Propulsive Trajectory Optimization to Minimize Surface Contamination

Abstract

Verbatim from NASA NTRS. Not paraphrased, not summarized.

Descent retroburns using hydrazine thrusters will generate contaminants in their exhaust that can alter underlying samples, such as water-rich surfaces coinciding with possible life signatures or other science measurements of interest. We present an optimization technique that aims to autonomously minimize contamination during surface approach and landing for propulsive vehicles. In addition to short-range hoppers, the optimization technique is also fully applicable to traditional orbit-to-surface landers. This study addresses scenarios where surface alterations from propulsion events are counterproductive or hazardous to the mission objectives. This is of interest for landers (whether human or robotic), that may rely on pristine soils collected in the immediate vicinity of landing sites to accomplish science investigations, mining, or In Situ Resource Utilization (ISRU) surface operations. Such missions are averse to various surface-plume interactions such as thermal scoring, physical agitation, and contamination. The capability can be applied with minimal impact to the baseline concept.

Authors

• A. G. Yew Goddard Space Flight Center
• P. C. Calhoun Goddard Space Flight Center

Keywords

• Plume
• Surface
• Interaction
• Hydrazine
• Contamination
• Optimization
• Trajectory
• Descent
• Landing