Papers: Space
| Year | Title | Authors | Summary |
|---|---|---|---|
| 2024 | Test and validation of pressure fed rocket engine test stands feedline systems. ESPSS Glasgow 2024 | U. Kayabasi(1), M.C. Kose (1), U. Poyraz(1) (1) Roketsan Inc., Ankara, Turkey | This work targets the safe and repeatable operation of pressure-fed rocket engine test stands by accurately predicting transients and pressure oscillations in the feedline. The team builds a detailed 1D model of the pressurisation system and feed circuits in EcosimPro/THRUST, correlating it against test data to tune losses, valve behaviour and sensor dynamics. Using EcosimPro makes it possible to explore critical scenarios virtually, reduce hardware iterations and de-risk test campaigns while optimising the layout for cost and reliability. |
| 2024 | Design, test and validation of cavitating venturi element using in LPRE. ESPSS Glasgow 2024 | M.C. Kose(1), U. Kayabasi(1), U. Poyraz(1) (1) Roketsan Inc., Ankara, Turkey | The activity focuses on designing a cavitating venturi for liquid-propellant rocket engines to provide robust flow control and damping of feed system instabilities. A virtual prototype of the venturi and surrounding plumbing is developed in EcosimPro/THRUST, allowing engineers to predict cavitation onset, pressure drops and dynamic response before committing to hardware. EcosimPro supports rapid sensitivity studies on geometry and operating conditions, shortening the design loop and leading to a venturi design that meets performance and stability targets with fewer tests. |
| 2024 | Fluidic testing of an in-orbit monopropellant refuelling system. ESPSS Glasgow 2024 | Isheeta Ranade (1), James Magson (1), Richard Tait (1), Avichai Elimelech(1), Mark Pollard(1), Ray Riley-Davis(1), Lahib Balika(1), Andrew Davies (2) (1) Thales Alenia Space UK, Harwell, United Kingdom (2) Astroscale UK, Harwell, United Kingdom | The goal of this activity is to demonstrate and de-risk a hydrazine monopropellant refuelling concept for the COSMIC active-debris-removal spacecraft using a visiting tanker. A representative fluidic breadboard with water as hydrazine simulant is built to characterise priming, water-hammer events and propellant transfer over a wide range of conditions. EcosimPro with the ESPSS toolkit is used to create and calibrate numerical models that reproduce both steady-state and transient pressure and flow behaviour seen in the tests, turning them into validated digital twins. This gives mission designers a powerful way to define safe operating envelopes, optimise procedures and support future in-orbit refuelling missions with significantly reduced technical risk. |
| 2024 | Towards interplanetary journeys : Modelling of a nep system with ECOSIMPRO. ESPSS Glasgow 2024 | E. Bragalli (1), B. Zitouni (2), M. Peukert (3) (1) OHB, Bremen, Germany | This paper targets the preliminary design and performance assessment of a Nuclear Electric Propulsion (NEP) system for deep-space missions based on a Rankine-cycle thermal power conversion architecture. Using EcosimPro, OHB engineers build an integrated NEP model that combines reactor, thermal conversion loop, turboalternator, power management and electric thrusters, extending existing ESPSS libraries with tailored components. The model is run on representative mission scenarios and compared with Solar Electric Propulsion options to analyse mass, power and transfer-time trade-offs. For customers, EcosimPro enables these complex NEP architectures to be explored in a single environment, rapidly testing design options and control strategies long before hardware exists. |
| 2024 | Modeling postcritical two-phase heat transfer in EcosimPro/ESPSS environment. ESPSS Glasgow 2024 | Matteo Fiore(1), Marco Fabiani(1), Francesco Nasuti(1) (1) Sapienza University of Rome, Rome, Italy | This activity targets more accurate prediction of coolant wall temperatures and Critical Heat Flux location in liquid rocket engine regenerative cooling channels using cryogenic fluids. New flow-boiling heat transfer correlations and a regime-switching criterion are implemented directly in the EcosimPro/ESPSS environment and validated against hydrogen and nitrogen test data. By embedding these models in EcosimPro, engineers can run efficient system-level simulations that capture post-critical two-phase behaviour much better than before, providing a more reliable digital tool to size cooling channels, assess safety margins and optimise engine designs with fewer costly hardware changes. |
| 2024 | Updating the pump and injector plate components of the ESPSS library in view of transient analysis of LOx/Methane engines. ESPSS Glasgow 2024 | Marco Fabiani(1), Beatrice Latini(1), Francesco Nasuti(1), Chiara Boffa(2), Mikhail Rudnykh(2), María Aranda Rosalez(3), Csaba Jeger(4) (1) Sapienza University of Rome, Rome, Italy (2) AVIO S.p.A., Colleferro, Italy (3) Empresarios Agrupados Internacional S.A., Madrid, Spain (4) ESTEC - European Space Agency, Noordwijk, The Netherlands | This work improves modelling of turbopumps and injector plates for LOX/LCH4 engines, with a special focus on transient phases such as start-up, chilldown and shutdown. Within EcosimPro/ESPSS, the injector pressure-loss model is refined to include geometry and swirl effects, and an enhanced thermal layout is introduced to predict injector-plate temperatures more realistically, while the pump component gains additional fluid and thermal paths for more faithful dynamic response. Using these upgraded components inside EcosimPro lets propulsion engineers explore architectures and operating sequences faster and more flexibly, reducing test iterations and increasing confidence in early design decisions. |
| 2024 | Development testing and analysis of the integrated gateway-esprit bipropellant refuelling system. ESPSS Glasgow 2024 | Andrew Hughes (1), Kiran Pazhayattinkal (1), Isheeta Ranade (1), Abhijit Pandit (1), William Harper (1), Alex Millington-Cotes (1), Avichai Elimelech (1), Lahib Balika(1), Olivier Zagoni (2), Alexandra Bulit (3), Adela Han (4), Brian Lusby (4), Pooja Desai (4), Chris Radke (4) (1) Thales Alenia Space UK, Harwell, United Kingdom (2) Thales Alenia Space France, Cannes, France (3) ESA-ESTEC, Noordwijk, Netherlands (4) NASA - Johnson Space Centre, Houston, USA | This work supports the Lunar Gateway’s ESPRIT module by developing and testing a complex bipropellant refuelling architecture for chemical propellants. A high-fidelity EcosimPro/ESPSS model of the complete fuelling chain is built and correlated with breadboard test campaigns to capture steady and transient behaviour, including priming and water hammer. EcosimPro becomes the central design and verification tool, allowing ESA, NASA and Thales to iterate safely on operating procedures and hardware configuration without costly additional hardware trials. |
| 2024 | Multifunctional upper stage express propulsion system concepts and technologies. ESPSS Glasgow 2024 | Christian Hessel (1) , Sylvain Goek (1), Armin Isselhorst(1), Jörg Klatte (1), Nora Volling (1), Bart van Zegbroeck (1) | Explores concepts for a highly flexible upper-stage “Express” propulsion system, including tank architectures, insulation and operations. The concepts are intended to be analysed further with simulation tools such as EcosimPro/ESPSS, using the paper’s results as a basis for detailed thermofluid modelling. |
| 2022 | Analysis and verification of in-orbit fuelling system during development and breadboard testing. Space Propulsion 2022 | A. Elimelech(1), P. Fleith(1), E. Tavani(1), R. Davis(1), S. Aziz(2), S. Hill(1), D. Shah(1), M. Pollard(1), M. Coletti(1). (1) Thales Alenia Space in the UK, Fermi Avenue, Harwell Oxford. (2) European Space Agency, ESA, ESTEC, Noordwijk, Netherlands. | This activity supports the design of the Hydrazine Transfer System for ESA’s ESPRIT module on the Lunar Gateway, ensuring safe in-orbit fuelling between ESPRIT, the Power and Propulsion Element and visiting tankers. Thales Alenia Space develops a detailed EcosimPro/ESPSS model of the complete refuelling architecture and then builds a water-based breadboard to reproduce priming, refuelling and refilling operations on the ground. By correlating simulation and test data, EcosimPro is shown to predict pressure peaks, pressure evolution and mass-flow trends across the system with conservative behaviour for critical transients. This validated digital twin helps engineers size orifices, confirm safety margins and tune operating procedures, cutting development risk and cost while preparing for future in-orbit servicing campaigns. |
| 2022 | Liquid upper stage demonstrator engine (lumen): component test results and project progress. Space Propulsion 2022 | Tobias Traudt(1), Michael Börner(1), Dmitry Suslov(1), Robson dos Santos Hahn(1), Anirudh Mukund Saraf(1), Sebastian Klein(1), Jan Deeken(1), Justin Hardi(1), Michael Oschwald(1), Stefan Schlechtriem(1). (1) Institute of Space Propulsion, German Aerospace Center (DLR), Hardthausen, Germany. | This paper reports on component testing for DLR’s LOx/LNG LUMEN upper-stage demonstrator and the associated system engineering. Transient engine behaviour and control strategies are analysed with EcosimPro/ESPSS, which links detailed component models with the overall engine cycle. Using EcosimPro enables rapid iteration on operating sequences and pressurisation concepts, supporting risk reduction and performance optimisation for future reusable upper stages. |
| 2022 | Functional and thermal 1d modeling of a reusable lh2-tank using EcosimPro/ESPSS and comparison to cfd results.. Space Propulsion 2022 | Lukas Opp, Henning Scheufler, Malte Stief, Jens Gerstmann. German Aerospace Center (DLR), Bremen, Germany. | The target is to design a reusable liquid-hydrogen tank with controlled boil-off by capturing its thermal and fluid behaviour throughout a mission. A detailed 1D EcosimPro/ESPSS model of the tank, pressurisation and heat paths is developed and benchmarked against high-fidelity CFD simulations. EcosimPro provides a fast system-level tool that matches the CFD trends, allowing engineers to perform many operational trade-offs and sizing studies that would be impractical with CFD alone. |
| 2022 | A validation of a high-pressure xenon cold gas thruster simulation under EcosimPro ESPSS.. Space Propulsion 2022 | Christophe KOPPEL(1), Maria ARANDA-ROSALES(2). (1) KopooS Consulting ind., Dolmayrac, France. (2) Empresarios Agrupados Internacional, Madrid, Spain. | This work aims to accurately predict the performance of a high-pressure xenon cold-gas attitude thruster. The authors build a detailed EcosimPro/ESPSS model of the feed system and nozzle, then validate thrust, mass flow and transient response against test data. With a validated EcosimPro model, mission and system engineers can size tanks, valves and operational scenarios more confidently, avoiding over-design and reducing qualification effort. |
| 2022 | Development of a test infrastructure for a neural network controlled green propellant thruster.. Space Propulsion 2022 | Till Hörger(1), Kai Dresia(1), Günther Waxenegger-Wilfing(1), Lukas Werling(1), Stefan Schlechtriem(1). (1) Institute of Space Propulsion, German Aerospace Center (DLR), Hardthausen, Germany. | The activity develops a test infrastructure for a green-propellant thruster controlled by neural-network algorithms. EcosimPro/ESPSS models of the thruster, feed system and test bench are used to design the facility, pre-tune control laws and interpret measured data. Using EcosimPro reduces commissioning risk, ensures safe operation windows are respected and provides a virtual environment to train and validate AI controllers before firing hardware. |
| 2022 | Ai-assisted control systems for rocket engine test facilities within the ESA flame program.. Space Propulsion 2022 | Kai Dresia(1), Eldin Kurudzija(1), Günther Waxenegger-Wilfing(1,2), Hendrik Behler(1), Daniel Auer(1), Karsten Fröhlke(1), Heike Neumann(1), Anja Frank(1), Jérôme Laurent(3) and Luce Fabreguettes(3). (1) German Aerospace Center (DLR), Institute of Space Propulsion, 74239 Lampoldshausen, Germany. (2) University of Würzburg, Institute of Computer Science, 97074 Würzburg, Germany. (3) European Space Agency (ESA), Paris, France. | This paper targets smarter, more automated control of rocket engine test facilities using artificial intelligence. Digital twins of the test stands are created in EcosimPro/ESPSS and coupled with AI algorithms for sequence generation, fault detection and anomaly monitoring. The combination of EcosimPro models and AI reduces test preparation time, supports safer operations and points the way toward more flexible and cost-effective test infrastructure. |
| 2022 | Simulation of the complete electric propulsion system associated to het on ESPSS/EcosimPro.. Space Propulsion 2022 | Jorge Ruiz-Torralba(1)(2), José Moral(2), F. Rodríguez(2), M. Aranda(2), J. Steelant(3), V. Fernández(3), M. Leonardi(4), F. Di Matteo(4). (1) OHB System AG, Universitätsallee 27-29, 28359 Bremen. (2) Empresarios Agrupados Internacional. S.A., Magallanes 1, 28015 Madrid, Spain. (3) ESA-ESTEC, Section of Flight Vehicles and Aerothermodynamics, Keplerlaan 1, 2200 AG Noordwijk, The Netherlands. (4) ESA-ESRIN, Section of VEGA & Space Rider Mechanical and Propulsion Engineering, Largo Galileo Gali lei 1, 00024 Frascati, Italy. | Uses EcosimPro/ESPSS together with power-system libraries to model an entire electric propulsion chain: PPU, thruster, xenon feed and spacecraft interfaces. The simulations support design and verification by allowing system-level performance assessment, fault studies and optimisation of operating modes. |
| 2022 | Low-order modelling and validation of film cooling in liquid rocket combustion chambers.. Space Propulsion 2022 | Pierluigi Concio (1), Simone D’Alessandro (1), Maria Aranda-Rosales(2), Daniele Bianchi(1), Francesco Nasuti (1), Johan Steelant(3). (1) Sapienza University of Rome, Via Eudossiana 18, 00184 Italy. (2) Empresarios Agrupados Internacional, Madrid, Spain. (3) ESTEC-ESA, Noordwijk, Netherlands. | This activity provides engineering-level models of liquid and gaseous film cooling for rocket thrust chambers. New low-order film-cooling correlations are implemented in EcosimPro/ESPSS and verified against experiments and dedicated CFD analyses. Embedding these models into EcosimPro lets designers evaluate film-cooling options directly within full engine simulations, improving thermal margin prediction and shortening the design loop for high-performance engines. |
| 2022 | Development and validation of nozzle erosion models for solid and hybrid rockets in the ESPSS libraries.. Space Propulsion 2022 | Marco Rotondi(1), Pierluigi Concio(1), Simone D’Alessandro(1), Fernando R. Lucas(2),Daniele Bianchi(1), Francesco Nasuti(1), Johan Steelant(3). (1) Department of Mechanical and Aerospace Engineering, Sapienza University of Rome, Rome, Italy. (2) Empresarios Agrupados Internacional, Madrid, Spain. (3) Flight Vehicles and Aerothermodynamics Engineering, ESTEC-ESA, Noordwijk, Netherlands. | The paper targets reliable prediction of nozzle erosion in solid and hybrid rocket motors. Several reduced ablation models are selected, implemented and validated inside EcosimPro/ESPSS using CFD results and experimental data. Thanks to these new components, users of ESPSS can study performance drift and lifetime issues due to erosion directly within their system models, improving design robustness and reducing the need for conservative margins. |
| 2022 | The astris kickstage propulsion system development status & outlook.. Space Propulsion 2022 | Dietmar Welberg(1), Benedikt Determann(1), Christian Hessel(1), Torben Birck(2), Tina Büchner da Costa(3). (1) ArianeGroup GmbH, Bremen, Germany. (2) ArianeGroup GmbH, Ottobrunn, Germany. (3) ESA Space Transportation, Paris, France. | This contribution presents the architecture and development status of the Ariane 6 Astris kickstage propulsion system. EcosimPro/ESPSS is used to model propellant management, pressurisation and engine operation to support design trade-offs and mission analysis. Using EcosimPro enables ArianeGroup to explore a wide range of mission profiles and system options virtually, helping to maximise performance and flexibility while keeping development risk under control. |
| 2022 | Scaling performance analyses within bi-propellant systems using ESPSS. Space Propulsion 2022 | Jorge Ruiz-Torralba, Bayrem Zitouni, Markus Peukert, Ingolf Fischer. OHB System AG, Universitätsallee 27-29, 28359 Bremen. | The activity aims to define scaling rules for MON/MMH bi-propellant systems so that different thrust levels and clusters can be derived efficiently from a reference design. The authors implement and apply these scaling methodologies using EcosimPro/ESPSS, exploiting its flexible component models to rapidly generate consistent system variants. EcosimPro makes it straightforward to extend the rules to alternative, greener propellants and to evaluate performance and thermal behavior without starting from scratch for each configuration. |
| 2022 | Water electrolysis propulsion in cubesats: a case study.. Space Propulsion 2022 | Sascha Dengler(1), Felix Ebert(1), Chiara Manfletti(1), Sebastian Leichtfuß(2) (1) Technical University of Munich, Munich, Germany. (2) Technical University of Darmstadt, Darmstadt, Germany. | This paper evaluates a water-electrolysis propulsion concept for a 3U CubeSat used as a de-orbiting and attitude-control kit. A parametrised propulsion system model is built and simulated, with EcosimPro/ESPSS providing detailed thermo-fluid behaviour for tanks, pipes and thrusters while optimisation routines search for mass-efficient operating points. Using EcosimPro allows the team to capture the complexity of on-orbit propellant generation and blow-down while still running fast design trade-offs, demonstrating the feasibility and benefits of this green technology. |
| 2021 | Nonlinear Control of an Expander-Bleed Rocket Engine using Reinforcement Learning. Space Propulsion 2020+1 | Kai Dresia(1), Günther Waxenegger-Wilfing(1), Robson dos Santos Hahn(1), Jan Deeken(1) and Michael Oschwald(1,2) (1) German Aerospace Center (DLR), Institute of Space Propulsion, Germany (2) RWTH Aachen University, Institute of Jet Propulsion and Turbomachinery, Germany | The target is to develop an intelligent controller for the LUMEN expander-bleed engine based on reinforcement learning. The neural-network controller interacts with a high-fidelity EcosimPro/ESPSS engine model, learning how to adjust valves to track chamber-pressure set-points while respecting constraints. EcosimPro provides a safe, accurate training environment and later serves as a virtual testbed, reducing development risk before applying the controller to hardware. |
| 2021 | Overview of the development of a H2O2 based chemical attitude control system for Vega-C. Space Propulsion 2020+1 | B. Haemmerli(1), D. Digre(1), T. Jøraholmen(1), R. Lillekvelland(1), H. Solerød(1),T. Valle(1),J. White(2),E. Mcguiness(2), B. Larkin(2), L. Torre(3), G. Filomeno(3), F. Di Matteo(4). (1) Nammo Raufoss AS, Norway. (2) Nammo Ireland Limited, Ireland. (3) Avio – Colleferro, Italy. (4) ESA-ESRIN – Frascati, Italy. | This work describes the design of a green hydrogen-peroxide attitude control system for Vega-C upper stages. EcosimPro/ESPSS models of tanks, feed lines and thrusters are used to assess architectures, dimension components and analyse mission duty cycles. With EcosimPro, Nammo and partners can iterate on system design and operating strategies quickly, ensuring performance and safety while replacing hydrazine with a more sustainable solution. |
| 2021 | Development of a film-cooled thrust chamber component in the ESPSS library. Space Propulsion 2020+1 | Pierluigi Concio, Simone D’Alessandro, Francesco Nasuti. Sapienza University of Rome, Italy. | The activity develops a reusable ESPSS component for film-cooled liquid rocket thrust chambers. Detailed modelling of liquid and gaseous films is integrated into EcosimPro/ESPSS and tuned with experimental and numerical data. This new component lets engine designers study film-cooling strategies directly within full-system simulations in EcosimPro, improving prediction of wall heat fluxes and enabling more aggressive yet safe chamber designs. |
| 2021 | Validation of a xenon propulsion system simulation model with 5-KW class Hall-effect thruster coupled tests. Space Propulsion 2020+1 | Patrick Fleith (1), Andrea Leporini (1), Romain Fafet (2) Michele Coletti (1) (1) Thales Alenia Space UK. (2) Thales Alenia Space France. | This paper compares the coupled test results of a 5 kW-class Hall-Effect Thruster (HET) to the simulation results of a complete Xenon Propulsion System (XPS) model. The simulator has been set up in EcosimPro software. It includes detailed component models of the fluidic lines, a pressure regulation assembly, a Power Processing Unit, a Flow Control Unit and a Hall-Effect Thruster |
| 2018 | Optimum Trim of an Experimental Hypersonic Glider. HiSST: International Conference on High-Speed Vehicle Science Technology 26–29 November 2018, Moscow, Russia | Victor F. Villace(1), Sergey A. Takovitskii(2). (1) European Space Agency (ESA), The Netherlands (2) Central Aerohydrodynamic Institute (TsAGI), Russian Federation | The goal is to compute optimum trim conditions for an experimental hypersonic glider across its trajectory, taking into account variations in centre of gravity and aerodynamics. A dedicated flight-mechanics library based on FLIGHT_SIM is used within EcosimPro to model the glider and optimise control settings along the path. EcosimPro’s optimisation and multidisciplinary capabilities allow ESA and TsAGI to evaluate many trim scenarios efficiently, improving mission robustness and glide performance. |
| 2018 | Hybrid propulsion for a moon sample return mission Space Propulsion 2018 Seville | C. Schmierer(1),(3), M. Kobald(1), J. Steelant(2), and S. Schlechtriem(1). (1) DLR, Institute of Space Propulsion, Germany. (2) ESA-ESTEC, The Netherlands. (3) Institute of Space Systems, University of Stuttgart, Germany | This activity analyses a Moon sample return mission using hybrid propulsion stages as an alternative to bi-liquid systems. Trajectory optimisation in ASTOS is coupled to detailed hybrid propulsion models in EcosimPro/ESPSS, enabling realistic predictions of performance, tank residuals and thermal behaviour. Using EcosimPro within this loop demonstrates that hybrid propulsion can meet mission needs while reducing toxicity and potentially lowering development costs. |
| 2018 | Experimental and Numerical Investigation of Cryogenic Two-Phase Flows and Application to Liquid Rocket Propulsion Systems Space Propulsion 2018 Seville | S. Soller(1), K. Claramunt(2), L. Peveroni(3), N. Pouvesle(4), S. Schmidt(5), J. Steelant(6) (1) Ariane Group, Germany. (2) Numeca, Belgium. (3) Von-Karman Institute for Fluid Dynamics, Belgium. (4) Energie-Technologie GmbH, Germany. (5) Technische Universität München, Germany. (6) ESTEC, The Netherlands. | The paper investigates cryogenic two-phase phenomena such as cavitation and chill-down in liquid rocket engines through a coordinated experimental and numerical campaign. Test data are used to benchmark engineering and CFD tools, with ESPSS/EcosimPro models playing a key role in representing system-level transients. The improved understanding and validated EcosimPro models enable more reliable prediction of start-up behavior and cooling performance, supporting safer and more efficient cryogenic engine designs. |
| 2018 | Helium passivation: calibration with in-orbit data Space Propulsion 2018 Seville | B. Zitouni, I. Fischer, M. Peukert. (1) OHB System AG, Bremen, Germany | This work aims to predict helium passivation behavior at end-of-life for satellites by combining flight data and simulation. An EcosimPro/ESPSS model of tanks, regulators, valves and vent lines is built and calibrated with telemetry, capturing thermal effects and mass-flow evolution. With this calibrated model, OHB can assess passivation strategies for future missions, demonstrating compliance with space debris regulations while minimising impact on mission design. |
| 2018 | Implementation of a two-phase pipe component inside the ESPSS library Space Propulsion 2018 Seville | F. Pinna(1), M. Leonardi(2), F. Nasuti(2), J. F. Moral(3), and J. Steelant(4). (1) Von-Karman Institute for Fluid Dynamics, Belgium. (2) Università di Roma La Sapienza, Italy. (3) Empresarios Agrupados, Spain. (4) European Space Agency, The Netherlands. | The activity develops a new two-phase pipe component for ESPSS to better capture liquid–vapour dynamics in propulsion feed lines. The model is formulated and implemented within EcosimPro/ESPSS and validated against reference cases to ensure robustness over a wide range of conditions. This enhancement allows users to simulate complex priming, flashing and water-hammer phenomena directly in EcosimPro, increasing fidelity for launcher and spacecraft propulsion analyses. |
| 2018 | Innovative xenon regulation for electric propulsion Space Propulsion 2018 Seville | Pascal Barbier (1), Yoann Fendler (1), François Martin(1), Eric Guilbaud(1), Simon Carpentier(1), Pascal Lasgorceix(2) and Claude Boniface(3). (1) Air Liquide Advanced Technologies, France. (2) CNRS – Centre National de la Recherche Scientifique, France. (3) CNES – French Space Agency, France. | Describes a compact, low-mass xenon regulation device that meters flow directly from the tank to electric thrusters. While the design is mainly hardware-oriented, its characterisation data are intended for inclusion in EcosimPro/ESPSS electric-propulsion models to simulate xenon feed behaviour accurately. |
| 2018 | An overview of the ESPSS libraries: latest developments and future Space Propulsion 2018 Seville | J. Vilá(1), J. Moral(1), V. Fernández-Villacé(2), J. Steelant(2) (1) Empresarios Agrupados Internacional. S.A., Madrid, Spain. (2) ESA-ESTEC, The Netherlands. | Provides a global overview of the ESPSS libraries implemented in EcosimPro, covering chemical, electric and cold-gas propulsion. The paper presents new components, recent validation efforts and planned extensions, positioning ESPSS/EcosimPro as ESA’s reference framework for propulsion simulation. |
| 2017 | Comparative Study of Ethanol and Kerosene Propellant for Gas-generator Fed Upper Stage Application, Using EcosimPro | Robson H. S. Hahn, Jan Deeken, Stefan Schlechtriem. German Aerospace Center (DLR), Institute of Space Propulsion, Germany. | Performs a cycle analysis of LOX/ethanol versus LOX/RP-1 gas-generator engines using EcosimPro for steady-state performance prediction. The study shows that, when cooling and gas properties are included, LOX/ethanol can reach performance comparable to RP-1, demonstrating EcosimPro’s value for trade-off studies between “green” and conventional propellants. |
| 2017 | Combined Trajectory Simulation and Optimization for Hybrid Rockets using ASTOS and ESPSS | Christian SCHMIERER (1)(2), Mario KOBALD (1), Johan STEELANT (3) and Stefan SCHLECHTRIEM (1)(2). (1) Institute of Space Propulsion, German Aerospace Center (DLR), Lampoldshausen, Germany. (2) Institute of Space Systems (IRS), University of Stuttgart, Germany. (3) European Space Research and Technology Centre (ESTEC), European Space Agency (ESA), Netherlands. | Couples the ASTOS trajectory optimizer with EcosimPro/ESPSS hybrid-rocket models to co-simulate propulsion and flight path. This integrated tool chain is used to optimise missions for launchers and spacecraft with hybrid engines, illustrating how ESPSS models support system-level design and performance trade-offs. |
| 2016 | Transient Simulation Capabilities for the ORION-ESM Propulsion System Development | Corinna von Graeve(1), Francesco Di Matteo(1), Nicola Ierardo(2). (1) ESA-ESTEC, Aerothermodynamics and Propulsion Analysis, Netherlands. (2) ESA-ESRIN LAU-DVL, Italy. | The NASA ORION Multi-Purpose Crew Vehicle (MPCV) is a pressurized, crewed spacecraft, designated to trans- port up to four crew members from Earth's surface to a destination beyond Low Earth Orbit. It provides for all services necessary to support the crew while on-board and ensures a safe return to Earth at the end of the mission. Based on an agreement between NASA and ESA, the ORION will thereby be supported by a European Service Module (ESM), which is based on ATV heritage and provides the following main resources. |
| 2016 | Comparison of Methods and Devices for High Pressure Vessel Passivation Space Propulsion 2016 Roma | B. Zitouni, L. Denies, M. Peukert. OHB System AG, Germany | Compares high-pressure system passivation options to reduce on-orbit fragmentation risk, including begin-of-life and end-of-life venting strategies. Models helium blow-down and thermal constraints, and contrasts propulsive and non-propulsive vent geometries using plume/impingement analysis for informed selection. |
| 2016 | Progress in Coupled Simulation Propulsion System and Vehicle with ESPSS SATELLITE Library Space Propulsion 2016 Roma | Christophe R. Koppel(1), Francesco Di Matteo(2), Johan Steelant(2), José Moral(3), Javier Vila Vacas(3). (1) KopooS Consulting Ind., France (2) ESA-ESTEC, The Netherlands (3) Empresarios Agrupados, Spain | Documents upgrades to the ESPSS Satellite library enabling coupled simulation of spacecraft dynamics, AOCS and propulsion system fluid behaviour. Introduces a compact Archimedes-pressure formulation for combined acceleration and rotation, improving prediction of tank/line conditions and inertia interactions. |
| 2016 | A Generic Thermodynamic Assessment of Reusable High-Speed Vehicles Space Propulsion 2016 Roma | V. Fernandez Villace, J. Steelant. ESA-ESTEC, The Netherlands | Performs a thermodynamic assessment of reusable high-speed/space-transport vehicles where cryogenic fuel is also used as a coolant for subsystems. The study defines generic modelling approaches that are implemented and further explored within EcosimPro/ESPSS for future high-speed concepts. |
| 2016 | Multiphase Fluid Hammer With Cryogenic Fluids Space Propulsion 2016 Roma | J.-B. Gouriet (1), A. Huertas-Martinez(1), J.-M. Buchlin (1), M.-R. Vetrano (1) and J. Steelant (2). (1) von Karman Insitute for Fluid Dynamics, Belgium (2) ESA-ESTEC, The Netherlands | Describes VKI experiments on multi-phase water/cryogen hammer and compares them to numerical predictions. The database is used to improve and validate ESPSS/EcosimPro fluid-hammer models for cryogenic lines in launchers and spacecraft. |
| 2016 | Improving combustion chamber and pipe components of the European Space Propulsion System Simulation(ESPSS) library with AUSM scheme Space Propulsion 2016 Roma | Marco Leonardi(1), Francesco Nasuti(1), Francesco Di Matteo(2), Johan Steelant(2), Jòse Francisco Moral(3), and Javier Vila Vacas(3). (1) University of Rome “La Sapienza”, Italy (2) ESA-ESTEC, The Netherlands (3) Empresarios Agrupados, Spain | Extends ESPSS/EcosimPro with AUSM-family numerical schemes for compressible flow in nozzles, injectors and lines. The new discretisations are validated on benchmark test cases, improving the accuracy and robustness of high-speed flow simulations in propulsion components. |
| 2016 | Modelling Chug Instabilities by Variable Time Lag Approach Space Propulsion 2016 Roma | Marco Leonardi (1), Francesco Di Matteo (2), Johan Steelant (2), Francesco Nasuti (1), and Marcello Onofri (1). (1) University of Rome “La Sapienza”, Italy (2) ESA-ESTEC, The Netherlands | Develops a linearised model of chug instabilities in liquid rocket engines and implements it in EcosimPro/ESPSS. The paper uses the model to generate stability maps as a function of feed-line and chamber parameters, giving designers a practical tool to avoid low-frequency instabilities. |
| 2016 | Overview of the Euclid Reaction Control System and Micro Propulsion Feed Assembly Space Propulsion 2016 Roma | R. Delanoë(1), R. Linde(1), M. Pessana(2), M. D’Ambrogio(2). (1) OHB Sweden, Stockholm, Sweden (2) Thales Alenia Space Italy, Torino, Italy | Describes Euclid’s monopropellant RCS and nitrogen micro-propulsion feed system, including architecture, requirements and key design choices. EcosimPro/ESPSS simulations of the micro-feed are used to analyse pressure transients and flow stability in the 1–1000 μN regime. |
| 2016 | An EcosimPro Model of a Power Processing Unit for a Low Power Hall Effect Thruster Space Propulsion 2016 Roma | A. Sollazzo(1), D. Ricci(2), P. Natale(3), F. Battista(3). (1) Environmental Acoustics & Pollutant Emissions Lab., Italian Aerospace Research Centre, Italy (2) Electric Propulsion Facility Lab., Italian Aerospace Research Centre, Italy (3) Space Propulsion Lab, Italian Aerospace Research Centre, Italy | Builds a detailed EcosimPro model of a PPU driving a low-power Hall-effect thruster. The simulation includes converters, control and interfaces with the propulsion system, enabling virtual testing of operating modes and supporting the design of robust, efficient PPU architectures. |
| 2016 | New Component Developments for Electric Propulsion Systems Space Propulsion 2016 Roma | Aurélien Moureaux. Air Liquide Advanced Technologies, France | Presents Air Liquide’s portfolio of tanks, valves and fluid-control equipment for space propulsion. The component data and operating envelopes described are intended to feed system-level simulations, including those built in EcosimPro/ESPSS for propulsion architectures using cryogenic or high-pressure gases. |
| 2016 | Solar Orbiter Purge System: Modelling with Ecosim Space Propulsion 2016 Roma | Massimo Marchionni. Airbus Defence and Space Ltd, United Kingdom | How does the solar system work?” the Solar Orbiter mission was proposed by the European Scientific Community and selected by ESA as first medium-class mission. Solar Orbiter is specifically designed to identify the origins and causes of the solar wind, the heliospheric magnetic field, the solar energetic particles, the transient interplanetary disturbances, and the Sun\'s magnetic field itself. The near-Sun part of the operational orbit will enable the spacecraft to approach the Sun as close as 0.28 AU during part of its orbit. |
| 2016 | Challenges on modelling fluid-dynamic problems of space propulsion systems Space Propulsion 2016 Roma | Jose Longo. Netherlands ESA, Technical Centre ESTEC | Reviews current and future needs in launcher propulsion modelling, from feed systems to full engines. The paper highlights how modular, object-oriented tools such as EcosimPro/ESPSS can be used as integration platforms to combine fluid, structural and control models in end-to-end launcher simulations. |
| 2016 | Modeling Fluid Transient Phenomena in LRE Feedlines Space Propulsion 2016 Roma | C. Bombardieri, T. Traudt, C. Manfletti. Institute of Space Propulsion - German Aerospace Center (DLR) | A Liquid Rocket Engine (LRE) is a complex pipe network in which each propellant must be delivered from the tank to the combustion chamber. Along its path, the fluid is conditioned by means of pumps, filters and several different valves. A model with EcosimPro has bees done of the full system. |
| 2016 | Final Test Campaign on Fluidic Mock-Up for EXOMARS EDM Propulsion Design Validation (With Hydrazine) Space Propulsion 2016 Roma | F. Laverty, G. Lubrano, P. Capus, A. Iffly, P. Garçon. Thales Alenia Space, Cannes, France | Reports a final campaign on a fluidic mock-up representative of a complex propulsion subsystem, including priming and pressure-surge tests. The results are used to verify and adjust EcosimPro/ESPSS models previously correlated on earlier campaigns, increasing confidence in predictions for flight hardware. |
| 2016 | ESPSS Model of a Simplified Combined-Cycle Engine for Supersonic Cruise 5th ESPSS Workshop 2016 | J. Moral(1), J. Vilá(1), V. Fernández-Villacé(2), F. Di Matteo(2), J. Steelant(2) (1) Empresarios Agrupados Internacional. S.A., Division of Simulation and Transport Systems, Magallanes 3, 28015 Madrid, Spain. (2) ESA-ESTEC, Section of Aerothermodynamics and Propulsion Analysis, Keplerlaan 1, 2200 AG Noordwijk, The Netherlands | Uses EcosimPro/ESPSS to build a simplified combined Brayton–turbo-rocket cycle model for a supersonic cruise engine. The paper sizes turbomachinery and heat exchangers and simulates start-up and ascent, showing how ESPSS can capture both design and off-design behaviour of advanced air-breathing concepts. |
| 2015 | Novel dynamical model for an object-oriented space tether simulator 25th International Symposium on Space Flight Dynamics | F. Rodríguez-Lucas(1)(2), M. Sanjurjo-Rivo(1)(3), and J. Peláez(1)(4) (1) Space Dynamics Group (SDG-UPM) (2) Empresarios Agrupados, Madrid, Spain (3) Universidad Carlos III de Madrid (UC3M), Spain (4) Universidad Politécnica de Madrid (UPM), Spain | Presents a new space-tether dynamics model implemented in an object-oriented framework within EcosimPro. By discretising the tether into elastic rods and masses and coupling orbital propagation, the simulator analyses deployment and de-orbit scenarios for electrodynamic tethers, providing a basis for future EcosimPro-based tether studies. |
| 2014 | The thermal and structural paradox for hypersonic cruisers | J. Steelant (1), V. Fernandez-Villace (1), M. Dalenbring (2), G.-S. Wang (2). (1) ESA-ESTEC, Section of Aerothermodynamics and Propulsion Analysis, Keplerlaan 1, 2200AG Noordwijk, Netherlands (2) FOI, Swedish Defence Research Agency, Division of Information and Aeronautical Systems, SE-164 90 Stockholm, Sweden | High-speed cruise vehicles require the use of high temperature materials to withstand the high thermal fluxes during flight. The long duration of a flight dictates a proper thermal protection system to cope with the integrated heat load accumulated during flight while a part of this heat might need to be evacuated after touchdown. Structural analysis shows that the thermo-mechanical fatigue is the sizing parameter for the hypersonic vehicle structural design. |
| 2014 | Installed performance evaluation of an air turbo-rocket expander engine | V. Fernández-Villacé (1), G. Paniagua (1), J. Steelant (2). (1) Von Karman Institute for Fluid Dynamics, Chaussée de Waterloo 72, Rhode-St-Genèse, Belgium (2) European Space Agency, Keplerlaan 1, Noordwijk, The Netherlands | The propulsion plant of a prospective supersonic cruise aircraft consists of an air turbo-rocket expander and a dual-mode ramjet. A comprehensive numerical model was constructed to examine the performance of the air turbo-rocket during the supersonic acceleration of the vehicle. |
| 2014 | PEPS, A tool for Power System Simulatiom (ESPC14) | Arturo Fernández, Gianfelice D'Accolti, Brandon Buergler, Borja García. European Space Agency, Netherlands | Introduces PEPS, an ESA tool built on EcosimPro to simulate spacecraft electrical power systems and energy balance. The paper shows how PEPS models orbits, solar arrays, batteries and loads to find worst-case scenarios and verify that the power subsystem can safely meet mission needs. |
| 2014 | Propulsion System Development and Verification Activities for the 2016 ExoMars Trace Gas Orbiter | R. Lescouzères(1), M. Wolf(2), B. Wollenhaupt(1), S. Goodburn(1), M. Peukert(1), T. Biehler(2), M. Abele(2), M. Pastorino(3), T. Walloschek(4) (1) OHB System AG, Germany (2) Airbus Defence and Space (Astrium GmbH), Germany (3) Thales Alenia Space, France (4) ESA, Netherlands | Summarises the design, qualification and verification of the ExoMars Trace Gas Orbiter propulsion system. Test and in-flight experience provide key reference cases for EcosimPro/ESPSS models, which are used to analyse transients and to support ongoing improvements of ESA’s propulsion simulation capability. |
| 2014 | Fluid transient simulation for the ExoMars bi-propellant propulsion subsystem | V. Tregubow, A. Pasquier, B. Wollenhaupt, R. Lescouzères, M. Peukert OHB-System AG, Bremen, Germany | Uses EcosimPro/ESPSS to build a detailed transient model of the ExoMars orbiter propulsion system. The paper analyses priming, water-hammer and other fast phenomena, showing how ESPSS supports the identification of worst-case scenarios and helps define safe operating procedures and component requirements. |
| 2014 | Live Propellant Transient Test Results Achieved in the ExoMars Test Campaign | A. Pasquier, R. Lescouzères, V. Tregubow, B. Wollenhaupt, M. Peukert. OHB-System AG, Bremen, Germany | Reports transient tests (priming, valve operations, etc.) on the ExoMars bipropellant propulsion system. The measured pressure and flow transients are compared with EcosimPro/ESPSS simulations, validating the models used to predict critical events such as water hammer and ensuring safe margins in the feed system design. |
| 2014 | Development of an Attitude Control and Propellant Settling System for the aA5ME Upper Stage | D. Kajon(1), F. Masson(2), T. Wagner(1), D. Welberg(1), T. Büchner da Costa(1), J. Mansouri(3) (1) Airbus Defence and Space, Germany (2) CNES, France (3) ESA, Directorate of Launchers, France | Describes the design of a combined attitude-control and propellant-settling system for the Ariane 5ME upper stage. System studies and transient analyses, supported by EcosimPro/ESPSS simulations, are used to compare candidate propulsion concepts and to define settling thrust profiles compatible with Vinci re-ignition. |
| 2014 | Test campaign on hydraulic mock-up for EXOMARS EDM propulsion design validation | F. Laverty, P. Capus, G. Lubrano, Y. Le-Marchand, A. Iffly, P. Garçon Thales Alenia Space, Cannes, France | Describes a flight-like hydraulic mock-up of the ExoMars propulsion subsystem used to investigate priming and pressure surges. EcosimPro/ESPSS models are correlated with the test data to refine transient predictions and to derisk the design before hot-fire testing with real propellants. |
| 2014 | Propulsion subsystem for the EXOMARS entry and descent module (2016 mission demonstrator) | G. Lubrano, P. Capus , D. Lebleu, O. Maillan, P. Garcon Thales Alenia Space, Cannes, France | Presents the design of the cold-gas/chemical propulsion subsystem for the ExoMars Entry, Descent and Landing Module. Experimental characterisation and system-level design are complemented by simulations that are later used as reference and validation data for EcosimPro/ESPSS models of EDL propulsion. |
| 2014 | Experimental and numerical analysis of water hammer during the filling process of pipelines | Cristiano Bombardieri, Tobias Traudt, Chiara Manfletti. Engine Transients Group, Institute of Space Propulsion, German Aerospace Center (DLR), 74239 Hardthausen, Germany | Combines DLR water-hammer experiments with detailed EcosimPro/ESPSS simulations of filling transients in a propulsion feed system. The work shows that ESPSS can reproduce measured pressure surges and is therefore suitable for predicting loads and guiding design of feed lines, valves and protections. |
| 2014 | Helium Electronic Pressure Regulator breadboard testing and development | R. Delanoë (1), A. Demairé (1), T. Grönland (2), G. Khimeche (3), S. Hyde (4) (1) OHB Sweden, Stockholm, Sweden (2) Nanospace, Uppsala, Sweden (3) Airbus Defence and Space, Toulouse, France (4) European Space Agency, Noordwijk, Netherlands | Describes the development and testing of an electronic helium pressure regulator for telecom platforms. Test results are used by ESA and partners to build and tune EcosimPro/ESPSS regulator and pressurisation models, improving the accuracy of launcher and spacecraft tank-pressurisation simulations. |
| 2014 | Current Activities for the Development of a LOX/LCH4 Regenerative Thrust Chamber at the Italian Aerospace Research Centre | Vito Salvatore (1), Francesco Battista (1), Piero de Matteis (1), Leonardo De Rose (2) (1) Italian Aerospace Research Centre (CIRA), Capua (CE), Italy (2) AVIO S.p.A., Colleferro (RM), Italy | Reports the HYPROB programme’s work on LOX/LCH₄ regeneratively cooled engines. Experimental campaigns and design work are supported by numerical tools, with results feeding back into ESPSS/EcosimPro thrust-chamber models used for future design and cycle studies of methane engines. |
| 2014 | Single-injector LOX/GCH4 combustion chambers manufacturing and experimental characterization in the framework of HYPROB-BREAD project | Francesco Battista, Michele Ferraiuolo, Pasquale Natale, Daniele Cardillo, Ainslie French, Daniele Ricci, Manrico Fragiacomo, Vito Salvatore CIRA (Italian Aerospace Research Centre), Capua (CE), Italy | Details the design, manufacturing and hot-fire testing of single-injector LOX/methane chambers within HYPROB-BREAD. The test database is used to validate and tune EcosimPro/ESPSS combustion-chamber components, improving their capability to predict performance and thermal behaviour for methane propulsion. |
| 2014 | Fluidic simulations and tests of space mechanical pressure regulators | Thomas Liénart (1), Kilian Pfaab (1), Jérémy Vidal (2), Stéphane Galéra (2), Christophe Koppel (3) (1) Centre National d’Etudes Spatiales (French Space Agency), Toulouse, 31000, France (2) ALTRAN Sud-Ouest, Blagnac, 31700, France (3) KopooS Consulting Ind., Paris, 75008, France | Analyses mechanical pressure regulators for cold-gas propulsion using a mix of testing and fluidic simulations. EcosimPro-based models of regulators and feed lines are employed to reproduce dynamic behaviour and to size components for missions such as MICROSCOPE, demonstrating the usefulness of EcosimPro in regulator design. |
| 2014 | Thrust chamber modelling for the analysis of liquid rocket engine transients | Marco Leonardi (1), Francesco Di Matteo (2), Johan Steelant (2), Francesco Nasuti (1), and Marcello Onofri (1) (1) University of Rome La Sapienza, Dip. Ingegneria Meccanica e Aerospaziale, Rome, Italy (2) ESA-ESTEC, Aerothermodynamic and Propulsion Analysis Section, Noordwijk, The Netherlands | Develops detailed EcosimPro/ESPSS thrust-chamber models to study ignition, shutdown and throttling transients in liquid rocket engines. Coupled with feed-system models, these simulations help understand pressure and flow evolution, supporting safer operating procedures and more robust engine designs. |
| 2014 | Pressurization modeling for launcher tanks | A. Dufour Airbus Defence and Space, Les Mureaux, France | Builds system models of cryogenic launcher tanks, pressurisation lines and valves, using EcosimPro/ESPSS to simulate multi-phase behaviour and control strategies. The study evaluates pressurant mass requirements and pressure evolution, providing design guidance for future European launchers. |
| 2014 | Assessment for Hydrazine detonability during priming system activities | Ferran Valencia-Bel, Francesco Di Matteo, and William van Meerbeeck European Space Agency – ESTEC, Netherlands | Investigates the conditions leading to hydrazine detonations under compression, building a test database across many setups and parameters. The results are used by ESA and partners as reference to define safe regimes and to improve the fidelity of EcosimPro/ESPSS models for hydrazine feed systems and transients. |
| 2014 | Experimental database with real propellants to study multi-phase fluid hammer phenomena | J. Anthoine (1), J-Y. Lestrade (1), J. Steelant (2) (1) ONERA - The French Aerospace Lab (2) ESA-ESTEC, Noordwijk, The Netherlands | Provides a high-quality database of multi-phase flow and fast transients obtained with real propellants. These data sets are specifically intended to validate and calibrate ESPSS/EcosimPro component models (e.g. valves, lines, cavitation), improving prediction of critical events in propulsion systems. |
| 2014 | MPS Constellation: Flight experiences | M. Battistel, PP. Baubias, P. Garcon Thales Alenia Space, Cannes, France | Summarises flight experience from MMH/MON monopropellant propulsion systems used on various satellites. Operational data on anomalies, margins and ageing are used to refine engineering practices and offer real-flight reference cases that complement EcosimPro/ESPSS simulations of these systems. |
| 2014 | 1-D Simulation of Solid and Hybrid Combustors with EcosimPro/ESPSS | J. Moral(1), F. Rodríguez(1), J. Vilá(1), F. Di Matteo(2), J. Steelant(2) (1) Empresarios Agrupados Internacional. S.A, Madrid, Spain (2) Aerothermodynamics and Propulsion Analysis Section (TEC-MPA), ESTEC-ESA, Noordwijk, The Netherlands | Introduces new ESPSS components for 1-D simulation of solid and hybrid rocket combustors inside EcosimPro. The paper applies these models to Ariane-6-related configurations, illustrating how ESPSS can capture internal ballistics and transient behaviour for advanced solid/hybrid propulsion. |
| 2013 | Development Status of an Open Capillary Pulsed Plasma Thruster with Non-Volatile Liquid Propellant | S. Barral (1), J. Kurzyna (1), E. Remírez (2), R. Martín (2), P. Ortiz (3), J. Alonso (3), S. Bottinelli (4), Y. Mabillard (4), A. Zaldívar (5), P. Rangsten (5), C. R. Koppel (6) (1) Institute of Plasma Physics and Laser Microfusion, 01497 Warsaw, Poland (2) JMP Ingenieros, 26371 Sotés (La Rioja), Spain (3) Najera Aerospace, 26371 Sotés (La Rioja), Spain (4) Mecartex, 6933 Muzzano, Switzerland (5) NanoSpace AB, Uppsala Science Park, SE-751 83 Uppsala, Sweden (6) KopooS Consulting Ind., 75008 Paris, France | Summarises the design status of ARES, a regenerative air-revitalisation system providing CO2 removal, oxygen generation from water electrolysis, and CO2 reduction to water and methane. It outlines rack-level accommodation and the remaining development steps toward operational deployment on the ISS. |
| 2012 | Development of a Cold Gas Attitude Control System for a Lander Demonstrator | K. Odic, C. Muñoz-Moya, N. Sauvage Astrium GmbH Space Transportation, 28199 Bremen, Germany | Describes the design and qualification of a cold-gas attitude-control system for a planetary lander. System analyses and test results are used to create and validate EcosimPro models of the cold-gas system, which then support performance prediction and guidance strategy studies. |
| 2012 | Satellite Library Ecosimpro for AOCS Effects on Propulsion | Christophe R. Koppel (1), Marco de Rosa (2), José Moral (3), Johan Steelant (2) (1) KopooS Consulting Ind., Paris, France (2) European Space Agency ESTEC, Noordwijk, The Netherlands (3) Empresarios Agrupados, Madrid, Spain | Documents the implementation and validation of an AOCS/satellite library inside EcosimPro, compatible with existing propulsion libraries. The paper shows how coupled AOCS–propulsion simulations can reproduce the effect of attitude manoeuvres, sloshing and accelerations on tanks and lines, enabling more realistic system studies. |
| 2012 | Effects of a Satellite Mission on the Propulsion Subsystem | Christophe R. Koppel (1), Marco de Rosa (2), José Moral (3), Johan Steelant (2) (1) KopooS Consulting Ind., Paris, France (2) European Space Agency ESTEC, Noordwijk, The Netherlands (3) Empresarios Agrupados, Madrid, Spain | Documents Phase-3 upgrades to the ESPSS libraries on the EcosimPro platform, extending modelling from component physics to mission-coupled behaviour. New capabilities capture how spacecraft accelerations, tank fill levels and shifting mass properties influence pressures and flows. This enables more realistic end-to-end propulsion/AOCS trade studies and validation planning. |
| 2012 | Engineering validation model for the Exomars bi-propellant propulsion subsystem | S. Pavón, V. Tregubow, M. Peukert, R. Lescouzères OHB-System AG, Bremen, Germany | Presents the Engineering Validation Model campaign for ExoMars’ bipropellant propulsion subsystem, combining representative hardware with targeted tests to de-risk operations and interfaces. Steady-state and transient behaviour (pressure drops, priming, water-hammer, residuals) is predicted in EcoSimPro and cross-checked with test data to support qualification decisions. |
| 2012 | OHB System’s Propulsion Achievements - Heritage and Prospects | Markus Peukert OHB-System AG, Bremen, Germany | Reviews OHB System’s propulsion heritage (e.g., SAR-Lupe and SmallGEO) and the design approaches that improved performance, robustness and cost efficiency. It outlines future needs such as passivation assemblies and electric helium regulation for next-generation missions. The paper also highlights analysis capability for subsystem engineering, including the use of EcosimPro. |
| 2012 | Zooming Capabilities of the 1D ESPSS Propulsion Simulation Tool with 3D-CFD Solvers: Implementation and Validation | Kaname Kawatsu (1), Nobuhiro Yamanishi (1), Francesco Di Matteo (2) and Johan Steelant (2) (1) Japan Aerospace Exploration Agency JAXA JEDI, Japan (2) ESTEC-ESA, Aerothermodynamics and Propulsion Analysis Section (TEC-MPA), The Netherlands | Introduces a practical “zooming” workflow that couples 1D EcosimPro/ESPSS system models with 3D CFD solvers, so engineers can increase fidelity only where it matters most. The framework is implemented and validated on propulsion-relevant cases, improving local physics prediction while keeping end-to-end design trades fast. |
| 2012 | Transient simulation of the RL-10A-3-3A rocket engine | Francesco Di Matteo (1), Marco De Rosa (2) and Marcello Onofri (1) (1) Sapienza University of Rome (2) ESA-ESTEC, Propulsion Engineering, The Netherlands | Develops and validates a detailed transient model of the RL-10A-3-3A expander-cycle engine, focusing on start-up and shut-down dynamics. Built in EcosimPro with ESPSS, the integrated 1D model captures key component interactions and compares well with experimental trends. It supports safer valve sequencing and helps reduce costly test iterations. |
| 2012 | Study of Electronic Pressure Regulator for Telecommunications Satellite Applications | J. Stanojev(1), N. Pokrupa(1), R. Delanoë(1), A. Demairé(1) and Simon Hyde (2) (1) OHB Sweden, Stockholm, Sweden (2) European Space Agency, Noordwijk, Netherlands | ESA-funded study proposing an electronic helium pressure regulator as a robust alternative to mechanical regulators for telecom chemical propulsion systems. Using an EcosimPro performance model, the concept demonstrates tight pressure control across a wide inlet-pressure range and offers potential helium tank downsizing. It also brings operational flexibility, including independent set-points and end-of-life re-pressurisation options. |
| 2012 | Propulsion System for the European Lunar Lander. Development Status and Breadboarding Activities | Martin Riehle, Thomas Diedrich, David Perigo, Stephan Kraus and Matthias Bühner EADS Astrium Space Transportation GmbH Germany and ESA-ESTEC The Netherlands | Summarises the consolidated chemical propulsion architecture for ESA’s European Lunar Lander and early breadboard activities that de-risk key elements. Hydraulic characterisation and mission-sequence simulations are used to validate an EcosimPro modelling setup for residuals and transients. The work is complemented by hot-fire demonstrations and pressurisation regulator testing. |
| 2012 | Small GEO Xenon propellant supply assembly pressure regulator panel: test results and comparison with EcosimPro predictions | Stefano Naclerio, Jesús Soto Salvador, Ernesto Such, Raúl Avezuela, Ramón Pérez Vara IberEspacio, Madrid, Spain | Reports thermal-vacuum functional testing of SmallGEO’s xenon Propellant Supply Assembly electronic regulator, covering end-of-life conditions and the full operating temperature range. Key metrics (actuation frequency, downstream pressure rise and regulation accuracy) are benchmarked against EcosimPro/ESPSS predictions to strengthen model-based valve-timing tuning. |
| 2012 | Adaptation of the ESPSS/EcosimPro platform for the design and analysis of liquid propellant rocket engines | J. Amer (final thesis, 1), J. Moral(2), J.J. Salvá(1) (1) School of Aerospacial Engineering UPM, Madrid, Spain (2) Empresarios Agrupados Internacional, Madrid, Spain | Presents a modular EcosimPro/ESPSS pre-design tool linking mission requirements, performance and sizing, coupled to optimisation. Validated against Aestus and demonstrated with transient start-up/shutdown simulations. |
| 2011 | Sustained Hypersonic Flight in Europe: First Technology Achievements within LAPCAT II | J. Steelant European Space Research and Technology Center (ESA-ESTEC), 2200 AG Noordwijk, The Netherlands | The LAPCAT II Mach 8 has been designed to identify the main constraints for this high demand propulsion system. |
| 2011 | Study of an Airbreathing Variable Cycle Engine | Peter Vyvey(1), Walter Bosschaerts(1), Victor Fernandez Villace(2), Guillermo Paniagua(2) (1) Royal Military School of Belgium (2) von Karman Institute for Fluid Dynamics | This paper describes the Revolutionay Turbine Accelerator in EcosimPro . It is a variable cycle engine developed by NASA and General Electric in the frame of the Next Generation Launch Technology Program . |
| 2010 | HM7B Simulation with ESPSS Tool on Ariane 5 ESC-A Upper Stage | Armin Isselhorst Propulsion Systems TE59, EADS Astrium GmbH, Bremen, Germany | Presents ESPSS, an ESA-backed EcosimPro-based platform intended to standardise European propulsion system simulation. An HM7B gas-generator cycle model is built and its predictions are compared with Ariane 5 ESC-A flight data to support model credibility. |
| 2010 | VEGA-AVUM-PLS model under EcosimPro Environment: Development and Validation | L. Boccaletto, M. Marchionni ESA ESTEC, Propulsion Engineering Section | Develops and validates an EcosimPro performance model of the VEGA AVUM Liquid Propulsion System. Enables consistent prediction and test data reduction using available technical data and schematics. |
| 2010 | Semi-empirical heat transfer correlations in combustion chambers for transient system modelling | Francesco Di Matteo(1), Marco De Rosa(2), Marcello Onofri(1) (1)Sapienza University of Rome, Italy (2)ESA-ESTEC, Propulsion Engineering, Noordwijk, Netherlands | Defines semi-empirical heat-transfer correlations for cooled combustion chambers aimed at transient system simulations. Implemented in EcosimPro/ESPSS to improve prediction of wall temperatures and heat flux during dynamic operation. |
| 2010 | Object oriented steady state analysis and design of liquid rocket engine cycles | Francesco Di Matteo(1), Marco De Rosa(2) (1)Sapienza University of Rome, Italy (2)ESA-ESTEC, Propulsion Engineering, Noordwijk, Netherlands | Introduces a fast, object-oriented steady-state library in EcosimPro for liquid rocket engine cycle pre-design. Reuses ESPSS thermochemistry and property functions to run parametric and off-design studies efficiently. |
| 2010 | Modelling environmental control and life support systems (ECLSS) and loop heat pipes with EcosimPro | Almudena Rueda, Raúl Avezuela, Pedro Cobas (1) and Ramón Pérez-Vara (2) (1) Empresarios Agrupados Internacional, Madrid, Spain (2) IberEspacio, Madrid, Spain | Explains how EcosimPro supports multidisciplinary ECLSS analysis through object-oriented modelling and robust DAE solving, and highlights key usability upgrades in version 4.6. Shows how these capabilities enable practical modelling and trade studies for ECLSS loops and loop heat pipes. |
| 2010 | Development of a Propellant Supply Assembly for Small GEO | Stefano Naclerio, Raúl Avezuela, Ramón Perez(1), Alain Demairé, Bjarne Andersson(2), Niccola Kutufa(3) (1) IberEspacio (2) Swedish Space Corporation (3) European Space Agency | Describes a xenon bang-bang Propellant Supply Assembly that feeds both electric propulsion and cold-gas thrusters over a wide flow range. Performance is analysed with EcosimPro/ESPSS and planned tests confirm predictions. |
| 2010 | Simulation of Ariane 5 SCA System with euces Tool | Armin Isselhorst (1), Gunnar Sieber (2) (1) Propulsion Systems TE59, EADS Astrium GmbH, Bremen, Germany (2) Thermal and RCS Engineering TE52, EADS Astrium GmbH, Bremen, Germany | Applies euces to model the Ariane 5 ES SCA-VUS hydrazine reaction control system, including bladder tanks, valves, feed lines and thruster clusters. Uses mission firing profiles to reproduce key trends and compares results with flight transducer data for validation. |
| 2010 | Multiphase Fuid Hammer in Propellant Lines | Lema, M.(1)(2), Porca-Belío, P.(1), Steelant, J.(3), López-Peña, F.(2) and Rambaud, P.(1) (1) von Karman Institute for Fluid Dynamics, Belgium (2) University of A Coruña, Spain (3) ESTEC-ESA, Noordwijk, The Netherlands | Builds an experimental facility to reproduce priming and the resulting multiphase fluid hammer in spacecraft lines. Provides data to calibrate transient models (including EcosimPro/ESPSS) for cavitation, boiling and non-condensable gas effects. |
| 2010 | Development testing of a new bipropellant propulsion system for the GMP-T spacecraft | Andrew Devereaux(1), François Cheuret(2) (1)Surrey Satellite Technology Ltd (SSTL), UK (2)European Space Agency (ESA-ESTEC), Noordwijk, The Netherlands | Presents design and verification testing of a 400 N MMH/NTO propulsion system with 16 RCS thrusters for a small GEO platform. Uses system analysis/modelling (including EcosimPro where relevant) to correlate test results. |
| 2010 | Heat Transfer at Wall. Experimental Characterisation in Supersonic Flows with Induced Condensation Phenomena | Luca Boccaletto (1), Matteo Appolloni (2), Rogier Schonenborg (3) (1) ESA-ESTEC, TEC-MPC, Noordwijk, The Netherlands (2) ESA-ESTEC, TEC-TCE, Noordwijk, The Netherlands (3) Schonenborg Space Engineering B.V. at ESA-ESTEC, TEC-MPC, Noordwijk, The Netherlands | Presents a cryogenically cooled 2-D nozzle test article to measure wall heat transfer in supersonic flow with induced condensation. Data supports validation of phase-change and heat-transfer models, including EcosimPro-based analyses. |
| 2010 | An EcosimPro model of Herschel and Planck propulsion systems | A. Iffly, A. Jamin, L. Lecardonnel Thales Alenia Space, Cannes, France | EcosimPro model of the Herschel/Planck propulsion and RCS for system-level performance prediction. Supports design trade-offs, operational tuning and troubleshooting across nominal and off-nominal scenarios. |
| 2010 | European Space Propulsion System Simulation (ESPSS) platform | J. Moral, R. Pérez-Vara (Empresarios Agrupados Internacional S.A.) J. Steelant, M. de Rosa (Aerothermodynamics and Propulsion Analysis Section TEC-MPA, ESTEC-ESA) | This paper describes the EcosimPro Libraries provided with the ESPSS (European Space Propulsion System Simulation) software, which is concerned with setting up a common European platform for propulsion system simulation. |
| 2010 | Simulation of a Combined Cycle for High Speed Propulsion | Víctor Fernández Villacé and Guillermo Paniagua. Von Karman Institute for Fluid Dynamics, Belgium | A modelisation of the selected engine Synergistic Air- Breathing Rocket Engine (SABRE), which is the power plant of the Skylon space plane. The particularities of this engine comprise the use of a pre-cooler in the accelerating air-breathing phase. |
| 2009 | Design Status of the Closed-Loop Air Revitalization System ARES for Accommodation on the ISS | Klaus Bockstahler (1), Helmut Funke (1), Joachim Lucas (1), Johannes Witt (2), Scott Hovland (2) (1) Astrium GmbH, Dept. TO51, 88039 Friedrichshafen, Germany (2) European Space Agency | Summarises the design status of ARES, a regenerative air-revitalisation system providing CO2 removal, oxygen generation from water electrolysis, and CO2 reduction to water and methane. It outlines rack-level accommodation and the remaining development steps toward operational deployment on the ISS. |
| 2009 | Ballistic Flight Phase Simulation with euces Tool for ESC-A Upper Stage | Armin Isselhorst (1), Kai Bergemann (2) (1) Functional Propulsion Engineering TE59, EADS Astrium GmbH, Bremen, Germany (2) Commercial Programs TP431, EADS Astrium GmbH, München, Germany | Introduces euces, a functional simulation environment for launcher-stage propulsion behaviour in ground and flight conditions. A simplified Ariane 5 ESC-A ballistic-flight model is demonstrated and benchmarked against flight measurements to build confidence for engineering use. |
| 2009 | Master Thesis: "Modelling and Simulation of the Revolutionary Turbine Accelerator" | Jelle Goyvaerts. Von Karman Institute for Fluid Dynamics, Belgium | Master’s thesis modelling NASA/GE’s Revolutionary Turbine Accelerator turbomachinery section in EcosimPro, including new components such as a conical inlet and a core-driven fan stage. The model is validated against literature and a reference tool to establish credible performance trends. It demonstrates how system simulation can bound unknown parameters for high-speed propulsion concepts. |
| 2008 | euces Software Development | Armin Isselhorst, Nico Rackemann Thermal and Functional Propulsion Engineering TE52 EADS-SPACE Transportation, Bremen, Germany | Describes euces, an object-oriented software effort to create reusable physics-based component libraries for time-domain simulation of launcher propulsion systems. The paper presents the library structure and an Ariane 5 EPS upper-stage case study with comparisons to flight data. |
| 2008 | Applicability of EcosimPro to simulate a Life Support System | Victor Guirado Viedma NTE, Spain | The project MELiSSA Adaptation for Space Phase II carried out by NTE consists of finding a preliminary design of a Life Support System (ECLSS) using EcosimPro/ECLSS for a future Moon base providing 100% air closure, 90% water closure and a 5% food production first and a 40% food production in a second step. |
| 2006 | euces: european cryogenic engineering software tool | Armin Isselhorst Thermal and Functional Propulsion Engineering TE52 EADS-SPACE Transportation, Bremen, Germany | The euces project was initiated to be prepared for the future role of EADS as stage system prime for stage and launcher developments. Launcher stages for NGLV (New Generation Launch Vehicles) need to meet ambitious mission and operational demands. The paper presents a brief overview of the EcosimPro S/W kernel. |
| 2006 | Simulation of the Smart-1 Electric Propulsion System with a system simulation software EcosimPro | Jesús Álvarez (Iberespacio), Ramón Pérez-Vara (Iberespacio), and Christophe R. Koppel (Koopos) | SMART-1 is the first European spacecraft using Electric Primary Propulsion. A detailed simulation model of the Electric Propulsion System has been developed using EcosimPro® , a multi-disciplinary dynamic system simulation tool. The need of a simulation model was recognised early in the project, and the model was developed at the same time that the system was being designed. |
| 2006 | An ESA state-of-the-art simulation tool for space applications | Pedro Cobas-Herrero, and Borja García-Gutiérrez, EA Internacional, Madrid, Spain | EcosimPro is a project developed by EA Internacional (Madrid) under contract with ESA. The project commenced in the early ‘90s with the aim of creating simulation software to model Environmental Control and Life Support Systems (ECLSS) for the European modules COLUMBUS) of the International Space Station (ISS) and for Hermes. The original objective was not to construct a generic simulation tool, but a specific tool for the ECLSS. With time, it became evident that the software we had developed could be used to model any physical system (mainly in 0-D) which could be represented by algebraic and differential equations |
| 2006 | Mathematical Modeling of Multiple Evaporator-Multiple Condenser Loop Heat Pipes (LHP) Using EcosimPro | Carmen Gregori, Alejandro Torres, Ramón Pérez-Vara (Iberespacio) and Tarik Kaya (Carleton University) | To solve the thermal control problems of modern spacecraft with complex payloads and configurations, there is an increasing demand for multiple evaporator and/or multiple condenser loop heat pipes (LHPs). As a result, several initiatives, including flight demonstration, are being proposed and research is under way. It is well known that mathematical modeling of a conventional LHP is highly challenging due to the complex two-phase phenomena involved. |
| 2005 | Advances in two phase capillary loop modelling with EcosimPro | Carmen Gregori, Ramón Pérez-Vara (Iberespacio) | Improvements in the Loop Heat Pipe library for modelling advanced thermal devices. |
| 2005 | Simulation Model of the Air Revitalization System for ISS | Raúl Avezuela Rodríguez (1), Helmut Funke (2), Johannes Witt (3) (1) IBERESPACIO (2) EADS SPACE Transportation GmbH (3) ESA/ESTEC | An air revitalization system was designed with EcosimPro for the ISS. The name of this system is ARES, which stands for Atmosphere Regeneration System. Its major functions in the Life Support System of the ISS would be to:Generate breathable oxygen from water, collect the produced CO2 from air cabin and to control cabin CO2-level as required, convert CO2 into water and methane and recover the produced water for use in the water management system. |
| 2005 | Loop Heat Pipes (LHP) modeling with Ecosimpro and experimental validation | Carmen Gregori, Alejandro Torres, Ramón Pérez-Vara (Iberespacio) and Tarik Kaya (Carleton University) | An advance Loop Heat Pipe modelling library has been created with EcosimPro You can model any typical calculation as start-up, heating, two-phase flow, etc. |
| 2004 | MELISSA higher plants compartment modelling using EcosimPro | Luis Ordoñez, Christophe Lasseur (ESA), Lauren Poughon (Univ. Blaise Pascal), and Geoffrey Watters (Univ. of Guelph) | This paper introduces two modeling approaches in consideration for the MELiSSA Higher Plants Compartment using EcosimPro/ECLSS. This includes an empirical light response curve modeling approach and the Modified Energy Cascade (MEC) model. |
| 2004 | Loop Heat Pipes (LHP) transient modeling with Ecosimpro | Carmen Gregori (Iberespacio) | Loop heat pipes (LHP) are two--phase capillary heat phase capillary heat transfer devices that are becoming very interestingtransfer devices that are becoming very interesting for space thermal control applications. |
| 2003 | Preliminary static and dynamic analysis of MELISSA components using EcosimPro | Luis Ordoñez, and Alexander Rodriguez, ESA-ESTEC, Holland | This paper documents the development of an EcosimPro Library to model a bio-regenerative Life Support System. |
| 2003 | Plant grow chamber simulation using EcosimPro | Luis Ordoñez, ESA-ESTEC, Holland | It is a closed ecosystem intended as a tool to gain understanding of artificial ecosystems and to develop new technologies for a long term manned mission life support system. |
| 2003 | Overview of European applications of EcosimPro to ECLSS, CELSS and ATCS | R. Perez (EA), O. Pin (ESA), R. Müller (Astrium), and S. Mannu (Alenia) | The standard ECLSS library is well adapted to the thermo-hydraulic analysis of air cabin loops, but CELSS (Controlled Ecological Life Support System) and ATCS (Active Thermal Control System) have also been modeled by developing specific libraries of components. |
| 2003 | Preliminary design and simulation of a liquid propellant rocket engine (ES) | Carmen López and Germán García, ETSIA-UPM, Madrid, Spain | This paper synthesises the qualification project carried out by the authors. The main objectives of the project was to perform the preliminary design of a liquid propellant rocket engine in accordance with certain design specifications and simulate its actions. |
| 2002 | Comparing EcosimPro and ESATAN modelling | R. Müller, L. Eicher (Astrium), O. Pin (ESA), and R. Perez (EA) | The Crew Refrigerator/Freezer Racks (RFR) are being developed and built at Astrium Friedrichshafen under ESA contract. The RFR will provide conditioned storage volume for astronaut food during transport in the MPLM and on board the ISS |
| 2002 | Application of EcosimPro to Bioregenerative Life Support Components | Alexander Rodríguez and Luís Ordóñez, ESA/ESTEC, Holland | BLSS is a system that is capable of recovery of edible biomass, water and oxygen from waste, carbon dioxide and minerals based on processes driven by biological entities |
| 2001 | Using EcosimPro for thermal and thermo-hydraulic analysis in European Space Agency (slides) | Olivier Pin, Thermal and Structures Division, ESA/ESTEC, Holland | EcosimPro is increasingly being used at ESA and in Industry to carry out thermal and thermo-hydraulic simulations. This paper describes how EcosimPro can be used in this context and provides recent application examples |
| 2001 | Simulation of a liquid rocket engine (ES) | Nuria Margarit i Bel and Prof. Manuel Martínez Sánchez, Massachussetts Institute of Technology (MIT), Cambridge, MA, USA | A study has been carried out by a MIT student of the dynamic behaviour of the liquid propellant that circulates through the different engine components of a liquid.fuelled rocket. |
| 2000 | Multidisciplinary simulation using EcosimPro | Ramón Pérez-Vara (EA Internacional), Pedro Cobas (EA Internacional), and Olivier Pin (ESA-ESTEC) | ESA and Empresarios Agrupados have been developing EcosimPro since 1989. The initial objective was to provide powerful capabilities to handle the simulation of Environmental Control and Life Support Systems (ECLSS) for the International Space Station. Because of the multi-disciplinary nature of ECLSS (thermal, fluids, chemical reactions,electrical and control features) |
| 2000 | Mode transition analysis of the attached pressurized module cabin air loop with EcosimPro | J. A. Romera-Pérez, J. Persson, and J. Witt, ESA, Holland | The change in mode status of the Attached Pressurized Module (APM), termed a mode transition, is due to the need of changing the APM configuration triggered by nominal or contingency events, i.e: initial system activation and further de/reactivation, payload activation, crew, ground or station initiated mode changes, etc. |
