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Aircraft Plenum Air Outlet Optimization Method

Embraer-Fernando Stancato
  • Technical Paper
  • 2020-01-0021
To be published on 2020-03-10 by SAE International in United States
It is possible to observe a growing interest by mobility industry toward a increased passenger comfort perception. This tendency is being characterized in the aviation sector by interior project that would guarantee the passenger comfort in entertainment, ergonomics, lightning, air quality, acoustics and thermal environment. Regarding this last three aspects, the air distribution through the plenum has a great impact on them. In this work it is presented a method to select the best outlet orifice configuration. The method was applied on seven different plenums. Acoustic evaluation was done using a rig experiment. Based on noise levels of each configuration, the dominant frequency range is identified. Objectives metrics, such as overall levels, speech interference level (SIL3) and loudness were applied. Subsequently, subjective analysis was conducted using the paired comparison method. Finally, an acoustic performance classification was established. Draft effect and air temperature distribution inside the cabin was done using CFD simulation. Besides that, a one-dimensional duct model was done for each configuration to evaluate plenum velocity and pressure distribution. Through these models, it was possible…
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System integration in aircraft environment – Hydraulic performances through coupled simulations

Airbus Operations GmbH-Henning Witt lng
Airbus Operations India-Ashutosh Singh
  • Technical Paper
  • 2020-01-0004
To be published on 2020-03-10 by SAE International in United States
An Airbus methodology for the assessment of accurate hydraulic performance at early program stages in the complete aircraft and power consuming systems environment based on joint collaboration with Chiastek is presented. The aim is to comfort the prediction of an aircraft hydraulic performance in order to limit the need for a physical integration test bench and extensive flight test campaign but also to avoid late system redesign based on robust early stage model based engineering and to secure the aircraft entry-into-service
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Introduction to Control Volume Based Transient Thermal Limit

Army Corps Of Engineers-Mark Bodie
PC Krause & Associates-Rodney Yeu, Tim Deppen, Brian Raczkowski, Nicholas Jones, Eric Walters
  • Technical Paper
  • 2020-01-0039
To be published on 2020-03-10 by SAE International in United States
Advancement in modern aircraft with the development of more dynamic and efficient technologies has led to these technologies increasingly operated near or at their operation limits. More comprehensive analysis methods based on high-fidelity models co-simulated in an integrated environment are needed to support the full utilization of these advanced technologies. Furthermore, the additional information provided by these new analyses needs to be correlated with updates to traditional metrics and specifications. One such case is the thermal limit requirement that sets the upper bound on a thermal system temperature. Traditionally, this bound is defined based on steady-state conditions. However, advanced thermal management systems experience dynamic events where the temperature is not static and may violate steady-state requirements for brief periods of time. Due to the large thermal time constants for many components, such transient violations may not represent system failure and an understanding of transient temperature limits is beneficial. To meet this need, this paper introduces the transient thermal limit via control volume representation. Instead of a constant thermal limit, the transient thermal limit approach generates…
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A Systematic Approach to Development Assurance and Safety of Unmanned Aerial Systems

Textron Aviation-Cory R. Laflin
  • Technical Paper
  • 2020-01-0043
To be published on 2020-03-10 by SAE International in United States
The unrestrained design space for unmanned aerial systems (UAS) presents challenges to accurate safety assessment and the assurance of development to appropriate levels of rigor within those systems. The established safety and development assurance standards and practices were developed for vehicles operating in highly controlled conditions with continuous oversight. The very nature of unmanned systems introduce new failure conditions, even in those systems operating within the strict rules of the National Airspace System (NAS), particularly failures of control and command, situational awareness, and control security. Beyond those, the new concepts of operation being conceived by UAS developers introduce their own new set of considerations with regards to operating in uncontrolled airspace, often in close proximity to bystanders. These new concepts require new technologies beyond those currently supported by the hardware and software development assurance processes. However, the established standards and practices of aircraft development assurance and safety assessment can be adapted for the broader world of UAS applications, provided that the considerations driven by the new concepts of operation can be identified and properly analyzed.…
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Extended Endurance Unmanned Aerial Vehicle via Structural Electrical Power Storage and Energy Generation Devices

Geoffrey Smith Oetting
  • Technical Paper
  • 2020-01-0041
To be published on 2020-03-10 by SAE International in United States
Through the substitution of some aircraft structural components with power storage and generation devices that possess adequate structural strength and stiffness, flight endurance time and performance of solar powered unmanned aerial vehicles (UAV’s) may be increased by reducing the parasitic weight penalties of the power systems. This innovation of the ‘Flying Battery’ along with energy generation devices such as structural solar cells, thermo-electric generators, and vibration induced power generators are integral to creating a flying structure that will be more efficient and more useful to the electric powered commercial and hobby markets. This paper discusses plans and the progress toward achieving potential endurance and efficiency increases in unmanned aerial vehicles through laboratory and eventual model flight experiments of novel structural designs for graphene super-capacitors, solar cells, and other power generation devices.
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A MATLAB Simulink Based Co-Simulation Approach for Vehicle Systems Model Integration

Army Corps Of Engineers-Mark Bodie
PC Krause & Associates-Brian C. Raczkowski, Nicholas Jones, Tim Deppen, Charles Lucas, Rodney Yeu, Eric Walters
  • Technical Paper
  • 2020-01-0005
To be published on 2020-03-10 by SAE International in United States
In this paper, a MATLAB-Simulink based general co-simulation approach is presented which supports multi-resolution simulation of distributed models in an integrated architecture. This approach was applied to simulating aircraft thermal performance in our Vehicle Systems Model Integration (VSMI) framework. A representative advanced aircraft thermal management system consisting of an engine, engine fuel thermal management system, aircraft fuel thermal management system and a power and thermal management system was used to evaluate the advantages and tradeoffs in using a co-simulation approach to system integration modeling. For a system constituting of multiple interacting sub-systems, an integrated model architecture can rapidly, and cost effectively address technology insertions and system evaluations. Utilizing standalone sub-system models with table-based boundary conditions often fails to effectively capture dynamic subsystem interactions that occurs in an integrated system. Additionally, any control adjustments, model changes or technology insertions that are applied to any one of the connecting subsystems requires iterative updates to the boundary conditions. When evaluating a large set of trade studies, the number of boundary condition models and time to generate these models…
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A Study on the development of Aerostructures Design for Assembly guidelines and their effective use to proactively identify opportunities for improvement in mitigating common defects of the Aerostructures Assembly.

GITAM School of Technology, Hyderabad-Mani Rathinam Rajamani, Eshwaraiah Punna
  • Technical Paper
  • 2020-01-0009
To be published on 2020-03-10 by SAE International in United States
An Aircraft’s assembly process plays a vital part in its design, development and production phases and contributes to about half of the Total cost spent in its entire product lifecycle. DFA principles have been one of the proven effective methodologies in Automotive and Process industries. Use of DFA principles have resulted in proactively simplifying and optimizing engineering designs with reduced product costs, and improved inefficiencies in product design and performance. Standardization of Assembly guidelines is vital for “Design and Build” and “Build-To-Print” manufacturing supplier organizations. However, Standardizing design methodologies, through use of proven tools like Advanced Product Quality Planning, (APQP) are still in the initial stages in Aerospace part and process design processes. Thus, there is a tremendous opportunity for research on the application of the existing DFA guidelines to optimize Engineering Aerospace Assembly processes aiming to simplify, standardize design methodologies by building on existing industry practices which have a common platform for design communication and are easy to adopt within the existing process/systems. This technical paper is to discuss the framework for application of…
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A communication-free Human-Robot-Collaboration approach for aircraft riveting process using AI planning

Saarland University-Jörg Hoffmann
ZeMA gGmbH-Khansa Rekik, Rainer Mueller, Matthias Vette
  • Technical Paper
  • 2020-01-0013
To be published on 2020-03-10 by SAE International in United States
In large scale industries attempts are continuously being made to automate assembly processes to not only increase productivity but also alleviate non-ergonomic tasks. However this is not always technologically possible due to specific joining challenges and the high number of special-purpose parts. For the riveting process, for example, semi-automated approaches represent an alternative to optimizing aircraft assembly and to reduce the exposure of workers to non-ergonomic conditions entailed by performing repetitive tasks. In (Mueller, Rainer, et al. 2019) a semi-automated solution is proposed for the riveting process of assembling the section barrel of the aft section to its pressure bulkhead. The method introduced a dynamic task sharing strategy between human and robot that implements interaction possibilities to establish a communication between a human and a robot in Human-Robot-collaboration fashion. Although intuitive, interacting with the robot constantly is still not natural for the worker as in the manual process no explicit communication between both workers is needed. In this work a communication-free Human-Robot-collaboration solution is presented. The method developed not only enables sharing assembly missions by…
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Optimal Sizing and Control of Battery Energy Storage Systems for Hybrid Turbo-Electric Aircraft

Georgia Institute of Technology-Christopher Perullo
Ohio State University-Aaronn Sergent, Michael Ramunno, Matilde D'Arpino, Marcello Canova
  • Technical Paper
  • 2020-01-0050
To be published on 2020-03-10 by SAE International in United States
Hybrid-electric gas turbine generators are considered a promising technology for more efficient and sustainable air transportation. The Ohio State University is leading the NASA University Leadership Initiative (ULI) Electric Propulsion: Challenges and Opportunities, focused on the design and demonstration of advanced components and systems to enable high-efficiency hybrid turboelectric powertrains in regional aircraft to be deployed in 2030. Within this large effort, the team is optimizing the design of the battery energy storage system (ESS) and, concurrently, developing a supervisory energy management strategy for the hybrid system to reduce fuel burn while mitigating the impact on the ESS life. In this paper, an energy-based model was developed to predict the performance of a battery-hybrid turboelectric distributed-propulsion (BHTeDP) regional jet. A study was conducted to elucidate the effects of ESS sizing and cell selection on the optimal power split between the turbogenerators (TGs) and ESS. To this extent, the supervisory energy management strategy is formulated into a discrete time optimal control problem and solved via dynamic programming. The performance of BHTeDP was compared to a turboelectric…
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Adaptive Test Feedback LoopA Modelling Approach for Checking Side Effects During Test Executionfor Advised Explorative Testing

Bremer Inst. Für Produktion Und Logistik-Marco Franke, K. A. Hribernik
University of Bremen-K. D. Thoben
  • Technical Paper
  • 2020-01-0017
To be published on 2020-03-10 by SAE International in United States
The main objective of testing is to evaluate the functionality, reliability, and operational safety of products. However, this objective makes testing a complex and expensive stage in the development process. This is particularly true for complex and large systems, such as trains or aircrafts, which require maximum operational safety. From the perspective of an aircraft manufacturer, the checks are carried out via test cases on the integration, system and application levels. Thus, they certify the products against the requirements using black box testing approach. In doing so, a test plan defines a sequence of test cases whereby it sets up the environment, stimulates the fault, and then observes the system under test for each case. Subsequently, the post processing of the test execution classifies the test plan in passed or failed. The ongoing digitization and interconnectedness between aircraft systems is leading to a high number of test cases and a multitude of reasons why a specific test-case fails. A corresponding error analysis and adaptation of the test plan is a complex and lengthy process, which…