MBSE approach to support and formalize mission alternatives generation and selection processes for hypersonic and suborbital transportation systems

Fusaro, Roberta; Ferretto, Davide; Viola, Nicole

doi:10.1109/syseng.2017.8088275

Cited by 11 publications

(7 citation statements)

References 8 publications

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“…Mission simulation [36,37] is run at the end of each iteration, considering the highestfidelity aerodynamic data available at each design step. The software ASTOS (release 9.17), by Astos Solutions GmbH (Stuttgart, Germany), is used to perform the simulations.…”

Section: Mission Simulationmentioning

confidence: 99%

Aerodatabase Development and Integration and Mission Analysis of a Mach 2 Supersonic Civil Aircraft

Roncioni,

Marini,

Gori

et al. 2024

Aerospace

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The request for faster and greener civil aviation is urging the worldwide scientific community and aerospace industry to develop a new generation of supersonic aircraft, which are expected to be environmentally sustainable and to guarantee a high-level protection of citizens. A key aspect to monitor the potential environmental impact of new configurations is the aerodynamic efficiency and its impact onto the real mission. To pursue this goal, this paper discloses increasing-fidelity aerodynamic modeling approaches to improve the conceptual design of high-speed vehicles. The disclosed methodology foresees the development of aerodynamic aerodatabases by means of incremental steps starting from simplified methods (panels methods and/or low-fidelity CFD simulations) up to very reliable data based on high-fidelity CFD simulations and experimental measurements with associated confidence levels. This multifidelity approach enables the possibility of supporting the aircraft design process at different stages of its design cycle, from the estimation of preliminary aerodynamic coefficients at the beginning of the conceptual design, up to the development of tailored aerodatabases at advanced design phases. For each design stage, a build-up approach is adopted, starting from the investigation of the clean external configuration up to the complete one, including control surfaces’ effects and, if any, the effects of the integration of the propulsive effects. In addition, the applicability of the approach is guaranteed for a wide range of supersonic and hypersonic aircraft, and the developed methodology is here applied to the characterization of Mach 2 aircraft configuration, a relevant case study of the H2020 MORE&LESS project.

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Section: Mission Simulationmentioning

confidence: 99%

Aerodatabase Development and Integration and Mission Analysis of a Mach 2 Supersonic Civil Aircraft

Roncioni,

Marini,

Gori

et al. 2024

Aerospace

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“…The mission design methodology adopted in this paper follows the guidelines of the model-based approach of Refs. [42,43]. The approach is highly oriented toward both functional analysis [42,44,45], and scenario-based assessments [46,47].…”

Section: An Mbse Approach To Mission Designmentioning

confidence: 99%

“…The described conceptual design methodology stemming from Refs. [42,43] has been used to define the mission objectives and constraints, to provide a first design box for the cave explorer, and to identify the mission architecture that will enable the lava tube exploration. These higher-level results will be briefly presented and discussed before diving into the parametric design of the cave explorer.…”

mentioning

confidence: 99%

Integrated Conceptual Design and Parametric Control Assessment for a Hybrid Mobility Lunar Hopper

Rimani

Bucchioni²,

Ryals³

et al. 2023

Aerospace

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The lunar lava tubes are envisioned as possible hosting structures for a human base in the Moon’s equatorial regions, providing shelter from radiations, micrometeoroids, and temperature excursion. A first robotic mission is set to scout the habitability of these underground architectures in the near future. The communication inside these underground tunnels is heavily constrained; hence, the scouting system should rely on a high degree of autonomy. At the same time, the exploration system may encounter different types of terrain, requiring an adaptable mobility subsystem able to travel fast on basaltic terrain while avoiding considerable obstacles. This paper presents a cave explorer’s mission study and preliminary sizing targeting the lunar lava tubes. The study proposes using a hybrid mobility system with wheels and thrusters to navigate smoothly inside the lava tubes. The peculiar mobility system of the cave explorer requires an accurate study of the adaptability of its control capabilities with the change of mass for a given set of sensors and actuators. The combination of conceptual design techniques and control assessment gives the engineer a clear indication of the feasible design box for the studied system during the initial formulation phases of a mission. This first part of the study focuses on framing the stakeholders’ needs and identifying the required capabilities of the cave explorer. Furthermore, the study focuses on assessing a design box in terms of mass and power consumption for the cave explorer. Following different mission-level assessments, a more detailed design of the cave explorer is discussed, providing an initial design in terms of mass and power consumption. Finally, the objective shifts toward studying the performances of the guidance, navigation, and control (GNC) algorithms varying the mass of the cave explorer. The GNC significantly impacts the design box of the surface planetary system. Hence, investigating its limitations can indicate the feasibility of mass growth to accommodate, for example, more payload.

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“…Thus, this work has identified the potential areas for fuel consumption reduction, and research studies looked at historical facts about fuel consumption in the aviation sector (Seitz et al , 2021) are shown in Figure 2. Fusaro et al (2017a) emphasized and discussed model-based systems engineering, focusing on significant operational and technology constraints of air transport systems. Yanto and Liem (2018) have applied two-dimensional linear regression models, by using flight missions on different aircraft at certain gross weight (MTOW) and range (R).…”

Section: Introductionmentioning

confidence: 99%

Assessment on fuel economy of MoM transport aircraft using empirical approach: modelling with a case study

Dhara

Jeyan

2023

AEAT

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Purpose This research is associated with the real-time parameters of wide- and narrow-body aircraft to recognize the quantitative relationship framework. This paper aims to find the superiority of aircraft design technology which triggers the reduction in specific fuel consumption (SFC) and economic competitiveness. Design/methodology/approach The real case study is performed with 22 middle-of-the-market (MoM) aircraft. This paper develops a fuel burn mathematical model for mid-size transport aircraft by a multi-linear regression approach. In addition, sensitivity analysis is performed to establish the authentication of the fuel burn model. Findings The study reveals that the MoM aircraft would be the future aircraft design in terms of better fuel economy and carbon footprint. From the multi-regression analysis, it is observed that the logarithmic regression model is the best fit for estimating the SFC. Moreover, fineness ratio, aspect ratio, gross weight, payload weight fraction, empty weight fraction), fuel weight fraction, payload, wing loading, thrust loading, range, take-off distance, cruise speed and rate of climb are observed as the suitable parameters which provide the best fitness value as 0.9804. Originality/value Several existing literature reveals that a few research has been performed on the MoM aircraft with wide-body configuration. Moreover, mathematical modelling on the fuel consumption was insignificantly found. This study examines several parameters which affect the fuel consumption of a wide-body aircraft. A real-case study for design configurations, propulsive systems, performance characteristics and structural integrity parameters of 22 different MoM aircraft are performed. Moreover, multi-regression modelling is developed to establish the relation between SFC and other critical parameters.

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MBSE approach to support and formalize mission alternatives generation and selection processes for hypersonic and suborbital transportation systems

Abstract: MBSE approach to support and formalize mission alternatives generation and selection processes for hypersonic and suborbital transportation systems ieee Publisher:

Cited by 11 publications

References 8 publications

Aerodatabase Development and Integration and Mission Analysis of a Mach 2 Supersonic Civil Aircraft

Aerodatabase Development and Integration and Mission Analysis of a Mach 2 Supersonic Civil Aircraft

Integrated Conceptual Design and Parametric Control Assessment for a Hybrid Mobility Lunar Hopper

Assessment on fuel economy of MoM transport aircraft using empirical approach: modelling with a case study

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