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IPPW-Enabled International Collaborations in EDL: Lessons Learned and Recommendations

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IPPW-Enabled International Collaborations in EDL: Lessons Learned and Recommendations IPPW-Enabled International Collaborations in EDL: Lessons Learned and Recommendations Ethiraj Venkatapathy Ali Gülhan Michelle Munk Senior Technologist DLR Principal Technologist NASA ARC Cologne, Germany STMD, NASA LaRC 15th International Planetary Probe Workshop University of Colorado, Boulder, USA June 11-15, 2018 6/15/2018 1 Acknowledgements NASA: DLR: Ø Ø Office of International and Interagency DLR –USA Relationship, Legal Aspects Relationships and Export Licence Tim Tawney, Judith Carrodeguas and Neal Thorsten Nix, Helena Weissenberger, Newman Ø Yvonne Richter, Michael Baumann NASA Ames Center Export Administrator Ø Hypersonic Testing in H2K Mary Williams Ø Dr. Sebastian Willems, Patrick Seltner, The Asteroid Threat Assessment Team: Dominik Neeb, Ansgar Marwege Ø Dr. James Arnold, Dr. Donovan Mathias, Dusty Flow in the Arc Jet Test Facility Dr. Michael Aftosmis and Dr. Eric Stern Dirk Kerkhoff, Dr. Burkard Esser, Lars Ø The EDL Simulation and Modeling Team: Steffens Ø Dr. Michael Wright and COMARS Sensors Dr. Michael Barnhardt Ø Thomas Thiele, Dr. Frank Siebe, Rolf Engineering Science Investigation and Dragonfly Kronen Dr. Michael Wright, Dr. Aaron Brandis, Dr. Jay Grinstead and Dr. Helen Hwang Ø ESA HEEET and Common Probe Ø HERA and Ice-Giant Mission Proposals to ESA Dr. Donald Ellerby, Dr. Peter Gage and Olivier Mousis (PI) Dr. Helen Hwang 6/11/18 IPPW-15, University of Colorado, Boulder, June, 2018 2 Outline Ø IPPW and International Collaboration Ø Unique Capabilities at DLR – Dr. Ali Gülhan Ø NASA Needs and Collaborations § Fundamental aspects as well as enabling missions. Ø Concluding Remarks 6/11/18 IPPW-15, University of Colorado, Boulder, June, 2018 3 IPPW and International Collaboration: Opportunities, Challenges and Constraints Ø International Collaborations § EDL / technology areas are more challenging Ø Challenges and Constraints § § Cost/benefit analysis has to benefit all sides § Export Control and ITAR regulations and restrictions § Institutional requirements and organizational responsibilities Long lead time to establish collaboration Ø §IPPW – Provides an opportunity space Presentations, posters, student mentoring, short courses § and professional interactions An opportunity for one-on-one in-depth discussions International Planetary Probe Workshop 2018 6/15/2018 University of Colorado, Boulder, Co 4 DLR Unique Capabilities Ali Gulhan International Planetary Probe Workshop 2018 6/15/2018 University of Colorado, Boulder, Co 5 Importance of Collaboration : DLR perspective • The DLR’s supersonic and hypersonic technologies: • Unique testing capabilities in support of design and development • Instrumentation for flight and ground experiments. • DLR’s high speed test facilities in Cologne are • Equipped with modern diagnostics and allow gathering important data for the improvement of physical modelling and validation of numerical tools. • DLR has limited interplanetary missions and flight expertise. • NASA has extensive long term flight expertise and unique capability in numerical simulation. • The complementary capabilities of both institutions are the main motivation for DLR to explore long term co-operation with NASA. 6/11/18 IPPW-15, University of Colorado, Boulder, June, 2018 6 DLR Capabilities: Experimental set-up of free flight testing in H2K 6/11/18 IPPW-15, University of Colorado, Boulder, June, 2018 7 DLR Capabilities: Stereo Tracking in H2K streamwise vertical 6/11/18 IPPW-15, University of Colorado, Boulder, June, 2018 8 DLR Capabilities - Free flight testing in H2K Two Spheres Interaction Flow Condition !" = 600 °' (" = 5,2 ,-. /0 = 2,1 2 103 1⁄5 6- = 7,0 6/11/18 IPPW-15, University of Colorado, Boulder, June, 2018 9 DLR Capabilities: Testing Ablative Materials in Dust- Loaded Flow and Dust Particle CharacterizationL2F velocity measurements CO2/N2 flow - 50 mm flat faced cylinder model 2100 2000 ] s / m 1900 [ P v 1800 SiO2 particles Al2O3 particles 1000.0 K 1000.0 K 1000 1000 1700 -15 -10 -5 0 x [mm] 800 800 q Freestream velocity 600 600 q 1987 m/s (SiO2) 0 s 60 s 1000.0 K 1000.0500.0 K K q 1903 m/s (Al2O3) 1000 500.0 K1000 q Deceleration depends on the particle type 800 800 and size q Shock stand-off distance: 9-10 mm 600 600 30 s 90 s 500.0 K 500.0 K 6/11/18 IPPW-15, University of Colorado, Boulder, June, 2018 10 DLR Capabilities: Flight Instrumentation 6/11/18 IPPW-15, University of Colorado, Boulder, June, 2018 11 DLR Capabilities: Hypersonic Flight Experiments • DLR has a unique capability performing hypersonic flight experiments using sounding rockets. descent • Flight experiments SHEFEX-I, SHEFEX-II and ROTEX-T provided very useful data on TPS and descentH1 aerothermal heating. AKTIV • Coming flight experiments ATEK H4 H2 (2018) and REFEX (2021) will H3 create complementary flight data. 6/11/18 IPPW-15, University of Colorado, Boulder, June, 2018 12 NASA Needs and Collaborations Ethiraj Venkatapathy International Planetary Probe Workshop 2018 6/15/2018 University of Colorado, Boulder, Co 13 Asteroid Break-up Modeling Visualization of fragmenting asteroid Analytical model for asteroid fragmentation and break-up Ø Fragmentation, and subsequent dispersal of the fragments, results in rapid deposition of energy in the atmosphere. This, in turn given rise the to the “airburst” blast-wave which poses a danger to human populations Ø Analytical risk assessment tools capture this phenomenon by modeling the spread rate of the fragments after a fragmentation event Leveraging collaboration between DLR’s unique experimental facilities, and NASA’s simulation capability is enabling for development of better predictive models for asteroid entry and break-up 1 5/14/18 Presented at the IPPW-14, The Hague, June 2017 4 Asteroid Break-up Modeling DLR experiment Cart3D Simulation Inviscid flow solver Cart3D has been shown able to accurately predict the trajectories of two spheres in “shock surfing” configurations 5/14/18 Presented at the IPPW-14, The Hague, June 2017 15 Asteroid Break-up Modeling DLR experiment US3D Simulation Simulations of two-sphere experiments performed by DLR have shown that a Navier-Stokes solver is required to accurately predict trajectories when trailing body is in the wake of the leading body 5/14/18 Presented at the IPPW-14, The Hague, June 2017 16 Toward a New Model for Asteroid Break-up… Simulation of free flight motion of two spheres falling through Mach 7 • ATAP is developing a fast-running database hypersonic flow (case 06-1) approach to fragmentation break-up modeling for asteroid risk assessments wants to move backward • Database is comprised of several thousands of wants to move forward Cart3D and US3D (in the wake) simulations of two sphere configurations • Trajectories for arbitrary configurations of spheres (“fragments”) may then be integrated analytically to obtain fragment spread rates • Comparisons between database approach and data from experiments performed at DLR show very good agreement for both wake interaction Wake Interaction Shock-Shock Interaction and shock-shock interaction cases The ATAP — thanks to the synergy between the unique, high-quality experimental techniques at DLR and the state-of-the-art computation capabilities at NASA Ames — are poised to deliver a first of its kind physics-based model for asteroid energy deposition and threat assessment 1 5/14/18 Presented at the IPPW-14, The Hague, June 2017 7 Publications Ø Venkatapathy, E., Gülhan, A., Aftosmis, M. J., Brock, J. M., Mathias, D. L., Neeb, D., et al. (2017). IN PURSUIT OF IMPROVING AIRBURST AND GROUND DAMAGE PREDICTIONS. Presented at the Planetary Defense Conference, Tokyo, Japan. Ø Marwege, A., Willems, S., Gülhan, A., Aftosmis, M. J., & Stern, E. C.. Superposition method for force estimations on interacting bodies in supersonic and hypersonic flows. Journal of Spacecraft and Rockets (accepted, January 2018) Ø Register, P., Stern, E., Mathias, D., Aftosmis, M., Seltner, P., Gülhan, A., “Fragment-Wake Interaction: A New Approach to Asteroid Fragmentation Modeling,” Planetary and Space Science (in process) Ø Seltner, P., Willems, S., Gülhan, A., Brock, J., Stern, E., "Aerodynamics of cylindrical bodies free-flying in hypersonic flow." AIAA Journal (in process) International Planetary Probe Workshop 2018 6/15/2018 University of Colorado, Boulder, Co 18 Aeothermal-Mechanical Erosion of TPS Due to Dust Ø Martian dust storms can augment TPS recession through mechanical erosion and greater heating. Global dust storms have been observed to occur every 3-4 years. Source: Dunbar, 1975 Ø State of the art traces back to mid- Heating increases with particle 90s studies for Mars Pathfinder concentration § Decoupled CFD-material response § Phenomenological models of erosion based on scant experimental data § Source: Vasilevskii, 2001 Applied as recession augmentation to material response model Ø Source: DLR Risks carried for § Mars InSight § ExoMars Schiaparelli Observed erosion patterns due to particle-laden flow 6/11/18 IPPW-15, University of Colorado, Boulder, June, 2018 19 NASA-DLR Implementing Arrangement: Fundamental Studies of Combined Aerothermal-Mechanical Erosion Scope: Perform fundamental studies on mechanical erosion of materials due to atmospheric dust at Mars during entry. Coupled particle-based simulation techniques under Objectives: development will accurately capture multiphase transport • Design and conduct experiments to and surface interaction. This will then be coupled to quantify the material erosion caused improved material response models for a complete, by particle-laden flows
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