Mars Science Laboratory Simulations for Entry, Descent, and Landing

Abstract

Two primary simulations have been developed and are being updated for the Mars Science Laboratory entry, descent, and landing. The high-fidelity engineering end-to-end entry, descent, and landing simulation is based on NASA Langley Research Center's Program to Optimize Simulated Trajectories II and the end-to-end realtime, hardware-in-the-loop simulation test bed, which is based on NASA Jet Propulsion Laboratory's Dynamics Simulator for Entry, Descent, and Surface landing. The status of these Mars Science Laboratory entry, descent, and landing end-to-end simulations at this time is presented. Various models, capabilities, as well as validation and verification for these simulations, are discussed. Nomenclature decln star = angle between the spacecraft subplanet radius vector and equatorial plane gcrad = geocentric radius to spacecraft hgtagl = height above ground level rcalc = calculated radius to surface α = spacecraft-center-surface angle (angle between gcrad and rcalc) β = center-spacecraft-subsurface angle (angle between gcrad and hgtagl) θ = center-surface-spacecraft angle (angle between rcalc and hgtagl)

An innovative navigation scheme of powered descent phase for Mars pinpoint landing

“…They are normally distributed, with mean equals to the true states and standard deviation defined according to the EDL process of the MSL. (Striepe et al, 2006) …”

Reconstruction of the Mars Science Laboratory Parachute Performance and Comparison to the Descent Simulation

“…2,3 This simulation included numerous models related to the parachute system and its performance. 4 This paper's secondary objective is to compare the parachute models and simulation's predictions against parachute performance reconstruction results.…”

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

“…Additionally, it is beneficial to consider methods that can quantify uncertainty in the estimated EDL parameters so that they could be used in the Mars EDL design process. Looking at the work of Striepe et al, 7 who performed design analysis of the MSL mission, one sees a long list of design parameters with their associated uncertainties. Uncertainties exist in the entry conditions (such as flight path angle), center of mass location of the vehicle and sensor biases that will affect the deployment of a stage in the mission.…”