Session
2024 Session 5
Location
Salt Lake Community College Westpointe Campus, Salt Lake City, UT
Start Date
5-6-2024 10:50 AM
Description
Deployable space structures that incorporate thin, flexible solar cells allow for innovative designs that are capable of high stowing efficiency. The purpose of this work is to present an approach to predicting the deflection of deployable space structures with flexible panels connected with thin sheets as a function of their material properties, geometry, and applied moments. Related methods are described. An analytical model and finite element analysis are compared and validated with a physical model. The end angle, coordinates, and radius of curvature of each segment are calculated and the results are compared. Important factors related to the reliability of the membrane-like hinges are described. Beam thicknesses can be adjusted to increase curvature to intended sections of the beam. The approach is then applied in the preliminary design of a z-fold used as a deployable space array. The compliant-stepped beam deflected in a z-fold pattern provides designers with a straightforward model to analyze the position and curvature of a deployable array and tailor it to meet design requirements. Percent differences of each analysis are presented and discussed. The analytical model agrees well with FEA and physical solution results. Case assumptions are described and validated. Potential for future work related to large deflections of flexible-panel deployable space structures is described.
Developing Membrane Hinges to Enable Predictable and Reliable Arrays for Spacecraft
Salt Lake Community College Westpointe Campus, Salt Lake City, UT
Deployable space structures that incorporate thin, flexible solar cells allow for innovative designs that are capable of high stowing efficiency. The purpose of this work is to present an approach to predicting the deflection of deployable space structures with flexible panels connected with thin sheets as a function of their material properties, geometry, and applied moments. Related methods are described. An analytical model and finite element analysis are compared and validated with a physical model. The end angle, coordinates, and radius of curvature of each segment are calculated and the results are compared. Important factors related to the reliability of the membrane-like hinges are described. Beam thicknesses can be adjusted to increase curvature to intended sections of the beam. The approach is then applied in the preliminary design of a z-fold used as a deployable space array. The compliant-stepped beam deflected in a z-fold pattern provides designers with a straightforward model to analyze the position and curvature of a deployable array and tailor it to meet design requirements. Percent differences of each analysis are presented and discussed. The analytical model agrees well with FEA and physical solution results. Case assumptions are described and validated. Potential for future work related to large deflections of flexible-panel deployable space structures is described.