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 12:40 LUNCH BREAK SP 2020+1, Preliminary Program DAY 1 Page 2 KEYNOTE SPEECH #1: Space democratization 14h00 Angelo FONTANA , AVIO 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/Methane 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 rocket Engine 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 Vega-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 liquid oxygen 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 16:20 COFFEE BREAK SP 2020+1, Preliminary Program DAY 1 Page 3 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