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This paper will present a reconstruction of aerothermal environment and thermal protection system response of the Mars Science Laboratory (MSL) entry vehicle. The heat shield of the MSL entry vehicle was instrumented with thermocouples, ablation sensors, and pressure transducers that acquired engineering data during the guided hypersonic entry. The instrumentation suite is called the MSL Entry, Descent, and Landing Instrumentation (MEDLI). Using inverse parameter estimation and uncertainty analysis of TPS response models, best estimates of time-varying aeroheating and TPS response will be presented. A validation of predictive models and its impact on design margins will also be presented. 10:45 AAS Telecom Performance and Mission Design during the Entry, Descent, and 13-312 Landing of the Mars Science Laboratory Brian Schratz, NASA / Caltech JPL; Allen Chen, NASA / Caltech JPL; Fernando Abilleira, NASA / Caltech JPL; Jeremy Shidner, Analytical Mechanics Associates, Inc. This paper discusses the MSL UHF and X-band telecommunications configuration during EDL , and the mission design and configuration of the supporting Mars orbiters and Earth tracking stations. Actual link performance will be compared to predictions including signal strength, Doppler, plasma attenuation, and the geometries between MSL, and its relay and DTE partners. Predictions were generated using link models developed at JPL and incorporated into NASA Langley’s Monte Carlo simulations of EDL. Extensive coordination efforts and testing occurred to ensure that all the relay and Earth stations were ready to capture this historic and critical event. 11:05 AAS Mars Science Laboratory Post-Landing Location Estimation Using POST2 13-313 Trajectory Simulation Jody Davis, NASA Langley Research Center; Jeremy Shidner, Analytical Mechanics Associates, Inc.; David Way, NASA Langley Research Center The MSL Curiosity rover landed safely on Mars August 5th, 2012 at 10:32 PDT, ERT. Immediately following touchdown confirmation, best estimates of position were calculated to assist in determining official MSL locations during EDL. POST2 was the primary trajectory simulation tool used to predict MSL EDL performance. This paper presents the methods and results of pre/post-landing MSL location estimates and associated MRO HiRISE camera imagery. POST2 Monte Carlo data, MSL flight telemetry, MRO/ODY relay orbiter positions and HiRISE DEM’s were utilized in generating these estimates. Predicted versus actual rover and balance mass locations are compared. 11:25 AAS Design and Performance of the Parachute Descent Segment of the Mars 13-423 Science Laboratory Mission Devin Kipp, NASA / Caltech JPL On August 5th 2012, the Mars Science Laboratory spacecraft landed the Curiosity rover safely inside Gale crater. Development and testing of the entry descent and landing (EDL) system was functionally decomposed into three segments: (1) Entry – comprising the period from atmospheric interface until parachute deployment, (2) Parachute Descent – comprising Page 52 23 rd AAS / AIAA Space Flight Mechanics Meeting
the period from parachute deployment until the powered descent vehicle is released from the parachute, and (3) Powered Flight – comprising the remainder of the EDL sequence including touchdown and flyaway. This paper provides an overview of the development, testing, implementation, and performance of the parachute descent segment of EDL. 23 rd AAS / AIAA Space Flight Mechanics Meeting Page 53
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Hopkins University Applied Physics
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Harvey,Nate .......................
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