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Research, Development and Programmes of Hypersonics Within ESA's Flight Vehicles & Aerothermodynamics Engineering section, activities and an overview of hypersonic projects and technologies Jeroen VAN DEN EYNDE European Space Agency 3rd International Symposium on Hypersonic Flight Air Force Academy (Pozzuoli), Italy, May 30-31, 2019 AAA – Sez. Roma Due “Luigi Broglio” AAA Sez. Roma Due "Luigi Broglio" ESA's Flight Vehicles & Aerothermodynamics Engineering section, activities and an overview of hypersonic projects and technologies Jeroen Van den Eynde et al. (TEC-MPA) 3rd International Symposium on Hypersonic Flight Air Force Academy (Pozzuoli), Italy, 30-31 May 2019 ESA UNCLASSIFIED - For Official Use FLIGHT VEHICLES AND AEROTHERMODYNAMICS ENGINEERING ESA UNCLASSIFIED - For Official Use Scope of the section Focal point for the architecture design, analysis and technical assessment of space transportation vehicles for suborbital, orbital and exploration applications, including upper stages, (re)-entry, expendable, and reusable vehicles Overall feasibility and viability assessments, as well as quick design iterations with the support of the necessary TEC competences Coordination of the specialised support and R&D initiatives with other D/TEC Sections in the frame of the relevant Competence Domains Engineering support, research, development and testing activities related to flight vehicles, flight physics, aerodynamics, thermodynamics and fluid dynamics engineering and the architecture design and analysis of suborbital, (re-)entry, space transportation, and exploration vehicles ESA UNCLASSIFIED - For Official Use Jeroen Van den Eynde et al. | 31/05/2019 | Slide 4 Activities Flight Vehicle Engineering Decelerators Design for Demise Heat transfer and heat Upper stages, Re-usability, Parachute and parafoil, rejection, Micro-launchers, Inflatable Devices, Drogue Ablation materials, Heat Hypersonic flight Chutes Shields, Thermal Blankets Aerodynamics Technology Test Beds Post Flight Analysis Shape optimisation, Loads Design, Computational Wind Tunnel Testing, Tool-set for Post Flight methods, High Speed Plasma Tunnels, Drop Analysis, Exploitation of Flight Atmospheric Flight Tests, Avionics Test Beds Data Thermodynamics Fluid Dynamics Contamination Heat Transfer, Lattice Boltzmann Acoustics and Particle Computational Fluid Methods, Cryogenic Contamination, Plume Dynamics and Mechanics Sloshing, Flows in Micro- Contamination gravity ESA UNCLASSIFIED - For Official Use Jeroen Van den Eynde et al. | 31/05/2019 | Slide 5 EUROPEAN HYPERSONIC PROJECTS AND TECHNOLOGIES ESA UNCLASSIFIED - For Official Use Hypersonic projects and technologies in Europe OUTLINE 1. Entry and Re-entry: exploration and exploitation 2. Access-to-Space: Airbreathing and/or Rocket Mode 3. High-Speed Cruisers 4. Flight-Experiment: Technology Demonstrator 5. Hypersonic Technologies RTD 6. Facilities and Measurement Techniques 7. Hypersonic Fundamentals ESA UNCLASSIFIED - For Official Use Jeroen Van den Eynde et al. | 31/05/2019 | Slide 7 Space Rider Programme Goals: To develop an affordable and sustainable reusable European space transportation system: • to enable routine access to and return from space • to provide a standardized platform for Payloads for multiple space application in a multitude of Orbits To focus on the demonstration of a recurring service Main Mission Scenario: Free Flyer: Microgravity Lab In Orbit Demonstration: . Exploration (e.g. robotics) entry: exploration entry: and exploration exploitation . Earth observation (e.g. instrumentation); - . Others (e.g. Earth science, telecommunication). Surveillance applications (e.g. earth monitoring, satellite inspection) Phase-B1 completed in December 2017 Activities for Phase-B2/C started on January 2018: System PDR in Q4 2018 ESA and Entry Re UNCLASSIFIED - For Official Use Jeroen Van den Eynde et al. | 31/05/2019 | Slide 8 Decelerators: Inflatable vs Deployable Decelerator technology (Vorticity/Fluid Gravity Foldable -Flare for Stabilizing and Control Engineering, UK) Flexible TPS and inflatable / deployable aero-decelerators. Testing in plasma wind tunnel @ DLR-K Next-generation Mars entry vehicles, Mars Penetrators, Mars Sample Return…. Modelling of large-diameter deployable entry vehicles. Construction of a 2.5m diameter functional demonstrator Foldable Heat Shield (Exploration) model with (low-speed) wind-tunnel deployment tests entry: exploration entry: and exploration exploitation - ESA and Entry Re UNCLASSIFIED - For Official Use Jeroen Van den Eynde et al. | 31/05/2019 | Slide 9 Air Launchable Microsatellite with aerobraking reentry MINI-IRENE FLIGHT EXPERIMENT capability MISTRAL MAIN RESULTS ACCOMPLISHED February 2018 Deployable 20-30kg-class satellite in LEO Qualification of the Engineering Model including mechanisms and TPS • Orbital module (50 W power) April 2018 • Umbrella-like reentry system: 15 Kg ESA’ Critical Design Review (CDR) successful completed • Mission capabilities: Microgravity experiments/ISS June 2018 Independent LEO experiments Thermal Qualification of the Flexible TPS at SCIROCCO Plasma Wind Aerodynamic controlled deorbit Tunnel successfully accomplished entry: exploration entry: and exploration exploitation - December 2018 Shock & Vibration, Thermal-Vacuum Qualification (Space Qualification Lab) and ESA’ Acceptance Review (AR) NEXT STEPS AND MILESTONES Summer 2019 Launch of the Demonstrator scheduled in 2019 with a ESA and Entry Re UNCLASSIFIED - For Official Use Sounding Rocket Jeroen Van den Eynde et al. | 31/05/2019 | Slide 10 Demise: destructive re-entry Simulation and experiments for heating rates FLPP-3 Demise Observation Capsule DOC during demise (Imperial, Oxford & FGE, UK) Objective: Modelling using FGE in-house codes – heating rates Development of an Observation Capsule, to faceted shapes. Heat flux measurements being collecting specific data relevant to upper stage undertaken in Oxford Low Density Tunnel. break-up and demise, and observing the critical phenomena Status: EQM Qualified w.r.t. mechanical environment at the CIRA Space Qualification laboratories. CDR successfully concluded. Aerothermodynamic/chemistry testing at VKI entry: exploration entry: and exploration exploitation - 휏 =0 sec, injection 휏 =10 sec 휏 =20 sec EQM Integration EQM during test 휏 =30 sec, jump 휏 =40 sec 휏 =50 sec ESA and Entry Re UNCLASSIFIED - For Official Use Jeroen Van den Eynde et al. | 31/05/2019 | Slide 11 Hypersonic projects and technologies in Europe OUTLINE 1. Entry and Re-entry: exploration and exploitation 2. Access-to-Space: Airbreathing and/or Rocket Mode 3. High-Speed Cruisers 4. Flight-Experiment: Technology Demonstrator 5. Hypersonic Technologies RTD 6. Facilities and Measurement Techniques 7. Hypersonic Fundamentals ESA UNCLASSIFIED - For Official Use Jeroen Van den Eynde et al. | 31/05/2019 | Slide 12 SABRE - SKYLON Hot heat exchanger test rig completed, testing to SABRE™ core test demonstrator in PDR review. Test commence soon. Inflow air at up to Mach 5 enthalpy facility ready end of 2019. Testing commences in 2020 Access to Space Space to Access 2018 2020 INTEGRATE FLIGHT TEST HOT HX SABRETM D FIRST ENGINE TEST CORE TEST APPLICATION TEST Programme SABRE Core ESA UNCLASSIFIED - For Official Use Jeroen Van den Eynde et al. | 31/05/2019 | Slide 13 Access to Space by Airbreathing Propulsion Skylon vehicle aerodynamics SPARTAN intake testing (Oxford & Reaction Engines LTD, UK) (Oxford, UK and UQ, Aus) Aerodynamic coefficients measured using free- 3 stage to orbit concept – scramjet powered flight optical measurement technique in Oxford 2nd stage. Developed novel high response High Density Tunnel mass capture/back pressure device for testing intake performance in Oxford High Density Tunnel Access to Space to Access ESA UNCLASSIFIED - For Official Use Jeroen Van den Eynde et al. | 31/05/2019 | Slide 14 Hypersonic projects and technologies in Europe OUTLINE 1. Entry and Re-entry: exploration and exploitation 2. Access-to-Space: Airbreathing and/or Rocket Mode 3. High-Speed Cruisers 4. Flight-Experiment: Technology Demonstrator 5. Hypersonic Technologies RTD 6. Facilities and Measurement Techniques 7. Hypersonic Fundamentals ESA UNCLASSIFIED - For Official Use Jeroen Van den Eynde et al. | 31/05/2019 | Slide 15 HEXAFLY-INTernational Project co-funded by European Commission, ESA, Russian Federation and Australia Project goals: Mission objective: manufacturing, assembling and flight testing an to perform a high-speed flight experiment with a unpowered hypersonic glider with high target flight Mach number of 7 to 8 and altitude aerodynamic efficiency. range between 27 and 33 km. To increase TRL of a number of breakthrough Cruisers technologies suitable for future high speed civil 1. VS-43 Launch Vehicle lifts off; 2. Fairing release (about 80 km); transportation systems. 3. 3. Payload release (90km); 4. Cruise phase to the experiment window To integrate breakthrough technologies with (Stabilization by CGS); Speed 2. 4. - standard aeronautical technologies. 5. ESM separation from the EFTV (55 km); 6. Experimental window; gliding phase. 5. High ESM 6. 1. EFTV ESA UNCLASSIFIED - For Official Use Jeroen Van den Eynde et al. | 31/05/2019 | Slide 16 STRATOFLY Stratospheric Flying Opportunities for High-Speed Propulsion STRATOFLY Coordinator STRATOFLY main objectives Expertise: Aircraft and Systems Design, Life Expertise: Noise Emission Cycle Cost Estimation, Safety Assessment • To refine the design and the concept of Expertise: Plasma assisted combustion STRATOFLY Deputy Coordinator operations of a Mach 8 reference vehicle.
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