Mars Phoenix Entry, Descent, and Landing Trajestory and Atmosphere Reconstruction

Blanchard, Robert C.; Desai, Prasun N.

doi:10.2514/1.46274

Cited by 37 publications

(24 citation statements)

References 7 publications

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“…These results showed that the multibody parachute system reliably damped out rotational motion of the capsule. This rotational damping was of great interest [8,9].…”

Section: Monte Carlo Simulationmentioning

confidence: 97%

Multibody Modeling and Simulation for Mars Phoenix Entry, Descent, and Landing

Queen

Prince

Desai

2011

Journal of Spacecraft and Rockets

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A multibody flight simulation for the Phoenix Mars Lander was developed that included high-fidelity six-degreeof-freedom rigid-body models for the parachute and lander system. The simulation predicted attitude and rate histories of all bodies throughout the flight. In so doing, a realistic behavior of the descending parachute/lander system dynamics was simulated that allowed assessment of the Phoenix descent performance and identification of sensitivities for landing. This simulation provided a complete end-to-end capability of modeling the entire entry, descent, and landing sequence for the mission. The simulation was used to predict the parachute and lander aerodynamic angles during entry and the response of the lander system to various wind models and windshears. Several different wind models were analyzed to determine which was most effective at exciting vehicle attitude dynamics. The simulation was used to drive a Monte Carlo analysis that provided a statistical evaluation of the performance capability of the Phoenix landing system.entry time Ixx, Iyy, Izz = moments of inertia about the X, Y, and Z axes L = spacecraft landing time M = Mach number = inertial flight-path angle

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“…These results showed that the multibody parachute system reliably damped out rotational motion of the capsule. This rotational damping was of great interest [8,9].…”

Section: Monte Carlo Simulationmentioning

confidence: 97%

Multibody Modeling and Simulation for Mars Phoenix Entry, Descent, and Landing

Queen

Prince

Desai

2011

Journal of Spacecraft and Rockets

Self Cite

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“…Results from the deterministic trajectory reconstructions can be found in the literature for Viking 1 and 2, 1 Mars Pathfinder, 2 Mars Exploration Rovers (MER) 3 and the Phoenix lander. 4,5 Unfortunately, these reconstructions do not take into account measurement and process uncertainties and lack the ability to quantify the uncertainty of the estimated parameters. Phoenix X In-depth temperature (during EDL) X X X i Pathfinder only took pressure measurements during subsonic parachute descent…”

Section: Mars Edl Reconstruction Backgroundmentioning

confidence: 99%

“…The predicted measurement for each sigma point ‫ݕ(‬ ො () ) and the estimate of the mean value for the predicted measurement ‫ݕ(‬ ො ) can be calculated using Eqs. (5). The covariance of the predicted measurement (P y ) and the cross covariance between the estimated state and measurement (P xy ) are used for the Kalman gain and state update steps.…”

Section: Unscented Kalman Filtermentioning

confidence: 99%

“…Most of the past reconstructions of Mars vehicle data have been conducted largely using a deterministic methodology, [1][2][3][4][5] where the flight data, such as onboard sensed accelerations and angular rates, were used to reconstruct the trajectory without explicitly considering uncertainties in the measurement value or in the flight dynamics. Unfortunately, under such a situation, off-nominal data could lead to the divergence of the estimate of the trajectory.…”

Section: Introductionmentioning

confidence: 99%

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

Dutta

Braun

Russell

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Flight data from an entry, descent, and landing (EDL) sequence can be used to reconstruct the vehicle's trajectory, aerodynamic coefficients and the atmospheric profile experienced by the vehicle. Past Mars missions have contained instruments that do not provide direct measurement of the freestream atmospheric conditions. Thus, the uncertainties in the atmospheric reconstruction and the aerodynamic database knowledge could not be separated. The upcoming Mars Science Laboratory (MSL) will take measurements of the pressure distribution on the aeroshell forebody during entry and will allow freestream atmospheric conditions to be partially observable. This data provides a mean to separate atmospheric and aerodynamic uncertainties and is part of the MSL EDL Instrumentation (

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“…10 For this type of reconstruction, the required data types are body frame accelerations T x y z a a a    a and angular rotation rates…”

Section: B Inertial Navigation Solutionmentioning

confidence: 99%

Trajectory Reconstruction and Uncertainty Analysis using Mars Science Laboratory Pre-Flight Scale Model Aeroballistic Testing

Lugo

Tolson

Schoenenberger

2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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As part of the Mars Science Laboratory (MSL) trajectory reconstruction effort at NASA Langley Research Center, free-flight aeroballistic experiments of instrumented MSL scale models was conducted at Aberdeen Proving Ground in Maryland. The models carried an inertial measurement unit (IMU) and a flush air data system (FADS) similar to the MSL Entry Atmospheric Data System (MEADS) that provided data types similar to those from the MSL entry. Multiple sources of redundant data were available, including tracking radar and on-board magnetometers. These experimental data enabled the testing and validation of the various tools and methodologies that will be used for MSL trajectory reconstruction. The aerodynamic parameters Mach number, angle of attack, and sideslip angle were estimated using minimum variance with a priori to combine the pressure data and pre-flight computational fluid dynamics (CFD) data. Both linear and non-linear pressure model terms were also estimated for each pressure transducer as a measure of the errors introduced by CFD and transducer calibration. Parameter uncertainties were estimated using a "consider parameters" approach.

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Mars Phoenix Entry, Descent, and Landing Trajestory and Atmosphere Reconstruction

Cited by 37 publications

References 7 publications

Multibody Modeling and Simulation for Mars Phoenix Entry, Descent, and Landing

Multibody Modeling and Simulation for Mars Phoenix Entry, Descent, and Landing

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

Trajectory Reconstruction and Uncertainty Analysis using Mars Science Laboratory Pre-Flight Scale Model Aeroballistic Testing

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