Delfi-C3 control system development and verification
- Paper number
IAC-06-C1.2.02
- Author
Mr. Fedde Poppenk, Delft University of Technology, The Netherlands
- Coauthor
Mr. Rouzbeh Amini, Delft University of Technology, The Netherlands
- Year
2006
- Abstract
Delfi-C3 is a nanosatellite, currently under development by primarily Msc. students from Delft University of Technology in the Netherlands. Delfi-C3 is to fly three payloads: Thin Film Solar Cells (TFSC), an Autonomous Wireless Sun Sensor (AWSS) and a highly efficient transceiver. The paper explains the feasibility to obtain valuable results using a simple passive hysteresis based attitude control system keeping angular velocities between acceptable boundaries. Both the Thin Film Solar Cells and the Autonomous Wireless Sun Sensor are best tested under gradually changing light conditions. None of the payloads require a fixed or stable attitude. Therefore, the satellite is designed to gently tumble about all three axes in its orbit. As the satellite is carried into space as a piggyback payload and deployed from a P-POD or T-POD canister, orbital parameters and initial and angular velocity can not be chosen, but are the consequence of the launcher’s primary mission and uncontrolled deployment velocities respectively. To obtain valuable results from the TFSC and the AWSS, high angular velocities as well as zero rotation rates are undesirable. This is because Delfi-C3 carries 4 TFSC panels and two AWSS, all facing different directions, that all have to be in Sun light some time. Delfi-C3 should therefore have an attitude control system to keep its angular velocities within certain boundaries. Currently a concept using hysteresis rods on all three axes is designed to passively control the attitude of Delfi-C3. Although hysteresis based control mechanisms in combination with a permanent magnet have been used in many missions before, Delfi-C3 would be the first to fly with hysteresis rods on all three axes. Subject of the paper is to present the principle of a hysteresis based passive control system on all three axis of a satellite; the system as designed for Delfi-C3; the boundaries in which Delfi-C3 functions and how the control system achieves to keep the angular velocities within these boundaries. The paper discusses the validation of the system using simulations and a test setup including a Helmholtz cage to create a simulated in-orbit magnetic field. The paper will go into detail on the results of the simulation and test results and aim to draw conclusions about the feasibility of the designed system.
- Abstract document
- Manuscript document
IAC-06-C1.2.02.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.