The RazakSAT® is a cost-effective 180kg mini satellite capable of high resolution Earth Observation missions.
The satellite will be launched in the middle of July 2009. The design and manufacturing process of this satellite follows the exacting and rigorous established standards of space programs. Using these standards, the RazakSAT® has passed through the phases of Engineering, Qualification and Flight Models.
The primary payload of RazakSAT® is a high resolution Medium-Sized Aperture Camera or MAC, that will provide 2.5 meter resolution panchromatic (black-and-white) and 5 meter resolution multispectral (red, green, blue and near-infrared) images of the earth. RazakSAT will orbit the Earth fourteen times a day. The satellite is three-axis stabilized and has a comprehensive sensor suite including space borne GPS receiver, star tracker, fiber optic gyroscopes, magnetometers, fine and coarse sun sensors. Satellite actuator systems, which include reaction wheels and magnetorquers, allow accurate positioning of the satellite.
The combination of high resolution and large attitude maneuverability allows RazakSAT® to provide highly customised and configurable imaging missions according to customer requirements.
RazakSAT® Satellite Images can be applied for the following applications:
- Agriculture
- Landscape Mapping
- Forest Biomass
- Urban Planning
- Road Network Planning
In brief, the specifications of RazakSAT® are as follows:
| Subsystems | Specifications |
|---|---|
| Altitude | 685 km |
| Inclination | 9 ° |
| Payload (MAC) | GSD : 2.5 m (PAN), 5 m (MS) Swathwidth : 20 km @ 685 km |
| Attitude Determination & Control Subsystem (ADCS) | Three-axis stabilization based on four (reaction wheels) Pointing Accuracy : < 0.2° (2 s) Pointing Knowledge : 1 arcmin (2 s) |
| Electrical Power Subsystem (EPS) | GaAs/Ge solar cells on honeycomb substrate NiCd batteries (18 Ahr) Peak Power Tracking (PPT) & constant current control Solar Power : >300 W @ EOL |
| Command & Data Handling Subsystem (C&DH) | Two on-board computers Telemetry and command interface modules Analog Telemetry channels : up to 90 Digital Telemetry channels : up to 120 |
| Telecommunication Subsystem (TS) | 9,600 bit/s / 1,200 bit/s S-brand TT&C uplink 38.4 kbs / 9,600 bit/s / 1,200 bit/s S-brand TT&C downlink |
| Payload Data Management | 32 Gbit On-board solid-state memory 30 Mbit/s X band payload data downlink |
| Structure & Thermal | Ø1,200 x 1,200 mm Hexagonal shape Mass : 180 kg Modular structure Passive & Active thermal control |
| Mission Lifetime | > 3 Years |
RazakSAT® Launch and Early Operation Phase (LEOP)
RazakSAT® Launch and Early Operation Phase (LEOP) is the next phase in the satellite's lifecycle after completion of the satellite Flight Model. The primary objective is to commision the satellite after separation from the Falcon-1 launcher. The LEOP activities consist of the satellite launch, separation from the launcherm first contact with the satellite with the ground station, conduct in-orbit performance check, calibrating the first payload images and declaring the satellite is ready for nominal operations. All in-orbit operational requirements must be met to ensure full readiness of the satellite.
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