Planetary Entry Probe Dataset: Analysis and Rules of Thumb for Future Missions

TL;DR

This paper analyzes historical planetary entry probe data to derive engineering rules of thumb and proposes a new empirical correlation for predicting thermal protection system mass, aiding future mission design to planets like Uranus and Neptune.

Contribution

It compiles and analyzes an augmented dataset of planetary entry probes and introduces a novel empirical correlation for thermal protection system mass prediction.

Findings

Enhanced understanding of entry conditions across planets.

New empirical correlation for TPS mass fraction prediction.

Guidelines for designing future planetary entry probes.

Abstract

Since the beginning of robotic interplanetary exploration nearly six decades ago, successful atmospheric entry has been accomplished at Venus, Earth, Mars, Jupiter, and Titan. More entry probe missions are planned to Venus, Titan, and Uranus in the next decade. Atmospheric entry subjects the vehicle to rapid deceleration and aerothermal loads which the vehicle must be designed for, to deliver the robotic instruments inside the atmosphere. The design of planetary probes and their mission architecture is complex, and involves various engineering constraints such as peak deceleration, heating rate, heating load, and communications which must be satisfied within the budget and schedule of cost constrained mission opportunities. Engineering design data from previous entry probe missions serve as a valuable reference for designing future missions. The present study compiles an augmented version of the blue book entry probe dataset, performs a comparative analysis of the entry conditions, and provides engineering rules of thumb for design of future missions. Using the dataset, the present study proposes a new empirical correlation which aims to more accurately predict the thermal protection system mass fraction for high heat load conditions during entry and aerocapture at Uranus and Neptune.