Aerothermodynamic Design of the Mars Science Laboratory Heatshield

Abstract

Aerothermodynamic design environments are presented for the Mars Science Laboratory entry capsule heatshield. The design conditions are based on Navier-Stokes flowfield simulations on shallow (maximum total heat load) and steep (maximum heat flux, shear stress, and pressure) entry trajectories from a 2009 launch. Boundary layer transition is expected prior to peak heat flux, a first for Mars entry, and the heatshield environments were defined for a fully-turbulent heat pulse. The effects of distributed surface roughness on turbulent heat flux and shear stress peaks are included using empirical correlations. Additional biases and uncertainties are based on computational model comparisons with experimental data and sensitivity studies. The peak design conditions are 197 W/cm 2 for heat flux, 471 P a for shear stress, 0.371 Earth atm for pressure, and 5477 J/cm 2 for total heat load. Time-varying conditions at fixed heatshield locations were generated for thermal protection system analysis and flight instrumentation development. Finally, the aerothermodynamic effects of delaying launch until 2011 are previewed.

Comparison of Statistical Estimation Techniques for Mars Entry, Descent and Landing Reconstruction from MEDLI-like Data Sources

“…A methodology to utilize MEADS data for reconstruction is described here. Edquist et al 21 and Mahzari et al…”

Coupled Fluids-Radiation Analysis of a High-Mass Mars Entry Vehicle

“…[11 -16]. DPLR has also been previously applied to analyze the heating rates experienced by Mars entry vehicles both on the heatshield [17][18] and afterbody [19].…”

“…For the MSLbased high-mass Mars entry vehicle, the grids used by Edquist et al [18] for their MSL analysis were scaled up to a 15 m diameter and used as starting grids in this study. Only the heatshield was considered, and the surface grid is shown in Fig.…”

Comparison of MSL RCS jet computations with flow visualization and velocimetry

“…Therefore, the current strategy for future entry vehicle design is still to use RANS-based models for prediction and rely on a robust and comprehensive validation against trusted ground-based experiments. 2,3,8 As a result of the NESC initiative, recent detailed experimental data of flow separation and jet interaction associated with the MSL vehicle are now available for a rigorous CFD validation. 4 Validation is crucial, especially for RANS-type models, since they have difficulty in predicting turbulent flows with streamline curvature or flow separation.…”