Origami-based TPS Folding Concept for Deployable Mars Entry Vehicles

摘要

A novel deployable Mars aeroshell architecture is developed. Rigid thermal protection system (TPS) panels are connected between retractable ribs, following origami principles, and then deployment behavior is investigated. An optimal fold pattern is selected to ensure efficient flat stowage during launch and repeatable deployment. Optimization is carried out to minimize the number of folds to reduce stacking height, and to maximize the angles between each fold line to avoid an unfavorable aero-thermodynamic response. The panel deployment is vital to the performance of the aero-decelerator. Therefore, a dynamic multi-body analysis model has been developed and validated that shows that the process of deployment is robust, repeatable and controllable. Results for this are shown and verified through experimental testing of a scale-model.