Structural Design of an Autonomously Deployable, Static, Large-Scale, Martian Surface Solar Array

Abstract

Presently, there exists no “off-the-shelf” option for power generation on the order of magnitude necessary for sustaining a long-term human presence on the surface of Mars. In this thesis work, an investigation was performed to determine the optimal design for a large-scale, static, autonomously deployable, lightweight Martian surface solar array. A principle aim of the design study was to articulate a concept whose stowage volume and mass performance is, at the very least, comparable to that of the Compact Telescoping Surface Array (CTSA) which was developed by the National Aeronautics and Space Administration (NASA) in 2016 to address the same challenge. Divided into two main sections, the first portion of this research consisted of a conceptual design phase which resulted in the generation of numerous different deployable solar array concepts. Through detailed analysis as well as cross-comparison, the Stripped Array concept was determined to likely be the only concept that can outperform the CTSA. At a high level, the Stripped Array is a square shaped, monolithic deployable array whose solar array membrane subassembly is divided into strips of varying length. It deploys above a Martian lander and is supported at its center by additional payload on the vehicle’s payload deck as well as at its corners by four telescoping composite booms which are evenly spaced around the perimeter of the landing vehicle. A main reason for the Stripped Array’s improvement in volume and mass performance is based on the reduction in deployment length and in total number of telescoping supports. Furthermore, the stripped membrane configuration in conjunction with the quad slip wrapping stowage method results in low stowed volumes by comparison to the other concepts. The second portion of this research consisted of a number of preliminary sensitivity studies to further characterize the Stripped Array concept. Specifically, system response to changes in total array area, level of pretension, and sizing of various subcomponents of the solar array membrane was evaluated. Furthermore, a preliminary study was performed to understand the effect of solar array membrane pre-tension, level of gravitational loading, supporting architecture cross-sectional sizing, and assumed support conditions on assembly stresses, deflections, and natural frequencies.