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MECHANICAL CHARACTERIZATION OF DEPLOYABLE THIN SHELL CFRP BOOMS FOR THE CUBESAT “DE-ORBIT SAIL”

Zander, Martin und Hillebrandt, Martin und Sinapius, Michael und Hühne, Christian (2015) MECHANICAL CHARACTERIZATION OF DEPLOYABLE THIN SHELL CFRP BOOMS FOR THE CUBESAT “DE-ORBIT SAIL”. IAC 2015 – The 66th International Astronautical Congress, 2015-10-12 - 2015-10-16, Jerusalem, Israel. (im Druck)

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Kurzfassung

The risk for spacecraft in Low Earth orbit (LEO) to be hit or damaged is increasing due to a growing space debris population. Reduction and limitation of this risk is addressed by de-orbiting end-of-life maneuvers. To realize such a maneuver a drag augmentation device that increases the drag efficient surface of a satellite, acting with the residual atmosphere and accelerating the decay of orbit altitude until re-entry into Earth’s atmosphere, is necessary. Currently such a device is being flown with the CubeSat based drag sail satellite DeorbitSail by the University of Surrey, DLR, and other partners. The goal is to demonstrate the in-orbit deployment of a 4 m x 4 m drag sail, suitable for small and medium size satellites, as an end-of-life de-orbiting device. The device has a squared sail design utilizing 4 triangular membrane sail segments that are deployed and spanned out by thin shell CFRP (carbon fiber reinforced plastics) booms developed by DLR. The focus of this paper is on one of the main structures, the deployable thin shell CFRP-booms that are susceptible to buckling. Properties and characteristics of full scale booms regarding structural load capacities in all applicable load directions are being determined in a newly introduced vertical test stand. Thresholds and robustness for certain load cases like axial compression and lateral bending, and load carrying capabilities after buckling several times, are determined and quantified in practical testing, thus specifying the boom performance in reality. This is of high importance in order to be able to predict and design a robust drag sail structure, not failing due to overloading in space. This paper gives information of the applicable loading on the booms derived by the space application, the used test stand and equipment as well as the testing itself. Finally the acquired test results are analyzed and discussed.

elib-URL des Eintrags:https://elib.dlr.de/111631/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:MECHANICAL CHARACTERIZATION OF DEPLOYABLE THIN SHELL CFRP BOOMS FOR THE CUBESAT “DE-ORBIT SAIL”
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Zander, MartinMartin.Zander (at) dlr.dehttps://orcid.org/0000-0001-5972-2938NICHT SPEZIFIZIERT
Hillebrandt, MartinMartin.Hillebrandt (at) dlr.dehttps://orcid.org/0000-0003-1248-9504NICHT SPEZIFIZIERT
Sinapius, MichaelTU Braunschweig / DLR BraunschweigNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Hühne, Christiandlr – institut für faserverbundleichtbau und adaptronik, braunschweighttps://orcid.org/0000-0002-2218-1223NICHT SPEZIFIZIERT
Datum:Oktober 2015
Referierte Publikation:Ja
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
Status:im Druck
Stichwörter:Gossamer structures, CFRP, booms, testing
Veranstaltungstitel:IAC 2015 – The 66th International Astronautical Congress
Veranstaltungsort:Jerusalem, Israel
Veranstaltungsart:internationale Konferenz
Veranstaltungsbeginn:12 Oktober 2015
Veranstaltungsende:16 Oktober 2015
Veranstalter :IAF International Astronautical Federation
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Raumfahrt
HGF - Programmthema:Technik für Raumfahrtsysteme
DLR - Schwerpunkt:Raumfahrt
DLR - Forschungsgebiet:R SY - Technik für Raumfahrtsysteme
DLR - Teilgebiet (Projekt, Vorhaben):R - Entfaltungstechnologie . Solar Sail (alt)
Standort: Braunschweig
Institute & Einrichtungen:Institut für Faserverbundleichtbau und Adaptronik > Funktionsleichtbau
Hinterlegt von: Zander, Martin E.
Hinterlegt am:29 Jun 2017 13:06
Letzte Änderung:24 Apr 2024 20:16

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