Innovative Multiple Matching Charts approach to support the conceptual design of hypersonic vehicles

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

Propellant subsystem design for hypersonic cruiser exploiting liquid hydrogen

The possibility of establishing a new paradigm for commercial aviation towards high-speed flight in the next decades shall be inevitably preceded by the increase of Technology Readiness Level for those relevant enabling technologies associated to propulsion, thermal management and on-board subsystems, with particular attention also to environmental sustainability and economic viability of the proposed concepts. New design methodologies for both aircraft and on-board subsystems design shall then be based on holistic approaches able to catch the strong interactions between vehicle configuration, mission and subsystems architecture, which characterize high-speed aircraft layouts. This paper proposes a methodology for the preliminary sizing of propellant subsystems for liquid hydrogen powered hypersonic cruisers. Making benefit of traditional approaches, the process aims at introducing new design aspects directly connected to the peculiar multifunctional architecture of on-board subsystems for high-speed vehicles, so to be able to include additional analyses in early design stages, especially in case of high level of on-board integration. Notably, impact of requirements for Center of Gravity control, thermal, and, in general, energy management are considered as integral part of the method, with crucial implications on architecture selection. After the introduction of design algorithms for subsystem sizing, the STRATOFLY MR3 hypersonic cruiser is taken as reference case study in order to provide a practical example of application of the proposed approach on a highly integrated platform

Systems Engineering and Its Application to Industrial Product Development

PREFACE : Mastering the complexity of innovative systems currently looks a challenging goal of design and product development as well as embedding a suitable degree of smartness in devices, machines and equipment to make them able of adapting their operation to variable conditions or effects of a harsh environment. This goal is achieved through a continuous monitoring of the system in service, an effec-tive control of its behavior and a wide connectivity towards many other systems. Only an effective system design and manufacture, able to cover all the required actions, can assure this kind of assessment overall the life cycle since a very ear-ly concept of the product to a full disposal and service. Complexity makes hard managing the product development, because of the number of functions, subsystems, components and related interfaces usually in-volved, like in motor vehicles, robots, railways systems, aircrafts and spacecrafts as well as in large industrial manufacturing systems or very innovative microsys-tems and bioinspired devices. A crucial issue in this activity is performing a bright and complete elicitation of requirements, which need to be fully and suit-ably allocated to the system components, through a clear traceability, especially in systems produced as a result of material processing and assembling of parts. Moreover, the product must fit the requirements associated to some customer needs, innovation targets, and technical standards and be compatible with the manufacturer’s capabilities. As it looks clear from the current state–of–art, since several years the Systems Engineering assures a suitable answer to the needs above mentioned. It provides a methodology to drive the product lifecycle assessment that is implemented through a well defined process, being based on some specific and graphical lan-guages and even formalized in several tools enabling the required analyses, tak-ing advantage of the capabilities of some dedicated commercial software. Those contents lead to create a platform, consisting of a sort of tools chain, which might be used and shared among different industrial and professional partners to digitalize both the information and even the whole industrial product develop-ment, as far as the current strategy referred to as “Industry 4.0 / The Factory of the Future” brightly suggests and supports. The so–called Model Based Systems Engineering (MBSE) is then successfully proposing an effective and modern al-ternative to the document-based approach, using data models as a main element of the design process. Some technical standards already drive the user in imple-menting the Systems Engineering, thus leading to develop a systematic approach the design aimed at satisfying the customer needs. Suitable capabilities in the manufactured system are assured by the so–called architectural frameworks, which support the system development and integration. The Model Based Systems Engineering allows proceeding with a modeling activity which investigates requirements, behavior and architecture through a combined operational, functional and logical analysis, being linked and interop-erated with a mathematical and physical modeling, which is typically more known and widely used within the industrial engineering. A full integration of all the activities of the Product Lifecycle Management (PLM) is currently going on, to include the system architecture definition and its Application Lifecycle Man-agement (ALM) as well as the Product Data Management (PDM), i.e. the design activity together with the tasks of production, testing, homologation and service. A recognized standard certification to qualify the Systems Engineer is even available as the International Council on Systems Engineering (INCOSE) pro-vides. The scenario above described is strongly integrated with the increasing devel-opment of both the network and the cyber–physical systems, for a fully distribut-ed connectivity, to be exploited in advanced smart systems and devices as well as in intelligent manufacturing, according to the most recent strategies of innova-tion as the “Industry 4.0” initiative and the “Lean manufacturing” idea. Simulta-neously, the system smartness and connectivity together increase the demand of data transmission and elaboration, thus linking this topic to the technology of big data management, whilst they benefit of the progress in information technology, through a secure cloud based on the network. The context just described motivates the fast diffusion of the Model Based Systems Engineering as a tool for innovating all the production processes. The increasing demand of specialized software and of educational activities as well as the number of workshops and conferences focused on this topic confirm this trend. However, it might be remarked that several contributions to the literature about the Systems Engineering widely grew up during the last years, thus making the Reader sometimes confused, especially when approaching this topic at first. The Systems Engineering topics are so many that it looks rather difficult mas-tering its skills, without a preliminary classification of contents. Technical do-mains involved are mainly those of engineering and computer science, although many other ones play the role of a daily user of this methodology. According to the most recent development of the Systems Engineering, whose typical applica-tion fields were the software and electronic systems even for space missions, the current focus consists of several industrial systems, being gradually innovated by introducing the tailored solutions of mechatronics. It is worthy noticing that a significant advancement was introduced between the very early implementation of the Systems Engineering and its recent evolution, since several new applica-tions are focused on the production of systems, which need to be manufactured through a material processing. Usually, they exhibit some attributes related both to their physical nature and to the functions performed, thus requiring to model both their functional and physical behaviors together. This need is changing the scenario of the typical applications of the Systems Engineering as software de-sign. This handbook expressively avoids to cover all the typical contents of the spe-cialized literature of the Model Based Systems Engineering, whilst is aimed at making easier a first approach to this topic and sharing a preliminary experience performed by the authors within some industrial domains, by proceeding in the modeling activity in a real industrial environment. The main goal is drawing a sort of simple and hopefully clear roadmap in modeling and developing the in-dustrial and material systems and in implementing the Systems Engineering, par-ticularly in the design activity. Therefore, the target audience of this handbook includes professional engineers, scientists and students dealing with the Applica-tion Lifecycle Management and the system architecture assessment, more than the Product Data Management or the whole Product Lifecycle Management. The approach followed is that of introducing some examples of implementa-tion of the Systems Engineering, by proceeding step by step from the screening of needs and the elicitation of requirements till a synthesis of the system design. Each action will be referred to the literature, related to the implementation of the Systems Modeling Language or SysML and to the use of some tools available on market, thus highlighting benefits, drawbacks and current limitations of some dedicated software or even of some proposed methodologies. Several comments will be provided to describe the troubles shared among some users of the Sys-tems Engineering as they were detected in daily practice by the authors. They wish that this handbook could briefly and gradually provide the Reader with a preliminary guideline to approach professionally the Model Based Systems En-gineering, by understanding its main contents and applying it to the industrial environment. As a desired result, this work might be considered as an integration of some textbooks of Machine Design, and it is aimed at completing the education within Engineering Design or at simply providing a friendly introduction to the Systems Engineerin

Cost estimation methodology and tool for future Reusable Access To Space Systems

This paper aims at presenting the latest upgrades to HyCost Methodology and Tool, developed by Politecnico di Torino under funding and supervision of the European Space Agency (ESA), to support Life Cycle Cost (LCC) estimation of reusable access to space vehicles. The main idea is to support engineers in cost estimation activities during conceptual and preliminary design phases, allowing for the evaluation of Research, Development, Test and Evaluation (RDTE) Costs, Production Costs, as well as Direct and Indirect Operating Costs (DOC and IOC), for a wide set of high-speed aerospace systems. Politecnico di Torino has already disclosed a LCC methodology and tool specifically tailored to air-breathing high-speed transportation systems. Complementary, this paper discloses the methodology upgrades to extend the methodology and tool capabilities to future Reusable Access to Space Vehicles. At first, the applicability of already existing parametric cost estimation relationships (CERs) to the peculiarities of Reusable Access to Space Vehicles is assessed and then, when necessary, new parametric equations are defined. Specifically, the new set of equations is considered fundamental to capture the impact of different vehicle configurations (e.g. staging strategy, staging Mach number, parallel or series configuration, etc…) onto costs, as well as the impact of the most promising propulsive solutions, ranging from scramjet and combined cycle engines to rocket engines. Ultimately, the upgraded methodology is validated against the available SpaceX Starship cost data

Progettazione di sistemi complessi tramite il ‘Systems Engineering’ e interoperabilità tra modelli funzionali e numerici

La crescente richiesta del mercato verso prodotti intelligenti, capaci di adattarsi autonomamente a condizioni di esercizio variabili, motiva l’incremento di complessità di molti sistemi. Il ‘Systems Engineering’ si propone come efficace metodologia per affrontare il problema dello sviluppo e della gestione di sistemi complessi. I modelli che introduce si soffermano, infatti, sull’analisi dei requisiti e degli scenari operativi e sulla preliminare definizione di blocchi funzionali e di architetture del sistema che prescindono dai componenti utilizzabili, per permettere un’ottimizzazione della configurazione. Questo lavoro propone una panoramica del metodo applicato a due casi, di ambito meccatronico e aeronautico, esponendo come le attività di modellazione numerica e funzionale si integrano tra loro, anche a livello di software, per raggiungere la cosiddetta interoperabilità tra strumenti di lavoro

A methodology for preliminary sizing of a Thermal and Energy Management System for a hypersonic vehicle

This 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

A methodology for preliminary sizing of a Thermal and Energy Management System for a hypersonic vehicle

This paper addresses a methodology to parametrically size thermal control subsystems for high-speed transportation systems. 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 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, all along the point-to-point hypersonic mission. Eventually, specific comments about the results will be provided together with suggestions for future improvements

Sviluppo di tecniche di simulazione eterogenea funzionale e numerica applicate all’ingegneria di sistemi aeronautici

Questo studio illustra l’impiego del ‘Model Based Systems Engineering’ (MBSE), in cui strumenti di modellazione funzionale si integrano con modelli numerici, da tempo impiegati in progettazione, per la realizzazione di sistemi complessi. E’ analizzato un sistema antighiaccio aeronautico, sviluppato nell’ambito del progetto ‘CRYSTAL’. L’obiettivo è stato raggiunto collegando il gestore di requisiti IBM DOORS®, IBM RHAPSODY®, che opera in ambiente SysML, e SIMULINK® o DYMOLA®. L’interoperabilità è stata garantita dallo standard di connessione Functional Mock–up Interface (FMI), che ha permesso di validare il processo realizzando la cosiddetta ‘simulazione eterogenea’ di modelli funzionali e numerici integrati

Single hadron response measurement and calorimeter jet energy scale uncertainty with the ATLAS detector at the LHC

The uncertainty on the calorimeter energy response to jets of particles is derived for the ATLAS experiment at the Large Hadron Collider (LHC). First, the calorimeter response to single isolated charged hadrons is measured and compared to the Monte Carlo simulation using proton-proton collisions at centre-of-mass energies of sqrt(s) = 900 GeV and 7 TeV collected during 2009 and 2010. Then, using the decay of K_s and Lambda particles, the calorimeter response to specific types of particles (positively and negatively charged pions, protons, and anti-protons) is measured and compared to the Monte Carlo predictions. Finally, the jet energy scale uncertainty is determined by propagating the response uncertainty for single charged and neutral particles to jets. The response uncertainty is 2-5% for central isolated hadrons and 1-3% for the final calorimeter jet energy scale.Comment: 24 pages plus author list (36 pages total), 23 figures, 1 table, submitted to European Physical Journal