Steering Committee Organization Team Members Schedule
Space Segment Ground Segment Launch Segment

XSAT Bus Parameters

The project focuses mainly on developing the XSAT bus for carrying the various mission payloads. The XSAT Micro-satellite carrying the intended mission payloads will have the following design parameters:

Orbit Altitude
Sun-synchronous LEO with altitude about 680-800km
Mass
 < 120 kg Micro-Satellite Class
Physical Dimension 0.6mx0.6m at the base and 0.8m in height
Attitude Control 3 axis stabilized to 0.35o accuracy (no propulsion)
Solar Panel 2 Deployable & 1 fixed panel (0.82 m2)
Power Maximum 240 watts
TT&C S Band (CCSDS Protocol)
Payload Downlink X band
Battery Li-Ion Type (13.5 Ahr capacity)

XSAT Primary Payloads

The primary payload is an electro-optical instrument (called IRIS) from SaTRaCi with design specifications such as:

  • 3 Band Multi-spectral (0.52~0.60, 0.63~0.69, 0.76~0.89 mm)
  • 10m GSD at 685KM orbital altitude
  • More than 50km swath width
  • 25W power comsumption
  • 12kg mass (for optics assembly and electronics)
  • Dimension of 180mmx530mm for optical portion (EOU)
  • Dimension of 320mmx210mmx150mm for electronic portion (PCU)

    Secondary Payloads

    The two secondary payloads are PPU and DLR-GPS.
    (a) PPU: A NTU-developed software payload (called Parallel Processing Unit)  for experimentation of COTS electronics and FPGAs to perform reliable imaging algorithmic functions (image selection, classification, compression) in space.
    (b) DLR GPS: A GPS receiver that would be provided by DLR of Germany for on-board experimentation using XSAT micro-satellite mission.