In orbit bonding (IOB) of long deployable structures

Details In orbit bonding (IOB) of long deployable structures In orbit bonding (IOB) of long deployable structures

Sep 2003

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2003esasp.524..365s&link_type=abstract

In: Proceedings of the 10th European Space Mechanisms and Tribology Symposium, 24-26 September 2003, San Sebastián, Spain. Compi

Computer Science

Deployment Mechanisms

Scientific paper

A number of space missions in the coming years will base on evolving technologies for large structural members. Application scenarios reaching from solar sail missions over solar array structures to tethered spaceships for building up large instruments are focussed. Extensive activities have been performed in the field of in-orbit deployable booms which are the main element of large structures, beside inflatables. These studies have revealed a lot of useful results on boom concepts. According to experience the length capacity of such deployable booms is driven by the packaging process, packing density and concepts for the pre-manufactured booms, resulting in all cases in limited boom length and locally overloaded areas (e.g. by buckling). Solutions which successfully developed to overcome the packing problem possess lower stiffness and load capability. Therefore, a novel solution by in orbit assembly of semifinished parts is proposed, allowing higher packing density and therefore greater boom length (the goal is 100m), in combination with active curvature control for obtaining not only straight booms (by controlled feed and active correction if needed) but also slightly curved booms with predefined shapes. HTS has performed a conceptual design study with the purpose to select a practicable solution and demonstrate the functional feasibility of such a solution. A hardware demonstration model was manufactured for process visualisation and testing of the implemented functions.

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