High-Fidelity Aerothermal Engineering Analysis for Planetary Probes Using DOTNET Framework and OLAP Cubes Database

Prabhakar Subrahmanyam

doi:10.1155/2009/326102

Abstract

This publication presents the architecture integration and implementation of various modules inSpartaframework.Spartais a trajectory engine that is hooked to an Online Analytical Processing (OLAP) database for Multi-dimensional analysis capability. OLAP is an Online Analytical Processing database that has a comprehensive list of atmospheric entry probes and their vehicle dimensions, trajectory data, aero-thermal data and material properties like Carbon, Silicon and Carbon-Phenolic based Ablators. An approach is presented for dynamic TPS design. OLAP has the capability to run in one simulation several different trajectory conditions and the output is stored back into the database and can be queried for appropriate trajectory type. An OLAP simulation can be setup by spawning individual threads to run for three types of trajectory:Nominal,Undershoot and Overshoot trajectory. Sparta graphical user interface provides capabilities to choose from a list of flight vehicles or enter trajectory and geometry information of a vehicle in design. DOTNET framework acts as a middleware layer between the trajectory engine and the user interface and also between the web user interface and the OLAP database. Trajectory output can be obtained in TecPlot format, Excel output or in a KML (Keyhole Markup Language) format. Framework employs an API (application programming interface) to convert trajectory data into a formatted KML file that is used by Google Earth for simulating Earth-entry fly-by visualizations.

Highlights

Space exploration directorate’s national vision calls for “The human and robotic exploration of the Solar System and beyond.” Human and Robotic exploration of the solar system is to search for evidence of life, to understand the history of the solar system, and to support human exploration
In support of this mission, a complete computational design framework is necessary that automates the calculations for stagnation point heating, thermal protection system (TPS) sizing so that better probes can be built with this analysis
An integrated planetary probe design framework that automatically generates grids for planetary probes given vehicle geometry and entry trajectory flight conditions is presented in this publication

Summary

Introduction

Space exploration directorate’s national vision calls for “The human and robotic exploration of the Solar System and beyond.” Human and Robotic exploration of the solar system is to search for evidence of life, to understand the history of the solar system, and to support human exploration. Human and Robotic exploration of the solar system is to search for evidence of life, to understand the history of the solar system, and to support human exploration Before they arrive, planetary probes will likely have preceded them to provide the understanding required to make further exploration possible. Advances in technologies ranging from new instrumentation, sophisticated heatshield materials, and improvized nanotechnology make planetary probes a vital tool in pursuit of scientific truth and the origins. In support of this mission, a complete computational design framework is necessary that automates the calculations for stagnation point heating, TPS sizing so that better probes can be built with this analysis. Once the grids are generated, they can be automatically linked to CFD tools for analysis

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