Membrane Deployment Technology Development at DLR for Solar Sails and Large-Scale Photovoltaics

Following the highly successful flight of the first interplanetary solar sail, JAXA’s IKAROS, with missions in the pipeline such as NASA’s NEAscout nanospacecraft solar sail and JAXA’s Solar Power Sail solar-electric propelled mission to a Jupiter Trojan asteroid, and on the back-ground of the ever increasing power demand of GEO satellites now including all-electric space-craft, there is renewed interest in large lightweight structures in space. Among these, deployable membrane or ‘gossamer’ structures can provide very large functional area units for innovative space applications which can be stowed into the limited volumes of launch vehicle fairings as well as secondary payload launch slots, depending on the scale of the mission. Large area struc-tures such as solar sails or high-power photovoltaic generators require a technology that allows their controlled and thereby safe deployment. Before employing such technology for a dedicated science or commercial mission, it is necessary, to demonstrate its reliability, i.e., TRL 6 or higher. A reliable technology that enables controlled deployment was developed in the Gossamer-1 solar sail deployment demonstrator project of the German Aerospace Center, DLR, including verifica-tion of its functionality with various laboratory tests to qualify the hardware for a first demonstration in low Earth orbit. We provide an overview of the Gossamer-1 hardware development and qualification campaign. The design is based on a crossed boom configuration with triangular sail segments. Employing engineering models, all aspects of the deployment were tested under ambient environment. Several components were also subjected to environmental qualification testing. An innovative stowing and deployment strategy for a controlled deployment and the required mechanisms are described. The tests conducted provide insight into the deployment process and allow a mechanical characterization of this process, in particular the measurement of the deploy-ment forces. The stowing and deployment strategy was verified by tests with an engineering qualification model of one out of four Gossamer-1 deployment units. 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, and deployment on system level was demonstrated to be robust and controllable. The Gossamer-1 solar sail membranes were also equipped with small thin-film photovoltaic arrays to supply the core spacecraft. In our follow-on project GoSolAr, the focus is now entirely on deployment systems for huge thin-film photovoltaic arrays. Based on the Gossamer-1 experience, deployment technology and qualification strategies, new technologies for the integration of thin-film photovoltaics are being developed and qualified for a first in-orbit technology demonstration within five years. Main objective is the further development of deployment technology for a 25 m^2 gossamer solar power generator and a flexible photovoltaic membrane. GoSolAr enables a wider range of deployment concepts beyond solar sail optimized methods. It uses the S2TEP bus system developed at the Institute of Space Systems as part of the DLR satellite roadmap