An integrated tool for system analysis of sample return vehicles

Abstract

Abstract-The next important step in space exploration is the return of sample materials from extraterrestrial locations to Earth for analysis. Most mission concepts that return sample material to Earth share one common element: an Earth entry vehicle. The analysis and design of entry vehicles is multidisciplinary in nature, requiring the application of mass sizing, flight mechanics, aerodynamics, aerothermodynamics, thermal analysis, structural analysis, and impact analysis tools.Integration of a multidisciplinary problem is a challenging task; the execution process and data transfer among disciplines should be automated and consistent. This paper describes an integrated analysis tool for the design and sizing of an Earth entry vehicle. The current tool includes the following disciplines: mass sizing, flight mechanics, aerodynamics, aerothermodynamics, and impact analysis tools. Python and Java languages are used for integration. Results are presented and compared with the results from previous studies.

A Structural Dynamics Analysis Methodology for Development of Earth Entry Vehicles

“…The parameters can easily be changed directly in any text editor, or if automation of a wide range of simulations is desired, a NASA automation code called M-SAPE currently under development can also be used. 4 Since construction of a full EEV prototype for structural dynamics testing is pending, experimental validation of the SDM is not currently possible. In a relevant NASA report by the authors on evaluating the impact response of the EEV, the work focused strongly on validations.…”

“…It is intended that the design methodology will be integrated into a larger system level analysis tool in a method proposed by Bayandor and Samareh. 3,4 The larger tool will allow NASA to evaluate all necessary aspects of an EEV design, including thermal, structural, and aerodynamic aspects. The developed structural dynamics analysis methodology allows, physical geometry, material properties, composite fiber orientation, reentry velocity, inertial launch loading, structure-borne vibration intensity, acoustic vibration intensity, trajectory, payload mass, etc.…”

The status of spacecraft bus and platform technology development under the NASA ISPT program

“…High-fidelity validated thermal protection system response models (FIAT) and trajectory simulation tools (POST) are incorporated into the baseline tool. [32] Plans for the next year of development include incorporating results from recent validation ground tests, and training and tool dissemination to the user community. Recent (FY11-12) model developments and validation testing include thermal soak model development, foam impact tests, and spin tunnel testing, with additional spin tunnel testing planned in FY13.…”

“…ISPT aerocapture project released its Aerocapture Quicklook Tool, formally the multidisciplinary tool for Systems Analysis of Planetary EDL (SAPE). [32] SAPE is a Python based multidisciplinary analysis tool for entry, decent, and landing (EDL) at Venus, Earth, Mars, Jupiter, Saturn, Uranus, Neptune, and Titan. The purpose of the SAPE tool is to provide a method of rapid assessment of aerocapture or EDL system performance, characteristics, and requirements.…”

Status of Sample Return Propulsion technology development under NASA's ISPT program

“…Highfidelity validated thermal protection system response models and trajectory simulation tools are incorporated into the baseline tool. [17] Plans for the next two years of development include ground tests to validate the other tool modules; in particular, the impact foam characteristics under thermal loads, and the impact dynamics.…”