| Educate
Me | Satellite
Talks was held on the cooperation
project of building an earth observation
network by the joint efforts of China and
Saudi Arabia on January 15 2010. The main
intention of the project is to purchase
China made satellite by Saudi Arabia for
the purpose of monitoring flood and water
logging as well as crude oil leakage over
the territory of SA and its surrounding
area and therefore.
Requirement Analysis
Monitoring of Flooding
and Water logging
- The Kingdom of Saudi Arabia locates
in the middle of Arabian Peninsular.
The Persian Gulf lies to the northeast
and Red Sea to its west. Most of its
territory is in between 35E~55E and
16N~30N. Its western plateau is of
Mediterranean Sea climate, while the
eastern region is of sub-tropical desert
climate. In recent years, because of
the severed rainstorm in the western
parts of Saudi Arabia, the flooding
merged the urban streets, which resulted
in landslide, building collapsed and
cause human casualties and economical
loss.
- Flooding and water logging were caused
by severe rainstorm, which is of middle
and small-scale weather system and is
the main reason causing catastrophic
weather. Nowadays, in terms of space
technology and remote-sensing applications,
Geostationary Metrological Satellite
plays an important role in monitoring
middle and small-scale weather disaster,
and this role can be substituted by
nothing. The Geostationary Metrological
Satellite takes advantage of its stationary
orbit to frequently acquire cloud images
and make animation. Therefore, it can
enhance the monitoring capability over
middle & small scale weather system,
and play an important role in typhoon
and rainstorm forecasting.
- In order to compensate the relatively
lower resolution of stationary orbit
metrological satellite (normally around
1 km for visible and about 5km for inferred),
Low Earth Orbit Metrological Satellite
equipped with mid-resolution spectrometer
can be used to improve the resolution
to about 250 m. And moreover, the swath
width of the low earth orbit satellite
is over 2845km, which can cover the
whole territory of Saudi Arabia, and
thus to enhance the ability of rainstorm
forecasting and facilitate monitoring
and assessment of disaster such as floods
and water logging disaster.
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 |
Global
Disk Image by Stationary Meteorological
Satellite
|
Rain Storm
Monitoring Image
by Mid-resolution Imaging Spectrometer |
Monitoring of Crude
Oil Leakage
- Saudi Arabia is a country with rich
petroleum resources, and is the world’s
leading petroleum exporter. Ghawar Oil
Field is the largest inland oil field,
while the Safaniya Oil Field is the
largest offshore one. Saudi Arabia is
near the Red Sea, Persian Gulf and Arabian
Gulf; moreover, oil pipelines are densely
laid. Hence, it is urgently needed to
have some means of round-the-clock,
all weather oil spill monitoring, especially
for oil leakage contamination in the
Gulf Area.
- Oil spill on the ocean can be monitored
by optical remote sensor. Oil contamination
is be discovered by different sunlight
reflection through visible and infrared
channels, the target can be checked
and identified by high contrast in narrow
band in electromagnetic wave.
- The oil film reflected by green, red
light band centered with 0.55μm and
0.645μm are the present the best. Therefore,
it can be selected as best choice for
ocean oil film monitoring band by high
spectrum remote sensing. The mid-resolution
spectrum imager with swath about 2845
Km can cover the whole SA territory
by one track, realizing better earth
surface environment monitoring.
- On April 20, 2010, oil spill occurred
in Mexico Gulf after explosion and sunk
of “Deepwater Horizon”. The contaminated
area was correctly evaluated by mid-resolution
spectrum imager MERSI of FY-3 over maritime
space of Louisiana State near Mexico
Gulf on April 29, 2010 by FY-3
 |
|
The position of “Deepwater Horizon”
explosion was detected
by FY-3 mid-resolution spectrum
imager
|
| |
 |
Oil
Spill was monitored by FY-3 mid-resolution
spectrum imager
over Mexico Gulf |
System Concept for Saudi
Arabia Earth Observation Satellite
- Based on the above project requirement
analysis, two concepts are proposed
to build a Sino-Saudi Arabia Earth Observation
System meeting demand of monitoring
flood, water logging and crude oil spill
over Saudi Arabia territory and surrounding
area.
- Concept 1: using
one Geostationary Meteorological
Satellite (GMS) and one Low Earth
Orbit Optical Satellite (LEOS);
- Concept 2: using
two Geostationary Meteorological
Satellite, one for operation, one
for
redundancy, realizing “two satellite
observing together, and mutually
redundant”; and two Low Earth Orbit
Optical Satellites observing SA
four
times daily. The specific concept
is decided by negotiation between
China and Saudi Arabia.
- The GMS is equipped with a multi-channel
Scanning Radiometer for small-and-medium
scale severe storm weather system forecast,
A medium resolution spectrometer onboard
the LEOS not only improved the forecast
of sever storm and evaluation of disastrous
lost owing to flood and water logging,
but also facilitates monitoring of oil
spill over the ocean
- Chinese meteorological satellite platform
FY-2 can be used for Geostationary Environmental
satellite. Its main payload a 5-channel
radiometer, among which, 1 for visible,
3 for infrared and 1 for water vapor.
The resolution of visible channel is
1.25 Km and 5 Km for both infrared and
water vapor, capable of obtaining 28
global disc images daily. Besides, more
images over Saudi Arabian mainland can
be obtained. During stormy season, when
working in repeated scanning mode, 48
images (among them, 28 are global disc
images, and 20 northern hemisphere images)
can be obtained daily. Moreover, quick
scanning and imaging over Saudi Arabian
territory can be realized in 5 minutes.
The liftoff mass of FY-2 is 1390 Kg;
maximum power at the end of life is
334w; and the designed lifetime is 5
years.
- The platform of Chinese meteorological
satellite FY-1 can be used for Low Earth
Orbit Optical satellite. A medium resolution
spectrometer (MRS) which is flown on
Chinese meteorological satellite FY-3
can be used for the main payload, which
has 10 visible, 7 near infrared and
2 infrared as well as 1 thermal infrared
channels, working in 10 or 40 element
parallel scanning modes realizing 1000m
and 250m ground resolution with a swath
of 2845 Km. The liftoff mass of LEOS
is 800 Kg, the long term power output
is 450 W and short term 600 W. The designed
lifespan is 4 years.
- The total Saudi Arabian Earth Remote
Observation System should include satellite,
ground telemetry and control network,
ground application system and launch
vehicle as well as the satellite launching
center.
- It is suggested to use Chinese Long
March series as the launch vehicle and
the satellite to be launched in China.
The launch vehicle of Long March series
has already launched more than 100 satellites,
therefore, rich experience has been
obtained for the launching service.
And what is more, the Long March series
totally matches Chinese Satellite Launching
Center in every aspect.
- It is also suggested to operate the
satellites under the unified planning
of China Satellite Telemetry and Control
Center by the joint efforts of China
and Saudi Arabia. Ground telemetry and
control stations can be built through
cooperation.
- The ground application system is recommended
to be built under China’s assistance.
Meanwhile, the existing ground facilities
in China can also be used for operating
the satellite and data reception, handling
and dissemination.
Geostationary
Meteorological Satellite
Item
|
Specifications
|
Orbit
|
Geostationary
orbit
positioning: 45E°(temporary operational
location)
60E°(temporary operational location)
Station keeping: S/N ±2.5°,E/W ±0.5°
|
Payload
|
Scanning
Radiometer:
⑴ visible channel: operational band:0.55~0.75μm
Spatial resolution:1.25Km
Signal to noise ratio:S/N≥1.2(albedo
0.5%)
⑵ infrared channel 1:operational band:10.3~11.3μm
Spatial resolution:5Km
NE△T:0.2K(300K)
⑶ infrared channel 2:operational band:11.5~12.5μm
Spatial resolution:5Km
NE△T:0.2K(300K)
⑷ infrared channel 3:operational band:3.5~4.0μm
Spatial resolution:5Km
NE△T:0.3K(300K)
⑸ water vapor channel:operational
band:6.3~7.6μm
Spatial resolution:5Km
NE△T: 0.3K(260K)
⑹ time resolution: normal observation:
28 full disc images/day
Densely Scanning observation: 48 images/day(28
full disc images, 20 Northern Hemisphere)
Regional observation:5min/Scan |
Data Transmission
and Image Disseminator
|
S-band,
Modulation:QPSK/PCM , Bite Rate:14Mbps
|
TT&C
|
UCB and
USB |
Power
supply
|
Solar
Array: ≥ 333W
Cd-Ni Battery: ≥ 243W |
Propulsion
|
Mono-propellant
Propulsion System,6 20N Thrusters,
Total Propellant: 60kg (N2H4) |
Attitude
Control
|
Spin Stabilization
Spinning Velocity: 99.5 rpm
Attitude Control Accuracy: ±0.5º
Attitude Measurement Accuracy:≤0.07º
Short-term Attitude Stability: 3.5
micro-radian/0.6s
Long-term Attitude Stability: 35 micro-radian/30
min |
Liftoff
Mass
|
1390kg |
Lifetime
|
5 Years |
Reliability
|
≥0.60 |
Low Earth Orbit
Optical Satellite
Item
|
Specifications
|
Orbit
|
Sun Synchronous
Orbit
Average Altitude: 826km
Eccentricity: e<0.003
Inclination: 98.6º
Period: 101min |
Payload
|
Medium-resolution
Imaging Spectrometer
Operational Band: 0.412~11.25 µm
Number of Channels: 20
Resolution: 250 and 1000m
Swath width: 2845km |
Data Transmission
and Storage
|
X band:
QPSK Modulation
Data Rate: 32Mbps2 |
TT&C
House-Keeping
|
TT&C
System: USB
Bus: 1553B |
Power
supply
|
Power
by solar array and batteries
Two-wing Solar array, Sun-orientated;
Solar Cell: Single Crystal Si
Battery: Cd-Ni |
Propulsion
|
Thrusters:16
thrusters of 5N, 20 thrusters of 8N
Total Weight of Hydrazine: 37.5kg |
AOC
|
Three-axis
Attitude Accuracy: 0.05(3)Three-axis
Attitude Stability : 310-3/s(3) |
Liftoff
Mass
|
800 kg |
Lifetime
|
4 years |
Reliability
|
≥0.6 |
Orbit and Related
Parameters
- With respect to the geological features
of Saudi Arabia, an orbit with an inclination
of 98.6° and an altitude of 826 Km is
chosen for the satellite. This altitude
allows the satellite to get a much broader
field of view. The swath of one satellite
can cover the whole territory of Saudi
Arabia twice a day and one in the day
and the other in the night.
- When operating in the orbit with an
altitude of 826 Km, the medium-resolution
imaging spectrometer on board the satellite
can get a plunge angle of -55º~+55°,
the ground swath can reach to 2845 Km.
Thereby, it can offer a 100% coverage
of S.A. and its surrounding areas.
| Item |
Parameters |
Average Orbit Altitude
|
826km |
Semi-major Axis
|
7197km |
Inclination
|
98.6° |
Eccentricity
|
<0.003 |
Period
|
101min. |
Revisit times per day
|
2 |
Cycles/day
|
14 |
 |
Daily
coverage over Saudi Arabia in ascending
and descending orbit
with an altitude of 826km (Optical
Payload) |
Geostationary Meteorological
Satellite System Concept
- Since Chinese first geostationary
meteorological satellite FY-2A was successful
launched, China had successfully launched
5 geostationary satellite till FY-2E
was sent to geostationary orbit in 2008.
- Now, FY-2C, FY-2D, and FY-2E are in
normal operation, which were positioned
in East Longitude of 123.5, 86.5 and
105 degree respectively over the equator,
realizing double satellite observing
together with one in-orbit standby mode
presenting excellent effect in the monitoring
disastrous weather such as typhoon,
rain storm, sand storm, forest fire
and environment monitoring.
- FY-2 satellite is of matured technology
has kept stable in orbit operation for
a long time. Therefore, this concept
takes FY-2 as design base line. Just
some adaptability modifications made,
user’s mission requirement can be met.
Satellite Configuration
The configuration of the
satellite is a cylindrical body with double
cylinders (inner and outer cylinders). The
diameter of outer cylinders is 2.1m which
serves as up and down solar array. The inner
cylinder is the central supporting structure.
The total height is 4.78m.

Main Specifications of
the Scanning Radiometer
No.
|
Waveband
(μm)
|
Spatial
Resolution (km)
|
Sensitivity/Signal
Noise Ratio
|
Main
Application |
| 1 |
0.55~0.75
|
1.25
|
S/N≥1.2(ρ=1%)
|
Images
of ground surface, cloud and vegetation
|
| 2 |
3.5~4.0
|
5 |
0.3(300K)
|
Surface
temperature,
Fire spot |
| 3 |
6.3~7.6
|
5 |
0.3(260K)
|
Water
Vapor |
| 4 |
10.3~11.3
|
5 |
0.2K(300K)
|
Day and
night cloud image, temperature of
the ground, ocean surface and cloud
top |
| 5 |
11.5~12.5
|
5 |
0.2K(300K)
|
Day and
night cloud image, temperature of
the ground and ocean surface and cloud
top |
- The maximum scanning range is no less
than 21°N/S×23°E/W. Earth disc image
observation; (19°N/S×19°E/W), it takes
about 30 min for each disc image.
- Observation over the territory of
Saudi Arabia: observation time is 5
min and the repeating time can be adjusted.
Block Diagram of the Scanning
Radiometer
Data Transmission and
Cloud Image Transponder
- S-band data transmission and cloud
image transponders are used for the
transmission of raw cloud image data,
low data rate information, data of main
ranging and sub-ranging stations, voice
signals obtained by the scanning radiometer
and reception and demodulation of uplink
operation signals; modulation and transmission
of operational telemetry signals.
- This system is composed of astronomic
filter, Re/Tr-multiplexer, receiver,
4-phase modulator (QPSK), local oscillator
for data transmission, operational telemetry
demodulator, operational telemetry modulator
and function switch.
Main Specifications of
Cloud image Date Transmitter
No.
|
Parameter
|
Specifications
|
| 1 |
Raw Cloud
Image
|
Data Rate:
14Mbit/s
Modulation Mode: QPSK |
| 2 |
Stretched
Digital Cloud Image
|
Data Rate:
0.66Mbit/S
Modulation Mode: PCM/BPSK |
| 3 |
Low Rate
Information
|
Modulation
Mode: AM/FM |
| 4 |
Operation
Telemetry Signal
|
Data
Rate: 100 bit/s
Modulation Mode: PCM/FSK-AM/FM |
| 5 |
Operation
Telemetry Signal
|
Data
Rate: 2000 bit/s
Modulation Mode: PCM/PSK/PM |
| 6 |
Simulation
Telemetry
|
Modulation
Mode: MFSK/PM |
| 7 |
Three
Points Ranging Signal
|
Modulation
Mode: AM/PM
Main Station;
Sub Station I;
Sub Station II; |
The Critical Specifications
of the Platform
No.
|
Parameter
|
Platform
Capability |
| 1 |
Suitable
Orbit
|
Geostationary
Orbit
Orbital Altitude: 35786km |
| 2 |
Attitude
Control
|
Spin Stabilized
(50~100rpm) |
| 3 |
Measuring
Accuracy
|
Better
than 0.07°(3σ) |
| 4 |
Antenna
Pointing Accuracy
|
Despun
Unit: ≤±0.4°(1σ) |
| 5 |
Attitude
Stability
|
Short
Term Stability: 3.5μrad/0.6s
Long Term Stability: 35rad/30min |
| 6 |
Propulsion
System
|
Mono-absolute
Hydrazine: 60 Kg |
| 7 |
Solar
Cell Array
|
Surface
Mounted with Unified Bus and Trickling
Charging |
| 8 |
Solar
Cell Type
|
Silicon
or Single Junction Ga-As |
| 9 |
Output
Power
|
In
Sunshine: 333W
In Shadow: 243W |
| 10 |
Battery
Unite
|
Complete
Sealing, Sintered Cd-Ni 28Ah |
| 11 |
Power
Bus
|
29±1V
(Whole Bus Regulated) |
| 12 |
Telemetry
System
|
UCB or
USB,Tele-command:254
Main Channel of Tele-measurement:
128 |
| 13 |
Data
Handling
|
/ |
| 14 |
Thermal
Control
|
Mainly
Passive, Partially Active |
| 15 |
Designed
Lifetime
|
5 Years |
Flight Sequence of Launching

Satellite Configuration
The satellite is of modular
design consisting two modules, service module
and the payload module. The size of the
whole satellite is
1420mm×1420mm×1200mm.
| |
 |
 |
 |
Launching
State Configuration |
In-orbit
Configuration |
|
Main Type of Image Product
and Quantitative Product
Items
|
Coverage
|
Frequency |
Full-disc
Stretched Image
|
Disc Image
Centered at Sub-satellite Point
|
25min/time |
Halfl
full-disc Stretched Image
|
Full-disc
Image of North Hemisphere
|
14min/time |
Image
over Saudi Arabia Territory
|
Saudi
Arabia and Its Surrounding Areas
|
5min/time |
Temporary
Observation Image
|
Maneuvering
Selection
|
Irregularly |
Floods
Monitoring
|
Arabian
Peninsula and its surrounding seas
|
1time/day |
Drought
monitoring
|
Arabian
Peninsula
|
1time/day |
Fire monitoring
|
Arabian
Peninsula
|
24times/day |
Dust
storm
|
Arabian
Peninsula
|
8time/day |
 |
| Composition
of the Ground Operational System |
Delivery Schedule
Item
|
EDC
|
Activities |
EDC+1
Mon
|
Initiation
of the Project |
EDC+6
Mon
|
PDR |
EDC+10
Mon
|
CDR |
EDC+16
Mon
|
FDR |
EDC+20
Mon
|
AIT
Start |
EDC+25
Mon
|
End of
Electrical Test, Large Scale Test
Starting |
EDC+32
Mon
|
Delivery
of the Satellite |
EDC+34
Mon
|
Launch
of the Satellite |
EDC+36
Mon
|
In-orbit
Test |
|