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Mars 2020 Entry, Descent and Landing Instrumentation (MEDLI2)This paper will introduce Mars Entry Descent and Landing Instrumentation (MEDLI2) on NASA's Mars2020 mission. Mars2020 is a flagship NASA mission with science and technology objectives to help answer questions about possibility of life on Mars as well as to demonstrate technologies for future human expedition. Mars2020 is scheduled for launch in 2020. MEDLI2 is a suite of instruments embedded in the heatshield and backshell thermal protection systems of Mars2020 entry vehicle. The objectives of MEDLI2 are to gather critical aerodynamics, aerothermodynamics and TPS performance data during EDL phase of the mission. MEDLI2 builds up the success of MEDLI flight instrumentation on Mars Science Laboratory mission in 2012. MEDLI instrumentation suite measured surface pressure and TPS temperature on the heatshield during MSL entry into Mars. MEDLI data has since been used for unprecedented reconstruction of aerodynamic drag, vehicle attitude, in-situ atmospheric density, aerothermal heating, transition to turbulence, in-depth TPS performance and TPS ablation. [1,2] In addition to validating predictive models, MEDLI data has highlighted extra margin available in the MSL forebody TPS, which can potentially be used to reduce vehicle parasitic mass. MEDLI2 expands the scope of instrumentation by focusing on quantities of interest not addressed in MEDLI suite. The type the sensors are expanded and their layout on the TPS modified to meet these new objectives. The paper will provide key motivation and governing requirements that drive the choice and the implementation of the new sensor suite. The implementation considerations of sensor selection, qualification, and demonstration of minimal risk to the host mission will be described. The additional challenges associated with mechanical accommodation, electrical impact, data storage and retrieval for MEDLI2 system, which extends sensors to backshell will also be described.
Document ID
20160000694
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Bose, Deepak
(NASA Ames Research Center Moffett Field, CA United States)
Wright, Henry
(NASA Langley Research Center Hampton, VA United States)
White, Todd
(Analytical Mechanics Associates, Inc. Moffett Field, CA, United States)
Schoenenberger, Mark
(NASA Langley Research Center Hampton, VA United States)
Santos, Jose
(Jacobs Technology, Inc. Moffett Field, CA, United States)
Karlgaard, Chris
(NASA Langley Research Center Hampton, VA, United States)
Kuhl, Chris
(NASA Langley Research Center Hampton, VA United States)
Oishi, TOmo
(Jacobs Technology, Inc. Moffett Field, CA, United States)
Trombetta, Dominic
(NASA Langley Research Center Hampton, VA United States)
Date Acquired
January 12, 2016
Publication Date
June 13, 2016
Subject Category
Spacecraft Instrumentation And Astrionics
Report/Patent Number
ARC-E-DAA-TN28017
Meeting Information
Meeting: AIAA Thermophysics Conference
Location: Washington, DC
Country: United States
Start Date: June 13, 2016
End Date: June 17, 2016
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NNL12AA09C
CONTRACT_GRANT: NNA09DB39C
WBS: WBS 389693.01.01.01
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Thermal Protection System
Aerodynamics
Aerothermodynamics
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