Ahmad Sabirin Arshad
Yasser Asrul Ahmad
Marini Abdul Hamid
Astronautic Technology (M) Sdn Bhd
2, Jalan Jururancang U1/21, Hicom Glenmarie Industrial Park
40000 Shah Alam, Selangor MALAYSIA
Tel: +603-55690100 Fax: +603-55690108
RazakSAT™ is the next generation of the small Earth Observation Satellite. It weighs less than 200kg carrying the optical sensors of the Medium-sized Aperture Camera (MAC. With an attitude accuracy of 0.21o and 3-axis stabilization using four momentum wheels, RazakSAT™ can provide an image with 10m accuracy with respect to the ground sampling distance (GCP). The RazakSAT™ is targeted to orbit the earth at 685km altitude with 9o inclination. It will serve the timely needs of Malaysian experts and users in remote sensing for various applications.
The RazakSAT™ mission is to provide optimum coverage for the Malaysian region using the unique characteristic of the NEqO mission. RazakSAT™ is a small LEO satellite that carries an electro-optical payload, Medium-sized Aperture Camera (MAC). MAC is a pushbroom camera with 5 linear detectors (1 panchromatic, 4 multi-spectral).
The satellite system is able to take images in near equatorial regions and shall be controlled by the Mission Control Station (MCS). Upon the request from image data users, Image Receiving and Processing Station (IRPS) shall request MCS schedule the satellite for imaging opportunity and inform IRPS the possible date, time for image download. The satellite system shall take images of desired near equatorial regions and download the image data along with attitude and ephemeris telemetry data to IRPS.
RazakSAT™ is designed to be compatible with a near-equatorial orbit with altitude ranging from 600 km to 800 km. RazakSAT™ with its stowed solar panels is compatible with most of small satellite launchers as a secondary payload or as a primary payload for small satellite launch such as Falcon 1. The spacecraft bus provides a typical pointing performance of 0.2 deg. The RazakSAT™ weighs less than 200 kg including 50 kg payload mass. The average power consumption is less than 150 Watts. Figure 1 depicts RazakSAT™ in stowed and deployed configuration respectively. The origin of the satellite coordinate system is located at the geometric center of the launch adaptor bottom plane. The +Z-axis is toward the payload optical axis. +X-axis is defined along the scanning direction of MAC, which is normal to the detector lines.
Figure 1: RazakSAT™ in stowed and deployed configuration