Minimize GEO-KOMPSAT-2

GEO-KOMPSAT-2 (Geostationary - Korea Multi-Purpose Satellite-2) Program / Cheollian-2 / GK-2

Spacecraft     Launch    Sensor Complement    Ground Segment    References

KMA (Korea Meteorological Administration) is planning for the follow-on geostationary meteorological satellite (GEO-KOMPSAT-2) to continue the Korean COMS (Communications, Ocean, Meteorological Satellite) mission. From 2009 onwards, KMA has prepared a feasibility study for the GEO-KOMPSAT-2 program under the cooperation of the following Ministries: Ministry of Science, ICT and Future Planning (MSIP), Ministry of Oceans and Fisheries (MOF), and Ministry of Environment (ME) of the Korean government. The GEO-KOMPSAT-2 program has been approved in September 2010, and was kicked off in the middle of 2012. 1)
Note: The nickname Cheollian means long distance view (literally "Thousand Li View") in Korean.

KMA/NMSC (Korea Meteorological Administration/National Meteorological Satellite Center) of Korea started the COMS-Next (GEO-KOMPSAT-2) program with the overall objective to obtain geostationary meteorological data for continuous monitoring of meteorological phenomena in the Asia-Oceania region.

Specific mission goals are: 2)

• Continuing the COMS (Communication, Ocean and Meteorological Satellite) meteorological mission

• Improving the severe weather monitoring

- Higher frequency of observation

- Retrieving the atmospheric structure (pseudo-sounding)

• Improving the support of the NWP (Numerical Weather Prediction) model with an efficient data assimilation model

• Intensifying the environment & climate monitoring

- Various surface information retrieval

- Air pollution monitoring

- Establishing long-term observation data.

The GEO-KOMPSAT-2 program comprises two satellites for multi-purpose applications: GEO-KOMPSAT-2A for meteorological missions and GEO-KOMPSAT-2B for ocean and environmental monitoring. KARI (Korea Aerospace Research Institute) of Daejeon, Korea, is responsible for the development of the GEO-KOMPSAT-2 space segment while KMA/NMSC implements the ground segment. 3)

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Figure 1: Schedule of the GEO-KOMPSAT-2 program (image credit: KMA/NMSC)

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Figure 2: National Satellite Development Plan (image credit: KARI) 4)

 

Spacecraft GEO-KOMPSAT-2 (GK-2A and GK-2B)

GK-2A is for the meteorological mission and the space weather monitoring mission, so it is equipped with the instruments: AMI(Advanced Meteorological Imager) and KSEM (Korean Space Environment Monitor).

The GEO-KOMPSAT-2 (GK-2) satellites will inherit the mission of COMS(Cheollian-1) to observe the weather and ocean environment and strengthen the national capability to monitor the environment around the Korean Peninsula. Two satellites will be developed: a weather and space weather observation satellite (GK-2A) and ocean and environmental observation satellite (GK-2B). 5) 6)

1) Meteorological Mission: GK-2A (GK2A)

• The objective is to continue and enhance the COMS meteorological observation mission.

• To monitor weather and climate phenomena with an enhanced measurement cycle.

• To monitor more accurately high-impact weather events with high spatial resolution.

The weather observation capability of GK-2A will be more than four times greater than that of COMS, while the observation interval and observation channels will both be improved more than threefold. The satellite is expected to greatly improve the accuracy of precision weather observation and weather forecasting, as well as enhance the capability to monitor and forecast unusual weather conditions in the Korean Peninsula and the Asian region.

2) Space Environment Monitoring Mission: GK-2B (GK2B)

• The objective is to provide monitoring of space weather phenomena

- Measurement of energetic particle flux and magnetic field in the GEO-orbit

- Monitoring of GK2A spacecraft charging.

The resolution of the ocean observation payload of GK-2B, an ocean/environmental observation satellite, is also more than four times that of the COMS satellite. The environmental observation payload will monitor the movement of border-crossing atmospheric pollutants such as fine dust and yellow sand in 7 km resolution 8 times a day.

 


 

GK-2A spacecraft:

The prime contractor for the design and development of the GK-2 satellites is KARI (Korea Aerospace Research Institute). The platform is being developed using procured qualified components, produced in Korea.

• GK2 platform is being developed by KARI

- The system design and flight software development are performed based upon COMS and previous knowledge and experience of KARI having in mind the maximum commonality between GK2A and GK2B

- Some units are manufactured and qualified by Korean industries with KARI's involvement

- Already qualified hardware are procured from qualified manufacturers

- Observation data communication subsystem (ODCS) for payloads is developed as a part of the platform

- As a conservative approach, Software Test Bed (STB), Electric Test Bed (ETB) are developed prior to Flight Model

- Also, Structure and Thermal Model (STM) are developed and qualified prior to Flight Model.

Table 1: Ensuring the GK2 system development under KARI's responsibility (Ref. 6)

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Figure 3: Modular concept of GK2 (image credit; KARI)

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Figure 4: Artist's rendition of the deployed GK-2A satellite (image credit: KARI)

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Figure 5: Illustration of the GEO-KOMPSAT-2A spacecraft (image credit: KARI)

In June 2014, KARI awarded a contract to Northrop Grumman to provide the Scalable SIRU (Space Inertial Reference Units) devices, an inertial reference system for each of the two GEO-KOMPSAT-2 satellites. The Scalable SIRU is the industry standard for high-precision, long-life attitude control solutions supporting commercial, government and civil space missions. At the heart of the Scalable SIRU is Northrop Grumman's patented HRG (Hemispherical Resonator Gyro) technology. HRGs have been used in space without a mission failure for more than 26 million operating hours and have been launched aboard more than 100 spacecraft. Since 2007, Northrop Grumman has supplied the Scalable SIRU for satellites developed and operated by KARI, including KOMPSAT-3, KOMPSAT-3A and KOMPSAT-5. 7)

In September 2014, KARI awarded Airbus Defence and Space a €45 million contract to deliver important subsystems and equipment for the two GEO- KOMPSAT-2 platforms (GK-2A and GK-2B). 8) Airbus Defence and Space will deliver the complete propulsion subsystem and the structure of the medium-sized/small geostationary satellite platforms, which have a launch mass of three to four tons. The Electronics Business Line of Airbus Defence and Space will supply the GK2 satellites with power and avionics units, while the Space Systems Business Line will provide them with a fully integrated propulsion subsystem consisting of the central cylinder structure, the chemical propulsion and the associated thermal control system.

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Figure 6: Photo of the GK-2A STM (Structure Thermal Model), image credit: KARI

 


 

GK-2B spacecraft:

The GK2B spacecraft has an expected launch mass of ~3200 kg. — A description of theGK-2B spacecraft will be provided when avalable.

GK-2B sensor complement:

• GOCI-II (Global Ocean Color Imager-II)

• GEMS (Geostationary Environment Monitoring Spectrometer).

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Figure 7: Illustration of the GEO-KOMPSAT-2B spacecraft (image credit: KARI)

Both GEO-KOMPSAT-2 spacecraft description will be updated when the information becomes available.

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Figure 8: Illustration of the COMS (GK1) spacecraft versus the GK2 spacecraft configurations (image credit: KARI, Ref. 6)

RF communications:

• Sensor data downlink rate in X-band : 115 Mbit/s for each spacecraft, GK2A and GK2B

• LRIT/HRIT (Low Rate Information Transmission/High Rate Data Transmission) downlink in L-band: 256 kbit/s, 3 Mbit/s (same as COMS, only for GK2A)

• LRIT/HRIT uplink in S-band: 256 kbit/s, 3 Mbit/s (same as COMS, only for GK2A)

• UHRIT (Ultra High Rate Information Transmission) downlink in X-band: 31Mbit/s (only for GK2A)

• UHRIT uplink in S-band: 31Mbit/s (only for GK2A)

 

Development status of GK2 satellites:

• June 21, 2017: The Harris-built AMI (Advanced Meteorological Imager) was delivered to KARI (Korea Aerospace Research Institute) and will be integrated into the next-generation GEO-KOMPSAT-2A weather satellite, scheduled to launch in 2018. 9)

Highlights of AMI:

• Provides three times more data, four times the resolution, than current capability

• Improves weather forecasting to help save lives and property

• Marks the third advanced imager sold internationally.

AMI is based on the Advanced Baseline Imager built for the U.S. National Oceanic and Atmospheric Administration's Geostationary Operational Environmental Satellite-16 (GOES-16). GOES-16 launched aboard a United Launch Alliance Atlas V rocket in November 2016. It is performing well and providing significantly increased capabilities to the National Weather Service. The data coming from the instrument will be used operationally beginning this fall. Two other advanced imagers are in orbit on Japan's Himawari-8 and Himawari-9 weather satellites.

"South Korea is frequently threatened by typhoons and needs improved forecast accuracy to help protect lives and property," said Eric Webster, vice president and general manager, Harris Environmental Solutions. "More detailed information about clouds, moisture and water vapor will make it easier to track the formation of storms. The imager can also distinguish between volcanic ash, smoke and dust, which can impact airlines by causing flight delays and cancellations."

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Figure 9: KARI and Harris Corporation employees pose with the Advanced Meteorological Imager, which was built by Harris in Fort Wayne, Ind., and was recently delivered to KARI for integration into its newest weather satellite (image credit: Harris Corporation)

• April 18, 2017: TAS (Thales Alenia Space) of Madrid, Spain has sent South Korea the third of three panels that make up the communications payloads on the two GEO-KOMPSAT-2 satellites being built by KARI (Korea Aerospace Research Institute). This last panel will be integrated in the GK-2B satellite, and follows the two panels already delivered by the company at the end of last year for the GK-2A satellite. 10)

- Thales Alenia Space integrated and tested three communication panels in its plant in Spain, two for GK2A and one for GK2B. These panels house the subsystems that transmit to Earth the raw data from the instruments, as well as a communications payload comprising two repeaters, used to retransmit processed data to end-users.

- Thales Alenia Space and the South Korean company Qnion teamed up to develop RF (RadioFrequency) filters as part of the COACH (Co-development for Advanced Channel Filters) program, co-financed by CDTI (Spain's Center for Industrial Technology Development) and KIAT (Korea Institute for Advancement of Technology). This program, completed on March 31, was instrumental in the development of several components and subassemblies used in the communications systems on GK2A and GK2B.

• CDR for GK2A and GK2B have been completed in Sept. 2015 and Jan. 2016, respectively.

• Functional verification is being done at ETB (Electric Test Bed) and STM (Structure Thermal Model) qualification has been completed in Feb 2016.

• GK2A FM (Flight Model) integration and Test started in May 2016.

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Figure 10: Launch schedule of GK2 satellite missions (image credit: KARI)

 

Launch: A launch of GK-2A (GEO-KOMPSAT-2A) is scheduled for 2018 on an Ariane-5 ECA vehicle from Kourou. 11) 12)

Launch: A launch of GK-2B (GEO-KOMPSAT-2B) is scheduled for 2019 on an Ariane-5 ECA vehicle from Kourou.

Orbit: Geostationary orbit over equator, mean altitude of 35786 km, inclination = 0º.

• Longitude of GEO-KOMPSAT-2A: 128.2ºE

• Longitude of GEO-KOMPSAT-2B: 128.0ºE.

 


 

Sensor complement: (AMI, KSEM, GOCI-II, GEMS)

The following sensor complements were selected for the two GEO-KOMPSAT-2 missions: 13) 14) 15) 16)

1) GEO-KOMPSAT-2A mission (meteorological / space weather sensors). The main purpose of GEO-KOMPSAT-2A is meteorological remote sensing. Sensor complement:

AMI (Advanced Meteorological Imager), formerly known as MI-II (Meteorological Imager-II)

KSEM (Korean Space Environment Monitor)

2) GEO-KOMPSAT-2B (ocean / environmental sensors), a launch is scheduled for 2019. Sensor complement:

• GOCI-II (Global Ocean Color Imager-II)

• GEMS (Geostationary Environment Monitoring Spectrometer).

Parameter

AMI (ABI heritage)

GOCI-II

GEMS

Spectral range

0.47 µm-13.3 µm

380-900 nm

300-500 nm

Spatial resolution

500 m, 1 km(VIS), 2 km(IR)

300 m

7.0 km

Spectral resolution

400~1,000 nm

10~40 nm, 500 nm

0.8 nm

No of bands

16

13

Hyperspectral

Coverage

FD, NHFD, North-East Asia, Korea Peninsula (LA)

2,500 x 2,500 km(LA), FD

FD, NHFD, North-East Asia, Korea Peninsula (LA)

Observation period

FD 4 times/hour
LA 120 times/hour

10 times/day

8 times/day

Observation time

FD 15 min, NHFD 5 min,
LA 30 sec

< 30 minutes (LA)

30 minutes

Table 2: Overview of the main GEO-KOMPSAT-2 payload requirements

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Figure 11: Illustration of spectral coverage of the GEO-KOMPSAT-2 payloads (image credit: KOSC/KIOST)

• The development of GK2 Satellite system is KARI's responsibility. This is the 1st attempt of KARI for Geostationary satellite.

• The GK2 payloads are acquired by Procurement (AMI), Joint development (GOCI-2, GEMS) and Domestic development (KSEM) through international/domestic competition.

• System level Integration & Test will be done by KARI using KARI facilities:

- Required EGSE are newly developed

- Some MGSE of COMS are reused and others are newly developed

- KARI accommodates payloads to platform and perform system test with the payload team support as necessary.

• Ground station will be developed by KARI and Korean industries.

Table 3: Ensuring the GK2 system development under KARI's responsibility (Ref. 6)

 

AMI (Advanced Meteorological Imager) / formerly MI-(Meteorological Imager-II)

The requirements of AMI call for:

• Multi-channel observation capability: 16 channels (4 VIS and 12 infrared)

• High spatial resolution: 0.5-1.0 km for VIS and 2 km for the infrared channels

• Fast imaging: within 10 minutes for FD (Full Disk) observations

• Flexibility for the regional area selection and scheduling.

In April 2013, KARI awarded a contract to ITT Exelis of Rochester, N.Y., USA (Harris Corporation as of 2015) to provide Korea an advanced geostationary weather imager to support the country's forecasting capabilities. Under the GEO-KOMPSAT-2A program, Exelis will deliver AMI (Advanced Meteorological Imager), which is based on the ABI (Advanced Baseline Imager) to be flown on the next-generation NASA/NOAA GOES-R (Geostationary Operational Environmental Satellite-R) series. In fact, ITT Exelis has or will design and develop all instruments (AMI, ABI,AHI and MI) listed in Table 4. 17)

AMI of GK-2A will have sixteen spectral bands (Table 4) which are slightly different from ABI of GOES-R and AHI (Advanced Himawari Imager) of Himawari-8/9, and will provide three times more spectral information, four times the spatial resolution, and more than four times faster temporal coverage than the current MI (Meteorological Imager) of COMS.

Channel No

Channel

AMI (µm)
GEO-KOMPSAT-2A

ABI (µm)
GOES-R, NASA

AHI (µm)
HIMAWARI-8/9, JAXA

MI (µm)
COMS, KARI

1

VIS (blue)

0.470

0.470

0.46

 

2

VIS (green)

0.511

 

0.51

 

3

VIS (red)

0.640

0.640

0.64

0.675

4

VNIR

0.865

0.865

0.86

 

5

SWIR

1.380

1.378

 

 

6

SWIR

1.610

1.610

1.6

 

 

 

 

2.250

2.3

 

7

MWIR

3.830

3.90

3.9

3.75

8

MWIR (WV)

6.241

6.185

6.2

 

9

MWIR (WV)

6.952

6.95

7.0

6.75

10

MWIR (WV)

7.344

7.34

7.3

 

11

TIR

8.592

8.50

8.6

 

12

TIR

9.625

9.61

9.6

 

13

TIR

10.403

10.35

10.4

10.8

14

TIR

11.212

11.20

11.2

 

15

TIR

12.364

12.30

12.3

12.0

16

TIR

13.31

13.30

13.3

 

Table 4: The channel characteristics (center wavelengths) of AMI on GEO-KOMPSAT-2A and comparison with ABI, AHI and MI 18)

AMI of GK-2A is designed to have an improved spectral, temporal, and spatial resolution compared to the first generation imager. For example, the number of channels will be increased at least threefold (from 5 to 16) while the spatial resolution will be 2 km for the 10 infrared channels and 1 km for 6 visible channels (only channel No 3 will have a resolution of 0.5 km). Furthermore, the time required to scan a full disk will be reduced to about one-fifth of the current 28 minutes. With these improvements, many of new value-added products are expected to be produced, in addition to the significant improvement of the current 16 products.

Among the new products, atmospheric instability information is one of the important new possibilities with the pseudo-sounding capability of AMI. Although its accuracy is expected to be limited due to the limited number of sounding channels, its high spatial and temporal resolution could provide a significant addition for the nowcasting applications.

In May 2015, KARI completed a multi-disciplinary design review of the AMI ( Advanced Meteorological Imager) and determined the team is ready to begin final production. KARI's review focused on the AMI and spacecraft interfaces and mission requirements. 19)

Bands

Nadir resolution

SNR (min)

NEDT (max)

MTF (Modulation Transfer Function)

Dynamic range

@ 240 K

@ 300 K

1/4

1/2

3/4

4/4

VNIR

VSI0.4

1 km

261

-

0.85

0.73

0.53

0.32

0~720W/m2/sr/µm

VSI0.5

1 km

299

-

0.84

0.65

0.41

0.22

0~710W/m2/sr/µm

VSI0.6

0,5 km

130

-

0.83

0.59

0.37

0.19

0~620W/m2/sr/µm

VSI0.8

1 km

300

-

0.86

0.64

0.40

0.20

0~320W/m2/sr/µm

NIR1.3

2 km

300

-

0.90

0.73

0.53

0.32

0~114W/m2/sr/µm

NIR1.6

2 km

300

-

0.90

0.73

0.39

0.32

0~77W/m2/sr/µm

MWIR

IR3.8

2 km

-

2.7 K

0.18 K

0.84

0.62

0.39

0.22

0~400 K

IR6.3

2 km

-

0.40 K

0.10 K

0.83

0.62

0.39

0.22

0~300 K

IR6.9

2 km

-

0.37 K

0.10 K

0.81

0.62

0.39

0.22

0~300 K

IR7.3

2 km

-

0.32 K

0.10 K

0.81

0.62

0.39

0.22

0~320 K

IR8.7

2 km

-

0.27 K

0.10 K

0.83

0.62

0.39

0.22

0~330 K

LWIR

IR9.6

2 km

-

0.22 K

0.10 K

0.82

0.61

0.39

0.22

0~300 K

IR10.5

2 km

-

0.21 K

0.10 K

0.80

0.60

0.39

0.22

0~330 K

IR11.2

2 km

-

0.19 K

0.10 K

0.80

0.59

0.39

0.22

0~330 K

IR12.3

2 km

-

0.26 K

0.12 K

0.79

0.57

0.38

0.22

0~330 K

IR13.3

2 km

-

0.48 K

0.30 K

0.78

0.56

0.37

0.20

0~305 K

Table 5: AMI specification requirements (Ref. 4)

Parameter

GK-2A AMI (Advanced Meteorological Imager)

COMS MI (Meteorological Imager)

Spectral bands

16 channels (4 VIS, 2 NIR, 10IR)

5 channels ((1 VIS, 4 IR)

Spectral resolution

0.64 µm: 0.5 km
Other VIS/NIR: 1.0 km
IR: 2 km

0.675 µm: 1 km
Other VIS/NIR: N/A
IR: 4 km

Observation duration

Full disk: ≤10 minutes

Full disk: ≤30 minutes

Lifetime

10 years

7 years

On-board calibration

Visible: Solar Diffuser
IR: Internal Blackbody Target


IR: Internal Blackbody Target

Table 6: Comparison of GK-2A AMI with COMS MI

AMI instrument:

FOV (Field of View)

0.9º x 1.9º; Large NS (North-South) FOV: Slower Scan Rate, Higher SNR

FOR (Field of Regard)

22º ((i.e. ±11º)

Two scan mirrors

(NS, EW), SiC with silver coating; Lower inertia and power; Less disturbance

Two beam-splitters(S1,S2)

S1 for VNIR; S2 for MWIR/LWIR

FMA (Four Mirror Anastigmatic) telescope

Aperture = 270 mm; Collecting sufficient photons for good SNR

Table 7: AMI optical design

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Figure 12: Schematic view of the AMI optical layout (image credit: Harris Corporation)

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Figure 13: Illustration of the AMI configuration (image credit: Harris Corporation)

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Figure 14: AMI scan pattern (image credit: Harris Corporation, KARI)

 

AMI on-board calibration in the IR bands:

• 3-bounce ICT (Internal Calibration Target)

• Robust against stray-light and contamination

• Very high Emissivity : 0.995

• Accommodated in anti-nadir location

- Observe the black body target at the start of every operational timeline iteration.

AMI on-board calibration in the visible bands:

• Solar calibration target : Spectralon®Diffuser

• Solar calibration cover open only when calibrating

- Solar calibration can occur any day of the year at 6:00~6:15 hours (spacecraft local time).

 

AMI development status:

• EDC (Effective Date of Contract) : February 18 2013 (completed)

• Kick-off Meeting : April 10, 2013 (completed)

• SRR (System Requirement Review) Meeting : October 23, 2013 (completed)

• PDR (Preliminary Design Review) Meeting : April 8, 2014 (completed)

• CDR (Critical Design Review)/EQSR Meeting : March 2-3, 2015 (completed)

• TRR (Test Readiness Review) Meeting : February 2016

• PER (Pre-Environmental Review) Meeting : April 2016

• PSR (Pre-Sip Review) Meeting : January 2017

• AMI Delivery : March 2017

 

KSEM (Korean Space Environment Monitor)

KMA in coordination with KARI selected KHU (Kyunghee University) of Seoulto develop the KSEM suite of instruments and post-delivery support for the assembly and integration test, pre- and post- launch test of Geo-KOMPSAT-2A. The suite of KSEM instruments consists of particle detector (PD); magnetometer (MAG); and SCM (Satellite Charging Monitor). The sensors are used to monitor the space environment 6 the severe space weather information of high-impact space storms, the radiation environment hazardous to spacecraft, aircraft and radio communication for 24 hours/7 days during 10 years mission life time. 20) 21)

• PD (Particle Detector): The PD is of THEMIS SST (NASA) heritage. It consists of 3 detector heads and measures the differential energy flux of electrons and ions within the energy range of 100 keV and 2 MeV, which are trapped within Earth's magnetic field.

• MAG, of THEMIS FGM (FluxGate Magnetometer) heritage, measures three components of near Earth magnetic field within the range of ±350 nT and monitors those variations caused by space storm and high-speed stream.

• SCM (also referred to as CM) measures the satellite internal charging current within the range of ±3 pA/cm2 due to high energy particles and provides advance warning of a possible electrical discharge.

KSEM is the first Korean space weather instrument suite aboard a GEO satellite. Like the Galaxy 15 anomaly on 2010, GEO satellites are easily exposed to the risk due to severe space weather. It is expected that KSEM data will contribute to secure the satellite operation and the high-tech ground infrastructure.

Sensor

Parameter

Requirement

Specification (after CDR)

PD (Particle Detector)

Energy range

100 keV ≤ E ≤ 2 MeV

100 keV ≤ E ≤ 2 MeV

Energy resolution

ΔE/E ≤ 30%

ΔE/E ≤ 30%

Time resolution

≤ 0.33 s

≤ 0.33 s

View direction

5-directions

6-directions

Geometric factor

≥10-3 (cm2 sr)

≥10-2 (cm2 sr)

Background contamination

≤3%

≤3%

Count resolution

≥8 bit

8 bit

MAG (Magnetometer)

Range

-350 nT to +350 nT (3-axis)

Variable up to ± 64,000 nT

Accuracy

≤1 nT

≤1 nT

Time resolution

≤0.1 s

0.1 s

Type

Non-deployable

Deployable

SCM (Satellite Charging Monitor)

Range

-3 pA/cm2 to +3 pA/cm2

-3 pA/cm2 to +3 pA/cm2

Accuracy

≤0.01 pA/cm2

≤0.01 pA/cm2

Time resolution

≤1 s

≤1 s

Table 8: KSEM requirements and capability

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Figure 15: KSEM configuration (image credit: KARI)

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Figure 16: KSEM Particle Detector (image credit: KSEM Team)

 

SOSMAG (Service Oriented Spacecraft Magnetometer):

Monitoring the solar wind conditions, in particular its magnetic field (interplanetary magnetic field) ahead of the Earth is essential in performing accurate and reliable space weather forecasting. The magnetic condition of the spacecraft itself is a key parameter for the successful performance of the magnetometer onboard. In practice a condition with negligible magnetic field of the spacecraft cannot always be fulfilled and magnetic sources on the spacecraft interfere with the natural magnetic field measured by the space magnetometer. 22)

The "ready-to-use" SOSMAG (Service Oriented Spacecraft Magnetometer) is developed for use on any satellite implemented without magnetic cleanliness programme. It enables detection of the spacecraft field AC variations on a proper time scale suitable to distinguish the magnetic field variations relevant to space weather phenomena, such as sudden increase in the interplanetary field or southward turning. This is achieved through the use of dual fluxgate magnetometers on a short boom (1m) and two additional AMR (Anisotropic Magneto-Resistance) sensors on the spacecraft body, which monitor potential AC disturbers. The measurements of the latter sensors enable an automated correction of the AC signal contributions from the spacecraft in the final magnetic vector. After successful development and test of the EQM prototype, a FM (Flight Model) is being built for the Korean satellite Geo-Kompsat 2A.

SOSMAG has the following basic features (Figure 19):

1) 2 fluxgate sensors (FG) on a short boom -the inboard (IB) and outboard (OB) sensor

2) 2 AMR sensors on spacecraft body

3) deployable boom of 1m length

4) a mounting interface for the boom, without specific requirements on the spacecraft structure

5) and the associated electronics.

Mass budget: sensor and electronics 2.0 kg; mounting plate and boom 1.1 kg. Power budget: 2.6 W.

All four sensors are operated continuously and simultaneously with a time resolution of at least 1 Hz or higher, depending on the type of effect to be characterized.

The operation shall be continuous and with higher time resolution in the early stages (commissioning phase) of the spacecraft flight, such that the typical operations of spacecraft subsystems and instruments are closely monitored and characterised in detail. The data of this early phase are studied on ground to detect and characterize the spacecraft AC effects and to determine correction factors for each specific AC disturbance. The correction factors are implemented in inflight algorithms, which then enable automated correction for these AC effects during further flight operation.

Advantages of SOSMAG:

For SOSMAG, the key point is that the use of 2 sensors on a boom but with 2 additional sensors on the spacecraft body, which monitor important AC disturbers, allows a considerable reduction of the boom length (estimated factor ~3 compared to conventional systems). The advantage of these additional spacecraft sensors is demonstrated here in the functionality test with the spacecraft mockup.

The experience from the Venus Express spacecraft with only two sensors (2 sensors on 1 m boom and no magnetic cleanliness for the spacecraft) showed that correction for AC disturbers is difficult. As long as spacecraft disturbers are only switched on/off, their effect may be identified from the difference of the measurements at the boom sensors. Yet the detection of all the "jumps" and precise determination of their respective amplitude, due to switching events during the whole flight, was a cumbersome task, even when semiautomated after a learning phase. It was also difficult to separate simultaneously active AC sources, due to their overlapping effect in the data. The correction for AC disturbers with a changing character needed a specific procedure; the correction for the AC effects of the Solar Array Drive Motors (SADAM) required permanently the housekeeping data from the spacecraft. The finally achieved precision was ± nT per component on DC level. 23)

Now with SOSMAG, two additional sensors are mounted on the spacecraft to monitor specific AC sources. These sensors are intended to measure mainly the signature of a single source or eventually a few sources together located near the sensor. This allows to clearly correlate their signal at that spacecraft sensor with the signal measured at the outboard boom sensor in a learning phase, where the individual AC disturbers are characterized and the correction factors determined. This is possible also for non-linear effects of the AC source, e.g. the motor in the mockup test-sequence. Later on during the spacecraft flight, the correction can be performed automatically with weighed subtractions; it is not necessary to detect and process each individual AC variation during flight. The achievable accuracy on AC level is ± 0.1 nT, which is appropriate to study space weather phenomena and to allow space weather forecast for Earth.

The main advantage of SOSMAG is, that no requirements of magnetic cleanliness are posed on the spacecraft. The effort of mounting the base plate with the boom and accommodation of two additional sensors on the spacecraft body is far lower than for any magnetic cleanliness programme. Furthermore, it is known from scientific spacecraft missions, e.g. Cluster
(ESA), MMS (NASA), Venus Express (ESA), Mars Express (ESA), that not the constant or slowly varying DC magnetic level is the main problem for the accuracy of the data, but the continuously occurring AC effects during flight (up to ~ 1000 per day), due to switching events, motors etc. The effect of induced spacecraft fields can generally be neglected in the low space field environment of interest.

The SOSMAG magnetometer system allows for an automated removal of AC effects during the spacecraft flight, thus solving the main problem of the dataaccuracy for space weather observation. In practice, any spacecraft on a suitable orbit for space weather monitoring could be equipped with a ready-to-go SOSMAG magnetometer package, increasing the availability of data required for eventual space weather alerts.

Flight model for GEO-KOMPSAT-2A:

KARI in cooperation with the KHU (Kyung Hee University) in Seoul is developing a satellite GEO-KOMPSAT-2A for meteorological observations, in geostationary orbit located 128.2° East. Space weather observation will be performed by the KSEM (Korean Space Environment Monitor) developed by KHU, with particle detectors, a charging monitor and a magnetometer (Figure 18). The SOSMAG system (when in the EQM development phase) was chosen as a suitable ready-to-go instrument without imposing a requirement on magnetic cleanliness to the spacecraft.

The development of this specific flight model of SOSMAG is funded by ESA (European Space Agency) in the framework of the SWE (Space Weather Environment) of the ESA's SSA (Space Situational Awareness) Program. 24)

The SOSMAG mounting plate with boom and two fluxgate sensors will be positioned on one side of the spacecraft; the two AMR sensors are located at selected positions near potential strong AC disturbers on the spacecraft body.

The flight model development with hardware and onboard software for the correction of the AC sources is ongoing. Delivery to KARI is foreseen for early 2017. After launch and a learning phase to determine the correction factors during the commissioning of the spacecraft, the automated correction will be standard procedure during the science phase of the spacecraft.

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Figure 17: Schematic view of the SOSMAG architecture (image credit: SOSMAG Team)

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Figure 18: Accommodation of SOSMAG as part of KSEM on the GEO-KOMPSAT-2A spacecraft (image credit: Kyung Hee University, SOSMAG Team)

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Figure 19: KSEM Magnetometer (image credit: KSEM Team)

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Figure 20: KSEM Charging Monitor (image credit: KSEM Team)

 

GEMS (Geostationary Environment Monitoring Spectrometer) on GK-2B

The Ministry of Environment (ME), Korea, is funding the GEMS instrument for atmospheric composition measurements in the Asia-Pacific region. Feasibility studies for the subsystem, system level and scientific missions had been finished. For the air quality mission, ME formally established the Global Environmental Satellite Program Office in June 2009 in NIER (National Institute of Environmental Research) of ME. 25)

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Figure 21: GEMS mission organization (image credit: GEO-KOMPSAT-2 collaboration) 26)

GEMS will contribute to the understanding of the globalization of pollution events, source/sink identification, and long-range transport of pollutants and SLCFs (Short-Lived Climate Forcers), as a part of the activities of the Atmospheric Composition Constellation under CEOS (Committee on Earth Observation Satellites). This Constellation coordination activity is focused on collaboration to improve and extend data utilization from the planned missions. The missions now funded are: Korea (GEMS), Europe (Sentinel-4), and the US (TEMPO), will enable the "baseline" constellation data products.

Science Questions

Objectives

• What are the temporal and spatial variations of concentrations and emissions of gases and aerosols that are important for air quality?

• To provide measurements of atmospheric chemistry, precursors of aerosols and ozone in particular, in high temporal and spatial resolution over Asia

• How do regional and intercontinental transport affect local and regional air quality?

• To monitor regional transport events: transboundary pollution and Asian dust

• How does air pollution drive climate forcing and how does climate change affect air quality?

• To quantify radiative forcing of aerosol and ozone and to monitor air quality for long term

• How does meteorology affect the air quality ?

• To improve our understanding on interactions between atmospheric chemistry and meteorology

• How can we quantify the outflow from Asia to cross Pacific ?

• To better understand the globalization of tropospheric pollution

• How can we improve the accuracy of air quality forecast using satellite measurements?

• To improve air quality forecast by constraining emission rates and assimilating chemical observation data

Table 9: Science questions and objectives of GEMS

In May 2013, KARI (Korea Aerospace Research Institute) awarded a contract to BATC (Ball Aerospace & Technologies Corporation) of Boulder, CO, USA to build the GEMS instrument for NIER (National Institute of Environmental Research) of the Ministry of Environment, Korea. 27)

GEMS is a geostationary scanning ultraviolet-visible spectrometer designed to monitor trans-boundary pollution events for the Korean peninsula and the Asia-Pacific region. The spectrometer provides high spatial and high temporal resolution measurements of ozone, its precursors, and aerosols. Hourly measurements by GEMS will improve early warnings for potentially dangerous pollution events and to support the monitoring of long-term climate change.

The GEMS instrument is the Asian element of a global air quality monitoring constellation of geostationary satellites that includes the TEMPO (Tropospheric Emissions: Monitoring of Pollution) spectrometer. Ball is the TEMPO instrument provider for NASA(LaRC (Langley Research Center) and the Harvard Smithsonian Astrophysical Observatory (SAO) on this EVI (Earth Venture Instrument) line program of NASA. TEMPO will be a hosted payload to be flown on a commercial geostationary satellite in the timeframe 2018/19. 28) 29) 30) 31)

Ball is building nearly identical geostationary ultraviolet visible spectrometers: TEMPO for NASA and GEMS for KARI. Both instruments will complete critical design in 2015 and be delivered in 2017. 32)

• TEMPO will be NASA's first UV-VIS spectrometer in GEO to make accurate observations of atmospheric pollution with high spatial and temporal resolution over North America, from Mexico City to the Canadian tar/oil sands, and from the Atlantic to the Pacific. TEMPO will provide hourly daylight measurements of ozone, nitrogen dioxide, sulfur dioxide, formaldehyde, glyoxal and other pollutants to create a revolutionary dataset that provides understanding and improves AQ (Air Quality) and climate forcing.

• The GEMS spectrometer is designed to monitor trans-boundary pollution events for the Korean peninsula and the Asia-Pacific region. The spectrometer provides high spatial and high temporal resolution measurements of ozone and its precursors. Hourly measurements by GEMS will improve early warnings for potentially dangerous pollution events and monitor long-term climate change. GEMS is manifested on the GEO-KOMPSAT-2B spacecraft.

GEMS is expected to contribute monitoring air quality and SLCFs including ozone and aerosols in Asia in high temporal and spatial resolution. Using a scanning UV-Visible spectrometer, its observations can contribute to provide a set of tropospheric column products over the Asia-Pacific region at spatial resolution of ~ 8 km and temporal resolution of 1 hour. Other products include NO2, HCHO, SO2, and aerosol optical depth.

The GEMS instrument has a 2-axis scan mirror and a 1 k x 2 k focal plane array using a CCD (Charge Coupled Device) to image the ultraviolet/visible spectrum. GEMS will scan a 5000 km East/ West area in less than 30 minutes with state-of-the-art calibration and high spatial and spectral resolution. In geostationary orbit, GEMS will collect images over an 8 to 12 hour period.

Parameter

Requirement

Design life, reliability

> 10 years after IOT (In-Orbit Test), > 0.85 @ 7 years

FOR (Field of Regard)

> 5,000 km(N/S) x 5,000 km(E/W) N/S: 45ºN-5ºS, E/W: Selectable between 75ºE -145ºE

Duty cycle/Imaging time

8 images during daytime
(30 min imaging + 30 min rest) x 8 times/day

GSD (Ground Sampling Distance)

< 7 km(N/S) at Seoul GSD area < 56 km2 at Seoul (Aspect ratio shall be less than 1:3)

Spectral range

300 nm to 500 nm

Spectral resolution

< 0.6 nm (hyperspectral)

Spectral sampling

< 0.2 nm

SNR (Signal-to-Noise Ratio)

> 720 @ 320 nm, > 1500 @ 430 nm

Data quantization

≥ 12 bit

MTF (Instrument level)

> 0.3 in N/S direction @ Nyquist frequency, > 0.3 in E/W direction @ Nyquist frequency

Radiometric calibration accuracy

< 4%

Spectral calibration accuracy

< 0.02 nm

Polarization factor

< 2% (310-500 nm), No inflection point within 20 nm for all wavelength ranges

Table 10: GEMS instrument requirements (Ref.25)

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Figure 22: Illustration of the GEMS instrument and its subsystems (image credit: KMA/NMSC)

In February 2015, the GEMS instrument passed the CDR (Critical Design Review) which allowed the program to move into the manufacturing, assembly, integration and testing phase with instrument completion expected in early 2017. 33)

• Step-and-stare UV-Visible imaging spectrometer scanning at least 8 x per day in 30 minutes

• Daily solar and dark calibration

• Images coadded at each position + mirror move back < 30 minutes

- [ ~2 s @ each position (= coadding x image) + step & settle ] x ~700 position + ~2 s scan mirror back to null position

• Scanning Schmidt telescope and Offner spectrometer

• Diffusers for on-orbit solar calibration and onboard LED light source

• 2-axis scan mechanism with gyro feed capability

• Redundant electronics for 10-year lifetime

Table 11: GEMS design features

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Figure 23: Schematic view of the GEMS instrument (image credit: BATC, KARI, Ref. 26)

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Figure 24: Spatial coverage of GEMS (image credit: KARI)

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Figure 25: GEMS concept of operations (image credit: KARI)

In summary:

• GEMS onboard the Geo-KOMPSAT-2B is expected to provide information on aerosol and O3 together with their precursors in high spatial and temporal resolution

- O3 NO2 HCHO SO2 AOD/AI/AEH, (possibly CHOCHO, BrO)

- Clouds, surface reflectance, UV radiation.

• The predicted performance of trace gases from the initial design of GEMS satisfies the product accuracy requirements of NO2, HCHO, O3. Meanwhile, the performance is expected to be poor in winter, in particular near Korea.

 

GOCI-II (Global Ocean Color Imager-II) on GK-2B

Korea established an independent national institute, KIOST (Korea Institute of Ocean Science & Technology), which is responsible for the definition of mission and user requirements and for the operation of GOCI-II. GOCI-II is the next-generation instrument of GOCI, one of the major payloads on COMS, the 1st ocean color imager in the world operating in the geostationary orbit.

GOCI had been developed to provide a monitoring of ocean color around the Korean Peninsula to detect, monitor, quantify, and predict short term changes of coastal ocean environment for marine science research and application purposes. As such, GOCI acquired only LA (Local Area) mode observations in an area of size 2500 x 2500 km. The requirements of GOCI-II call for two coverage modes: LA (Local Area) and FD (Full Disk) as illustrated in Figure 26.

In July 2013, KARI awarded a contract to Airbus Defence and Space (former EADS Astrium) to jointly design and manufacture the GOCI-II instrument for the future Korean mission GK-2B (GEO-KOMPSAT-2B), scheduled for launch in 2019. The GOCI-II instrument will be designed using the latest generation technologies developed by Airbus DS (former Astrium) for space applications, including a 7 Mpixel CMOS sensor, a silicon carbide telescope and a high-precision pointing mechanism. GOCI-II offers significant advances in comparison to GOCI: enhanced resolution (250 m), 12 spectral bands and daily coverage of full disk Earth data. 34) 35)

GOCI-II is being developed by the Joint Development Team, KARI, KIOST and Airbus DS. The contract signed with KARI also stipulates that six Korean engineers will help to develop the instrument at the Airbus Group site in Toulouse. Airbus Defence and Space has agreed to use South Korean industrial services amounting to 5% of the contract price. In addition, test resources made available by KARI at its Daejeon site in Korea will be used for environment testing.

GOCI-II requirements: 36) 37)

• GOCI-II is focused on the coastal and global ocean environment monitoring with better spatial resolution and spectral performance for the succession and expansion of the mission of GOCI.

• The user requirements of GOCI-II will have higher spatial resolution, 300 m x 300 m, and 13 spectral bands to fulfill GOCI's user requests, which could not be implemented on GOCI for technical reasons.

• GOCI-II will have a new capability, supporting user-definable observation requests such as clear sky area without clouds and special-event areas, etc. This will enable higher applicability of GOCI-II products. GOCI-II will perform observations 10 times daily (GOCI 8 times daily).

• The main difference between GOCI-II and GOCI is the addition of the FD (Full Disk) mode in addition to the LA (Local Area) mode. A daily FD monitoring mode is planned for GOCI-II in support of research for long-term climate change.

Item

GOCI Instrument Specification

GOCI-II Instrument Specification

Mission lifetime

7 years

10 years

Duty Cycle (Local Area : LA)

8 times / day

10 times / day

Duty Cycle (Full Earth Disk : FD)

1 time during day time

Observation Time

≤30 minutes for LA

≤30 minutes for LA, ≤240 minutes for FD

Spatial resolution (GSD)

≤500 m @ center of Ref. LA (130ºE, 36ºN)

≤250 m @ Nadir (Ref. LA : 2.500 km x 2.500 km)

Number of bands

8 bands (VIS/NIR)

12 bands (VIS/NIR)+1 wideband

Coverage

North-East Asian Sea around Korea

North-East Asian Sea + Event Area Full Disk

SNR @ nominal ocean radiance

~750-1200

~ 750-1200

MTF @ Nyquist frequency

> 0.3

> 0.25

Mass, Power, Volume

85kg, 116 W, 1.0 m x 0.8 m x 0.8 m

150 kg, 250 W, 1.5 m x 1.0 m x 0.9 m

Table 12: Summary of GOCI and GOCI-II performance requirements

Additional functions of GOCI-II:

• Improved optical design to eliminate the straylight

• Star imaging to enhance the geometric correction

• Lunar imaging to quantify the sensor degradation.

FOR (Field of Regard):

• SN (South North) FOR (±11.4 º)

- 1.1º instrument FOV set as margin

- 1.1º useful FOV for moon and star

- 0.5º margin for pointing bias

• EW (East West) FOR (±8.6º)

- 8.06º FD area

- 0.5ºmargin for pointing bias.

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Figure 26: Illustration of the selected LA mode (left) and the FD mode (within the red circle at right), image credit: KORDI

Band

Band Center (nm)

Bandwidth (nm)

Nominal Radiance

Maximum Ocean Radiance

Saturation (Threshold) Radiance

Maximum Cloud Radiance

SNR @ Nominal Radiance

B1

380

20

93

139.5

143.1

634.4

998

B2

412

20

100

150

152

601.6

1050

B3

443

20

92.5

145.8

148

679.1

1145

B4

490

20

72.2

115.5

116

682..1

1228

B5

510

20

55.3

85.2

122

665.3

1124

B6

555

20

55.3

85.2

87

649.7

1124

B7

620

20

40.3

67.8

70.5

616.5

1080

B8

660

20

32

58.3

61

589

1060

B9

680

10

27.1

46.2

47

549.3

914

B10

709

10

27.7

50.6

51.5

450

914

B11

745

20

17.7

33

33

429.8

903

B12

865

40

12

23.4

24

343.8

788

B13

643.5 (PAN)

483

-

-

-

-

-

Table 13: Spectral band requirements of GOCI-II

Band

Band Center (nm)

Primary Usage

B1

380

CDOM (Chromophoric Dissolved Organic Matter), absorbing aerosol correction

B2

412

CDOM, chlorophyll

B3

443

Chlorophyll absorption maximum

B4

490

Chlorophyll and other pigments

B5

510

Chlorophyll, absorbing aerosol in oceanic waters

B6

555

Turbidity, suspended sediment

B7

620

Phytoplankton species detection

B8

660

Baseline of fluorescence signal, Chlorophyll, suspended sediment

B9

680

Fluorescence signal

B10

709

Fluorescence base signal, atmospheric correction, suspended sediment

B11

745

Atmospheric correction, vegetation index

B12

865

Atmospheric correction, aerosol optical depth

B13

Wideband

Star Imaging for the INR (Image Navigation and Registration) performance

Table 14: The spectral channels and their primary uses of GOCI-II

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Figure 27: Alternate view of the GOCI-II imaging modes: Local Area and Full Disk (image credit: GOCI-II Team)

Design overview: The GOCI-II instrument consists of a SU (Sensor Unit) and one IEU (Instrument Electronic Unit) deported inside the satellite platform. The total mass is about 150 kg. The baseline instrument concept is a compact TMA telescope with a 200 mm pupil diameter, featuring a 7.3 Mpixel CMOS array. The 12 narrow band spectral channels are obtained by means of a filter wheel. A 13th wideband spectral channel is implemented for star imaging.

A PIP (Payload Interface Plate) supports a highly stable full SiC (Silicon Carbide) telescope, the two-dimensional FPA (Focal Plane Array) and a FEE (Front End Electronics), the pointing mirror mechanism, the filter wheel mechanism and also the shutter / calibration wheel mechanism.

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Figure 28: Functional architecture of the GOCI-II instrument (image credit: GOCI-II Team)

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Figure 29: Illustration of the GOCI-II instrument (image credit: GOCI-II Team)

Imaging and Operating Principles: The operating principle consists in imaging a portion of the specified image frame, termed slot. A 2-axes Pointing Mechanism provides a 2D scanning on the Earth. By successive pointing, the array is moved in the field of view to cover the complete image (local area around Korea or full Earth disk in global observation mode). Each slot is imaged over the 12 spectral channels, plus a dark position for offset monitoring and correction. The image is acquired for two gain levels corresponding to sea and cloud radiance levels, respectively. The image data are sent in quasi-real-time to the ground. One single slot acquisition period takes less than 100 seconds in Local Observation mode and less than 60 seconds in Global Observation mode. Star images are done from time to time to calibrate the instrument LOS (Line of Sight) and feed the image ground processing (INR). The instrument in-orbit radiometric calibration is achieved by a combination of Solar Calibration (possible every day) and Moon calibration (monthly).

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Figure 30: Two imaging modes are available: Local area acquisition and Full Disk acquisition (image credit: GOCI-II Team)

The instrument operations are managed by a programmable timeline uploaded in the instrument electronics. The timeline covers 24h operations (mechanism motions, slot acquisitions, detection electronics on/off) and is automatically repeated by default. Figure 31 illustrates a typical set of operations that can be autonomously executed by the instrument and shows the instrument flexibility for Earth observation and calibration activities. The coverage of the Reference Local Area is done in a short time frame (20 minutes in 12 slots) giving the user up to 10 minutes per hour for complementary acquisitions: star imaging for efficient INR processing and Full Disk slots to fulfill the global coverage mission during daytime with optimal illumination conditions.

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Figure 31: Typical example of GOCI-II imaging operation over 24 hours (image credit: GOCI-II Team)

Main challenges of GOCI-II development: Although the overall instrument architecture and operation principles are inherited from the first GOCI, the specified performance enhancements required major new developments of key components:

• New dedicated CMOS image sensor to fit the smaller sampling distance with increased number of pixels while keeping high level radiometric and MTF performances. This detector was developed in partnership between Airbus DS and ISAE.

• New 2-axes POM (Pointing Mechanism, Figure 32) to manage the enlarged instrument FOR (Field of Regard) and the increased pointing mirror size and mass, while keeping a high stability, an accurate restitution of the pointing direction and the capability of being launched without a Launch Locking Device. The POM was designed and developed by Airbus DS in Toulouse. A fully representative qualification model has been build and the qualification tests will be completed before the end of the summer 2016.

• The IEU (Instrument Electronic Unit) that has to manage more detection chains and has to provide higher level of autonomy and flexibility for the user, while keeping low size and mass (7.5 kg). The IEU was developed by the Airbus DS electronics division. The full functional and performance validation was reached in 2015 on an EM model and the Flight Model has been delivered in mid-2016.

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Figure 32: CAD model of GOCI-II 2-axes Pointing Mechanism (image credit: GOCI-II Team)

• The dedicated TMA telescope with enlarged pupil and improved straylight performances (field stop implementation) while keeping compactness and diffraction limited performances. The SiC telescope structure and mirrors are designed by Airbus DS and manufactured by Mersen Boostec. Mirror polishing is done by Amos (Belgium) and coating by Schott (Switzerland).

• The optical filters were newly designed by OBJ (Optics Blazers Jena) in Germany with barrels made by Sodern. After full qualification on dedicated models, the Flight Models have been delivered in mid-2016.

• Two Sun diffusers made of HOD material are also implemented to enhance radiometric calibration.

• In addition, several key elements (harness, structures, EGSE) have been subcontracted to the Korean industry.

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Figure 33: Left: Telescope during alignment; Right: Photo of the GOCI-II filter wheel (image credit: GOCI-II Team)

The GOCI-II CMOS imaging sensor: In order to meet the demanding radiometric performance requirements, a 7.3Mpixel CMOS imaging sensor has been specifically designed for the GOCI-II instrument. Die design and architecture have been carried out in partnership with ISAE (Institut Supérieur de l'Aéronautique et de l'Espace), Toulouse, France. Following the design phase, the silicon wafers (Figure 34) have been manufactured and processed in an Asian semiconductor foundry.

The 7.3MPixels CMOS image sensor features:

• 2720 rows by 2718 columns of 6.8μm pitch pixels with 10 analog outputs to answer at the closest to spatial resolution and acquisition duration requirements (Figure 35)

• Pixel topology optimization to meet detection efficiency and Modulation Transfer Function challenging requirements

• Adjustment of in pixel conversion factor (CVF) including design and manufacturing tolerances for SNR (Signal-to-Noise Ratio) and dynamic range budgets.

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Figure 34: Photo of a silicon wafer (image credit: GOCI-II Team)

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Figure 35: Die architecture of the CMOS imaging sensor (image credit: GOCI-II Team)

GOCI-II development schedule: The GOCI-II development started in July 2013 and the instrument Flight Model delivery is scheduled for mid-2017. The design, procurement and integration phase take place in Airbus DS in Toulouse (France) with the help of a detached Joint Development Team from KARI and KIOST.

A GOCI-II EM instrument made of EM electronics, including fully representative detector and mechanisms was built for early verification of the detection chains and full instrument functional validation. The EM instrument was delivered to KARI beginning of 2016.

The completion of the GOCI-II Flight Model integration is scheduled by the end of 2016. The first set of performance acceptance tests will be done at the Airbus DS premises in ambient conditions. Then the instrument will be shipped to Korea beginning of 2017 and all the environmental tests (mechanical, thermal vacuum, EMC) will be performed within the KARI facilities in close collaboration between the French and Korean teams.

After the completion of the acceptance tests, the instrument will be formally delivered to KARI. It will then be mounted on GK-2B satellite and launched aboard an Ariane-5 vehicle in 2019.

 


 

Ground System:

GK2A/2B Ground Centers

The GK2A/2B will have ground systems designed to support missions and operations over 10 years, respectively. It is composed of the SOC (Satellite Operations Center), NMSC (National Meteorological Satellite Center), KOSC (Korea Ocean Satellite Center), and ESC (Environmental Satellite Center), as shown in Figure 36. The SOC provides the functionality to operate the GK2A/2B satellite by receiving and transmitting commands to satellites. The NMSC, KOSC, and ESC converts payload data from the satellite into calibrated data. The AMI and GOCI-I/GOCI-II image data are disseminates to end users via the GK2A. The SOC and NMSC/KOSC/ESC will exchange the satellite operations data or image data using the terrestrial data. When required from NMSC, the SOC can resume backup xRIT(LRIT/HRIT/UHRIT) broadcasting service. The each ground center will be integrated by their organizations' responsibility before the satellite launch. 38)

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Figure 36: GK2A/2B Ground Centers (image credit: KARI)

SOC Ground System Configuration: The SOC will be located in Daejeon and fully operated by KARI. It serves the satellite operations and backup data preprocessing with two 9 meter diameter antennas for GK2A and GK2B respectively. The GK2A and 2B use S-band, X-band, and L-band communication frequencies. X-band is used for the downlink of payload data and the downlink of UHRIT dissemination channel.

The SOC is composed of following subsystems as shown in Figure 37.

- CDAS (Communication and Data Acquisition Subsystem) for TTC and imagery data

- ITOS (Integrated Test and Operation System) for TM/TC processing

- MPS (Mission Planning Subsystem) for Mission Scheduling; Two MPSs for GK2A and GK2B satellite

- FDS (Flight Dynamics Subsystem) for Maneuver Planning

- DPS (Data Pre-processing Subsystem) for Radiometric Calibration; Three dedicated DPSs for AMI, GOCI-II, and GEMS

- INR (Image Navigation and Registration) for Geometric Calibration; Three dedicated INRs for AMI, GOCI-II, and GEMS

- PDS (Product Dissemination Subsystem) for AMI xRIT Broadcasting; One PDS for AMI payload

- MSS (Management and Support Subsystem) for Unified Monitoring and Management to SOC operators.

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Figure 37: GK2A/2B SOC Ground Subsystems (image credit: KARI)

SOC Ground System Development Plan: Most ground subsystems of SOC are required to process both GK2A and 2B satellite data during the mission life time. Therefore possible subsystems are being development to cover both satellites as possible, though GK2A and GK2B satellite launch schedules are different. Some subsystems are dedicated for each payload data and payload development schedule. Unified subsystems for GK2A and 2B can be operated as separated systems, menu/function for each GK2A and 2B by configurations.

The SOC ground SW development is in progress with command components in order to improve development efficiency and consistent results among subsystems. Functionalities and interfaces which are required repetitively to all ground SW are developed as "common components" to be reused to all ground SW development. Common components can be categorized for entire GK2A/2B GS and for GK2A GS only, GK2B GS only as follows. There common components will be implemented in Java language for SW reusability.

• Common Components for GK2A/GK2B GS

- Handling components of Log, Status, Audio/Video alarm

- Access components of Data I/O, DBMS, User Authentication

- Common Interface components (FTP, Socket, RPC, REST API etc.)

- Common UI components (Graphic control, User Login, Search control etc.)

• Common Components for GK2A GS

- Access components for GK2A S/C, AMI Configuration and Telemetry

- AMI image products components

- Interface data components for GK2A GS SW

• Common Components for GK2B GS

- Access components for GK2B S/C, GOCI-II, GEMS Configuration and Telemetry

- GOCI-II, GEMS image products components

- Interface data components for GK2B GS SW

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Figure 38: Common Components Concept for SOC Ground SW Development (image credit: KARI)

 

Major Differences between COMS and GK2 Ground System

Comparing to the existing COMS system, the GK2A/2B ground system is required in the functional and performance aspects as follows:

- Satellite collocation operation for COMS and GK2A/2B

- Manual/automatic optional operation in mission scheduling and flight dynamics

- GEMS (Hyperspectral payload) preprocessing added

- Increased payload data volume more than 20 times in case of AMI

- Faster AMI timeliness requirement compared to the current COMS' requirement from 15minutes to 3 minutes (Calibration and broadcasting shall be completed within 3 minutes after the full Earth observation)

- New ultra-HRIT broadcasting service to disseminate the all AMI L1B product in the DVB-S2 protocol

- Compatible LRIT/HRIT services with the current COMS' services.

In addition to things mentioned above, there are more different items. The Ka-band communication payload (communication missions) does not exist in the GK2A/2B satellites but the GEMS (environmental monitoring missions) will be embarked to GK2B.

The AMI will exhibit higher performance in temporal, spatial, and spectral resolution in comparison with the COMS MI (Metrological Imager). The GK-2A AMI will provide 16 spectral bands in the visible, near-IR, and IR spectrum, 5 times better than current COMS MI. Its spatial resolution will be improved 2 times better capability of COMS. Moreover, the AMI can observe the full disk image as short as 10 minutes, 3 times faster than current imager. Large amount of AMI raw data will be delivered to ground in X-band.

For SOC which performs satellite operations and data preprocessing, entire SOC ground system and satellites operational status will be displayed in comprehensive configurations as shown in Figure39. Based on the COMS ground system experience, operator friendly functions such as report generation and primary/backup synchronization functions will be added to GK2A/2B ground system.

GeoKompsat2_Auto0

Figure 39: GK2A MSS (Management and Support Subsystem) GUI (Graphical User Interface), image credit: KARI

 

GK2 Broadcasting Service

The GK2A satellite will be equipped with an on-board transponder for data direct broadcasting like the COMS. The AMI/GOCI-II imagery data, AMI level 2 product and value-added data will be disseminated to end users. The GK2 broadcasting service can be categorized into 3 service channels depending on data rate and contents: LRIT, HRIT and UHRIT.

The GK2 LRIT (Low Rate Information Transmission) and HRIT (High Rate Information Transmission) will take over the current COMS' LRIT and HRIT broadcasting service. The GK2 ground system will process down-sizing of AMI imagery data in close bands with current MI to generate approximately identical contents and formats. Not to make any technical problems to existing COMS end-users systems, the GK2 LRIT and HRIT will be downlinked to end users system through same RF characteristics and data format. The current COMS provides LRIT and HRIT broadcasting service in L-band from 2011 for free but user registration is required to key information from KMA (Korean Meteorological Administration).

The UHRIT (Ultra-UHRIT) will be newly added as a means of AMI imagery data dissemination in full resolutions and channels using DVB-S2 (Digital Video Broadcasting-Satellite-Second Generation). The current COMS end-user can receive GK2 LRIT/HRIT signals but users who want to receive new UHRIT channel are required X-band reception system and processing system including DVB-S2 equipment. Table 15 shows the GK2 LRIT, HRIT and UHRIT downlink characteristics. Detailed sequences of AMI observation/dissemination mode and time frames are under consideration by KMA.

Parameter

LRIT

HRIT

UHRIT

Downlink frequency

1692.14 MHz

1695.4 MHz

8307.5 MHz

Max. data rate

256 kbit/s

3 Mbit/s

31 Mbit/s

Coding

RS(255, 223,4) + Conv(1/2, K=7)

RS(255, 223,4) + Conv(1/2, K=7)

BCH + LDPC 2/3 of DVB-S2 standard

Polarization

Linear in EW

Linear in EW

LHCP

Modulation

NRZ-L/BPSK

NRZ-L/QPSK

NRZ-L/8PSK

Compression

Yes

Yes

Yes

Encryption

Yes

Yes

Yes

Table 15: GK2 broadcasting downlink characteristics

The SOC ground system for GK2 is required to be operated 24hr/365days and to control 2 satellites, and high-resolution/ large amount of data preprocessing during lifetime. The required data preprocessing time has been shorten though image resolution and data amount have been increased. Therefore proper distributed processing, automatic recovery mechanism, optimized file transfer methods are being selected by related prototyping tests.

The SOC ground system for GK2A will be integrated in 2017 and SOC for GK2B will be integrated in 2018. During the GK2A IOT phase, GK2B SOC systems are supposed to be integrated and tested. The overlapped period in the SOC ground system development schedule for GK2A and 2B can get solved by using efficient development policy such as common component modules and unified operations system development. The unified operations system and automatic processing in mission planning/flight dynamics are expected to reduce burden for 2 satellite operations.


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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 (herb.kramer@gmx.net).

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