Coriolis is a US DoD satellite technology demonstration mission within the US Air Force STP (Space Test Program), sponsored by SPAWAR (Space and Naval Warfare Systems Command) of the US Navy and by NPOESS/IPO, managed by NRL, and implemented by AFRL (Air Force Research Laboratory) and NRL (Naval Research Laboratory). Coriolis is also referred to as STP mission P98-2.
The overall objective is to conduct an operational verification of new instrument technology, aimed at validating spaceborne multichannel polarimetric radiometry as a reliable and cost effective means for achieving wind vector measurements (speed and direction) that meet NPOESS (National Polar-orbiting Operational Environmental Satellite System) requirements. A further objective of the Air Force is to monitor solar activity for better predictive models of solar storms. 1) 2) 3)
Coriolis is a fully redundant three-axis stabilized spacecraft (nadir pointing) built by the contractor Spectrum Astro Inc. of Gilbert, AZ (now General Dynamics) for the U.S. Navy. The S/C bus is based on the SA-200HP catalog bus, an Al honeycomb/Al facesheet deck structure, as flown on DS1 (Deep Space 1), with specific tailoring to suit the Coriolis requirements. The overall dimensions are: 4.69 m height (without solar array), 1.34 m diameter. Power is provided by a solar array assembly (dual-junction GaAs solar cells, 1.174 kW at EOL) and by a single 50 Ah NiH2 battery for ecliptic period operations. Attitude sensing is provided by autonomous sun acquisition using coarse sun sensors and magnetometers, actuation is provided by reaction wheels (pitch momentum biased). GPS-based orbit knowledge of < 100 m, 10 cm/s, all axes. A hydrazine propulsion system is used for orbit transfer. The S/C has a total launch mass of 827.4 kg (S/C bus of 377 kg), the design life is three years.
Key features of the Coriolis spacecraft design include extremely low levels of electromagnetic interference for compatibility with the ultra-sensitive WindSat radiometer (e.g., radiated emissions are < 6.5 dB µV/m at 6.8 GHz); and a system architecture to support the 30 rpm yaw spin of WindSat's rotating assembly, while providing power plus precise attitude knowledge and control.
Table 1: Overview of Coriolis spacecraft parameters
Figure 1: Line drawing of the Coriolis spacecraft (image credit: Spectrum Astro)
Launch: A launch of Coriolis took place on Jan. 6, 2003, aboard a Titan 2 rocket from VAFB, CA.
RF communications: Command and data handling is provided by a VME-based architecture and a MIL-STD-1553B bus. An onboard solid-state recorder of 30 Gbit capacity is provided. TT&C communications are provided in S-band (128 kbit/s downlink, 2 kbit/s encrypted uplink). Instrument data are downlinked in X-band at 25.6 or 51.2 Mbit/s (use of CCSDS protocols). The US Navy uses a real-time S-band tactical downlink (256 kbit/s) to distribute radiometer data to deployed fleet units. AFSCN (Air Force Satellite Control Network) provides S/C operations in S-band.
Orbit: Sun-synchronous circular orbit, altitude = 840 km, inclination = 98.7º, period = 101 minutes, revisit time of 8 days, the longitude of the ascending node shifts westward by 138 km daily; local time of ascending node (LTAN) is 18:00 hours.
Figure 2: Illustration of the Coriolis spacecraft (image credit: NRL, AFRL)
Status of mission:
• According to NRL, Coriolis/WindSat is operating nominally in 2016. 4)
• In the fall of 2015, Coriolis/WindSat is operating successfully for 12 years and counting. 5)
• In 2014, Coriolis/WindSat continues to operate nominally.
• In 2013, theCoriolis/WindSat mission continues to operate smoothly. On January 6, 2013, Coriolis completed its 10th year on orbit. The plan is to extend the mission as long as it is providing useful data.
• In 2012, the Coriolis/WindSat mission continues to operate nominally (in its 10th year on orbit). No life-limiting trends have been identified. WindSat polarimetric microwave radiometer data are used operationally in numerical weather prediction (NWP) models by the US Navy , NOAA NCEP and the UK Met Office. Furthermore, products such as imagery, wind fields, sea ice concentration, and sea surface temperature are being used by a variety of operational users: Joint Typhoon Warning Center, Naval Oceanographic Office, NWS Forecasting Offices, and others.
- At this time, the secondary payload, SMEI (Solar Mass Ejection Imager), is powered off due to budgetary shortfalls.
• Coriolis/WindSat continues to operate successfully in 2011. There were no major issues or events regarding the satellite or payloads in 2010. WindSat data continue to be used operationally by the US Navy, NOAA/NCEP, the UK Met Office, the Joint Typhoon Warning Center and other agencies. In addition, further applications using land products such as soil moisture and vegetation water content are being developed.
The WindSat data is being used operationally by the US Navy and other agencies (NOAA/NCEP, UK Met Office, etc.). The system is not showing any significant signs of aging/degradation. The mission is expected to continue as long as WindSat is providing useful data to the user community. In addition to surface wind vectors, other products like SST (Sea Surface Temperature), rain rate, cloud liquid water, total precipitable water (water vapor), and microwave imagery are being produced. Furthermore, sea ice, soil moisture, and land surface temperature products are being developed. 6) - In 2010, SMEI continues to operate. 7)
• The SMEI instrument, a proof-of-concept experiment on Coriolis, continuous to detect and track CMEs (Coronal Mass Ejections). In March 2006, an irrevocable failure occurred on its A-side electronics. As a consequence, SMEI was switched to the B-side and continues to operate nominally. Camera 3 (closest to the sun) has run above predicted/planned for temperatures and performance continually degrades with accumulated radiation dose. 8)
In January 2009, the SMEI instrument marked the 6th anniversary in orbit. It has amassed an unprecedented dataset of ~25,000 full-sky images since 2003 with a 102-minute cadence, 1° spatial resolution, and better than 8th magnitude sensitivity. However, SMEI is nearing the end of its life.
• June 2006: WindSat Brightness Temperature and Environmental Data Now Available to Science and User Community. 9)
• As of early Feb. 2005, the WindSat project began to make the near real-time wind data from WindSat available to operational weather centers such as FNMOC (Fleet Numerical Meteorology and Oceanography Center) of US Navy, Monterey, CA, AFWA (Air Force Weather Agency) at Offutt Air Force Base (OAFB), Bellevue, Nebraska, and NCEP (National Centers for Environmental Prediction), USA. 10)
• WindSat experienced an anomaly on Feb. 13, 2005 and was put into a safe-hold mode while the problem was being investigated [the BAPTA (Bearing and Power Transfer Assembly) of the scan mechanism changed speed unexpectedly]. Up to the time of the anomaly the mission had been very successful (i.e., demonstration to use WindSat to measure the ocean surface winds).
• The recovery efforts of WindSat were successful - and the instrument returned to operations in late June, 2005. 11)
• In the week of April 25, 2005, the SMEI instrument performed some diagnostic tests to attempt to resolve a technical issue. Unfortunately, after this test was completed, parts of the instrument were reaching critical temperature limits and a solution was needed.
• On Apr. 28, 2005, the Coriolis spacecraft was commanded to enter a sun-pointing mode of operation, rather than the normal reference-point mode. This successfully brought the Coriolis temperatures back within safe limits, but this pointing mode has significantly impacted the quality of data that is being returned by the SMEI instrument.
Sensor complement: (WindSat, SMEI)
WindSat (Wind Microwave Radiometer):
WindSat is a polarimetric microwave radiometer developed and built by NRL. WindSat is also considered a precursor instrument to CMIS (Conical-scanning Microwave Imager/Sounder), a radiometric polarimeter to be flown on NPOESS (National Polar-orbiting Operational Environmental Satellite System). The objective of WindSat is to conduct an operational demonstration of the WindSat system and to measure the ocean surface wind vector (speed and direction) for a number of practical applications (secondary measurements are sea surface temperature, rain rate and water vapor). WindSat also provides insight into such problems as the upwind/downwind asymmetry and boundary layer conditions (Ref. 1). 12)
The measurement principle makes use of the natural microwave emissions of the sea surface which vary with the degree of sea surface roughness. The rougher the seas, the more intense the emissions. The wind direction is obtained from the relationship between the horizontal and vertical polarization characteristics of the received signal and the anisotropic distribution of wind-driven waves. The wind vectors are estimated (model algorithm) by the measurement of multi-frequency polarimetric brightness temperatures. 13)
The WindSat microwave polarimetric radiometer consists of 22 channels of polarized brightness temperatures operating at five frequencies of 6.8, 10.7, 18.7, 23.8, and 37 GHz. All receivers are total power radiometers. The receivers at 10.7, 18.7 and 37.0 GHz are fully polarimetric; that is, they establish all four Stokes parameters by measuring the six principal polarizations [3 dual-polarization feed horns are used: V/H, ±45º linear, and Left/Right circular; the third and fourth Stokes parameters are formed by taking the brightness temperature difference between the ±45º polarizations, and the left- and right-hand circular polarization, respectively]. The 6.8 GHz channel is dual-polarimetric (vertical and horizontal) and provides sea surface temperature (SST) as a secondary product. The 23.8 GHz channel is also dual-polarimetric, its purpose is to correct for atmospheric water vapor which is unpolarized. The WindSat frequencies are useful beyond the measurement of ocean surface wind vectors and SST. Other parameters can be extracted/estimated from the data such as: atmospheric water vapor, cloud liquid water, rain rate, sea ice (age, concentration, and boundary), snow cover extent, and water content of snow. 14) 15)
Table 2: WindSat configuration parameters
Figure 3: Illustration of the WindSat instrument (image credit: NRL)
WindSat is a yaw-spinning instrument; it uses a conically scanned 1.83 m parabolic offset reflector with multiple feeds (11 dual-polarized feed horns). The antenna beams view the Earth at incidence angles ranging from 50-55º. The orbit and antenna geometry result in a forward-looking swath of about 1000 km. The placement of external calibration targets allows for an aft swath of 350 km. The availability of fore and aft swath geometry enables evaluation of one-look versus two-look wind vector retrieval techniques. The WindSat instrument has a mass of 341 kg and 350 W of power consumption.
Swath definition: The position and pointing of each feedhorn relative to the main reflector determines its unique, unobstructed swath. The intersection of the 11 individual swaths is identified as the WindSat common fore and aft swaths. While some frequency bands have a swath width > 1200 km in the forward direction, the common swath is about 950 km (68º of scan angle); the aft common swath is 350 km (23º of scan angle). The aft common swath does not contain the 6.8 GHz channel, for which the aft swath does not intersect the other channels due to the position of that feed on the edge of the feedhorn layout. 16)
Table 3: Performance comparison of NPOESS requirements and WindSat parameters
The antenna/calibration subsystem consists of the main reflector, 11 feedhorns, a warm calibration load, and a cold sky calibration reflector. The main reflector is a 1.83 m diameter offset parabolic reflector fabricated of graphite epoxy with vapor deposited aluminum (VDA) coating. The reflector, along with the majority of the hardware, rotates at a nominal rate of 31.6 revolutions per minute. A composite truss with a very low coefficient of thermal expansion supports the main reflector. The 11 dual-polarized corrugated feedhorns provide the initial frequency channelization of the system and polarization splitting via OMT (Orthomode Transducers). The circularly polarized feeds use polarizers based on the design of Simmons. However, the WindSat polarizers achieve the necessary phase shift with tuning screws rather than dielectric vanes.
Instrument calibration: This absolute radiometric calibration procedure involves performing brightness temperature (Tb) measurements while the satellite's attitude is slowly varied in pitch to cause the antenna beams to point to space where the absolute brightness is a constant 2.7 K. These measurements are performed with the instrument in normal operational mode (i.e., antenna spinning and Tb sampling with both fore and aft viewing).Overall, the 22 channels have absolute Tb biases of order + 0.1 K when compared to the cold sky reflector received radiances. 17) 18) 19)
Initial operation of WindSat involved an extensive calibration and validation period. A large set of WindSat data were matched with environmental data from several sources, including the Global Data Assimilation System (GDAS), SSM/I, and QuikSCAT. Sensitivity to the wind direction was demonstrated and preliminary wind vector retrievals were developed in 2004 indicating significant potential. 20) Since then, ocean surface vector wind retrieval algorithms have been further developed, validated, and transitioned to operational use for the U.S. Navy and users of other agencies.
SMEI (Solar Mass Ejection Imager):
SMEI is a proof-of-concept imaging instrument designed and built by an international consortium comprising the US AFRL (Air Force Research Laboratory), the University of Birmingham, UK, the University of California, San Diego (UCSD), Boston College and Boston University. Funding is provided by NASA, AFRL and the University of Birmingham. SMEI is an all-sky camera experiment capable of imaging CMEs (Coronal Mass Ejections) as they propagate from the sun through the solar wind.
The objective is to monitor solar activity (detection of transient clouds of hot ionized gases - referred to as plasma) with the goal of more accurately predicting geomagnetic disturbances as they can have a serious effect on Earth-orbiting satellites, electrical power distribution networks, and long-distance radio communication. SMEI is required to image faint sources against a background that can be two orders of magnitude brighter. A differential photometric precision of about 0.1% is needed to separate the relatively faint emissions from CMEs and other propagating disturbances from the much brighter zodiacal dust cloud and stars. This separation and the necessary subtraction of the stellar contribution also requires accurate angular registration of individual images. The other major sources of background light are scattered sunlight, moonlight and Earth glow. 21) 22) 23) 24)
SMEI is designed to map large-scale variations in heliospheric electron densities from Earth orbit by observing Thomson-scattered sunlight from within the heliospheric volume (monitoring of solar optical radiation which is scattered off the plasma cloud as it moves out from the sun - measurement of the size, shape, speed, frequency, energy flux, mass, and momentum of CMEs). Conceived as an all-sky coronagraph, SMEI views the outward flow of structures in the solar atmosphere. These include CMEs, corotating structures (streamers), and other solar wind density enhancements (or depletions) such as the density variations behind shock waves. 25) 26)
Figure 4: Schematic view of the SMEI camera configuration (image credit: AFRL)
The SMEI instrument consists of three wide-angle CCD cameras each of which has a fan-beam field of view (FOV) of size 3º x 60º. The cameras with their baffles are mounted onto the S/C in such a way that the combined 180º long fan-beam of the three cameras sweeps around the entire sky once per orbit. The baffles reduce the amount of scattered sunlight reaching a camera by about 10 orders of magnitude when it is viewing a region near the sun. The CCDs are cooled to about -35ºC by passive radiators. A common data handling unit (DHU), interfacing to the S/C telemetry and telecommand systems, collects the data from all three cameras and controls their operation (a MIL-STD-1553B bus is used for on-board communications). The DHU includes a powerful processor system which is based around the digital signal processor SMJ320C50 of TI, operating at 19 MIPS making extensive use of field programmable gate arrays. The instrument mass of SMEI is 35 kg.
The flight software controls the data transfer between the cameras, data compression, data transfer from SMEI to the S/C telemetry system, and operational commands to SMEI from the ground. - The SMEI data is used to estimate the outbreak of CMEs (success means that 1-3 day warnings can be given with regard to Earth-intersecting solar shocks, etc.).
After the contribution of stars is removed, SMEI's basic product will be a 100 minute (one orbit) cadence of all-sky maps of heliospheric brightness flux with an angular resolution of about 1º and a photometric precision equivalent to the brightness of a 12th magnitude star.
The SMEI source data rate is 64 kbit/s. The heliospheric images are recorded in broadband white light without filters. The bandpass of the instrument is 450-1100 nm, determined mainly by the CCD response. The basic spatial resolution of the on-board binned pixels is 0.2º. The SMEI data analysis will be able to offer characteristic parameters of CMEs and shocks in the heliosphere (including the mass, energy and momentum fluxes, speed, pressure, shape, etc.), due to the instrument's high spatial and temporal resolution.
Figure 5: Artist's view of the SMEI instrumentation (image credit: AFRL)
Figure 6: The Coriolis spacecraft with the SMEI instrument (red rings) and the Windsat antenna prior to launch (image credit: NRL, AFRL) 27)
Figure 7: Photo of one of the SMEI cameras (image credit: University of Birmingham)
Figure 8: Illustration of FOV coverage of the three SMEI cameras (image credit: UCSD)
As of the fall of 2006, SMEI has seen over 200 CMEs; 30 of which were Earth-directed (halo) CMEs. With this major step of its mission achieved, SMEI is helping scientists to better understand, and predict with longer lead-times, the harmful solar effects on spacecraft and ground systems. 28)
1) Peter W. Gaiser, Karen M. St. Germain, Elizabeth M. Twarog, Gene A. Poe, William Purdy, Donald Richardson, Walter Grossmann, W. Linwood Jones, David Spencer, Gerald Golba, Jeffrey Cleveland, Larry Choy, Richard M. Bevilacqua, Paul S. Chang, "The WindSat Spaceborne Polarimetric Microwave Radiometer: Sensor Description and Early Orbit Performance," IEEE Transactions on Geoscience and Remote Sensing, Vol. 42, No 11, Nov. 2004, pp.2347-2361, URL: http://www.nrl.navy.mil/WindSat/pdfs/TGRS04_WindSat_Gaiser.pdf
3) Note: The NPOESS program is the merged successor program (next generation) of the weather satellite series: POES of NOAA and DMSP of DoD
5) John Stubstad, DoD Space S&T Community of Interest — Navy Success Story WindSat/Coriolis," Sept. 30, 2015, URL: http://www.defenseinnovationmarketplace.mil/resources/Space_ST_CoI_NDU_Brief.pdf
6) Information provides by Peter Gaiser of NRL.
7) Andrew Buffington, Mario M. Bisi, John M. Clover, P. Paul Hick, Bernard V. Jackson, Thomas A. Kuchar, Stephan D. Price, "Measurements of the Gegenschein brightness from the Solar Mass Ejection Imager (SMEI)," Icarus, Volume 203, Issue 1, September 2009, pp. 124-133
8) Janet C. Johnston, Paul E. Holladay, Thomas A. Kuchar, "Solar Mass Ejection Imager (SMEI) Mission: Final Report," Oct. 25, 2007, AFRL-VS-HA-TR-2007-1126, URL: http://www.dtic.mil/dtic/tr/fulltext/u2/a485524.pdf
9) Peter Gaiser, "WindSat Mission Overview and Status," June 5, 2006, URL: http://manati.star.nesdis.noaa.gov/SVW_nextgen/OVW%20Workshop/Gaiser_WindSat_Miami_05Jun06.ppt
10) Peter Gaiser, "WindSat Spaceborne Polarimetric Microwave Radiometer: Mission Overview," Polar Max 2006, URL: ftp://ftp.ifremer.fr/ifremer/cersat_salinity/exchange/jb/bibliography_ocean_passive
11) Information provided by Peter W. Gaiser of NRL, Washington D. C.
12) P. W. Gaiser, "WindSat - Remote Sensing of Ocean Surface Winds," 2004, URL: http://www.nrl.navy.mil/research/nrl-review/2004/featured-research/gaiser/
13) J. T. Johnson, W. H. Theunissen, S. W. Ellingson, "A Study of Sea Emission Models for WindSat," IGARSS 2003, Toulouse, France, July 21-25, 2003
14) K. M. St. Germain, P. W. Gaiser, "Spaceborne polarimetric radiometer and the WindSat Coriolis mission,",Proceedings of the IEEE Aerospace Conference, IEEE Vol. 5, 2000, pp. 159-164,
15) Nai-Yu Wang , P. S. Chang, R. M. Bevilacqua, C. K. Smith, P. W. Gaiser, "WindSat Atmospheric Forward Model Comparisons," Proceedings of IGARSS 2002, Toronto, Canada, June 24-28, 2002
16) W. E. Purdy, P. W. Gaiser, G. A. Poe, E. A. Uliana, T. Meissner, F. J. Wentz, "Geolocation and Pointing Accuracy Analysis for the WindSat Sensor," IEEE Transactions on Geoscience and Remote Sensing, Vol. 44, No 3, March 2006, pp. 496-505
17) W. L. Jones, J. Park, S. Soisuvarn, L. Hong, P. W. Gaiser, K. M. St. Germain, "Deep-Space Calibration of WindSat Radiometer," IEEE Transactions on Geoscience and Remote Sensing, Vol. 44, No 3, March 2006, pp. 476-495
18) W. L. Jones, J. Park, P. W. Gaiser, T. T. Wilheit, "Deep-Space Calibration of WindSat Radiometer," Proceedings of IGARSS 2004, Anchorage, AK, USA, Sept. 20-24, 2004
19) Special Issue (18 papers) on the WindSat Spaceborne Polarimetric Radiometer -Calibration/Validation and Wind Vector Retrieval," IEEE Transactions on Geoscience and Remote Sensing, Vol. 44, No 3, March 2006
20) P. W. Gaiser, E. M. Twarog, Li Li, K. M. St. Germain, G. A. Poe, W. Purdy, Z. Jelenak, P. S. Chang, L. Connor, "The WindSat Space Borne Polarimetric Microwave Radiometer: Sensor Description and Mission Overview," Proceedings of IGARSS 2004, Anchorage, AK, USA, Sept. 20-24, 2004
23) B. V. Jackson, A. Buffington, P. Hick, S.W. Kahler, S. L. Keil, R. C. Altrock, G. M. Simnett, D. F. Webb, "The Solar Mass Ejection Imager," Phys. Chem. Earth, 22, 441, 1997
24) D. F. Webb, J. C. Johnston, R. R. Radick, "The Solar Mass Ejection Imager (SMEI): A New Tool for Space Weather," EOS Transactions of AGU, Vol. 83, No 4, Jan. 22, 2002, pp. 33-39
25) D. F. Webb, D. R. Mizuno, A. Buffington, M. P. Cooke, C. J. Eyles, C. D. Fry, L. C. Gentile, P. P. Hick, P. E. Holladay, T. A. Howard, J. G. Hewitt, B. V. Jackson, J. C. Johnston, T. A. Kuchar, J. B. Mozer, S. Price, R. R. Radick, G. M. Simnett, S. J. Tappin, "Solar Mass Ejection Imager (SMEI) observations of coronal mass ejections (CMEs) in the heliosphere," Journal of Geophysical Research, Vol. 111, A12101, doi:10.1029/2006JA011655, 2006
26) B. V. Jackson, P: P. Hick, A. Buffington, R. Gold, G. M. Simnett, C. J. Eyles, M. P. Cooke, "SMEI: Design and Development of an Earth-Orbiting All-Sky Coronagraph," Proceedings of SPIE Vol. 5171, 2004, pp. 1-5
27) B. V. Jackson, M. M. Bisi, P. P. Hick, A. Buffington, J. M. Clover, D. F. Webb, "SMEI Observations of the Heliosphere During WHI," URL: http://ihy.boulder.swri.edu/WHI/AGUMAY08/POSTERS/Jackson_SMEI.pdf
28) "AFRL Solar Mass Ejection Imager New Tool for Space Weather," URL: http://www.kirtland.af.mil/shared/media/document/AFD-070404-102.pdf
The information compiled and edited in this article was provided by Herbert J. Kramer from his documentation of: "Observation of the Earth and Its Environment: Survey of Missions and Sensors" (Springer Verlag) as well as many other sources after the publication of the 4th edition in 2002. - Comments and corrections to this article are always welcome for further updates (email@example.com).