Title :
Microsatellite combined attitude/energy systems
Author_Institution :
Korea Adv. Inst. of Sci. & Technol., Daejeon, South Korea
fDate :
4/1/2004 12:00:00 AM
Abstract :
We have constructed a high-temperature super conductor-magnet momentum wheel for microsatellites and propose a micro high-temperature superconductor energy storage and attitude control system for nano/pico satellites. The momentum wheel for micro satellites has a mass of 1.1 kg with an angular momentum capacity of 3.5 J sec. It occupies a volume of 12.7 cm in diameter and 5 cm in height. It operates within the restricted power budget of a microsatellite with a total power supply of only 10 watts. It consumes less than 1 watt for sustenance. The micro high-temperature superconductor flywheel for nano/pico satellites has an angular momentum capacity of 0.083 Js and stores 2.32 kJ at 530 krpm. Its energy storage capacity is approximately 45 Wh/kg with an energy density of around 370 kJ/L. The HTS systems can perform the dual function of a power/attitude control system and are ideally suited for low Earth orbit energy storage, power generation, and attitude control of spacecraft.
Keywords :
aerospace instrumentation; artificial satellites; attitude control; high-temperature superconductors; superconducting devices; 10 W; Earth orbit energy storage; HTS systems; HTS-magnet momentum wheel; angular momentum capacity; attitude-energy systems; energy density; energy storage capacity; high-temperature superconductor; micro HTS flywheel; microsatellite; nanopico satellites; power control system; power generation; spacecraft control; superconductor attitude control system; superconductor energy storage; Control systems; Energy storage; Flywheels; Friction; High temperature superconductors; Low earth orbit satellites; Power supplies; Space vehicles; Superconducting magnets; Wheels;
Journal_Title :
Aerospace and Electronic Systems Magazine, IEEE
DOI :
10.1109/MAES.2004.1301771
