Aerodynamic Challenges for the Mars Science Laboratory Entry Descent and Landing

Schoenenberger, Mark; Dyakonov, Artem A.; Buning, Pieter G.; Scallion, W. I.; Norman, John Van

doi:10.2514/6.2009-3914

Cited by 45 publications

(36 citation statements)

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“…The conditions along the reference trajectory shown in Figure 3 were used as freestream conditions for the flight CFD calculations. More details of the MSL aerodynamic database are described in papers by Schoenenberger et al and Dyakonov et al [7,8]. The aerodynamic coefficients presented in this paper for comparison to the reconstructed aerodynamic coefficients derived from IMU and MEADS data were obtained using the same MSL aerodynamic database code as was used in preflight simulations (using reconstructed trajectory states).…”

Section: Msl Aerodynamic Databasementioning

confidence: 99%

“…Roll Torques Schoenenberger et al [7] showed how recession on the heatshield might lead to a pinwheel aerodynamic effect causing adverse roll moments. In off-nominal simulations, it was shown that roll torques could confuse the controller during bank reversals, causing the vehicle to fall off the guided trajectory and miss the desired landing ellipse.…”

Section: Interpretation Of Rcs Firing Historymentioning

confidence: 99%

“…The uncertainty model consists of a set of adders and multipliers applied to each aerodynamic coefficient [7]. The uncertainties were defined for three different flight regimes, rarefied/transitional, hypersonic continuum and supersonic continuum.…”

Section: Reconciliation Of Predicted and Reconstructed Aerodynamic Comentioning

confidence: 99%

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Assessment of the Reconstructed Aerodynamics of the Mars Science Laboratory Entry Vehicle

Schoenenberger

Norman

Karlgaard

et al. 2014

Journal of Spacecraft and Rockets

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On August 5, 2012, the Mars Science Laboratory entry vehicle successfully entered Mars atmosphere, flying a guided entry until parachute deploy. The Curiosity rover landed safely in Gale crater upon completion of the Entry Descent and Landing sequence. This paper compares the aerodynamics of the entry capsule extracted from onboard flight data, including Inertial Measurement Unit (IMU) accelerometer and rate gyro information, and heatshield surface pressure measurements. From the onboard data, static force and moment data has been extracted. This data is compared to preflight predictions. The information collected by MSL represents the most complete set of information collected during Mars entry to date. It allows the separation of aerodynamic performance from atmospheric conditions. The comparisons show the MSL aerodynamic characteristics have been identified and resolved to an accuracy better than the aerodynamic database uncertainties used in preflight simulations. A number of small anomalies have been identified and are discussed. This data will help revise aerodynamic databases for future missions and will guide computational fluid dynamics (CFD) development to improved prediction codes.

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Section: Msl Aerodynamic Databasementioning

confidence: 99%

Section: Interpretation Of Rcs Firing Historymentioning

confidence: 99%

See 1 more Smart Citation

Assessment of the Reconstructed Aerodynamics of the Mars Science Laboratory Entry Vehicle

Schoenenberger

Norman

Karlgaard

et al. 2014

Journal of Spacecraft and Rockets

Self Cite

View full text Add to dashboard Cite

show abstract

“…Because some RCS activity produces 8of16 unbalanced changes in the pressure distribution (like the example in the figure 11) it is beneficial to design the RCS such that the areas of high sensitivity are not affected by thrusters. where a0 = 8.325E-3, a1 = 1.1293E-1, a2 = -1.801 and a3 = 1.2885 (see, for example, Schoenenberger 8 ). This relation is currently applied to all Mars entry capsules to determine base pressure for aerodynamics.…”

Section: Of16 V Evolution Of Msl Rcs Configurationmentioning

confidence: 99%

“…The data, collected in this test series was compared with CFD predictions (LAURA and FUN3D) and the results were used as an estimate of confidence in numerical predictions. 8 Model nozzles were conical with a 10-degree half-angle of the divergent section. Throat diameter, nozzle half-angle and nozzle chamber pressures were selected to produce jet plumes as closely scaled to those in flight as possible.…”

Section: A Msl Unitary Tunnel Testmentioning

confidence: 99%