Minimize FY-3 (FengYun-3)

FY-3 (FengYun-3) 2nd Generation Polar Orbiting Meteorological Satellite Series

Spacecraft    Launch    Mission Status    Sensor Complement   Ground Segment   References

The FY-3 series of CMA/NSMC (China Meteorological Administration/National Satellite Meteorological Center) represents the second generation of Chinese polar-orbiting meteorological satellites (follow-on of FY-1 series). The FY-3 series represents a cooperative program between CMA and CNSA (China National Space Administration); it was initially approved in 1998 and entered full-scale development in 1999. Key aspects of the FY-3 satellite series include collecting atmospheric data for intermediate- and long-term weather forecasting and global climate research. 1) 2) 3) 4) 5) 6) 7) 8) 9) 10) 11) 12) 13) 14)

The overall objectives of the FY-3 series are:

• To provide global measurements of 3-D temperature and moisture soundings of the atmosphere, and to measure cloud and precipitation parameters in support of NWP (Numerical Weather Prediction).

• To provide global imagery of large-scale meteorological and/or hydrological events and biosphere environment anomalies

• To provide geophysical parameters in support of global change and climate monitoring.

• To provide global and local meteorological information for specialized meteorological users working in services of aviation, marine, etc.

• To collect and relay environmental data from the ground segment.

• The FY-3 operational phase will have two polar-orbiting satellites in service (one in the AM and one in the PM orbit, payload will be different for AM/PM satellites, time slots could be coordinated through WMO).

There are two development phases considered for the FY-3 series:

1) Experimental phase in the time period 2008-2010 with two spacecraft launches. These satellites have only limited sounding capabilities.

- FY-3A launch on May 27, 2008, LTDN (Local Time on Descending Node) = 10:00 hours.

- FY-3B launch on Nov. 4, 2010, LTDN = 14:00 hours.

2) Operational service phase beyond 2012. These satellites will have enhanced sounding and imaging capabilities.

- FY-3C launch on Sept. 23, 2013, LTDN =10:00 hours.

- FY-3D launch on November 14, 2017, LTDN = 14 hours.

The CMA plans call for a constellation of two FY-3 spacecraft in orbit, one in the morning slot (AM) and one in the afternoon slot (PM).

Spacecraft

Launch (projected launch)

LTDN (Local Time on Descending Node)

Mission Service Type

FY-3A

May 27, 2008

10:00 hours

R&D (Experimental)

FY-3B

Nov. 04, 2010

13:30 hours

R&D (Experimental)

FY-3C

Sept. 23, 2013

10:00 hours

Operational mission with MWHS-II (upgrade) and GNOS (new) instruments

FY-3D

Nov. 14, 2017

14:00 hours

Operational

FY-3E

2018

10:00 hours

Operational

FY-3F

2020

14:00 hours

Operational

Table 1: Overview of FengYun-3 spacecraft series of CMA/NSMC

In comparison with FY-1 spacecraft series, the principal improvements in the FY-3 series include:

1) Atmospheric sounding capacity

2) Microwave imaging capacity

3) Optical imaging with spatial resolution from 1 km to 250 m

4) Atmospheric composition detecting capacity

5) Radiation budget measuring capacity

6) Global data acquisition from within one day to within two to three hours.

The FY-3 series represents in fact a new chapter in the history of the Chinese meteorological satellites and satellite meteorology. The FY-3 series provides global air temperature, humidity profiles, and meteorological parameters such as cloud and surface radiation required in producing weather forecasts, especially in making medium numerical forecasting.

The FY-3 series satellites monitor large-scale meteorological disasters, weather-induced secondary natural hazards and environment changes, and provides geophysical parameters for scientific research in climate change and its variability, climate diagnosis, and predictions. The FY-3 series renders global and regional meteorological information for aviation, ocean navigation, agriculture, forestry, marine activities, hydrology, and many other economic sectors.

Note: The FY-3C spacecraft is equipped with all of the 11 payloads, but MWTS is upgraded to MWTS-II, MWHS to MWHS-II, and a new payload, GNOS (GNSS Occultation Sounder), is on board FY-3C. MWTS-II will increase the channels from 4 to 13, and MWHS-II will increase the channels from 5 to 15. GNOS will improve the measured temperature and moisture profiles in the upper atmosphere. 15)

Tentative Schedule for Future FY LEO Series:

For the FengYun LEO satellites, after FY-3A/B, the future FY-3 models (FY-3C/D/E/F) have been approved. CMA plans to develop certain observational capabilities for the follow-up models, for instance, the WindRAD for sea winds, the GAS for greenhouse gases absorption measurement. The atmospheric sounding shall be enhanced by replacing the current IRAS with HIRAS (Hyperspectral Infrared Atmospheric Sounder), and by the deployment of radio occultation sounder GNOS. Also, there is a plan to develop a rainfall measurement satellite: FY-3RM (2019), that shall carry Ku/Ka band radar, microwave sounding and imaging instruments. 16)

Feasibility Study on FY-3 Use of Early Morning Orbit: FY-3 series serves at least for another 15 years with the additional four satellites. Sixteen (16) improved or new instruments will be configured on FY-3C/D/E/F. It is unrealistic for CMA to fly three orbits (AM, PM, and Early Morning) at the same time. Since FY-3C & 3D are being manufactured now, there is no chance to make them changed for the Early Morning orbit. FY-3E is possibly the only opportunity for CMA to fly early morning orbit before 2020.

FY-3 Operational Satellite Instruments

FY-3C

FY-3D

FY-3E

FY-3F

MERCI (Medium Resolution Spectral Imager) (I, II)

√ (I)

√ (II)

√ (II)

√ (II)

MWTS (Microwave Temperature Sounder), (II)

MWHS (Microwave Humidity Sounder). (II)

MWRI (Microwave Radiation Imager)

 

WindRad (Wind Radar)

 

 

 

GAS (Greenhouse Gases Absorption Spectrometer)

 

 

HIRAS (Hyperspectral Infrared Atmospheric Sounder)

 

OMS (Ozone Mapping Spectrometer)

 

 

 

GNOS (GNSS Occultation Sounder)

ERM (Earth Radiation Measurement), (I, II)

√ (I)

 

√ (II)

 

SIM (Solar Irradiation Monitor), (I, II)

√ (I)

 

√ (II)

 

SES (Space Environment Suite)

IRAS (Infrared Atmospheric Sounder)

 

 

 

VIRR (Visible and Infrared Radiometer)

 

 

 

SBUS (Solar Backscatter Ultraviolet Sounder)

 

 

 

TOU (Total Ozone Unit)

 

 

 

Table 2: FY-3C/D/E/F payload configuration

 


 

Spacecraft:

The FY-3 series spacecraft are being designed and developed at SAST (Shanghai Academy of Spaceflight Technology). The spacecraft structure is a hexahedron of 4.4 m x 2.0 m x 2.0 m in stowed configuration and 4.4 m x 10 m x 3.8 m in the deployed state. The total spacecraft launch mass is estimated to be 2450 kg. The FY-3 features one solar panel mounted on one side of the satellite's main body (making the span length of the satellite 10 m in flight configuration). The attitude control of the satellite employs three-axis stabilization (bias momentum control) with a pointing precision of 50 m on the ground. The ADCS (Attitude Determination and Control Subsystem) employs a star sensor for attitude sensing.

The FY-3 bus contains three major modules: a service module, a payload module, and a propulsion module. The spacecraft design life is 3 years.

Spacecraft structure

Separated bay design, combined structure of center supporting cylinder and guest board for service module and propulsion module; combined structure of baffle plate and truss.

Thermal control

Thermal design for separated bay, relying mainly on passive thermal control assisted by active thermal control.

Spacecraft dimensions

Body size: 4400 mm x 2000 mm x 2000 mm (x, y, z)
Flight size: 4460 mm x 10000 mm x 3790 mm (x, y, z)

Attitude and orbit control

Attitude pointing accuracy = 0.3º (x, y, z)
Attitude measuring accuracy = 0.05º (x, y, z)
Attitude stability = 0.004º/s (x, y, z)

Power supply

Solar array of 22.464 m2 with an output power of 2.48 kW (EOL), average = 1100 W
Two NiCd battery units (36 cells) each of 50 Ah capacity provide power in ecliptic orbit phases

RF communications

The TT&C system uses a unified S-band system assisted by GPS

Data transmission

Real-time: L-band with BPSK modulation, data rate = 4.2 Mbit/s
Real-time: X-band with QPSK modulation, data rate = 18.2 Mbit/s
Playback: X-band with QPSK modulation, data rate = 93 Mbit/s

Onboard data recorder

144 Gbit capacity

Design life

3 years with a goal of 4 years

Spacecraft mass

2300 kg at launch, the amount of hydrazine is about 64 kg

Table 3: System design parameters of the FY-3 satellite series

FY3_Auto15

Figure 1: Illustration of the FY-3 satellite (image credit: CMA/NSMC)

 

Launch: A launch of the first satellite in the series, FY-3A, took place on May 27, 2008. The spacecraft was launched on a LM-4C launch vehicle from the Taiyuan Launch Center. 17)

Orbit of FY-3A: Sun-synchronous near-circular orbit, average altitude of 836.4 km, inclination of 98.75º, period = 101.49 min, local solar time on descending node at 10:10 hours, 14.1735 orbits/day, tropical cycle of about 6 days.

Launch: The FY-3B spacecraft was launched on Nov. 4, 2010 (UTC). The spacecraft was launched on a LM-4C launch vehicle from the Taiyuan Launch Center.

Orbit of FY-3B: Sun-synchronous near-circular orbit, average altitude of 836.4 km, inclination of 98.75º, period = 101.49 min, local solar time on ascending node at 13:30 hours, 14.1735 orbits/day, tropical cycle of about 6 days.

Launch: The FY-3C spacecraft was launched on Sept. 23, 2013. The spacecraft was launched on a LM-4C launch vehicle from the Taiyuan Launch Center. 18) 19)

Orbit of FY-3C: Sun-synchronous near-circular orbit, average altitude of 836 km, inclination of 98.75º, period = 101.49 min, LTDN (Local solar Time on Descending Node) at 10:00 hours, 14.1735 orbits/day, tropical cycle of about 6 days.

RF communications: The spacecraft communications links are S-band, L-band and X-band. Commands are via S-band only. Command and telemetry links are active in parallel. The S-band section of the communications subsystem provides primary telemetry and command (TT&C) service to and from FY-3A ground stations. The L-band and X-band section of the communication subsystem provide the science and engineering data downlink for the FY-3A common spacecraft.

Three modes of operation are provided:

1) DPT (Delayed Picture Transmission) - a direct playback mode. All the stored science and engineering data onboard (except the MERSI data) is transmitted in high data rate at 110 Mbit/s, to the NSMC national ground playback stations (Beijing, Guangzhou, Urumuqi, Jamusi, and Kiruna) whenever the satellite is passing over the acquisition range of these stations. The transmission band frequency will be within the range of 8025 - 8400 MHz, encoding: CONV (7, ¾).

2) MPT (Mission Picture Transmission). This mode provides the direct broadcast in X-band. The main function of this data format is for real-time broadcasting of the science and engineering data of the MERSI instrument with a data rate of 18.7 Mbit/s to any receiving station within view of the spacecraft. The broadcasting band frequency is in the range 7750-7850 MHz, QPSK modulation, encoding: CONV (7, ¾).

3) AHRPT (Advanced High Resolution Picture Transmission) -also referred to as HRPT. The AHRPT transmission band frequency is within the frequency range of 1698-1710 MHz at the data rate of 4.2 Mbit/s (real-time global broadcasting). The modulation is QPSK (Quadra‐Phase Shift Keying), encoding: CONV (7, ¾), real-time broadcasting. 20)

Launch: The FY-3D spacecraft was launched on 14 November 2017 (18:35 UTC; 2:35 Beijing Time on 15 Nov. 2017) on a LM-4C launch vehicle from the TSLC (Taiyuan Satellite Launch Center, China. 21)

Orbit of FY-3D: Sun-synchronous near-circular orbit, average altitude of 836 km, inclination of 98.75º, period = 101.49 min, LTAN at 14:00 hours.

From the view of consistency of meteorological satellite sequence, FY-3D satellite will replace FY-3B which has been operated for 8 years in space, launch network observation with FY-3C, and stand on duty with FY-4A at 800 km and 36,000 km, respectively, constituting the new-generation high-low orbit meteorological satellite constellation.

 

Spacecraft

Orbit

Status

Launch

FY-3A (experimental)

SSO, AM (10:15 hrs on LTDN)

R&D, nominal operations

May 27, 2008

FY-3B (experimental)

SSO, PM (14:40 hrs on LTAN)

R&D, nominal operations

November 5, 2010

FY-3C

SSO, AM (10:00 hrs on LTDN)

1st operational mission in series

September 23, 2013

FY-3D

SSO, PM (14:00 hrs on LTAN)

2nd operational mission

November 14, 2017

FY-3E

SSO, EM (Early Morning)

planned operational mission

2018

FY-3F

SSO, PM

planned operational mission

2019

FY-3 RF 1/2 (experimental)

Inclined orbit

planned R&D mission

2019-2025,TBD

FY-3G

TBD

planned operational mission

2021-2025,TBD

FY-3H

SSO, EM (Early Morning)

planned operational mission

2021-2025,TBD

Table 4: Overview of FY-3 LEO constellation missions of CMA as of fall 2015 (Ref. 29)

To support global NWP (Numerical Weather Prediction) services within the coordination framework of CGMS (Coordination Group for Meteorological Satellites), Dr. Zheng made a commitment in WMO (World Meteorological Organization) EC-66 in 2014 22) that CMA will adjust its satellite plan to develop an early morning orbit mission. Hence, the FY-3E mission has now been changed as an early morning orbit satellite rather than the previously assigned morning orbit (AM).

FY3_Auto14

Figure 2: Schematic illustration of the FY-3A spacecraft (image credit: CMA/NSMC)

 


 

Mission status:

• On 8 Dec. 2017, the FY-3D spacecraft acquired the first visible light image and transmitted it to the ground. 23)

- From mid-December, FY-3D will embark on a half-year in-orbit testing, and is on track to complete operational application before the flood season in 2018. At that time, it will form network observation operation with FY-3C.

- Accordingt to Yang Jun, director of NSMC (National Satellite Meteorological Center), FY-3D boasts a very high imaging quality judged by the detail and texture of the image. Marine and land information of South China Sea, the Yarlung Zangbo River, Qinghai-Tibet Plateau, and Northwest Desert are all visible from the image, as well as endemic information in salt lake, alluvial fan, and snow cover.

- The mission of FY-3D's first image was acquired by satellite ground stations in Guangzhou, Urumqi, and Kiamusze. At present, reception equipment in 5 ground stations at home and abroad in charge of global satellite data reception and transmission is in functional state. Especially the activation of Antarctica satellite data reception station ensures that 90% global observation data is transmitted to China 80 minutes upon observation. Satellite-ground data transmission rate has augmented by 30%. The computing capacity is up by 17.5 times and data storage capacity has multiplied by about 10 times.

FY3_Auto13

Figure 3: The first visible light image of FY-3D (true color image of 3 channels of MERSI-2), showing marine and land information of the South China Sea (image credit: CMA)

• The FY-3C mission is operational in 2018.

• According to WMO, the FY-3C mission is operational in 2017 with the following exemptions: 24)

- MWTS-2 failed on 2 February 2015. Operational service was suspended on 31 May 2015 for anomaly investigation. Recovered from 30 July onwards.

- Power supply limitation has led to turn off MERSI and MWTS on 31 May 2015.

FY3_Auto12

Figure 4: Global nephogram (image of clouds) of the VISR (Visible-Infrared Scanning Radiometer) on FY-3C (image credit: CMA)

• December 2016: Observations from MWHS-1 on board FY-3B and its more advanced successor, MWHS-2, on board FY-3C have been received at the UK Met Office since 2012 and 2014, respectively. Since then, both instruments have been the subject of several validation studies conducted internally at the Met Office and in collaboration with ECMWF (European Centre for Medium-Range Weather Forecasts). These studies concluded that observations from MWHS-1 and MWHS-2 183 GHz channels are, once appropriately bias corrected, of a quality matching well established operational instruments of similar sounding capability. 25)

- Several low and high resolution full system experiments showed the benefit of adding MWHS-1 and MWHS-2 observations to the global model. As a consequence, MWHS-2 has been successfully integrated into parallel suite 37 in November 2015, and has been assimilated in operations since March 2016, while MWHS-1 has been successfully integrated to the parallel suite 38 due to become operational on November 1, 2016.

- MWHS-2 operational monitoring showed the presence of a small residual bias in channels 11 and 12, and recurrent transient rises of temperature that are correlated to large bias changes affecting the channels 13 and 14. Nevertheless, forecast sensitivity to observations impacts analyses confirmed that MWHS-2 contributes to a significant level to the reduction of model forecast errors.

- Work is currently under way to implement the assimilation of MWHS-2 183 GHz channels over land. The addition of land observations is expected to further reduce forecast errors. — Finally, a bilateral Met Office-ECMWF evaluation of FY-3C MWRI data will lead the way to pre-operational testings in 2017.

• The FY-3A spacecraft was retired on January 5, 2015, ending the global image coverage service. FY-3A provided a substantial contribution to ocean and ice monitoring, climate monitoring - and a significant contribution to atmospheric chemistry and space weather. 26)

- FY-3A mission instruments: MWRI failed soon after launch; IRAS failed in October 2008 (inactive); SBUS failed in December 2008 (inactive); ERM-1 failed in May 2008 (inactive); MWTS-1 failed in December 2012 (inactive).

• The FY-3B spacecraft is operating in 2016 providing operational meteorology. 27)

- FY-3B mission instruments: ERM-1 failed in August 2011 (inactive).

• The FY-3C spacecraft and its instruments are operating in 2016. 28)

- FY-3C mission instruments: MWTS-2 failed on Feb. 2, 2015. Operational service suspended on 31 May 2015 for anomaly investigation. Recovered from 30 July onwards.

FY3_Auto11

Figure 5: FY-3 instrument status as of November 2015 according to Ref. 29)

FY3_Auto10

Figure 6: In-orbit FengYun Satellites(6/7) (6 operational, 1 retired) as of fall 2015 (image credit: CMA) 29)

• Feb. 2015: A new methodology is developed to detect the cloud structures at different vertical levels using the dual oxygen absorption bands located near 60 GHz and 118 GHz, respectively. Observations from MWTS (Microwave Temperature Sounder) and MWHS (Microwave Humidity Sounder) on board the recently launched Chinese FengYun-3C satellite are used to prove the concept. It is shown that a paired oxygen MWTS and MWHS sounding channel with the same peak weighting function altitude allows for detecting the vertically integrated cloud water path above that level. A cloud emission and scattering index (CESI) is defined using dual oxygen band measurements to indicate the amounts of cloud liquid and ice water paths. The CESI distributions from three paired channels reveal unique three-dimensional structures of clouds and precipitation within Super Typhoon Neoguri that occurred in July 2014. 30)

• Status of FY-3 satellite series in January 2015: 31)

- FY-3A (launch on May 27, 2008): Only reduced operations are possible in 2015. MWRI failed soon after launch; IRAS failed in October 2008; SBUS failed in December 2008; ERM failed in May 2010; MWTS failed in December 2012.

- FY-3B (launch on Nov. 4, 2010): The FY-3B spacecraft and its payload are operating nominally in 2015.

- FY-3C (launch on Sept. 23, 2013): The FY-3C spacecraft and its payload are operating nominally in 2015.

• October 2014: FY-3C/MERSI has some remarkable improvements compared to the previous MERSIs including better SRF (Spectral Response Function) consistency of different detectors within one band, increasing the capability of lunar observation by space view (SV) and the improvement of radiometric response stability of solar bands. During the In-orbit verification (IOV) commissioning phase, early results that indicate the MERSI representative performance were derived, including the signal noise ratio (SNR), dynamic range, MTF, B2B registration, calibration bias and instrument stability. The SNRs at the solar bands (Bands 1–4 and 6-20) was largely beyond the specifications except for two NIR bands. 32)

The FY-3C spacecraft and its payload was declared operational on May 5, 2014, according to CMA. 33) 34)

• The FY-3A and FY-3B spacecraft and their payloads are operating nominally in 2013 (Ref. 35).

The FY-3 project conducted cross-calibrations between the MWTS/FY-3 channels with those of the AMSU-A and AMSU-B channels of the NOAA fifth-generation satellites (NOAA-15, -16, -17, -18 and -19) using the RM (Ray-Matching) method over the South Pole and North Pole study area in 2011. 35)

The results show that the in-orbit calibrations of AMSU-A on the fifth-generation NOAA satellites are identical with averaging errors less than 0.45 K, except the channel 8, in which the averaging error is up to -1.53 K. No obvious impact of solar illumination on AMSU-A/NOAA channels was found. - The in-orbit calibrations of MWTS/FY-3 channels are basically consistent with those of the AMSU-A/NOAA-19 channels, and a small influence of solar illumination on MWTS/FY-3B channel 4 was observed.

Large in-orbit calibration discrepancies were found between the MWHS/FY-3 channels and the AMSU-B/NOAA-16 channels, especially in MWHS/FY-3A channel 5. Strong influences of solar illumination on MWHS/FY-3 channels 3, 4 and 5 were observed.

• The FY-3A and FY-3B spacecraft and their payloads are operating nominally in 2012. 36)

- On 16 December 2011, sounding data from FY-3B began to be received and test dissemination started on EUMETCast. The new products will be made available to EUMETSAT Member States on January 24, 2012. This is in addition to the data already received and disseminated from FY-3A since the end of 2010. 37)

The addition of FY-3B data to EUMETCast follows discussions between EUMETSAT and CMA. During a bilateral meeting between the two organizations in May 2011 in Geneva, CMA agreed to add FY-3B data to the FY-3A data it already shares with EUMETSAT and its Member States.

• On June 2, 2011, the FY-3B spacecraft started its operational service after finishing a six-month commissioning period (the spacecraft was launched on Nov. 4, 2010). The operational service was handed over to CMA on May 27, 2011. The FY-3B will join the FY-3A to create a comprehensive weather satellite system. 38)

The MWRI instrument of FY-3B is providing continuous and stable data sets since launch. Compared with the MWRI instrument on FY-3A, the MWRI instrument on FY-3B features a higher stability and a much lower nonlinearity. 39)

• In Jan. 2011, the FY-3B spacecraft is on-orbit (launch Nov. 4, 2010, in the afternoon orbit). All 11 instruments of the payload have been switched on. The spacecraft and its payload are currently in their commissioning phase conducted by the NSMC (National Satellite Meteorological Center) of CMA. 40) 41)

• The FY-3A spacecraft and its payload are operating nominally in 2011. 42)

• On Nov. 7, 2010, a first image of the VIRR instrument was obtained from the FY-3B spacecraft. 43)

• The FY-3A spacecraft and its payload are operating nominally in the fall of 2010.44)

• FY-3A started its operational phase on January 12, 2009. After the completion of the commissioning phase, the spacecraft operations was handed over from CNSA to CMA. 45) 46)

• After launch (May 27, 2008) the spacecraft and its payload were in the commissioning phase. However, in the following months, FY-3A has served the Beijing 2008 Olympic Games and the flood season in 2008 at the same time.

FY3_AutoF

Figure 7: Typhoon Fung-wong monitored by the MERSI instrument of FY-3A on 27 July, 2008 (image credit: NSMC)

FY3_AutoE

Figure 8: Total ozone in DU (Dobson Units) monitored from TOU on Nov. 1, 2008 (image credit: NSMC)

 


 

Sensor complement of FY-3D mission (GAS, GNOS, HIRAS, MERSI-2, MWHS-2, MWRI, MWTS-2, SES/IPM, SES/WAI, SES/SEM)

Main mission: operational meteorology. Substantial contribution to ocean and ice monitoring, climate monitoring, atmospheric chemistry and space weather. 47)

 

GAS (Greenhouse Gases Absorption Spectrometer)

Grating spectrometer operating in four NIR/SWIR bands. Objective: Atmospheric chemistry, measurement of CO2, CH4, CO, N2O. Scanning technique: Two views, nadir or pointing to sunglint.

Spectral range (µm)

Spectral range (cm-1)

Spectral resolution

SNR @ expected input radiance

0.75-0.77 µm

13000-13300 cm-1

0.60 cm -1

>300

1.56-1.72 µm

5800-6400 cm-1

0.27 cm-1

>300

1.92-2.08 µm

4800-5200 cm-1

0.27 cm-1

>300

2.20-2.38 µm

4200-4550 cm-1

0.27 cm-1

>300

Table 5: Parameters of GAS instrument

 

GNOS (GNSS Radio Occultation Sounder)

Objective: Temperature/humidity sounding with highest vertical resolution; also space weather. Same description as for FY-3A.

 

HIRAS (Hyper-spectral Infrared Atmospheric Sounder)

HIRAS is a Michelson interferometer with three bands, 1370 channels (replacing IRAS on FY 3A, 3B and 3C ).

The objective is temperature/humidity sounding, ozone profile and total-column green-house gases.

Scanning type: 58 pixels / scan line, arranged in 2 x 2 arrays; swath width of 2250 km.

Instrument mass = 120 kg, power = 129 W.

Spectral range (µm)

Spectral range (cm-1)

Spectral resolution(unapodized)

NEΔT @ specified scene temperature

8.80-15.39 µm

650-1136 cm-1

0.625 cm-1

0.15-0.4 K @ 250 K

5.71-8.26 µm

1210-1750 cm-1

1.25 cm-1

0.1-0.7 K @ 250 K

3.92-4.64 µm

2155-2550 cm-1

2.5 cm-1

0.3-1.2 K @ 250 K

Table 6: Parameters of the HIRAS instrument

 

MERSI-2 (Medium Resolution Spectral Imager -2)

MERSI-2 is a 25-channel VIS/IR spectroradiometer (replacing and merging MERSI-1 on FY-3A/3B and VIRR on FY-3A//3B/3C ). Scanning technique: Cross-track: 2048 detectors for channels at 1000 m resolution, or 8192 detectors for channels at 250 m resolution, swath 2900 km; Along-track: ten 10 km lines every 1.5 s.

Resolution: 250 m or 1.0 km at s.s.p. (sub-satellite point).

Coverage/Cycle: Global coverage once/day (VIS/NIR/SWIR channels), twice/day (MWIR/TIR).

Center wavelength

Bandwidth

SNR or NEΔT @ specified input

IFOV at s.s.p.

412 nm

20 nm

300 @ 44.9 W m-2 sr-1 µm-1

1000 m

443 nm

20 nm

300 @ 41.9 W m-2 sr-1 µm-1

1000 m

470 nm

50 nm

100 @ 35.3 W m-2 sr-1 µm-1

250 m

490 nm

20 nm

300 @ 32.1 W m-2 sr-1 µm-1

1000 m

550 nm

20 nm

100 @ 29.0 W m-2 sr-1 µm-1

250 m

555 nm

20 nm

500 @ 21 W m-2 sr-1 µm-1

1000 m

650 nm

50 nm

100 @ 22 W m-2 sr-1 µm-1

250 m

670 nm

20 nm

500 @ 10 W m-2 sr-1 µm-1

1000 m

709 nm

20 nm

500 @ 6.9 W m-2 sr-1 µm-1

1000 m

746 nm

20 nm

500 @ 9.6 W m-2 sr-1 µm-1

1000 m

865 nm

20 nm

500 @ 6.4 W m-2 sr-1 µm-1

1000 m

865 nm

50 nm

100 @ 25 W m-2 sr-1 µm-1

250 m

905 nm

20 nm

200 @ 10.0 W m-2 sr-1 µm-1

1000 m

936 nm

20 nm

100 @ 3.6 W m-2 sr-1 µm-1

1000 m

940 nm

50 nm

200 @ 15.0 W m-2 sr-1 µm-1

1000 m

1240 nm or 1030 nm

20 nm

100 @ 5.4 W m-2 sr-1 µm-1

1000 m

1380 nm

20 nm or 30 nm

60/100 @ 6 W m-2 sr-1 µm-1

1000 m

1640 nm

50 nm

200 @ 7.3 W m-2 sr-1 µm-1

1000 m

2130 nm

50 nm

100 @ 1.2 W m-2 sr-1 µm-1

1000 m

3.80 µm

0.18 µm

0.25 K @ 270 K

1000 m

4.05 µm

0.155 µm

0.25 K @ 300/380 K

1000 m

7.20 µm

0.50 µm

0.30 K @ 270 K

1000 m

8.55 µm

0.30 µm

0.25 K @ 270 K

1000 m

10.8 µm

1.0 µm

0.4 K @ 300 K

250 m

12.0 µm

1.0 µm

0.4 K @ 300 K

250 m

Table 7: Parameters of the MERSI-2 instrument

 

MWHS-2 (Micro-Wave Humidity Sounder -2)

Objective: Humidity sounding in nearly-all-weather conditions. Also, precipitation.

MWHS-2 is an instrument with 15 frequencies, including bands of 183 GHz (for humidity), and 118 GHz (for supporting information on temperature). MWHS-2 is replacing the MWHS-1 of FY-3A and FY-3B.

Central frequency (GHz)

Bandwidth (MHz)

Polarizations

NEΔT

89

1500

V

1.0 K

118.75±5.0

2000

H

1.0 K

118.75±3.0

1000

H

1.0 K

118.75±2.5

200

H

1.6 K

118.75±1.1

200

H

1.6 K

118.75±0.8

200

H

1.6 K

118.75±0.3

165

H

1.6 K

118.75±0.2

100

H

2.0 K

118.75±0.08

20

H

2.6 K

150

1500

V

1.0 K

183±7

2000

H

1.0 K

183±4.5

2000

H

1.0 K

183±3

1000

H

1.0 K

183±1.8

700

H

1.0 K

183±1

500

H

1.0 K

Table 8: Parameters of the MWHS-2 instrument

 

MWRI (Micro-Wave Radiation Imager)

Objective: Multi-purpose imagery with emphasis on precipitation.

MWRI is a 5 frequencies, 10 channels instrument and a new development. Operations of MWRI on FY-3A stopped in 2010.

Scanning technique: Conical: 53.1° zenith angle, swath 1400 km. Scan rate: 35.3 scan/min = 11.2 km/scan

Resolution: Changing with frequency, consistent with an antenna diameter of 90 cm.

Coverage/cycle: Global coverage once/day

Instrument mass =175 kg, power = 125 W, data rate = 100 kbit/s.

Central frequency (GHz)

Bandwidth (MHz)

Polarizations

NEΔT

IFOV

Pixel size

10.65

180

V, H

0.5 K

51 x 85 km

40 x 11.2 km

18.7

200

V, H

0.5 K

30 x 50 km

40 x 11.2 km

23.8

400

V, H

0.5 K

27 x 45 km

20 x 11.2 km

36.5

400

V, H

0.5 K

18 x 30 km

20 x 11.2 km

89

3000

V, H

0.8 K

9 x 15 km

10 x 11.2 km

Table 9: Parameters of the MWRI instrument

 

MWTS-2 (Micro-Wave Temperature Sounder - 2)

Objective: Temperature sounding in nearly-all-weather conditions

MWTS-2 is an evolution of MWTS-1 flown on FY-3A and FY-3B

Scanning technique: Cross-track: 30 steps of 32 km s.s.p., swath width = 2250 km

Resolution: 32 km at s.s.p.

Coverage/cycle: Near-global coverage twice/day

Central frequency (GHz)

Bandwidth (MHz)

Polarization

NEΔT

50.30

180

V or H

1.2 K

51.76

400

V or H

0.75 K

52.8

400

V or H

0.75 K

53.596

400

V or H

0.75 K

54.40

400

V or H

0.75 K

54.94

400

V or H

0.75 K

55.50

330

V or H

0.75 K

57.290

330

V or H

0.75 K

57.290 ± 0.217

78

V or H

1.2 K

57.290 ± 0.322 ± 0.048

36

V or H

1.2 K

57.290 ± 0.322 ± 0.022

16

V or H

1.7 K

57.290 ± 0.322 ± 0.010

8

V or H

2.4 K

57.290 ± 0.322 ± 0.0045

3

V or H

3.6 K

Table 10: Parameters of the MWTS-2 instrument

 

SES/IPM (Space Environment Suite / Ionospheric PhotoMeter)

Objective: X-ray spectrometry of the ionosphere

Description not available. Presumably, imaging spectrometer for the X-ray 3-100 keV

Scanning technique: Ionospheric viewing from a sun-synchronous orbit

Resolution: 80 km at the s.s.p.

Coverage(cycle: Global daily. Sampling at 60 s intervals.

 

SES/WAI (Space Environment Suite / Ionospheric PhotoMeter)

Objective: Observation of Aurora

Description not available. Presumably, UV imaging spectrometer for the range 115-180 nm (inclusive of the H Lyman-α line at 121.6 nm) and fluxmeter for the VIS range 427.8-630 nm

Scanning technique: Earth's limb observation from a sun-synchronous orbit

Resolution: 300 km (for the limb view)

Coverage/cycle: Full ionosphere, with sampling at 22 s (UV) and 180 s (VIS) intervals.

 

SES/SEM (Space Environment Suite / SEM (FY-3C))

SWS/SEM/HEPD: Space Weather Suite / Space Environment Monitor / High Energy Particle Detector

Objective: Space weather - Charged particles at platform level

Spectrometer for electrons (0.25-2.0 MeV), protons (6.4-38 MeV) and alpha-particles (15-60 MeV)

Scanning technique: N/A (in-situ in the platform environment)

SWS/SEM/IMS: Space Weather Suite / Space Environment Monitor / Ionosphere Measurement Sensor

Objective: To measure the ionospheric electron temperature and density, and platform charge and dose

Specially arranged Langmuir Probe for electron temperature (0-1 eV) and density in the 10- 106 e/cm3 range

Scanning technique: In-situ measurement in a sun-synchronous orbit.