Preliminary assessment of the Mars Science Laboratory entry, descent, and landing simulation

Way, David W.

doi:10.1109/aero.2013.6497404

Cited by 62 publications

(48 citation statements)

References 9 publications

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“…The data presented here is for the capsule dynamics before parachute deploy. More details of this TF analysis are described in a paper by Way et al [17].…”

Section: Extraction Of Aerodynamic Forces and Momentsmentioning

confidence: 99%

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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“…The data presented here is for the capsule dynamics before parachute deploy. More details of this TF analysis are described in a paper by Way et al [17].…”

Section: Extraction Of Aerodynamic Forces and Momentsmentioning

confidence: 99%

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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“…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.…”

Section: Introductionmentioning

confidence: 99%

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

Cruz

Way

Shidner

et al. 2013

AIAA Aerodynamic Decelerator Systems (ADS) Conference

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The Mars Science Laboratory used a single mortar-deployed disk-gap-band parachute of 21.35 m nominal diameter to assist in the landing of the Curiosity rover on the surface of Mars. The parachute system's performance on Mars has been reconstructed using data from the on-board inertial measurement unit, atmospheric models, and terrestrial measurements of the parachute system. In addition, the parachute performance results were compared against the end-to-end entry, descent, and landing (EDL) simulation created to design, develop, and operate the EDL system. Mortar performance was nominal. The time from mortar fire to suspension lines stretch (deployment) was 1.135 s, and the time from suspension lines stretch to first peak force (inflation) was 0.635 s. These times were slightly shorter than those used in the simulation. The reconstructed aerodynamic portion of the first peak force was 153.8 kN; the median value for this parameter from an 8,000-trial Monte Carlo simulation yielded a value of 175.4 kN -14% higher than the reconstructed value. Aeroshell dynamics during the parachute phase of EDL were evaluated by examining the aeroshell rotation rate and rotational acceleration. The peak values of these parameters were 69.4 deg/s and 625 deg/s 2 , respectively, which were well within the acceptable range. The EDL simulation was successful in predicting the aeroshell dynamics within reasonable bounds. The average total parachute force coefficient for Mach numbers below 0.6 was 0.624, which is close to the pre-flight model nominal drag coefficient of 0.615.

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“…Range measurement. Using radio communication for the Mars entry phase has been investigated (Boehmer, 1998;Lou et al, 2014;Way et al, 2013). The range measurement provides the distance between the entry vehicle and an orbiter or a surface beacon.…”

Section: Mars Entry Dynamic Modelmentioning

confidence: 99%

Multiple Model Adaptive Rank Estimation for Integrated Navigation During Mars Entry

Xiao

Wang

et al. 2016

J. Navigation

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Accurate navigation systems are required for future pinpoint Mars landing missions. A radio ranging augmented Inertial Measurement Unit (IMU) integrated navigation system concept is considered for the Mars entry navigation. The uncertain system parameters associated with the Three Degree-Of-Freedom (3-DOF) dynamic model, and the measurement systematic errors are considered. In order to improve entry navigation accuracy, this paper presents the Multiple Model Adaptive Rank Estimation (MMARE) filter of radio beacons/IMU integrated navigation system.

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Preliminary assessment of the Mars Science Laboratory entry, descent, and landing simulation

Cited by 62 publications

References 9 publications

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

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

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

Multiple Model Adaptive Rank Estimation for Integrated Navigation During Mars Entry

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