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Controlled Deployment of Gossamer Spacecraft

Seefeldt, Patric and Spröwitz, Tom and Spietz, Peter and Mikulz, Eugen and Reershemius, Siebo and Sasaki, Kaname and Toth, Norbert and jahnke, Rico (2017) Controlled Deployment of Gossamer Spacecraft. In: Proceedings of The Fourth International Symposium on Solar Sailing. The Fourth International Symposium on Solar Sailing, 2017-01-17 - 2017-01-20, Kyoto, Japan.

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Official URL: http://www.jsforum.or.jp/ISSS2017/


Deployable gossamer structures for solar sails need to be deployed in a controlled way. Several strategies present have the disadvantage that the sail membrane cannot always be tensioned during the deployment process. In combination with a slow deployment, this involves the risk of an entanglement of the sail. Slow deployments of at least several minutes are desirable in order to keep inertial loads low and to implement Fault-Detection, Fault-Isolation and Recovery Techniques (FDIR). This might further require completely stopping and resuming the deployment process. For gossamer spacecraft based on crossed boom configurations with triangular sail segments, a deployment strategy is described that is assumed to allow such a controlled deployment process. With a combination of folding and coiling, it is ensured that the deployed sail area can be held taut between the partly deployed booms. During deployment, four deployment units with two spools each on which the sail is mounted (a half segment stowed on each) moves away from the central bus unit, the center of the deployed sail. The development was made in the Gossamer-1 project of the German Aerospace Center (DLR). The folding and coiling of the membrane is mathematically modelled. This allows an investigation of the deployment geometry. It provides the mathematical relation between the deployed boom length and the deployed sail membrane geometry. By modelling the coiled zig-zag folding lines it is possible to calculate the deployment force vector as function of the deployment time. The stowing and deployment strategy was verified by tests with an engineering qualification model of the Gossamer-1 deployment unit. According to a test-as-you-fly approach the tests included vibration tests, venting, thermal-vacuum tests and ambient deployment. In these tests the deployment strategy proved to be suitable for a controlled deployment of gossamer spacecraft. A deeper understanding of the deployment process is gained by analyzing the deployment strategy mathematically.

Item URL in elib:https://elib.dlr.de/111053/
Document Type:Conference or Workshop Item (Speech)
Title:Controlled Deployment of Gossamer Spacecraft
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Seefeldt, PatricUNSPECIFIEDhttps://orcid.org/0000-0002-2067-9458UNSPECIFIED
Spröwitz, TomUNSPECIFIEDhttps://orcid.org/0000-0001-5369-6919UNSPECIFIED
Sasaki, KanameUNSPECIFIEDhttps://orcid.org/0000-0003-0365-4539UNSPECIFIED
Date:20 January 2017
Journal or Publication Title:Proceedings of The Fourth International Symposium on Solar Sailing
Refereed publication:No
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
Keywords:Deployment Systems, Deployment Strategy, Controlled Deployment
Event Title:The Fourth International Symposium on Solar Sailing
Event Location:Kyoto, Japan
Event Type:international Conference
Event Start Date:17 January 2017
Event End Date:20 January 2017
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space System Technology
DLR - Research area:Raumfahrt
DLR - Program:R SY - Space System Technology
DLR - Research theme (Project):R - Entfaltungstechnologie . Solar Sail (old)
Location: Bremen
Institutes and Institutions:Institute of Space Systems > Systems Enabling Technologies
Institute of Space Systems > Mechanic and Thermal Systems
Deposited By: Sznajder, Dr.-Ing. Maciej
Deposited On:10 Feb 2017 12:33
Last Modified:24 Apr 2024 20:16

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