VELOX-I is the first Singapore nanosatellite to operate in Low Earth’s Orbit (LEO). It is part of NTU’s Undergraduate Satellite Program, which provides an opportunity for engineering students to participate in a multidisciplinary hands-on space project.
Besides educational objective, VELOX-I also contributes to the nanosatellite research with its technology demonstration and scientific payloads.
• To launch the first Singapore’s nanosatellite VELOX-I, which is designed, built, and operated by students from different schools in the College of Engineering, NTU.
• To acquire images of Earth and transmit them back to ground station. A narrow angle camera with tele-optics is used to provide high-resolution images of Earth from LEO.
• To carry out experiments relevant to technology demonstration.Payloads include: a vision system, a dual-FOV sun sensor.
• To piggyback launch a picosatellite (VELOX-PIII) for intersatellite communication experiment.
||100mm x 100mm x 340mm (VELOX-I), 60mm x 70mm x 30mm (VELOX-PIII)|
||4088 grams (VELOX-I), 193 grams (VELOX-PIII), total 4281 grams|
||12 months (VELOX-I), 6 months (VELOX-PIII)|
||Sun-synchronous low earth orbit (LEO), 650 – 700 km altitude|
|Attitude determination and control system
||(VELOX-I) 3-axis stabilized and controlled with 1 GPS receiver, 2 IMUs, 1 dual-FOV sun sensor, 8 coarse sun sensors, 3 magnetic torquers and 3 RWs|
|On-board data handling
||Mainboard with 100MHz 8051 MCU, 2Gb SD card, UART and I2C data interfaces|
||9600bps BPSK downlink / 1200bps AFSK uplink, UHF & VHF dipoles|
||(VELOX-I) 4 deployable GaAs panels for 28.8W peak, 5200mAh Li-ion battery |
||Al. 7075 chassis, with stainless steel/Ti-6Al-4V load bearing parts; spring-loaded separator, solar panel deployer, and optics extension mechanism|
||Multi-Layer Insulation (MLI) and battery heaters|
||Vision system with extended optics for 20m GSD, GPS payload for precision navigation experiment|
||Ground station in NTU with UHF/VHF high-gain cross Yagi-Uda antennas|
VELOX-I launch configuration
VELOX-I after deployment
Satellite under vibration test
Attitude determination system comprises dual redundancy of MEMS IMU & GPS
Power supply system with fault redundancy and peak power tracking capability
Testing of attitude control system on an air bearing setup
Satellite under vacuum chamber test
Structure of VELOX-I