The Intersatellite Separation System: A Lightweight, Low-Power Deployment Mechanism for Formation Flying Nanosatellites
- Paper number
IAC-08.B4.6.B8
- Author
Mr. Benoit Larouche, York University, Canada
- Coauthor
Mr. Jonathan Grzymisch, University of Toronto Institute for Aerospace Studies, Canada
- Coauthor
Mr. Grant Bonin, University of Toronto Institute for Aerospace Studies, Canada
- Coauthor
Mr. Cordell Grant, University of Toronto Institute for Aerospace Studies, Canada
- Coauthor
Dr. Robert E. Zee, University of Toronto, Canada
- Year
2008
- Abstract
The Space Flight Laboratory (SFL) at the University of Toronto Institute for Aerospace Studies (UTIAS) is developing enabling technologies for future precise formation flying missions. These technologies will be validated on an upcoming mission under development as part of SFL’s Canadian Advanced Nanospace eXperiment (CanX) program. The CanX-4CanX-5 mission consists of a pair of identical nanosatellites, launched together, which will be the first to demonstrate autonomous on-orbit formation flight using nanosatellites. With a mass of only 7kg and 20 cm cubical form factor, these identical satellites will achieve relative position determination to within a few centimeters, while controlling their relative position to an accuracy of less than one meter. One integral technology being developed at SFL for the launch and commissioning stages of the formation flying mission is the intersatellite separation system (ISS). The primary function of the ISS is to maintain a mechanical link between the two satellites after deployment from the launch vehicle in order to avoid excessive drifting of the satellites before the propulsion system is commissioned. The basic requirements of the ISS are lightweight construction, small footprint, low activation power and perhaps most importantly, the ability to maintain the link with no power. The ISS will employ a basic spring loaded cup and cone system (one located on each satellite) that will be mated together using an electrically debonding agent. When the command is given, a small 12 Vdc potential will be applied across the bond, which will weaken the bond strength to 5 to 10% of its original strength. This weakening will allow the springs to create enough stress to break the bond, releasing the potential energy in the spring and giving each of the two satellites a small amount of delta V. This delta Vis used to achieve an initial separation distance of approximately 1 km at which point formation flying will begin. This paper will examine the design of the intersatellite separation system as well as the analysis performed to date. It will focus on the spring selection, the separation sensing and the imparted delta V required to achieve the initial positioning of the two satellites for the beginning of the formation flying mission. Furthermore, testing procedures and results will be explored as the electrically debonding agent is being qualified for space use for the first time in history.
- Abstract document
- Manuscript document
IAC-08.B4.6.B8.pdf (🔒 authorized access only).
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