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Автор: Grafiati

Опубліковано: 14 березня 2023

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Viola, Nicole, Roberta Fusaro, and Valeria Vercella. "Technology roadmapping methodology for future hypersonic transportation systems." Acta Astronautica 195 (June 2022): 430–44. http://dx.doi.org/10.1016/j.actaastro.2022.03.038.

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Viola, Nicole, Pietro Roncioni, Oscar Gori, and Roberta Fusaro. "Aerodynamic Characterization of Hypersonic Transportation Systems and Its Impact on Mission Analysis." Energies 14, no. 12 (June 16, 2021): 3580. http://dx.doi.org/10.3390/en14123580.

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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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Fusaro, Roberta, Valeria Vercella, Davide Ferretto, Nicole Viola, and Johan Steelant. "Economic and environmental sustainability of liquid hydrogen fuel for hypersonic transportation systems." CEAS Space Journal 12, no. 3 (April 18, 2020): 441–62. http://dx.doi.org/10.1007/s12567-020-00311-x.

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Veeran, Sasha, Apostolos Pesyridis, and Lionel Ganippa. "Ramjet Compression System for a Hypersonic Air Transportation Vehicle Combined Cycle Engine." Energies 11, no. 10 (September 25, 2018): 2558. http://dx.doi.org/10.3390/en11102558.

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This report assesses the performance characteristics of a ramjet compression system in the application of a hypersonic vehicle. The vehicle is required to be self-powered and perform a complete flight profile using a combination of turbojet, ramjet and scramjet propulsion systems. The ramjet has been designed to operate between Mach 2.5 to Mach 5 conditions, allowing for start-up of the scramjet engine. Multiple designs, including varying ramp configurations and turbo-ramjet combinations, were investigated to evaluate their merits and limitations. Challenges arose with attempting to maintain sufficient pressure recoveries and favourable flow characteristics into the ramjet combustor. The results provide an engine inlet design capable of propelling the vehicle between the turbojet and scramjet phase of flight, allowing for the completion of its mission profile. Compromises in the design, however, had to be made in order to allow for optimisation of other propulsion systems including the scramjet nozzle and aerodynamics of the vehicle; it was concluded that these compromises were justified as the vehicle uses the ramjet engine for a minority of the flight profile as it transitions between low supersonic to hypersonic conditions.

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Fusaro, Roberta, and Nicole Viola. "Preliminary reliability and safety assessment methodology for trans-atmospheric transportation systems." Aircraft Engineering and Aerospace Technology 90, no. 4 (May 8, 2018): 639–51. http://dx.doi.org/10.1108/aeat-11-2016-0214.

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Анотація:

Purpose This paper aims to propose a methodology for a safety and reliability assessment for the conceptual and preliminary design of very complex and disrupting innovative systems like trans-atmospheric vehicles. The proposed methodology differs from existing ones because it does not rely on statistical data at aircraft-level but exploits the statistical population at components-level only. For the sake of clarity, the paper provides some preliminary results of the application of the methodology at system level. The example deals with the safety and reliability assessment of a very complex propulsion system aimed at guaranteeing vertical take-off and landing capabilities of a suborbital vehicle. Design/methodology/approach The proposed methodology is strongly based on a systems engineering approach. It exploits safety and reliability assessment analyses which have already been developed in both aeronautical and space engineering domains, but it combines them in an innovative way to overcome the lack of statistics at aircraft level. The methodology consists of two different steps: a qualitative top-down process, allowing a functional and physical decomposition of the transportation system and a following quantitative bottom-up approach, which provides the estimation of system-level reliability and safety characteristics starting from the statistical estimation of the components’ characteristics. Findings The paper presents a new methodology for the preliminary reliability and safety assessment of innovative transportation systems, such as hypersonic transportation systems. The envisaged methodology will overcome the poorness of statistical data that is usually affecting the conceptual design of breakthrough systems. Research limitations/implications The paper shows the application of the articulated methodology to a limited case study. A complete example of application of the methodology to estimate safety and reliability characteristics at vehicle level will be provided in feature works. Practical implications The methodology has been proposed to be exploited in international research activities in the field of hypersonic transportation systems. Furthermore, a massive application of this approach would allow to create a database for the generation and the update of semi-empirical models focused on high-level estimations of reliability, availability, maintainability and safety (RAMS) characteristics. Moreover, the proposed safety assessment has been conceived to be fully integrated within a typical conceptual design process. Originality/value The existing literature about safety and reliability assessment at the early design stages proposes pure statistical approaches which are usually not applicable to highly innovative products, where the statistical population is not existing, for example, in the case of trans-atmospheric vehicles. This paper describes how to overcome this problem, through the exploitation of statistical data at components-level only through the combination of these data to estimate RAMS characteristics at aircraft-level thanks to functional analysis, concept of operations and typical safety assessment tools, like functional hazard analysis, failure mode and effect analysis, reliability block diagram and fault tree analysis.

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D’Oriano, Vera, Raffaele Savino, and Michele Visone. "Aerothermodynamic study of a small hypersonic plane." Aircraft Engineering and Aerospace Technology 90, no. 2 (March 5, 2018): 471–80. http://dx.doi.org/10.1108/aeat-06-2015-0151.

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Анотація:

Purpose This paper aims to present an aerothermodynamic analysis of a new concept of a small hypersonic airplane. Aerodynamics characteristics for different flow conditions encountered during the missions are analyzed. The effects of elevons deflection for pitch control and of the presence of engines on aerodynamic performances are also investigated for different flight conditions. The effects of boundary layer laminar–turbulent transition on aerodynamic heating are studied to preliminarily identify proper materials that can sustain the hypersonic phase. Design/methodology/approach Aerodynamic characteristics are predicted by means of the semi-empirical aerodynamic prediction code Missile DATCOM and computational fluid dynamics simulations. Computational fluid dynamics analysis is also performed to investigate aerodynamic heating phenomenon. Findings Major discrepancies between the results offered by the two methods have been registered in transonic regime, whereas in subsonic and super-hypersonic conditions, Missile DATCOM confirms to be a suitable tool for preliminary design steps. The results of the analysis show that for the identification of the materials that can sustain the hypersonic phase, the turbulent solution must be taken into account. Carbon fiber reinforced ceramics composite materials seem particularly well suited for the nose, wing and vertical tail leasing edges and control surfaces, while titanium alloys could be used for the rest of the vehicle surface. Originality/value This new concept of vehicle is designed both for point-to-point medium range hypersonic transportation and long duration suborbital space tourism missions, by integrating available technologies developed for aeronautical and space systems.

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Cresto Aleina, Sara, Nicole Viola, Roberta Fusaro, José Longo, and Giorgio Saccoccia. "Basis for a methodology for roadmaps generation for hypersonic and re-entry space transportation systems." Technological Forecasting and Social Change 128 (March 2018): 208–25. http://dx.doi.org/10.1016/j.techfore.2017.12.004.

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Ferretto, Davide, Roberta Fusaro, and Nicole Viola. "Innovative Multiple Matching Charts approach to support the conceptual design of hypersonic vehicles." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 12 (April 24, 2020): 1893–912. http://dx.doi.org/10.1177/0954410020920037.

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Анотація:

Several well-established best practices and reliable tools have been developed along the years to support aircraft conceptual and preliminary design. In this context, one of the most widely used tool is the Matching Chart (MC), a graphical representation of the different performance requirements (curves representing the thrust-to-weight ratio (T/W) requirement as function of the wing loading (W/S)) for each mission phase. The exploitation of this tool allows the identification of a feasible design space as well as the definition of a reference vehicle configuration in terms of maximum thrust, maximum take-off weight, and wing surface since the very beginning of the design process. Although the tool was originally developed for conventional aircraft, several extensions and updates of the mathematical models have been proposed over the years to widen its application to innovative configurations. Following this trend, this paper presents a further evolution of the MC model to support the conceptual design of high-speed transportation systems, encompassing supersonic and hypersonic flight vehicles. At this purpose, this paper reports and discusses the updates of the methodology laying behind the generation of the MC for high-speed transportation. Eventually, the results of the validation of the updated methodology and tool are reported, using as case study, the STRATOFLY MR3 vehicle configuration, a Mach 8 antipodal civil transportation system, currently under development within the H2020 STRATOFLY project.

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Viola, Nicole, Roberta Fusaro, Valeria Vercella, and Giorgio Saccoccia. "Technology RoadmappIng Strategy, TRIS: Methodology and tool for technology roadmaps for hypersonic and re-entry space transportation systems." Acta Astronautica 170 (May 2020): 609–22. http://dx.doi.org/10.1016/j.actaastro.2020.01.037.

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Bandivadekar, Deep, and Edmondo Minisci. "Modelling and Simulation of Transpiration Cooling Systems for Atmospheric Re-Entry." Aerospace 7, no. 7 (July 1, 2020): 89. http://dx.doi.org/10.3390/aerospace7070089.

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Aerothermodynamic heating is one of the primary challenges faced in progressing towards reliable hypersonic transportation. In the present study, the transpiration cooling method applied to the thermal protection system of re-entry vehicles is investigated. The complexity in analysing the incoming heat flux for re-entry lies not only in the extreme conditions of the flow but also in the fact that the coolant flow through the porous medium needs to be treated appropriately. While the re-entering spacecraft passes through various flow regimes, the peak conditions are faced only near continuum regime. Focusing on these conditions, traditional computational fluid dynamics techniques are used to model transpiration cooling for re-entry vehicles. In the current work, the open source CFD framework OpenFOAM is used to couple two different solvers iteratively and then analyse the thermal response for flow speed conditions typical of re-entry vehicles. Independent computations are performed using the explicit, loosely coupled procedure for high speed argon flow over a 2D axi-symmetrical cylindrical vehicle. The results presented indicate distinct heat flux drop along the surface of the cylindrical vehicle as a function of parameters such as coolant pressure and wall temperature.

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Kumar, SS Satheesh, M. Sudhakara Rao, I. Balasundar, Amit Kumar Singh, T. Raghu, and G. Madhusudhan Reddy. "Compressive behaviour of a nickel superalloy Superni 263 honeycomb sandwich panel." Journal of Sandwich Structures & Materials 22, no. 5 (July 10, 2018): 1426–49. http://dx.doi.org/10.1177/1099636218786438.

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Metallic thermal protection systems comprising of sandwich panels consisting of hexagonal honeycomb sandwich structures are envisaged to be used in advanced transportation systems like hypersonic vehicles and reusable launch vehicles. The assessment of compressive mechanical behaviour is necessary to understand the response of sandwich structures to aerothermal loads. The fabrication methodology for realizing Ni based superalloy Superni 263 hexagonal honeycomb sandwich panels is established. This work is aimed at understanding the effect of sandwich panel geometry parameters like hexagonal cell size and core thickness on the out-of-plane flatwise compressive behaviour at room temperature. The ultimate compressive strength decreases with increasing core height irrespective of the cell sizes investigated. The dependence of specific compressive strength on the cell size is established by a power law relationship. The compressed sandwich panels subjected to understand the deformation behaviour indicated the dominance of cell wall bending and occasional fracture, however in the case of sandwich panels with higher core thickness cell wall buckling coupled with shearing at the face sheet vicinity is noticed.

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Fusaro, R., D. Ferretto, N. Viola, V. Fernandez Villace, and J. Steelant. "A methodology for preliminary sizing of a Thermal and Energy Management System for a hypersonic vehicle." Aeronautical Journal 123, no. 1268 (August 28, 2019): 1508–44. http://dx.doi.org/10.1017/aer.2019.109.

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ABSTRACTThis paper addresses a methodology to parametrically size thermal control subsystems for high-speed transportation systems during the conceptual design phase. This methodology should be sufficiently general to be exploited for the derivation of Estimation Relationships (ERs) for geometrically sizing characteristics as well as mass, volume and power budgets both for active (turbopumps, turbines and compressors) and passive components (heat exchangers, tanks and pipes). Following this approach, ad-hoc semi-empirical models relating the geometrical sizing, mass, volume and power features of each component to the operating conditions have been derived. As a specific case, a semi-empirical parametric model for turbopumps sizing is derived. In addition, the Thermal and Energy Management Subsystem (TEMS) for the LAPCAT MR2 vehicle is used as an example of a highly integrated multifunctional subsystem. The TEMS is based on the exploitation of liquid hydrogen boil-off in the cryogenic tanks generated by the heat load penetrating the aeroshell throughout the point-to-point hypersonic mission. Eventually, specific comments about the results will be provided together with suggestions for future improvements.

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Fusaro, Roberta, Nicole Viola, Marco Fioriti, Davide Ferretto, and Sara Cresto Aleina. "Preliminary design of a cabin escape system for a suborbital vehicle aimed at parabolic flights." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 12 (August 2, 2017): 2179–91. http://dx.doi.org/10.1177/0954410017723671.

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The paper deals with the conceptual design and sizing of a cabin escape system to be applied to a trans-atmospheric transportation system. At first, the role of suborbital vehicles towards the development of a hypersonic transportation system is presented. From this analysis, it has been clear that one of the key points in enhancing the public consensus is to demonstrate a higher level of safety and reliability with respect to the current space vehicles. Since the time of the Space Shuttle enterprise, the development of a proper escape system has been considered crucial to diminish the risk of loss of lives per mission, moving from space-like reliability characteristics to values closer to the aeronautical case. In particular, this paper presents the conceptual design of an escape system for a single stage vehicle aimed at parabolic flights. The proposed design methodology starts with the identification of the major requirements that will lead the design and sizing activities. Then, special attention is devoted to the identification of the required capabilities of a Cabin Escape System and to the selection of the proper subsystems able to guarantee these functionalities. Indeed, considering the high-level of complexity of such a system, during the design process, specific attention should be paid to the impact of on-board systems integration on the overall transportation system architecture and layout. At this purpose, a proper utilization of CAD models can ease the integration process allowing fast verification of mass and volume budgets as well as integrated simulation techniques could be useful. Furthermore, the possibility of exploiting this system during the different phases of the mission should be properly evaluated and, eventually, a preliminary impact risk analysis is reported.

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DOGRA, Bharat Ankur, Mehakveer SINGH, Tejinder Kumar JINDAL, and Subhash CHANDER. "Technological advancements in Pulse Detonation Engine Technology in the recent past: A Characterized Report." INCAS BULLETIN 11, no. 4 (December 8, 2019): 81–92. http://dx.doi.org/10.13111/2066-8201.2019.11.4.8.

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Pulse Detonation Engine (PDE), is an emerging and promising propulsive technology all over the world in the past few decades. A pulse detonation engine (PDE) is a type of propulsion system that uses detonation waves to combust the fuel and oxidizer mixture. Theoretically, a PDE can be operate from subsonic to hypersonic flight speeds. Pulsed detonation engines offer many advantages over conventional air-breathing engines and are regarded as potential replacements for air-breathing and rocket propulsion systems, for platforms ranging from subsonic unmanned vehicles, long-range transportation, high-speed vehicles, space launchers to space vehicles. This article highlights the operating cycle of PDE, starting with the fuel-oxidizer mixture, combustion and Deflagration to detonation transition (DDT) followed by purging. PDE combustion process, a unique process, leads to consistent and repeatable detonation waves. This pulsed detonation combustion process causes rapid burning of the fuel-oxidizer mixture, which cannot be seen in any other combustion process as it is a thousand times faster than any other mode of combustion. PDE not only holds the capability of running effectively up to Mach 5 but it also changes the technicalities in space propulsion. The present paper is the extension of the previous study which is also a well characterized status report of PDE in different areas. The present study deals with the categorization of the design approach, computations & simulations, flow visualization, DDT & Thrust enhancement, PDRE’s, experimental detonation engines with some of the experience and research undertaken in Punjab Engineering College under the complete supervision and guidance of Prof. Tejinder Kumar Jindal followed by applications of PDE technology.

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Gaglio, Emanuela, Michele Visone, Marco Lanzetta, Stefano Mungiguerra, Anselmo Cecere, and Raffaele Savino. "Mixed-Compression Supersonic Intake and Engine–Airframe Integration." Journal of Spacecraft and Rockets, March 1, 2023, 1–12. http://dx.doi.org/10.2514/1.a35532.

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Hypersonic flight is gaining increasing attention by aerospace companies interested in designing and developing reusable aircraftlike vehicles (spaceplanes). Advanced concepts include a combination of space and aviation approaches able to fly few minutes in space for sightseeing or fast enough to enable point-to-point transportation. In this framework, a concept of hypersonic systems for space travel and high-speed transportation is presented, with a particular focus on the intake and engine–airframe configurations. The adopted intake is designed to ensure an efficient functioning, not only in nominal conditions but along the supersonic ascent trajectory thanks to a movable inner spike. A nonzero angle of attack resulted in a little degradation of the performances in terms of efficiency, spillage, and flow distortion. In the second part, the interaction between the engine and airframe is also investigated. An initial configuration, characterized by the propulsion system located on the fuselage side near the wing, is characterized by a strong interference responsible for an off-design functioning with a high percentage of air spillage. An alternative solution with engine–wing integration exhibits a completely different behavior with interference minimized, resulting in a design intake functioning without air spillage and a considerable drag reduction.

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