Aerodynamic Database Development for Mars Smart Lander Vehicle Configurations

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)

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Mars Science Laboratory Simulations for Entry, Descent, and Landing

Striepe

Way

Dwyer

et al. 2006

Journal of Spacecraft and Rockets

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Entry Vehicle Control System Design for the Mars Science Laboratory

Calhoun

Queen

2006

Journal of Spacecraft and Rockets

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The NASA Langley Research Center, in cooperation with the Jet Propulasion Laboratorty, participated in a preliminary design study of the entry, descent, and landing phase for the Mars Science Laboratory Project. This project uses advances in guidance, navigation, and control technology to significantly improve Mars surface targeting capability. A candidate entry controller based on the reaction control system controller for the Apollo command module digital autopilot is proposed for use in the entry attitude control. Modifications to the phase plane controller provide good bank-angle response, reduce jet-firing chattering for hogh-frequency updates, and allow for the option of aerodynamic angle feedback for the Martian entry probe application. The controller performance is demonstrated in a six-degrees-of-freedom simulation with representative aerodynamics. Nomenclature I= moment of inertia M θ = derivative of moment with respect to angle p = body-axis roll rate q = body-axis pitch rate r = body-axis yaw rate α = angle of attack α RCS = angular acceleration from reaction control system θ C = angle offset of center of elliptical trajectory θ DB = angle deadband θ E = angle error θ S = angle shift within phase plane because of error in trim ω SP = short-period mode frequency Subscript trim = trim condition

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Supersonic Aerodynamic Characteristics of Proposed Mars '07 Smart Lander Configurations

Murphy

Horvath

Erickson

et al. 2006

Journal of Spacecraft and Rockets

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Supersonic aerodynamic data were obtained for proposed Mars '07 Smart Lander configurations in NASA Langley Research Center's Unitary Plan Wind Tunnel. The primary objective of this test program was to assess the supersonic aerodynamic characteristics of the baseline Smart Lander configuration with and without fixed shelf/tab control surfaces. Data were obtained over a Mach number range of 2.3 to 4.5, at a free stream Reynolds Number of 1 x 10 6 based on body diameter. All configurations were run at angles of attack from-5 to 2 0 degrees and angles of sideslip of-5 to 5 degrees. These results were complemented with computational fluid dynamic (CFD) predictions to enhance the understanding o f experimentally observed aerodynamic trends. Inviscid and viscous full model CFD solutions compared well with experimental results for the baseline and 3 shelf/tab configurations. Over the range tested, Mach number effects were shown to be small on vehicle aerodynamic characteristics. Based on the results from 3 different shelf/tab configurations, a fixed control surface appears to be a feasible concept for meeting aerodynamic performance metrics necessary to satisfy mission requirements.

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Aerodynamic Database Development for Mars Smart Lander Vehicle Configurations

Abstract: An aerodynamic database has been generated for A

Cited by 6 publications

References 14 publications

Mars Science Laboratory Simulations for Entry, Descent, and Landing

Mars Science Laboratory Simulations for Entry, Descent, and Landing

Entry Vehicle Control System Design for the Mars Science Laboratory

Supersonic Aerodynamic Characteristics of Proposed Mars '07 Smart Lander Configurations

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