Year 2006 – 2007
Koushnir Gregory, Wiesel Yuval, Pianin Alex, Korolyov Anastasia, Belozerkovsky Maxim, Morgenstern Sarah, Semionov Semion
Faculty of Aerospace Engineering, Technion, Israel;
Herscovitz Jacob, RAFAEL, Israel
Dr. Ortenberg Fred, Asher Space Research Institute, Technion, Israel;
One of the main fields in satellite business is Little LEO Messaging Services. A possible use for such systems is automated meter reading – collection and distribution of small portions of data from various sources over large areas. Thus the primary objective of SABRES was to design a constellation of microsatellites (up to 75 kg), with the ability to monitor thousands of satellite models all over the world. The number of clients (meters) and the frequency of the communication sessions were chosen to simulate a realistic demand.
The designed constellation includes 8 satellites, spread equally along 2 planes. The orbits are circular, with altitude of 900 km, inclination angle of 63[deg] and relative RAAN between the planes of ΔΩ=120 [deg]. The ground segment includes 3 ground stations located in Haifa, Canberra and Los-Angeles. The chosen combination of space segment and ground segment allows to access more than 200,000 users each day, with at least 50% of a daily-monitored users.
Each satellite is of a conventional cubic form with side length of 0.5 m, and mass of 48 kg. The communication with the meters is conducted through UHF band (137-138MHz / 148-150MHz, uplink/downlink) using store-and-forward technique. The communication with the ground station is conducted through VHF band (149.9-150.05 MHz / 399-406 MHz). For those purposes 5 antennas were place on the nadir-oriented side – one for VHF, and 4 for UHF.
In addition to primary task, a secondary scientific mission was proposed. Utilizing the design requirement for a global constellation, and the equipment that was chosen in the conceptual design stage, the team has proposed to monitor the Earth’s magnetic field. It is accomplished using TFM-65 magnetometer (dynamic range of ±60 µT). To shield the sensor from spacecraft induced EMI, the magnetometer was placed on a deployable 5m boom, which also takes a major part in satellite control, adding gravity stabilization along the “z” axis.