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  • 1
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    Development and Test Plans for the MSR EEV (2005)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: The goal of the proposed Mars Sample Return mission is to bring samples from the surface of Mars back to Earth for thorough examination and analysis. The Earth Entry Vehicle is the passive entry body designed to protect the sample container from entry heating and deceleration loads during descent through the Earth s atmosphere to a recoverable location on the surface. This paper summarizes the entry vehicle design and outlines the subsystem development and testing currently planned in preparation for an entry vehicle flight test in 2010 and mission launch in 2013. Planned efforts are discussed for the areas of the thermal protection system, vehicle trajectory, aerodynamics and aerothermodynamics, impact energy absorption, structure and mechanisms, and the entry vehicle flight test.
    Keywords: Space Sciences (General)
    Type: 2nd International Planetary Probe Workshop; 269-274; NASA/CP-2004-213456
    Format: application/pdf
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  • 2
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    Technology for Entry Probes (2005)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: A viewgraph describing technologies for entry probes is presented. The topics include: 1) Entry Phase; 2) Descent Phase; 3) Long duration atmospheric observations; 4) Survivability at high temperatures; and 5) Summary.
    Keywords: Space Sciences (General)
    Type: 2nd International Planetary Probe Workshop; NASA/CP-2004-213456
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  • 3
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    Rotating Arc Jet Test Model: Time-Accurate Trajectory Heat Flux Replication in a Ground Test Environment (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Though arc jet testing has been the proven method employed for development testing and certification of TPS and TPS instrumentation, the operational aspects of arc jets limit testing to selected, but constant, conditions. Flight, on the other hand, produces timevarying entry conditions in which the heat flux increases, peaks, and recedes as a vehicle descends through an atmosphere. As a result, we are unable to "test as we fly." Attempts to replicate the time-dependent aerothermal environment of atmospheric entry by varying the arc jet facility operating conditions during a test have proven to be difficult, expensive, and only partially successful. A promising alternative is to rotate the test model exposed to a constant-condition arc jet flow to yield a time-varying test condition at a point on a test article (Fig. 1). The model shape and rotation rate can be engineered so that the heat flux at a point on the model replicates the predicted profile for a particular point on a flight vehicle. This simple concept will enable, for example, calibration of the TPS sensors on the Mars Science Laboratory (MSL) aeroshell for anticipated flight environments.
    Keywords: Aircraft Propulsion and Power
    Type: ARC-E-DAA-TN3214 , 8th International Planetary Probe Workshop (IPPW-8); Jun 06, 2011 - Jun 10, 2011; Portsmouth, VA; United States
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  • 4
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    Arcjet Testing of Woven Carbon Cloth for Use on Adaptive Deployable Entry Placement Technology (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes arcjet testing and analysis that has successfully demonstrated the viability of three dimensional woven carbon cloth for dual use in the Adaptive Deployable Entry Placement Technology (ADEPT). ADEPT is an umbrella-like entry system that is folded for stowage in the launch vehicle s shroud and deployed in space prior to reaching the atmospheric interface. A key feature of the ADEPT concept is its lower ballistic coefficient for delivery of a given payload than those for conventional, rigid body entry systems. The benefits that accrue from the lower ballistic coefficient include factor of ten reductions of deceleration forces and entry heating. The former enables consideration of new classes of scientific instruments for solar system exploration while the latter enables the design of a more efficient thermal protection system. The carbon cloth now base lined for ADEPT has a dual use in that it serves as ADEPT s thermal protection system and as the "skin" that transfers aerodynamic deceleration loads to its umbrella-like substructure. The arcjet testing described in this paper was conducted for some of the higher heating conditions for a future Venus mission using the ADEPT concept, thereby showing that the carbon cloth can perform in a relevant entry environment. The ADEPT project considered the carbon cloth to be mission enabling and was carrying it as a major risk during Fiscal Year 2012. The testing and analysis reported here played a major role in retiring that risk and is highly significant to the success and possible adoption of ADEPT for future NASA missions. Finally, this paper also describes a preliminary engineering level code, based on the arcjet data, that can be used to estimate cloth thickness for future missions using ADEPT and to predict carbon cloth performance in future arcjet tests.
    Keywords: Composite Materials
    Type: ARC-E-DAA-TN6341 , 2013 IEEE Aerospace Conference; Mar 02, 2013 - Mar 09, 2013; Big Sky, MT; United States
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  • 5
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    Two-Dimensional Finite Element Ablative Thermal Response Analysis of an Arcjet Stagnation Test (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The finite element ablation and thermal response (FEAtR, hence forth called FEAR) design and analysis program simulates the one, two, or three-dimensional ablation, internal heat conduction, thermal decomposition, and pyrolysis gas flow of thermal protection system materials. As part of a code validation study, two-dimensional axisymmetric results from FEAR are compared to thermal response data obtained from an arc-jet stagnation test in this paper. The results from FEAR are also compared to the two-dimensional axisymmetric computations from the two-dimensional implicit thermal response and ablation program under the same arcjet conditions. The ablating material being used in this arcjet test is phenolic impregnated carbon ablator with an LI-2200 insulator as backup material. The test is performed at the NASA, Ames Research Center Interaction Heating Facility. Spatially distributed computational fluid dynamics solutions for the flow field around the test article are used for the surface boundary conditions.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AIAA Paper 2011-3617 , NF1676L-11639 , 42nd AIAA Thermophysics Conference; Jun 27, 2011 - Jun 30, 2011; Honolulu, HI; United States
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  • 6
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    The Mysteries of Real Materials (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The presentation will consist of showing arc jet data mysterious to the modelers. It will show pictures from an arc jet test where a material (unidentified) exhibited a failure mode that nobody understands followed by thermocouple data from arc jet tests on another (unidentified) material of interest in which the T/Cs exhibit repeatable, consistent, fascinating yet frustrating response characteristics that have the modelers stumped. This all happens between RT and 200 F. Unless we figure out what the responsible phenomenology is and can model it, we can't size the TPS with any confidence.
    Keywords: Composite Materials
    Type: ARC-E-DAA-TN4856 , 5th Ablation Workshop; Feb 28, 2012 - Mar 01, 2012; Lexington, KY; United States
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  • 7
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    Arc Jet Testing of Carbon Phenolic for Mars Sample Return and Future NASA Missions (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The objective of the Mars Sample Return (MSR) Mission is to return a sample of MArtian soil to Earth. The Earth Entry Vehicle (EEV) brings te samples through the atmosphere to the ground.The program aims to: Model aerothermal environment during EEV flight; On the basis of results, select potential TPS materials for EEV forebody; Fabricate TPS materials; Test the materials in the arc jet environment representative of predicted flight environment;Evaluate material performance; Compare results of modeling predictions with test results.
    Keywords: Lunar and Planetary Science and Exploration
    Type: 55th Pacific Coast Regional and Basic Science Division Fall Meeting; Oct 19, 2003 - Oct 22, 2003; Oakland, CA; United States
    Format: application/pdf
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  • 8
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    Mars Science Laboratory Entry Capsule Aerothermodynamics and Thermal Protection System (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Mars Science Laboratory (MSL) spacecraft is being designed to carry a large rover (greater than 800 kg) to the surface of Mars using a blunt-body entry capsule as the primary decelerator. The spacecraft is being designed for launch in 2009 and arrival at Mars in 2010. The combination of large mass and diameter with non-zero angle-of-attack for MSL will result in unprecedented convective heating environments caused by turbulence prior to peak heating. Navier-Stokes computations predict a large turbulent heating augmentation for which there are no supporting flight data1 and little ground data for validation. Consequently, an extensive experimental program has been established specifically for MSL to understand the level of turbulent augmentation expected in flight. The experimental data support the prediction of turbulent transition and have also uncovered phenomena that cannot be replicated with available computational methods. The result is that the flight aeroheating environments predictions must include larger uncertainties than are typically used for a Mars entry capsule. Finally, the thermal protection system (TPS) being used for MSL has not been flown at the heat flux, pressure, and shear stress combinations expected in flight, so a test program has been established to obtain conditions relevant to flight. This paper summarizes the aerothermodynamic definition analysis and TPS development, focusing on the challenges that are unique to MSL.
    Keywords: Spacecraft Design, Testing and Performance
    Type: IEEAC Paper 1423 , 2007 IEEE Aerospace Conference; Mar 03, 2007 - Mar 10, 2007; Big Sky, MT; United States
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  • 9
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    Systems Analysis for a Venus Aerocapture Mission (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Previous high level analysis has indicated that significant mass savings may be possible for planetary science missions if aerocapture is employed to place a spacecraft in orbit. In 2001 the In-Space Propulsion program identified aerocapture as one of the top three propulsion technologies for planetary exploration but that higher fidelity analysis was required to verify the favorable results and to determine if any supporting technology gaps exist that would enable or enhance aerocapture missions. A series of three studies has been conducted to assess, from an overall system point of view, the merit of using aerocapture at Titan, Neptune and Venus. These were chosen as representative of a moon with an atmosphere, an outer giant gas planet and an inner planet. The Venus mission, based on desirable science from plans for Solar System Exploration and Principal Investigator proposals, to place a spacecraft in a 300km polar orbit was examined and the details of the study are presented in this paper.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA/TM-2006-214291 , L-19237
    Format: application/pdf
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