STRATOFLY MR3 – how to reduce the environmental impact of high-speed transportation

Viola, Nicole; Fusaro, Roberta; Gori, Oscar; Marini, Marco; Roncioni, Pietro; Saccone, Guido; Saracoglu, Bayindir H.; Ispir, Ali Can; Fureby, Christer; Nilson, Thommie; Iron, Christian; Vincent, Axel; Schramm, Jan Martinez; Grewe, Volker; Emmerig, Johannes; Hauglustaine, D.; Linke, Florian; Bodmer, Daniel

doi:10.2514/6.2021-1877

Cited by 17 publications

(16 citation statements)

References 13 publications

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“…The vehicle structural mass is equal to 218.75 Mg, while the propellant mass is 181.25 Mg. The maximum take-off weight is then equal to 400 Mg [2]. The propulsive database contains the data of the ATR and DMR engines, and it is derived from LAPCAT MR2 project.…”

Section: Methodology Overviewmentioning

confidence: 99%

“…Benefitting from the heritage of past European funded projects and, in particular, from the LAPCAT II project led by ESA [1], the waverider configuration has been adopted and investigated in-depth throughout all flight phases. STARTOFLY MR3 is a highly integrated system, where propulsion, aerothermodynamics, structures and on-board subsystems are strictly interrelated to one another, as highlighted in Figure 2a [2,3]. An overview of the vehicle dimensions is also reported in Table 1 [2].…”

Section: Stratofly Mr3: Vehicle and Mission Overviewmentioning

confidence: 99%

“…Nowadays, the high-speed air and space transportation systems are experiencing a revolution in the design process, which is resulting in highly innovative and integrated concepts, able to push the performance barrier beyond the limits. This is especially visible in the case of hypersonic civil transportation Energies 2021, 14, 3580 2 of 28 systems, such as the STRATOFLY MR3 concept, where the need to meet a set of challenging technical and operational requirements may impose the adoption of highly integrated waverider configurations [1][2][3][4]. In these cases, it is fundamental to support the vehicle design process with a set of aerodynamic investigations and mission analysis, with an increasing level of complexity.…”

Section: Introductionmentioning

confidence: 99%

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Aerodynamic Characterization of Hypersonic Transportation Systems and Its Impact on Mission Analysis

et al. 2021

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This paper aims to provide technical insights on the aerodynamic characterization activities performed in the field of the H2020 STRATOFLY project, for the Mach 8 waverider reference configuration. Considering the complexity of the configuration to be analyzed at conceptual/preliminary design stage, a build-up approach has been adopted. The complexity of the aerodynamic model increases incrementally, from the clean external configuration up to the complete configuration, including propulsion systems elements and flight control surfaces. At each step, the aerodynamic analysis is complemented with detailed mission analysis, in which the different versions of the aerodynamic databases are used as input for the trajectory simulation. eventually, once the contribution to the aerodynamic characterization of flight control surfaces is evaluated, stability and trim analysis is carried out. The comparison of the results obtained through the different mission analysis campaigns clearly shows that the accuracy of aerodynamic characterization may determine the feasibility or unfeasibility of a mission concept.

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Section: Methodology Overviewmentioning

confidence: 99%

Section: Stratofly Mr3: Vehicle and Mission Overviewmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Aerodynamic Characterization of Hypersonic Transportation Systems and Its Impact on Mission Analysis

et al. 2021

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“…Summarizing, the special methodology suitable formulated, designed and developed for the ATR chemical emission indexes (EI) evaluations consists in the following two fundamental steps (Viola et al, 2021): Arrhenius equations for every elementary reaction step included in the kinetic scheme using, also, in this case, the Z22-NO x 20 kinetic mechanism and the initial operative conditions to calculate the mass fractions of each chemical substance involved in the kinetic mechanism at the time instant t eq at which the mixture temperature reaches the T f value.…”

Section: Air Turbo Rocket Emissions Evaluationsmentioning

confidence: 99%

“…In the field of air-breathing hypersonic scramjet vehicles, design and development, the Italian Aerospace Research Centre (CIRA) and the von Karman Institute for Fluid Dynamics (VKI) have contributed to an international project called Stratospheric Flying Opportunities for High-Speed Propulsion Concepts (STRATOFLY) in collaboration with several other European organizations, coordinated by the Politecnico di Torino under the EC Horizon 2020 programme financial support (Viola et al , 2021).…”

Section: Introductionmentioning

confidence: 99%

Computational evaluations of emissions indexes released by the STRATOFLY air-breathing combined propulsive system

Saccone

Ispir

Saracoglu

et al. 2022

AEAT

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Purpose The purpose of this study is to provide the description of a computational methodology to model the combined propulsive systems of hydrogen propelled air-breathing scramjet vehicles and to evaluate the pollutant and climate-changing emissions. Design/methodology/approach Emissions indexes of nitrogen oxide (EINO) and water vapour released by the air turbo rocket (ATR) and dual mode ramjet (DMR) engines of the STRATOFLY air-breathing, hypersonic scramjet vehicle, propelled by hydrogen/air were evaluated. ATR engine operation was assessed for several cruise conditions in both subsonic and supersonic flight regimes in Ecosimpro software, which is an object-oriented thermodynamic design and simulation platform. ATR combustor inlet flow conditions play a key role in the computation of species mass fractions, and these conditions are highly dependent on turbomachinery performance and engine flight regime. A propulsive operational database was created by varying mass flow rates of fuel and flight conditions such as cruise speed and altitude to investigate possible engine operations. The all-inlet conditions in this map are provided to the Cantera-Python chemical/combustion chemistry solver implementing a specially designed and formulated 0D kinetic-thermodynamic methodology successfully used to model and simulate the electric spark ignition required to activate the combustion process of the reacting mixture in the ATR combustion chambers, whereas the coupled aero-thermodynamic/aero-propulsive 0D/1D code i.e. Scramjet PREliminary Aerothermodynamic Design (SPREAD), designed and developed by the Italian Aerospace Research Centre (CIRA) was used for DMR calculations. Results show low emissions of NO according to the optimized design of the ATR; on the other hand, a tuning of operational conditions is needed for DMR, with its complete re-design to be more conclusive. Analogously, the released amount of water vapour is in good agreement with the required combustion efficiency and the expected propulsive performance. Findings Results show low emissions of NO according to the optimized design of the ATRs; on the other hand, a tuning of operational conditions is needed for DMR, with its complete re-design to be more conclusive. Analogously, the released amount of water vapour is in good agreement with the required combustion efficiency and the expected propulsive performance. Originality/value Applications of innovative 0D/1D chemical kinetic methodology and in-house codes.

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Liquid Metals Heat-Pipe solution for hypersonic air-intake leading edge: Conceptual design, numerical analysis and verification

et al. 2022

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STRATOFLY MR3 – how to reduce the environmental impact of high-speed transportation

Cited by 17 publications

References 13 publications

Aerodynamic Characterization of Hypersonic Transportation Systems and Its Impact on Mission Analysis

Aerodynamic Characterization of Hypersonic Transportation Systems and Its Impact on Mission Analysis

Computational evaluations of emissions indexes released by the STRATOFLY air-breathing combined propulsive system

Liquid Metals Heat-Pipe solution for hypersonic air-intake leading edge: Conceptual design, numerical analysis and verification

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