential on the Earth).
The satellite's unique arrow shape and fins helped keep GOCE stable as it flew through the upper thermosphere at an altitude of 255 kilometres (158 mi). Additionally, an ion propulsion system continuously compensated for the variable deceleration due to air drag without the vibration of a conventional chemically powered rocket engine, thus limiting the errors in gravity gradient measurements caused by non-gravitational forces and restoring the path of the craft as closely as possible to a purely inertial trajectory.
After running out of propellant, the satellite began dropping out of orbit and made an uncontrolled reentry on 11 November 2013.
Discoveries and applications
- To determine gravity-field anomalies with an accuracy of 10−5 m·s−2 (1 mGal). To increase resolution, the satellite flew in an unusually low orbit.
- To determine the geoid with an accuracy of 1–2 cm.
- To achieve the above at a spatial resolution better than 100 km.
Gravity map and model
The final gravity map and model of the geoid will provide users worldwide with well-defined data product that will lead to:
- A better understanding of the physics of the Earth's interior to gain new insights into the geodynamics associated with the lithosphere, mantle composition and rheology, uplift and subduction processes.
- A better understanding of the ocean currents and heat transport.
- A global height-reference system, which can serve as a reference surface for the study of topographic processes and sea-level change.
- Better estimates of the thickness of polar ice-sheets and their movement.
The first Earth global gravity model based on GOCE data was presented at ESA’s Living Planet Symposium, in June 2010.
Initial results of the GOCE satellite mission were presented at the American Geophysical Union (AGU) 2010 Fall (Autumn) Meeting by Dr. Rory Bingham from Newcastle University, UK. The maps produced from the GOCE data show ocean currents in much finer detail than had been available previously. Even very small details like the Mann Eddy in the North Atlantic were visible in the data, as was the effect of Hurricane Igor (2010). Detailed analysis of GOCE's thruster and accelerometer data serendipitously revealed that it had detected the infrasound waves generated by the 2011 Tōhoku earthquake (whereupon it inadvertently became the first seismograph in orbit).
GOCE was launched from the Plesetsk Cosmodrome in northern Russia with a Rokot/Briz-KM vehicle on 17 March 2009 at 14:21 UTC. The Rokot is a modified UR-100N intercontinental ballistic missile that was decommissioned after the Strategic Arms Reduction Treaty. The launcher used the two lower liquid fuel stages of the original missile and was equipped with a Briz-KM third stage developed for precise orbit injection. GOCE was launched into a Sun-synchronous dusk-dawn orbit with an inclination of 96.70° and an ascending node at 18:00. Separation from the launcher was at 295 km. The satellite’s orbit then decayed over a period of 45 days to an operational altitude, planned at 270 km. During this time, the spacecraft was commissioned and the electrical propulsion system checked for reliability in attitude control[needs update].
The first launch attempt on 16 March 2009 was aborted due to a malfunction with the launch tower. Liftoff occurred successfully at 14:21 GMT on 17 March 2009. The Rokot launcher delivered the satellite northward over the Arctic. About 90 minutes later, after one orbital revolution and two Briz-KM upper-stage burns, the spacecraft was successfully released into a circumpolar orbit at 280 km altitude with 96.7° inclination to the Equator. Soon after the separation, contact was successfully established with the satellite.
In February 2010 a fault was discovered in the satellite's computer, which meant controllers were forced to switch control to the backup computer.
In July 2010, GOCE suffered a serious communications malfunction, when the satellite suddenly failed to downlink scientific data to its receiving stations. Extensive investigations by experts from ESA and industry revealed that the issue was almost certainly related to a communication link between the processor module and the telemetry modules of the main computer. The recovery was completed in September 2010: as part of the action plan, the temperature of the floor hosting the computers was raised by some 7 °C – resulting in restoration of normal communications.
In November 2010, the due completion date for the original 20-month mission before it was delayed by the glitches, it was decided to extend the mission lifetime till the end of 2012, in order to complete the original work and carry out a further 18-month mission to improve the collected data.
In November 2012 the orbit was lowered from 255 km to 235 km to get higher resolution data, at which time fuel remained for another 50 weeks.
End of mission and re-entry
In May 2013 a further lowering to 229 km took place.
The satellite ran out of propellant (xenon) in mid-October 2013, at which time it would take 2–3 weeks to re-enter.
On 18 October 2013, ESA reported that the pressure in the fuel system of GOCE's ion engine had dropped below 2.5 bar, which is the nominal operating pressure required to fire the engine. Subsequently end of mission was formally declared on 21 October when the ion drive stopped working at 03:16 UTC.
On 10 November ESA expected re-entry to occur between 18:30 UTC - 24:00 UTC, on 10 November; the most probable impact ground swath largely running over ocean and polar regions.
Its descending orbit on 11 November 2013 passed over Siberia, the western Pacific Ocean, the eastern Indian Ocean and Antarctica. The satellite finally disintegrated at around 1 a.m CET, according to the European Space Agency, near the Falkland Islands.
The satellite's main payload was the Electrostatic Gravity Gradiometer (EGG) to measure the gravity field of Earth. They were arranged in three pairs of ultra-sensitive accelerometers arranged in three dimensions that responded to tiny variations in the 'gravitational tug' of the Earth as it travelled along its orbital path. Because of their different position in the gravitational field they all experienced the gravitational acceleration of the Earth slightly differently. The three axes of the gradiometer allowed the simultaneous measurement of the five independent components of the gravity gradient tensor.
Other payload was an onboard GPS receiver used as a Satellite-to-Satellite Tracking Instrument (SSTI); a compensation system for all non-gravitational forces acting on the spacecraft. The satellite was also equipped with a laser retroreflector to enable tracking by ground-based lasers.
Power and propulsion
The ion propulsion electric engine, designed and built at QinetiQ's space centre in Farnborough, England, ejected xenon ions at velocities exceeding 40,000 m/s (140,000 km/h; 89,000 mph), which compensated for the orbital decay losses. GOCE's mission ended when the 40 kg (88 lb) xenon fuel tank emptied (with a predicted lifetime of about 20 months). The dual Kaufman-type ion thrusters could produce up to 20 mN of thrust.
An ESA report in June 2010 suggested that unusually low solar activity (meaning a calmer upper atmosphere, and hence less drag on the craft) meant the mission would be able to extend past its predicted 20 months due to fuel savings - possibly into 2014. In reality, the end of mission was formally declared on 21 October 2013 after 55 months, after being deployed for its final 11 months in a lower orbit (with greater air density and therefore greater fuel use).
The 5 × 1.1 m (16 × 4 ft) frame incorporates the fixed solar panels as fins to stabilise the spacecraft while it orbits through the residual air in the thermosphere.
- GRACE (NASA) (in orbit since 2002)
- ESA's Living Planet Programme
- SLATS (JAXA)
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