Aerodynamic Database Development for Mars Smart Lander Vehicle Configurations

摘要

An aerodynamic database has been generated for the Mars Smart Lander shelf-all configuration. Beginning with an effort to validate the computational tools against sets of experimental data, the static aerodynamic database was constructed by correcting experimental data to Mars atmospheric flight conditions at supersonic speeds, in addition to performing discrete hypersonic analyses in the continuum and noncontinuum atmospheric regimes. Three different computational fluid dynamics codes, two based on unstructured grid technology and one an established and validated structured grid-based code, were used. As part of this database development, the results for the Mars continuum atmosphere were validated with experimental data and comparisons made where applicable. The validation with the Unitary experimental data, the use of intermediate check analyses, and the validation with the Mach 6 CF4 experimental data provided a higher confidence in the ability of the computational analyses to provide accurate aerodynamic data for the determination of static trim characteristics for longitudinal stability within the continuum and noncontinuum atmospheric regimes. The analyses of the noncontinuum regime showed the existence of multiple trim angles of attack that can be unstable or stable trim points. These trends assisted in the development of an entry controller for a nominal trajectory.