SP 2020+1, Preliminary Program DAY 1 Page 1

DAY 1 : March 17th, 2021 SPACE DEMOCRATIZATION

PLENARY SESSION

9h00 CONFERENCE INTRODUCTION E X H I Plenary Round Table #1 : B I 9h20 AGENCIES MID AND LONG TERM POLICIES T Chair : C. MANFLETTI, ESA I O N

a 10h50 COFFEE BREAK n d

N Plenary Round Table #2 : E T 11h10 PRIMES AND OPERATORS VS SUPPLIERS FOR SPACE TRANSPORTATION and SPACECRAFT W Chairs : D. RIBEREAU, ArianeGroup, Jamila MANSOURI, ESA O R K I N G

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KEYNOTE SPEECH #1: Space democratization 14h00 Angelo FONTANA , S.p.A., IT PARALLEL SESSIONS Room 1 Room 2 Room 3 Room 4 Room 5 Room 6 Room 7 SESSION 01 - ST SESSION 02 - ST SESSION 03 - SC SESSION 04 - SC SESSION 05 - SC SESSION 06 - SC SESSION 07 - SC

Lox/ Engine developements Solid Rocket Motors Cubesat Propulsion Systems 1 Electric Propulsion 1 Modeling and Simulation 1 Capabilities and Techniques Chemical Thrusters 1

CHAIR 1 Marc VALES, Dassault Aviation, FR Yann TALAMONI, ArianeGroup, FR Alberto GARBAYO, AVS -UK, UK M. COLETTI, Thales Alenia Space, UK Victor FERNANDEZ (ESA) Mark FORD (ESA) Kenichi KIMOTO, IHI, JP

CHAIR 2 Simon HYDE (ESA) Marco LEONARDI (ESA) Davina DI CARA (ESA) Jose GONZALEZ DEL AMO (ESA) Helmut CIEZKI, DLR, DE Simone CIARALLI, OHB, SE Ferran VALENCIA (ESA) 00159 - Prometheus: Precursor of new low-cost 00007 - P120C Solid Rocket Motor - Synthesis of 00102 - Development of impulse bit-based 00080 - Development status of the Advanced Cusp 00291 - Demonstrator of a Continuously Operating 00079 - Electric Propulsion Torsional Thrust 00059 - An Overview of the LEROS 2c MMH/MON Family the development of the common propulsive SRM effective thrust control for fine precision Field Thruster propulsion system Divert- and Attitude Control System with Run Balance with wireless microwave power transfer High Performance, Cost Effective Apogee Engine for Ariane 6 and -C propulsion systems on CubeSats Time of One Minute Pamela Simontacchi Max Vaupel Kyaw Swar Robert Westcott E Tarquinio Germani Sakari Teerikoski Norman Hopfe 14:40 1 X ArianeGroup - FR Airbus - DE AVS - Added Value Solutions UK - UK Nammo - GB EUROPROPULSION - FR GomSpace Sweden - SE Bayern-Chemie Gmbh - DE H I B 00097 - Development status of the 00414 - Ariane 6 & VEGA-C Programs - The P120C 00314 - Assessment of the impact of a 00402 - The design, manufacture, and testing of a 00306 - Assessment of numerical diffusion effects 00263 - The Design, Fabrication And Test Progress 00458 - Effect of Chamber Pressure and Mixture and methane M10 rocket engine for the Vega-E SRM Nozzle Qualification and Manufacturing miniaturized electric propulsion system on the low powered magnetically shielded krypton Hall in magnetized plasma plume simulations Summary of the Iridium catalysed electrolysis Ratio variation in chamber temperature of Liquid I upper stage Transition Phase cubesat technologies effect thruster. thruster rocket thruster T Alberto Modesti Daniele Kajon Yann Talamoni Fabrizio Stesina Thomas Munro-O'Brien Charles Muir Mn Prakash I 15:00 2 Universidad Carlos III de Madrid - UC3M - ES AVIO SpA - IT ArianeGroup - FR Politecnico di Torino - IT University of Southampton - UK Imperial College London - UK Liquid Propulsion Systems Centre - ISRO - IN O N

00160 - HYPROB-NEW: recent developments of 00355 - A Sounding Rocket Solid Propellant First 00425 - Miniaturizing a resistojet manufacturing, 00155 - Model of the Space Charge Limited 00559 - A software for computational plasma 00168 - Laser-induced fluorescence technique 00459 - Sensitivity Study on Pulse mode a the LOX/LCH4 research line Stage postproduction analysis and testing Electron Emission from Dispenser Cathodes engineering for European space industry development for Hall thrusters diagnostic in 3D performance in AOCS Thruster due to temperature space variations n Francesco Battista Alexander Weigand Swati Thirumangalath Jan-Philipp Wulfkuehler Dejan Petkow Yordanka Dancheva M Ponnuswamy d 15:20 3 CIRA - IT Bayern-Chemie GmbH - DE VTT & Aurora Propulsion Technologies Oy - FI Technische Universität Dresden - DE SPARC Industries SARL - LU Aerospazio Tecnologie - IT Liquid Propulsion Systems Centre - ISRO - IN N E 00416 - Development of LOX-Methane 00401 - Collecting data on aluminum combustion 00311 - Modular impulsive green monopropellant 00470 - Ariane Group 5A Neutralizer qualification 00111 - Numerical simulation of the plume of a 00115 - A non-invasive HET plasma diagnostic tool 00462 - Devolepment of deep throttling engine for T Technology Demonstrator engine and its oxides in solid rocket motors propulsion system (MIMPS-G) overview Magnetically Enhanced Plasma Thruster based on a 1 MSa/s imaging acquisition platform interplanetry missions featuring narrow-band spectral filtering and quasi W Anish K C Stefania Carlotti Ahmed Nosseir Christian Altmann Simone Di Fede real-time processing Ebin Thomas O 15:40 4 Liquid Propulsion Systems Centre - ISRO - IN Politecnico di Milano - IT TU DELFT x University of Pisa - IT ArianeGroup - DE University of Padova - IT Yordanka Dancheva Indian Space Research Organisation - IN R

Aerospazio Tecnologie - IT K I

00088 - Development of a 25 kN Oxygen-Methane 00526 - Prediction of multi-factor coupling 00014 - ALGERIA’s first developed satellite 00117 - Emission characteristics and 1250h 00274 - Developing a 3D Numerical Model of a 00322 - Quartz Crystal Microbalance-based 00495 - Investigation of Low Power Arcjet N Test Chamber ablation of EPDM insulation in two-phase propulsion system based on green propellant endurance test of a cold electron field emitter Magnetized Vacuum Arc Thruster Examination of Sputtering Phenomena of RF Ion Thruster in Test Facilities at IRS and ESA-ESTEC G environment based on CNTs for space applications. Thrusters through Numerical Simulation Horacio Moreira Djamal Darfilal Adam Obrusnik Le Wang Martin Tajmar Jens Simon Partho Pratim Upadhyay 16:00 5 Omnidea Lda. - PT Satellites Development Center - DZ PlasmaSolve s.r.o. - CZ Northwestern Polytechnical University - CN Technische Universität Dresden - DE DLR - German Aerospace Center - DE Institut für Raumfahrtsysteme - DE

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Room 1 Room 2 Room 3 Room 4 Room 5 Room 6 Room 7 SESSION 08 - ST SESSION 09 - ST SESSION 10 - SC SESSION 11 - SC SESSION 12 - SC SESSION 13 - SC SESSION 14 - SC

Programs Aerospike Nozzles Cubesat Propulsion Systems 2 Electric Propulsion 2 Modeling and Simulation 2 Fluid Systems 1 Chemical Thrusters 2

CHAIR 1 Gérard ORDONNEAU, ONERA, FR U. PALMNÄS, SE Alberto GARBAYO, AVS -UK, UK M. COLETTI, Thales Alenia Space, UK Louis WALPOT (ESA) Markus PEUKERT, OHB, DE Gilles VIGIER ,3AF,FR

CHAIR 2 Johan STEELANT (ESA) Mark FORD (ESA) Kathe DANNEMEYER (ESA) Davina DI CARA (ESA) Bayrem ZITOUNI, OHB, DE Richard SCHWANE (ESA) Chris HUNTER (ESA) 00488 - Technology-driven Selection and Design 00403 - Research Activities in the Development of 00082 - Investigation of Thermal Behaviour of 00150 - Performance characterisation of the 00411 - OpenPlume for EP and CP plume 00040 - Modeling the Propellant-less Thrust 00045 - An Overview of the Medium and High for future Korean Launch Systems DemoP1: a LOX/LNG Aerospike Engine Additively Manufactured Green Bi-Propellant Water ElecTrolysis Hall Effect Thruster (WET-HET) modelling: tool developments status Obtainable from Quantised Inertia. Altitude Space Propulsion Test Facilities in Demonstrator Thrusters in CubeSat Applications Using Transient using direct thrust measurements Westcott Daeban Seo Thermal Modelling Bayrem Zitouni Mike Mcculloch E Federico Rossi Alexander Schwertheim Matthew Palmer 16:40 1 KARI - KR Peter Van Den Berg OHB - DE University of Plymouth - UK X Pangea Aerospace - ES Imperial College London - UK Nammo - GB H Delft University of Technology - NL I B 00587 - Innovations in Propulsion within ESA’S 00406 - Investigation of aerodynamic thrust- 00504 - Study of Plume Impingement on CubeSat 00254 - Design of an experimental ablative pulsed 00424 - Plasma brake deorbiting simulation using 00275 - The Development of Highly Efficient 00339 - Overview of Spacecraft Propulsion Future Launcher Preparatory Programme (FLPP) vector control for aerospike nozzles in cold-gas Structure and Solar Array by Different Propellants plasma thruster for micropropulsion dynamic space environment Miniaturised Proportional Valves Based on Activities in Thales Alenia Space in the UK I Advanced Technology experiments Piezoelectric PZT Actuators Harshit Saini Scherezade Barquero Pyry Peitso Mark Pollard T Kate Underhill Jan Sieder-Katzmann Charles Opoku 17:00 2 I SRM Institute of Science and Technology - IN Universidad Carlos III de Madrid - UC3M - ES Aurora Propulsion Technologies - FI Thales Alenia Space UK - UK ESA - NL Technische Universität Dresden - DE The Open University - UK O N

00461 - Overview of the activities promoted by 00480 - ACTiVE – Optimisation of a fluidic thrust 00226 - Experimental Study on Micropropulsion 00247 - Design, Set-Up, and First Ignition of the RF 00582 - Design of a Hollow Cathode Thruster: 00418 - Investigation of hysteresis on propellant 00567 - Overview of the space propulsion the Italian Space Agency in the field of liquid vector control on aerospike nozzles Using Dust Explosion of Aluminum/Magnesium Helicon-based Plasma Thruster Concepts, Parameter Study and Initial Test Results flow rate for 10 cm class microwave ion thruster activities at the CNES Toulouse Space Center a space propulsion with Water Vapor n Martin Propst Francesco Romano Norman Gondol Yusuke Yamashita Thomas Liénart Marco Pizzarelli Masaya Murohara d 17:20 3 Technische Universität Dresden - DE University of Stuttgart - DE Technische Universität Dresden - DE JAXA - JP CNES - FR ASI Italian Space Agency - IT The University of Tokyo - JP N E 00330 - Ignition system qualification and 00340 - Design and evaluation of aerospike 00212 - Propulsive Performance Analysis of 00359 - Mini Radio Frequency Thruster RIT-µX and 00391 - Characterization of a 5kW-class hall 00318 - Ongoing Development of next generation 00576 - Fusion energy based space propulsion T Flight production and successors nozzles for upper stage Energetic Ionic Liquid Mono-Propulsion Systems Mini Radio Frequency Neutralizer RIT-µN for Small thruster via 2D hybrid simulations Electric Propulsion Fluid Management Systems using a compact spherical tokamak for Micro-Spacecrafts Spacecraft W Rudi Matthijssen Francesco Nasuti Jesús Perales-Dĺaz Johan Kuiper Adam Baker Asato Wada Hans Leiter O 17:40 4 Aerospace Propulsion Products BV - NL Sapienza University of Rome - IT Universidad Carlos III de Madrid - UC3M - ES Bradford Engineering - NL Rocket Engineering Ltd - GB R JAXA - JP ArianeGroup - DE K I 00222 - Overview of rocket testing at the Westcott #N/A 00214 - ENPULSION Nano: A fully integrated 00467 - Serial Production of Space Components 00583 - Electrostatic Pump Development for micro 00049 - Development of a Chemical Thrusters N test facility (2018/2019) electric propulsion system for Small Satellites for Megaconstellations Liquid Pulsed Plasma Thrusters Plume Contamination Module in the frame of the Plume Impingement Tool “PITOT” G Edward Moore David Krejci Nils Hildebrand Cristian Dobranszki Andrea Binci 18:00 5 Airborne Engineering - GB Enpulsion - AT AST Advanced Space Technologies GmbH - DE University of Southampton - UK Thales Alenia Space - IT

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DAY 2 : March 18th, 2021 NEW BUSINESS, NEW MARKETS

PLENARY SESSION Plenary Round Table #3 : European Micro Launchers and Space ports Part 1 : Challenges for European Micro launchers, 9h00 Part 2 : Challenges for European Space ports Chairs : Thilo KRANZ, ESA, Jérôme BRETEAU, ESA, Ulf PALMNÄS, Palmnäs & Co

10h40 COFFEE BREAK PARALLEL SESSIONS Room 1 Room 2 Room 3 Room 4 Room 5 Room 6 Room 7 SESSION 15 - ST SESSION 16 - ST SESSION 17 - SC SESSION 18 - SC SESSION 19 - SC SESSION 20 - SC SESSION 21 - SC

Engine control Combustion chamber 1 & Ignition Cubesat Propulsion Systems 3 Electric Propulsion 3 Modeling and Simulation 3 Fluid Systems 2 Chemical Thrusters 3

CHAIR 1 Gérard ORDONNEAU, ONERA, FR Didier BOURY, ArianeGroup, FR Alberto GARBAYO, AVS -UK, UK Olivier DUCHEMIN, SAFRAN SEP Toru SHIMADA, JAXA, JAP Markus PEUKERT, OHB, DE Kate UNDERHILL (ESA)

CHAIR 2 Mark FORD (ESA) Carlos MUNOZ (ESA) Armin HERBERTZ (ESA) Neil WALLACE (ESA) Niccola KUTUFA (ESA) Luca FERRACINA (ESA) Lorenzo BISI, OHB, SE 00236 - VEGA-E Upper Stage Engine Control Unit 00043 - Low Order Modeling of High-Frequency 00234 - The concept and development status of 00109 - REGULUS: integration and testing of an 00385 - The study on the performances of the 00208 - European Electronic Pressure Regulator - 00038 - Estimation of thrust performance from with closed-loop control for M10 engine Combustion Instabilities in Liquid Rocket Engines new green propellant propulsion system named iodine electric propulsion system micro cathode arc thruster with different cathode Engineering Model Test Results the experimental results of the combustion of “Pinot-G” materials magnesium wires in water vapor Nicole Segala Alexandre Fougnie Mirko Magarotto Nicholas Solway Naoki Morita Jinyue Geng Mariko Akiyama 11:00 1 GMV-AD - ES EM2C - FR University of Padova - IT Nammo - GB E IHI Aerospace - JP Beijing Institute of Control Engineering - JP The University of Tokyo - JP X H I 00477 - Electrical Regulating Valve for Rocket 00325 - LES simulation for evaluation of acoustic 00057 - Experimental Investigation and In-flight 00085 - New EPIC findings: Impact of Mission 00273 - Simulation-guided engineering of an air- 00465 - Experimental studies on Pressure 00573 - Flow Analysis of a Supersonic Nozzle by Propulsion Systems response of subcritical coaxial flame submitted to Characterization of Micronewton Ultra-Precision Total Impulse on Technology Selection & breathing thruster concept Regulator for failure mode means of Quantitative Schlieren B high-frequency acoustic fields and Low Noise Proportional Propulsion Prerequisites for Lifetime Qualification via Matthias Günther Technology Analysis Krystof Mrozek M Stalin Emilia-Georgiana Prisacariu I Aurélie Nicole 11:20 2 T ArianeGroup - DE Xuhui Liu Birk Wollenhaupt PlasmaSolve s.r.o. - CZ Liquid Propulsion Systems Centre - ISRO - IN Romanian Research and Development Institute for ONERA - FR Gas Turbines - COMOTI - RO I Beijing Institute of Control Engineering - JP OHB System AG - DE O N 00533 - Nonlinear Control of an Expander-Bleed 00078 - Numerical characterization of the acoustic 00287 - Development of a cubesat green 00203 - Electric propulsion alternatives selection 00047 - Use of numerical modelling to assess the 00468 - Flow simulation studies on Pressure 00523 - Delta Qualification of a Normally Closed Rocket Engine using Reinforcement Learning damping in a cold flow experiment with coupled propellant tank with fine CoG control to interplanetary missions influence of the electrostatic configuration on the Regulator for Lunar Lander Module Valve with Shape Memory Alloy Actuator for cavities electric field in an electrospray thruster Hydrazine applications a Kai Dresia Michel Poucet Olga Starinova J. Nithya Bharathi David Marchal Mobin Yunus Malik Pilar Valles n 11:40 3 DLR - German Aerospace Center - DE LIFT ME OFF - UK Samara National Research University - RU Liquid Propulsion Systems Centre - ISRO - IN CentraleSupelec - FR The University of Manchester - UK ArianeGroup - DE d

N 00496 - On-Ground and In-Flight evaluation of a 00238 - Investigation of Laser Ignition Systems in 00207 - 0.5N Thruster for Small Satellite 00353 - Mission-driven selection of the propulsion 00585 - Modelling and Optimizing an 00249 - Development and Qualification of a 00536 - Effect of Post Weld Heat Treatment on AA- E Redundant Control Electronics for Variable Thrust LOX/Methane Thrust Chambers Propulsion System Using HAN/HN-Based “Safe” system for INNOSAT platform Electrohydrodynamic Thruster Compact Xenon Feed System for a 1500 W Hall 7075-T6 Pressure Vessel welded by Friction Stir Liquid Engine in Soft-Landing mission Green Monopropellant HNP225 Thruster Welding for Space Application T Sebastian Soller Simone Ciaralli Eduardo Calvo Kiran Ravikumar Shinji Igarashi Demet Ulusen Mohamed Khatir W 12:00 4 ArianeGroup - DE OHB Sweden AB - SE University of Porto - PT O Liquid Propulsion Systems Centre - ISRO - IN IHI Aerospace - JP TUBITAK UZAY - TR Algerian Space Agency - DZ R K 00095 - 2D Full-Cycle Simulation of Air-Breathing 00395 - Electric Thruster Selection Criteria: a 00175 - Answering the challenges for Electrical #N/A I Microwave Rocket System Point of View Capacitance Tomography systems in rocket propulsion tanks N Kuniyoshi Tabata Christophe Koppel G Philipp Behruzi 12:20 5 The University of Tokyo - JP KopooS Consulting ind. - FR ArianeGroup - DE

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KEYNOTE SPEECH #2 : Electric Propulsion Activities at ESA 14:00 Jose GONZALEZ DEL AMO, ESA PARALLEL SESSIONS Room 1 Room 2 Room 3 Room 4 Room 5 Room 6 Room 7 SESSION 22 - ST SESSION 23 - ST SESSION 24 - SC SESSION 25 - SC SESSION 26 - SC SESSION 27 - SC SESSION 28 - SC

LRE 1 & electro pumps Combustion chamber 2 Cubesat Propulsion Systems 4 Electric Propulsion 4 New Propulsion Concepts In orbit servicing and debris removal Programs and Projects

CHAIR 1 Victor FERNANDEZ (ESA) Didier BOURY, ArianeGroup, FR Alberto GARBAYO, AVS -UK, UK Olivier DUCHEMIN, SAFRAN SEP Jose GONZALEZ DEL AMO (ESA) Markus PEUKERT, OHB, DE Johan STEELANT (ESA)

CHAIR 2 Marc VALES, Dassault Aviation, FR Simon HYDE (ESA) Louis WALPOT (ESA) Cheryl COLLINGWOOD (ESA) Alain DEMAIRÉ, OHB, SE Jeroen VAN DEN EYNDE (ESA) Simone CIARALLI, OHB, SE 00374 - ArianeGroup R&T activities on Fluid 00081 - Wall Pressure Effects of Nitrogen and 00244 - Assessment on the low temperature 00301 - PN-3 helicon plasma device as a testing 00331 - Preliminary investigations of the 00486 - Active Debris Multi-Removal Mission 00033 - Ariane Group Electric Propulsion 2020 – Structure Interaction (FSI) for space Hydrogen Coolant Layers in a Transpiration Cooled operation of a high test peroxide reaction control facility for plasma propulsion study electromagnetic fields in the far plume of a Based on Electrodynamic Tethers An Overview E turbomachinery Model Scramjet Combustor system: compatibility and thruster firing test in Helicon Plasma Thruster X low temperature condition. Dmitry Kutuzov Gabriel Borderes Motta Hans Leiter Ariane Deneuve Friedolin Strauss Pedro José Jiménez H 14:40 1 Yao-Chung Hsu National research center “Kurchatov institute” - Universidad Carlos III de Madrid - UC3M - ES ArianeGroup - DE ArianeGroup - FR DLR - German Aerospace Center - DE RU Universidad Carlos III de Madrid - UC3M - ES I National Space Program Organization - TW B I 00549 - Optimization And Performance 00337 - Dependency of Coolant Mass Flow on 00218 - Searching for chaotic behavior in the ion 00143 - Validation of a Xenon Propulsion System 00091 - Plasma acceleration by oscillating electric 00286 - Development of a Thruster Gimbal 00288 - Ongoing Satellite Propulsion Activities at T Characterization At Off-Design Conditions For Heat Flux and Surface Temperature in Rocket current waveforms of a Hall effect thruster Simulation Model with 5-kW class Hall-Effect and magnetic fields Mechanism for Accurate Proximity Operations Bradford Space Supersonic Impulse Turbine Blades Combustion Chambers Thruster Coupled Tests I Agnieszka Szelecka Amnon Fruchtman Marcos Perez William Van Meerbeeck Robson Hahn Pascal Kringe Michele Coletti O 15:00 2 IPPLM - PL H.I.T. - Holon Institute of Technology - IL LIFT ME OFF - UK Bradford Engineering - NL N DLR - German Aerospace Center - DE DLR - German Aerospace Center - DE Thales Alenia Space - IT

a

00071 - Experimental Validation of Supersonic 00122 - A comparison between film and 00270 - E X B probe measurements in the plasma 00471 - Electron and ion properties in the beam 00281 - Faraday cup design for low power electric 00006 - Analysis and verification of in-orbit 00531 - Overview of electric propulsion activities n Turbines for Launcher applications transpiration cooling performance in a rocket plume of a 100 W-class Hall thruster and discharge of a Helicon plasma source for thrusters fuelling system during development and at CNES combustion chamber application in spacecraft propulsion breadboard testing d Cosmin Petru Suciu Thibault Hallouin Valentin Hugonnaud Alberto Rossi Stijn Koehler Alfio Emanuele Vinci Avichai Elimelech 15:20 3 Romanian Research and Development Institute for ICARE - CNRS - FR Enpulsion - AT CNES - FR N Gas Turbines - COMOTI - RO Delft University of Technology - NL CNRS - FR Thales Alenia Space UK - UK E T

00578 - Concept for compact electropump for 00182 - Implementation of an Acoustic Modes 00396 - A numerical parametric investigation on 00070 - Improvement of a numerical tool for the 00108 - Two-dimensional Full Particle-in-Cell 00145 - An experimental study of the ion injector W thruster engines Calculation Method for an 25 kN Engine with the optimal design and operation of coaxial ECR simulation of an Helicon Plasma Thruster Simulation of Magnetic Sails in Formation Flight with C/C-Ipresskon® grids O Comparison to the L75 Engine Results thrusters Alexandru-Claudiu Cancescu Nabil Souhair Akane Wada Oleg Peysakhovich R Arthur Durigan Bahdur Alvaro Sanchez-Villar 15:40 4 Romanian Research and Development Institute for Università di Bologna - IT Tohoku University - JP JSC Kompozit - RU K Gas Turbines - COMOTI - RO CLA - Alcântara Launch Center - BR Universidad Carlos III de Madrid - UC3M - ES I N G #N/A 00482 - Subsonic and supersonic combustion in 00110 - Quasi 2D PIC Model of a Magnetically 00023 - Design, Manufacture and Testing of a #N/A 00290 - ESA Propulsion Laboratory at ESTEC the flight Mach number range from 5 to 6 Enhanced Plasma Thruster Laser Micro-manufactured Electrospray Hole Emitter Eduard Bosch Borràs Luciano Galfetti Marco Minute Sahil Maharaj ESA - NL 16:00 5 Politecnico di Milano - IT University of Padova - IT University of Manchester - UK

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Room 1 Room 2 Room 3 Room 4 Room 5 Room 6 Room 7 SESSION 29 - ST SESSION 30 - ST SESSION 31 - SC SESSION 32 - SC SESSION 33 - SC SESSION 34 - SC SESSION 35 - SC

LRE Turbopumps 2 Engine/Vehicle Interfaces Cubesat Propulsion Systems 5 Electric Propulsion 5 New propulsion Concepts 2 Hybrid Systems 1 Manufacturing and Processess

CHAIR 1 Lilian PREVOST, (CNES), FR Chris HUNTER (ESA) David KREJCI, Enpulsion, DE M. COLETTI, Thales Alenia Space, UK Helmut CIEZKI, DLR, DE Davar FEILI (ESA) Sébastien BIANCHI, Air Liquide, FR

CHAIR 2 Csaba JEGER (ESA) Gérard ORDONNEAU, ONERA, FR Matthew SMITH (ESA) Jose GONZALEZ DEL AMO (ESA) Mark FORD (ESA) Toru SHIMADA, JAXA, JAP Marco DE ROSA (ESA) 00417 - Mathematical Modeling of Powerhead 00157 - Research on Propellant Slosh Dynamics of 00289 - Endurance Test of PETRUS 5J and 00176 - HEMPT electric propulsion status update 00198 - Net-shape Technologies for Low-cost 00278 - The SpaceDrive Project - Conclusion of 00352 - Development and Qualification of an Test Article for a Semi-Cryogenic Engine a Martian Moon Lander Presentation of a Flight Model Design Manufacture of Tank Shells and Weld-free COPV Mach-Effect-Thruster Experiments on High- Electric Propulsion Thruster Orientation Ernst Bosch Liner Precision Balances in Vacuum Mechanism for Electra GEO satellite Avinash Chandra Keitaro Anii Christoph Montag E Thales - DE Ralf Becker Maxime Monette Hans Hellman 16:40 1 Liquid Propulsion Systems Centre - ISRO - IN The University of Tokyo - JP University of Stuttgart - DE X TISICS Limited - UK Technische Universität Dresden - DE OHB Sweden AB - SE H I

00537 - Development of High Speed Hybrid 00361 - Drag analysis of a modern lightweight 00272 - Long lifetime solenoid valve for Electric 00192 - Hybrid PIC-Fluid Simulation of a 00513 - Observation of electron detachment in a 00283 - Hybrid Propulsion System for Deep Space 00224 - Magnetic Field Enhancement of the Quad B Bearings for Reusable Pump-Fed Liquid Rocket at high mach numbers Propulsion Systems Waveguide ECR Magnetic Nozzle Plasma Thruster magnetic nozzle CubeSat mission Confinement Thruster (QCT): Design and Early I Engines Development of the QCT Phoenix Ainslie French Bohdan Yurkov Marco Riccardo Inchingolo Shadrach Hepner Fredrik Persson T Angelo Pasini Emmanuelle Rosati Azevedo 17:00 2 CIRA - IT Space Electric Thruster Systems - UA Universidad Carlos III de Madrid - UC3M - ES University of Michigan - US GomSpace Sweden - SE I University of Pisa - IT AVS - Added Value Solutions UK - UK O N

00569 - Contributions regarding the gas dynamics 00588 - Design optimisation and analysis of very 00112 - MEMS thruster based 6DoF propulsion 00326 - Status of the On-Going Qualification Life 00104 - Thrust Measurements and Evaluation of 00541 - Common Propellant Hybrid Propulsion 00493 - Market Entries for SUPREMETM Thrusters: of a turbine with partial admission high power transportation system to Mars system for CubeSats Test of the PPS®5000 Hall Thruster Unit Asymmetric Infrared Laser Resonators for Space System Architecture using Applied-Field Commercialization of Superconductor-based-AF- a Propulsion Magnetoplasmadynamic Thrusters MPD Alexandru-Claudiu Cancescu Guillermo Ortega Umut Cindemir Olivier Duchemin n Oliver Neunzig Marcus Collier-Wright Manuel La Rosa Betancourt 17:20 3 d Romanian Research and Development Institute for ESA - NL GomSpace Sweden - SE SAFRAN SEP - FR Gas Turbines - COMOTI - RO Technische Universität Dresden - DE Neutron Systems - DE Neutron Star Systems - DE N E 00552 - Versatile water test bench for launchers 00584 - Rocket Engine Digital Twin – Modeling and 00285 - Development of an Innovative Chemical 00521 - Development activities on the Engineering 00308 - Plasma Acceleration by Electromagnetic 00024 - Comparison of green and conventional 00491 - High Temperature Superconductor based T liquid engines turbo-pumps and fluids Simulation Benefits Propulsion Subsystem for 12U Earth Observation Qualification Model of SITAEL’s 5kW-class Hall Nozzle for an Inertial Electrostatic Confinement rocket propellants: system analysis tool for in- propulsion and power system architectures as management devices and Telecommunication Missions thruster unit Cathode: Development and Characterization space propulsion enablers for high power missions W David Jimenez Mena Dan Ifrim Marcos Perez Tommaso Andreussi Yung-An Chan Lukas Werling Marcus Collier-Wright O 17:40 4 Siemens Digital Industry Software - FR R Romanian Research and Development Institute for LIFT ME OFF - UK SITAEL - IT University of Stuttgart - DE DLR - German Aerospace Center - DE Neutron Star Systems - DE Gas Turbines - COMOTI - RO K I 00580 - Development of turbines nitrogen feed 00169 - The Evolution of the Liquid Cores in Flash 00044 - Spectral radiance measurements of 00012 - Lunar Mission Tanks Using Surface 00013 - Investigation of Next Generation 00268 - The Spacedrive-Project – Latest Thrust N systems for liquid rocket engines turbo-pumps Boiling Liquid Nitrogen Sprays SPT140 thrusters Tension Propellant Management Devices for Combined Propulsion Architectures for Electric Measurements of the EMDrive with Advanced test benches Propellant Acquisition and Supply and Chemical Propulsion Testing Facilities G Andreas Rees Véronique Perrin Bailly Dan Ifrim Don Jaekle Oscar Jennings Martin Tajmar 18:00 5 DLR - German Aerospace Center - DE Thales Alenia Space - FR Romanian Research and Development Institute for Pmd Technology - US Airbus - GB Technische Universität Dresden - DE Gas Turbines - COMOTI - RO

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DAY 3 : March 19th, 2021 ENVIRONMENT PLENARY SESSION Plenary Round Table #4 : Green propulsion for space applications between the different demands 9h00 of old and new mission conditions, cost reduction, and increasing environmental and health regulations H. CIEZKI, DLR

10h40 COFFEE BREAK PARALLEL SESSIONS Room 1 Room 2 Room 3 Room 4 Room 5 Room 6 Room7 SESSION 36 - ST SESSION 37 - ST SESSION 38 - SC SESSION 39 - SC SESSION 40 - SC SESSION 41 - SC SESSION 42 - SC

Green & Hybrid Propulsion 1 LUMEN Project Green Propulsion 1 Cold Gas Thrusters Propellants 1 Electric Propulsion 6 ISRU 1

CHAIR 1 Jérôme ANTHOINE, ONERA, FR Stefan SCHLECHTRIEM, DLR, DE Helmut CIEZKI, DLR, DE Gilles VIGIER ,3AF,FR Sébastien BIANCHI, Air Liquide, FR George SCHMIDT, NASA, US Nathalie GIRARD (CNES)

CHAIR 2 David PERIGO (ESA) Marco DE ROSA (ESA) Wilhelm DINGERTZ, Bradford Ecaps Niccola KUTUFA (ESA) Stephan SCHUSTER (ESA) Kathe DANNEMEYER (ESA) George SCHMIDT, NASA, US E 00499 - Preliminary assessments for the 00375 - LUMEN Demonstrator – Project Overview 00312 - A survey on energetic ionic liquid green 00089 - Development of cold gas propulsion 00017 - Using of Iodine as Propellant in Electric 00307 - Performance characteristics and efficiency X development of a green storable bipropellant propellants and investigation of feed and system for a Portuguese EO & maritime Thrusters analysis of a microwave cathode - 200 W Hall rocket engine based on H2O2 Jan Deeken pressurization systems for small satellites high- surveillance satellite thruster system H thrust impulsive propulsion Konstantinos Katsonis Stefania Carlotti DLR - German Aerospace Center - DE Filipa Lourenço Takato Morishita I 11:00 1 Ahmed Nosseir DEDALOS Ltd - GR KEYNOTE SPEECH #3 : B Politecnico di Milano - IT Omnidea - PT The University of Tokyo - JP TU DELFT x University of Pisa - IT I Lunar ISRU propellant production for T in-situ refueling: Operational 00363 - Overview of the development of a H2O2 00345 - LUMEN – Status of the 00532 - Ground and flight tests of ALSAT 1B 00257 - Direct Thrust Measurements of an Iodine 00171 - Effects of bias potential inside the water 00297 - Radial particle-in-cell simulations of a Hall challenges and implications for space I based chemical attitude control system for VEGA- Development and Testing electrothermal butane propulsion system Cold Gas Propulsion System ion thruster on thrust performance Thruster discharge with different anomalous propulsion C transport models O Tobias Traudt Djamal Darfilal Elena Zorzoli Rossi Yasuho Ataka N Bastien Haemmerli Alberto Marĺn-Cebrĺan Laurent SIBILLE, NASA, USA 11:20 2 DLR - German Aerospace Center - DE Satellites Development Center - DZ ThrustMe - FR University of Tokyo - JP Nammo Raufoss AS - NO Universidad Carlos III de Madrid - UC3M - ES a n

00373 - Hydrogen Peroxide RCS on a sounding 00292 - LUMEN Thrust Chamber - Injector 00381 - Development of Hydrogen Peroxide based 00455 - Proba-2 Cool Gas Generator Experiment: 00061 - The investigation of alternative solid 00090 - Design and preliminary study of a 200W 00016 - Spacecraft Propulsion with ISRU near Mars d rocket - a milestone towards launch vehicles and Performance and Stability Monopropellant Thruster 10 years in orbit, experiences and lessons learned propellants in Hall Effect Thrusters Cylindrical Hall Thruster and Venus, Based on CO2 Propellant satellite platforms applications. Justin Hardi Narender Kumar Berry Sanders Vlad-George Tirila Tatiana Perrotin Chloe Berenguer N Tomasz Noga 11:40 3 DLR - German Aerospace Center - DE Liquid Propulsion Systems Centre - ISRO - IN HDES Service & Engineering BV - NL University of Southampton - UK Universidad Carlos III de Madrid - UC3M - ES DEDALOS Ltd - GR E Łukasiewicz Research Network - Institute of T Aviation - PL W O 00485 - Design of a Hovering Sonding Rocket Stage 00048 - LUMEN Thrust Chamber - flame anchoring 00413 - Development of Catalyst for HAN based 00087 - (X)MET: DESIGN AND TEST OF 00054 - Research on Multiphase Flow and 00056 - Development Status of the ST-40 Hall 00018 - Evaluation of Earth Atmosphere Remnants for Measurements in the High Atmosphere for shear coaxial injectors Monopropellant Thruster MICROWAVE ELECTROTHERMAL THRUSTERS Catalytic-Combustion Reaction of Microthruster Thruster Used as Propellant in Electric Thruster Technology R WITH ARGON and XENON with ADN-Based Monopropellant K Karl Wieland Naumann Michael Börner Savitry Kumari Danill Shcherbak Chloe Berenguer Thomas Baxter Xuhui Liu 12:00 4 I Bayern-Chemie GmbH - DE DLR - German Aerospace Center - DE Liquid Propulsion Systems Centre - ISRO - IN Space Electric Thruster Systems - UA DEDALOS Ltd - GR AVS - Added Value Solutions UK - UK Beijing Institute of Control Engineering - JP N G

00233 - Controlling Low Frequency Instability in 00068 - LUMEN – Design of the Regenerative 00426 - Influence of hot-firing tests on the 00020 - Innovative Xenon/Krypton FMS (Feed 00118 - Alternative Propellants for Gridded Ion 00195 - About Development Feasibility of a High 00364 - Oxygen and propellant production on Hybrid Rocket Combustion Cooling System for an Expander Bleed Cycle characteristics and activity of a catalyst for the Management System) for Electric Propulsion, from Engines: Performance Analysis of different types Thruster with Closed Electron Mars by non-equilibrium plasmas Engine using Methane hydrogen peroxide decomposition R&D to serial production. of thrusters Drift Jina Kim Vasco Guerra Jan Haemisch Santiago Casu Pierre Cordesse Nazareno Fazio Alexander Solodukhin 12:20 5 Konkuk University - KR Universidade de Lisboa - PT DLR - German Aerospace Center - DE Heraeus Deutschland GmbH & Co. KG - DE Air Liquide - FR University of Southampton - UK SSC Keldysh Research Centre - RU

12:40 LUNCH BREAK SP 2020+1, Preliminary Program DAY 3 Page 8

KEYNOTE SPEECH #3: Can Space Propulsion Reusability turn dreams in reality ? 14:00 - A space launcher designer point of view - Jean Philippe DUTHEIL, ArianeGroup, FR - From reusability to space plane daily flights" - Marc VALES, Dassault Aviation, FR

PARALLEL SESSIONS Room 1 Room 2 Room 3 Room 4 Room 5 Room 6 Room 7 SESSION 43 - ST SESSION 44 - ST SESSION 45 - SC SESSION 46 - SC SESSION 47 - SC SESSION 48 - SC SESSION 49 - SC

Green & Hybrid Propulsion 2 Propellant behavior Green Propulsion 2 Mission Analysis and Flight Experience Propellants 2 Electric Propulsion 7 ISRU 2

CHAIR 1 Jérôme ANTHOINE, ONERA, FR Gilles VIGIER ,3AF,FR Kenichi KIMOTO, IHI, JP Stephan SCHUSTER (ESA) Sébastien BIANCHI, Air Liquide, FR Niccola KUTUFA (ESA) Nathalie GIRARD (CNES)

CHAIR 2 Dirk GREUEL (ESA) Ferran VALENCIA (ESA) M. PEUKERT, OHB, DE Yann TALAMONI, ArianeGroup, FR Carlos MUNOZ (ESA) Birk WOLLENHAUPT, OHB, DE George SCHMIDT, NASA, US 00524 - Green Propellants for In-Space Propulsion: 00250 - Experimental study on visualization of gas- 00280 - Ignition investigations of a novel 00444 - Overview of an optimised thrust balance 00191 - Performance analysis of alternative 00264 - Experimental characterisation of the novel 00384 - A Detailed Global Model of Hydrogen in E Experimental and Modelling Study on the liquid two-phase flow with self-pressurization for hypergolic ionic liquid with hydrogen peroxide in used for accurate measurements during propellants for a helicon plasma thruster Halo plasma thruster for small satellite Support of Neptune Study Combustion Chemistry of Ethane/Ethene-Nitrous rocket propellants drop tests qualification endurance testing of an electrical applications X Oxide Mixtures thruster Jiewei Zhou Konstantinos Katsonis H Kazuki Yasuda Felix Lauck Silvia Masillo 14:40 1 Sandra Richter Pierre Moutet Universidad Carlos III de Madrid - UC3M - ES DEDALOS Ltd - GR I Muroran Institute Of Technology - JP DLR - German Aerospace Center - DE Surrey Space Centre (SSC) - UK DLR - German Aerospace Center - DE DACTEM Développement - FR B I

00376 - Dynamic model for Hydrogen Peroxide 00190 - Studies on Thermodynamic Vent System 00379 - 100 mN Green Monopropellant Thruster 00397 - EP plasma plume in-Orbit experiments 00002 - New possibilities on creating apogee 00266 - Hall Thruster ST--25 developed by Space 00494 - ISRU produced hydrogen peroxide as T monopropellant thruster for Cryogenic Propellant Storage Tank. Development propulsion systems with electropump propellant Electric Thruster Systems (SETS) multipurpose fuel for spacecraft propulsion, fuel I (Verification Test for Jet Mixing with Self Jens Laube supply systems cells, and life support systems. Sukmin Choi Pressurization) Tomas Hasanof Dmitro Voronovskiy O OHB System AG - DE Andrey Kukhta Onno Verberne 15:00 2 KAIST - KR Ryoji Imai Plasma Processes LLC - US Space Electric Thruster Systems - UA N Yuzhnoye State Design Office - UA Nammo Raufoss AS - NO Muroran Institute Of Technology - JP a n 00058 - Development of Hybrid-Hybrid Rocket 00579 - Optimizing by numerical simulation the 00441 - Optimization of the catalytic bed in a 00338 - Plasma Jet Pack (PJP) Technology in-flight 00132 - Investigation of Silver Nanoparticles as 00133 - Advances on low-dimensionality fluid 00386 - Mars Ascent Vehicle Propulsion System Propulsion Technology and Its Prospect in Space Anti-Vortex Device for swirling flow reduction decomposition chamber for H2O2/liquid results Novel Catalysts for Hypergolic Hydrocarbon modeling of Hall thruster discharges Design By Using CO2 As An In-Situ Oxidizer d Exploration during the drainage of a cryogenic liquid in a tank bipropellant thruster Propellants with Hydrogen Peroxide Compound Luc Herrero Enrique Bello-Benítez Jong-Shinn Wu Alexandru-Claudiu Cancescu Hugo Quintens Sophie Ricker Ozan Kara 15:20 3 N COMAT - FR Universidad Carlos III de Madrid - UC3M - ES National Chiao Tung University - TW Romanian Research and Development Institute for CNES - FR DLR - German Aerospace Center - DE KOC University - TR E Gas Turbines - COMOTI - RO T W 00029 - Investigation of novel metallized 00527 - Effects of compounds in liquefied 00473 - ECAPS HPGP 1N Thruster Development 00005 - Long-Duration Wear Test & Status Update 00119 - Performance and Behaviour of 00302 - Electron parameters and ion current #N/A O monopropellants methane on rocket engine operation and Implementation – State of the Art and for the Ascendant Sub-kW Transcelestial Electric Unconventional Molecular Propellants in a measurements in the plasma plume of a high Heritage Propulsion System (ASTRAEUS) Cylindrical Hall Thruster power dual-mode Hall thruster R Maxim Kurilov Elke Goos Wilhelm Dingertz Ryan Conversano Rachel Moloney Stéphane Mazouffre K 15:40 4 DLR - German Aerospace Center - DE DLR - German Aerospace Center - DE I Bradford Ecaps - SE JPL - US University of Surrey - UK CNRS - FR N G 00530 - Status of Gel Propulsion in the Year 2020 #N/A 00067 - ICE: A Modular Water Electrolysis 00448 - MARS-/EUROPA-INPPS Flagship Missions: 00025 - Development of Iodine Propellant and 00483 - AIRBUS DS Power Processing Units New #N/A with a Special View on the German Activities Propulsion System High and Low Power Electric Thrusters, Flow Control Units Suitable for Multiple developments for HET & GIT and technologies Orbits/Payloads and Co-Flying Satellites Propulsion Systems status Christoph Kirchberger Alberto Garbayo Frank Jansen Javier Martínez Fernando Javier Pintó Marín 16:00 5 DLR - German Aerospace Center - DE AVS - Added Value Solutions UK - UK DLR - German Aerospace Center - DE ThrustMe - FR Airbus DS - ES

16:20 COFFEE BREAK SP 2020+1, Preliminary Program DAY 3 Page 9

Room 1 Room 2 Room 3 Room 4 Room 5 SESSION 50 - ST SESSION 51 - ST SESSION 52 - SC SESSION 53 - SC SESSION 54 - SC

Manufacturing & Process Modeling Thrust chamber Green Propulsion 3 Electric Propulsion 8 Cathodes

CHAIR 1 Pedro HERRAIZ (ESA) Gérard ORDONNEAU, ONERA, FR Wilhelm DINGERTZ, Bradford Ecaps Olivier DUCHEMIN, SAFRAN SEP M. COLETTI, Thales Alenia Space, UK

CHAIR 2 Marc VALES, Dassault Aviation, FR Lilian PREVOST, (CNES), FR Lorenzo BISI, OHB, SE Dennis ESTUBLIER (ESA) Birk WOLLENHAUPT, OHB, DE E 00099 - Development of an ALM Thrust Chamber 00240 - Investigation of Liquid Cooling Films for 00094 - Experimental testing of small H2/O2 00100 - Development update of the X-EPT 00131 - Investigation of C12A7 electride as a X for VEGA-E M10 Rocket Engine storable propellant rocket engines thrusters in atmospheric and vacuum conditions Microwave Gridded Ion Thruster for the IMPULSE thermionic neutralizer Propulsion Architecture H Daniele Liuzzi Sebastian Soller Razvan Nicoara Nils Gerrit Kottke I Sam Reeve 16:40 1 AVIO SpA - IT ArianeGroup - DE Romanian Research and Development Institute for Airbus - DE B Gas Turbines - COMOTI - RO AVS - Added Value Solutions UK - UK I T

00219 - Additive manufacture of rocket engine 00259 - Machine Learning Methods for Design and 00064 - Electrolysis Based Water Propulsion for 00421 - HIPATIA: a project for the development of 00153 - Endurance Test of a Heaterless Hollow I combustion chambers from CuCrZr (C-18150) Operation of Liquid Propellant Rocket Engines Future 1-Ton Class LEO Mission Satellites the Helicon Plasma Thruster and its associated Cathode using the Emitter Material C12A7 O using the DMLS process technologies to intermediate-high TRLs Electride Guenther Waxenegger-Wilfing Nuno Fernandes N Iain Waugh Mercedes Ruiz Christian Drobny 17:00 2 DLR - German Aerospace Center - DE Omnidea-RTG GmbH - DE Airborne Engineering - UK SENER Aeroespacial - ES Technische Universität Dresden - DE a n d 00220 - Additive manufacture of rocket engine 00362 - Development of a film-cooled thrust 00243 - Conceptual design of dual plates 00295 - Power Processing Unit Activities at Thales 00334 - Helical Plume Instabilities in a 25A LaB6 combustion chambers using the ABD®-900AM chamber component in the ESPSS library throttleable injector for monopropellant thruster: Alenia Space in Hollow Cathode Nickel superalloy a cold flow study Pierluigi Concio Eric Bourguignon Giulia Becatti N Iain Waugh Yehyun Kim 17:20 3 E Sapienza University of Rome - IT Thales Alenia Space in Belgium - BE University of Pisa - IT Airborne Engineering - UK Korea Advanced Institute of Science and T Technology - KR W O 00165 - Selective laser manufactured cooper alloy 00519 - Injector wall heat transfer quantification 00299 - Optical Investigation on the Hypergolic 00158 - XJET: Design upgrade and preliminary 00392 - 2 dimensional modelling of heaterless nozzle for sub-scale thrust chambers in supercritical nitrogen injection Reaction Between Green Liquid Ionics and Highly characterization for an electrodeless ECR thruster hollow cathodes R Concentrated Hydrogen Peroxide K Dmitry Suslov Leandro Barbosa Magalhães Emmanuelle Rosati Azevedo Stephen Gabriel Robert Stützer I 17:40 4 DLR - German Aerospace Center - DE University of Beira Interior - PT AVS - Added Value Solutions UK - UK University of Southampton - UK DLR - German Aerospace Center - DE N G

KEYNOTE SPEECH #4: Conclusions of the Space Propulsion Conference, 7th Edition 18:00 H. CIEZKI, DLR, A. GARBAYO, AVS UK

18:30 END OF CONFERENCE