ADEO Passive De-Orbit Subsystem Activity leading to a Dragsail Demonstrator: Conclusion and Next Steps
- Paper number
IAC-17,A6,IP,14,x38951
- Author
Dr. Thomas Sinn, HPS GmbH, Germany
- Coauthor
Dr. Lars Tiedemann, HPS GmbH, Germany
- Coauthor
Mr. Arne Riemer, HTS GmbH, Germany
- Coauthor
Mr. Hahn Robert, HTS GmbH, Germany
- Coauthor
Mr. Tom Spröwitz, DLR German Aerospace Center - Institute of Space Systems, Germany
- Coauthor
Mr. Patric Seefeldt, German Aerospace Center (DLR), Germany
- Coauthor
Mr. Siebo Reershemius, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), Germany
- Coauthor
Dr. Maciej Sznajder, DLR German Aerospace Center - Institute of Space Systems, Germany
- Coauthor
Mr. Sebastian Meyer, German Aerospace Center (DLR), Germany
- Coauthor
Mr. Martin Zander, German Aerospace Center (DLR), Germany
- Coauthor
Dr. Karl Dietrich Bunte, Eta Max Space GmbH, Germany
- Coauthor
Mr. Sven Weikert, Astos Solutions GmbH, Germany
- Coauthor
Mr. Andreas Wiegand, Astos Solutions GmbH, Germany
- Coauthor
Ms. Tiziana CARDONE, European Space Agency (ESA), The Netherlands
- Coauthor
Mr. Daniele Teti, European Space Agency (ESA), The Netherlands
- Coauthor
Dr. Robert Knockaert, ESA - European Space Agency, The Netherlands
- Year
2017
- Abstract
The space debris environment, especially in low earth orbit, is an increasing risk for all spaceflight missions. Without effective mitigation measures the debris density will increase to a level where spaceflight becomes more and more endangered. Therefore, to ensure safety for future space flight, end-of-life de-orbiting of satellites and upper stages is required by the respective standards. Deployable gossamer structures for drag sails might offer a passive de-orbit solution. The paper at hand outlines the development of such a system applicable for LEO satellites between 100 kg to 1000kg. It is based on the Gossamer-1 technology of the German Aerospace Center (DLR). Further developments are pursued in the ESA project “Architectural Design and Testing of a De-orbiting Subsystem” (ADEO). The ADEO subsystem is a scalable drag augmentation device that uses the residual Earth atmosphere present in low Earth orbit. For initiation of the de-orbit maneuver a large surface is deployed which multiplies the drag effective surface of the satellite. Thereby the drag force is increased as well causing accelerated decay in orbit altitude. Advantageous about a drag augmentation device is that it does not require any active steering and can be designed for passive attitude stabilization thereby making it applicable for non-operational, tumbling spacecraft as well. The ADEO subsystem consists of four deployable CFRP booms that span four sail segments with a total area of 25 m2 in a truncated pyramid shape configuration. While the sails are made of an aluminum coated polyimide foil, its coating thickness was chosen such that it provides sufficient protection from the space environment. To prove the survivability of the sail material in the space environment over 25 years de-orbiting time, multiple environmental tests were performed at material and sample level, including mechanical strength and stiffness tests, thermal cycling, atomic oxygen exposure tests, UV exposure tests, and high velocity impact tests, as well as crack propagation tests at room and reduced temperature. A fully functional full scale demonstrator with one sail and two booms has been subjected to environmental testing including, vibration, rapid decompression, deployment testing in thermal-vacuum environment and ambient conditions showing great performance. An overview of the design, the results the extensive demonstrator test campaign as well as the next steps leading to an in orbit demonstration will be the main body of this paper.
- Abstract document
- Manuscript document
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