4,041 research outputs found
Nicole Kootz, viola, March 31, 2015
No full textThis is the concert program of the Nicole Kootz, viola performance on Tuesday, March 31, 2015 at 8:30 p.m., at the Marshall Room, 855 Commonwealth Avenue. Works performed were Concerto for Viola and Orchestra by William Walton, Waltz for Betz by James Grant, and Suite No. 1 by Johann Sebastian Bach. Digitization for Boston University Concert Programs was supported by the Boston University Humanities Library Endowed Fund
Nicole Kootz, viola, May 4, 2016
No full textThis is the concert program of the Nicole Kootz, viola performance on Wednesday, May 4, 2016 at 8:30 p.m., at the Marshall Room, 855 Commonwealth Avenue. Works performed were Cello Suite No. 4 in Eb major by Johann Sebastian Bach, Djembach, Suite for Solo Viola and Percussion by Christian Woehr, and Sonata in F minor, Op. 120 No. 1 by Johannes Brahms. Digitization for Boston University Concert Programs was supported by the Boston University Humanities Library Endowed Fund
A Viola Recital (Nicole Jordan) Program (2007-04-29)
No full textUniversity of Minnesota Duluth. Department of Music. (2007). A Viola Recital (Nicole Jordan) Program (2007-04-29). Retrieved from the University Digital Conservancy, https://hdl.handle.net/11299/263379
Preliminary Design and Simulation of a Thermal Management System with Integrated Secondary Power Generation Capability for a Mach 8 Aircraft Concept Exploiting Liquid Hydrogen
No full textThis paper introduces the concept of a thermal management system (TMS) with integrated on-board power generation capabilities for a Mach 8 hypersonic aircraft powered by liquid hydrogen (LH2). This work, developed within the EU-funded STRATOFLY Project, aims to demonstrate an
opportunity for facing the challenges of hypersonic flight for civil applications, mainly dealing with thermal and environmental control, as well as propellant distribution and on-board power generation, adopting a highly integrated plant characterized by a multi-functional architecture.
The TMS concept described in this paper makes benefit of the connection between the propellant storage and distribution subsystems of the aircraft to exploit hydrogen vapors and liquid flow as the means to drive a thermodynamic cycle able, on one hand, to ensure engine feed and thermal
control of the cabin environment, while providing, on the other hand, the necessary power for other on-board systems and utilities, especially during the operation of high-speed propulsion plants, which cannot host traditional generators. The system layout, inspired by concepts studied within
precursor EU-funded projects, is detailed and modified in order to suggest an operable solution that can be installed on-board the reference aircraft, with focus on those interfaces impacting its performance requirements and integration features as part of the overall systems architecture of
the plane. Analysis and modeling of the system is performed, and the main results in terms of performance along the reference mission profile are discussed
Preliminary reliability and safety assessment methodology for trans-atmospheric transportation systems
No full text
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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Advanced European Re-Entry System Based on Inflatable Heat Shields Technology Roadmap and Technical challenges (EFESTO project)
No full textThe payload capability and the landing sites for Mars exploration missions may be boosted using inflatable decelerators. Similarly, these may allow recovering launcher upper stages for Earth re-entry enabling reusability. The EFESTO project, funded by the European Union programme H2020, aims at raising the European TRL of Hypersonic Inflatable Aerodynamic Decelerators. It includes design, development, and test for the flexible TPS (F-TPS) and the inflatable structures of the heat shield for atmospheric entry missions, as well as validation of tools used in the project. The project culminates with the design of an In-Orbit Demonstration (IOD) mission, setting the basis for a technology development programme. Within EFESTO, the technology roadmap, planning the necessary development activities, is generated to support the European strategic decisions in this field. A rational and logical methodology is proposed for the technology roadmap generation, considering the robustness of the result and the influence of the chosen parameters through sensitivity analysis. Multi-attribute theories are considered and implemented to include features of different nature and the preference among them. An ad hoc database of the past, present, and planned efforts in the field of atmospheric entry systems is developed and implemented in the process. The technology roadmap defined responds to the multiple technical challenges identified in the different disciplines involved: system aspects, addressing geometric and functional integration of critical uncommon sub-systems as the F-TPS and the inflatable structure in folded state, concerning the available volume and cross-section, and during re-entry conditions in consideration of the centre of gravity position and related impact on flight stability and control; aerothermodynamic aspects, strong fluid-structure interactions along the atmospheric entry which are critical for the TPS design; materials and structures aspects related with not yet matured technologies including the design of a flexible thermal protection sheet able to withstand the peak heat fluxes experienced during entry, as well as a suitable underlying inflatable structure that allows maintaining the optimal aerodynamic shape during the entirety of the mission; mission and GNC aspects, controlled entry on Earth combined with parafoil descent and Mid-Air Retrieval and ballistic entry combined with supersonic retro propulsion for Mars. Purpose of this paper is to propose a methodology to define the technology roadmap for a hypersonic inflatable aerodynamic decelerator, addressing the main technical challenges and giving the incremental technology development to cope with them. This project has received funding from the European Union’s Horizon 2020 research and innovation programme under grant agreement No 821801
Cost Estimation for Innovative Space Systems: A Methodology for Microlaunchers and Inflatable Heatshields
No full textCost estimation for innovative space systems, such as microlaunchers and inflatable heatshields, presents significant challenges due to the lack of historical data and their complex and novel nature. In this study, a cost estimation methodology for these systems was developed, which is based on the assumption that there may be similarities in the development and manufacturing costs among these systems. The cost estimation methodology for microlaunchers considers the cost drivers at the subsystem level and the commercial nature of these systems. The methodology provides a tool for assessing the feasibility and profitability of microlauncher projects. The methodology for inflatable heatshields adapts the cost estimation methodology used for microlaunchers to account for the innovative nature of this technology. The methodology estimates the development and manufacturing costs of inflatable heatshields for future missions. The research activity was part of various research projects, including collaborations with the European Space Agency (ESA) and projects funded by the European Commission in H2020 and Horizon Europe programs. Overall, the cost estimation methodology for microlaunchers and inflatable heatshields provides a useful tool for assessing the feasibility and profitability of innovative space projects. The methodology can help provide rough estimates of costs, and its application can inform decision-making processes and improve the affordability of future space missions
Voice Recital: Nicole Baker, Stephanie Milazzo and Caitlin Smith
No full textThis program was produced by the Rhodes Dept of Music.Sopranos Nicole Baker, Stephanie Milazzo, and Caitlin Smith performed a combined voice recital in Tuthill Performance Hall/Hassell Hall, accompanied by Andrew Drannon, piano. Other performers on the program were Nicole Baker, flute; Josie Holland, viola; Will Lang, guitar; and Fred Lankford, baritone
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