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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 35E~55E and 16N~30N. 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.
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: 32Mbps2
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 : 310-3/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

 

 

Main body of Scanning Radiometer

Temperature Control Circuit of Radiation Cooler
Secondary Power of Radiometer
TM&TC
TC      
Signal Processor, VDM, CPU and other Electronic Equipment
   
Signal to Transmitter
TM
   
   
Scan Driving Circuit
TM & TC
Clock Signal
Precision Sun Signal
Time Sequence Signal
 

 

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

 

 

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