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Technical Paper (34)



Aerospace (34)


Aircraft (14) Simulation and modeling (9) Architecture (7) Avionics (6) Electric aircraft (6) Computer software and hardware (5) Electric power (5) Research and development (5) Sensors and actuators (5) Design processes (4) Hardware (4) Unmanned aerial vehicles (4) Wings (4) Control systems (3) Power electronics (3) Systems engineering (3) Terminology (3) Aerodynamics (2) Analysis methodologies (2) Carbon dioxide (2) Computational fluid dynamics (2) Cost analysis (2) Failure modes and effects analysis (2) Integrated modular avionics (2) Logistics (2) Machine learning (2) Mathematical models (2) Pressure (2) Production (2) Simulators (2) Soils (2) Technical review (2) Test procedures (2) Tools and equipment (2) Transmissions (2) Additive manufacturing (1) Airships (1) Artificial intelligence (AI) (1) Balloons (1) Big data (1) Buses (1) CAD, CAM, and CAE (1) Camber (1) Certification (1) Compressors (1) Computer simulation (1) Continuously variable transmissions (1) Coolants (1) Crashes (1) Defense industry (1)


Bozhko, Serhiy (3) Norman, Patrick (3) Rashed, Mohamed (3) Trancossi, Michele (3) Browning, Patrick H. (2) Burt, Graeme (2) Liscouet-Hanke, Susan (2) Pascoa, Jose (2) Abel, Andreas (1) Adhikari, Jeevan (1) Alata, Eric (1) Andreev, Maxim (1) Anekstein, David (1) Balaghi Enalou, Hossein (1) Beaulac, Sebastien (1) Berthon, Guy-Andre (1) Binder, Bastian (1) Boutin, Yanik (1) Burgio, Gilberto (1) Burns, David (1) Cannistraro, Giuseppe (1) Chaudemar, Jean-Charles (1) Cohen, Emily (1) Cornett, Jacob (1) Cotton, Ian (1) Couto, Luis Diogo (1) Coutts, Lindsey (1) Cremona, Fabio (1) Damien, Alienor (1) Dufresne, Stephane (1) Edman, Robert (1) Faudou, Raphael (1) Ferrante, Orlando (1) Fong, Chung Man (1) Fowler, Chris (1) Fowler, Kevin (1) Fumey, Marc (1) Gardner, Richard (1) Gauthier, Jean-Marie (1) George Mathew, Prince (1) Goi, Tatsuhiko (1) Gorur, Ravi Prakash (1) Gottschall, Marcel (1) Guerrero, Marc (1) Guo, Dian (1) Haghighi, Hasti (1) Higgins, Nigel (1) Hildenbrand, Yannick (1) Hubbard, Levi S. (1) Hugues, Jerome (1)


SAE (34)


Sheffield Hallam University (3) United Technologies Research Center (3) University of Central Florida (3) University of Nottingham (3) University of Strathclyde (3) Bombardier Aerospace (2) Concordia University Montreal (2) ESI ITI GmbH (2) Universidade Da Beira Interior (2) UTC Aerospace Systems (2) West Virginia University (2) Adventium Labs (1) Airbus Operations Ltd. (1) ANSYS (1) AVIC Digital Corporation Ltd. (1) COMAC (1) Cranfield University (1) Dassault Aviation (1) dSPACE France SARL (1) dSPACE GmbH (1) German Aerospace Center (DLR) (1) Henri Coanda Labs LLC (1) IHI Corporation (1) Infosys Ltd. (1) ISAE SUPAERO, Université de Toulouse (1) Kawasaki Heavy Industries, Ltd. (1) LAAS-CNRS, Université de Toulouse, CNRS (1) LAAS-CNRS, Université de Toulouse, CNRS, INSA (1) RMIT University (1) Samares-Engineering (1) Thales Avionics (1) Thales AVS (1) Thales AVS & LAAS-CNRS (1) Universita degli Studi di Messina (1) Université de Toulouse (1) University of Manchester (1) Yokohama National University (1)


Aerospace Systems and Technology Conference (34)

Model-Based Systems Engineering Methodology for Implementing Networked Aircraft Control System on Integrated Modular Avionics – Environmental Control System Case Study

  • Bombardier Aerospace-Yann Le Masson
  • Concordia University Montreal-Prince George Mathew, Susan Liscouet-Hanke
  • Technical Paper
  • 2018-01-1943
Published 2018-10-30 by SAE International in United States
Integrated modular avionics (IMA) architectures host multiple federated avionics applications on a single platform and provide benefits in terms of size, weight, and power, which, however, leads to increased complexity, especially during the development process. To cope efficiently with the high level of complexity, a novel, structured development methodology is required. This paper presents a model-based systems engineering (MBSE) development approach for the so-called “distributed integrated modular architecture” (DIMA). The proposed methodology adapts the open-source Capella tool, based on the Architecture Analysis & Design Integrated Approach (ARCADIA) methodology, to implement a complete design cycle, starting with requirements captured from the aircraft level to streamline the development, culminating in the integration of an avionics application into an ARINC 653 platform. This paper shows how to address the variability of technology implementations at the aircraft and system levels and how the specification artifacts are efficiently managed and traced from the aircraft to the system to the item level to implement the SAE ARP4754A guidelines. The effectiveness of the methodology is presented via a case study of the…

Multi-level Modeling Methodology for Aircraft Thermal Architecture Design

  • Bombardier Aerospace-Yanik Boutin, Sebastien Beaulac, Stephane Dufresne
  • Concordia University Montreal-Florian Sanchez, Susan Liscouet-Hanke
  • Technical Paper
  • 2018-01-1910
Published 2018-10-30 by SAE International in United States
This paper proposes a new methodology to conduct thermal analysis in the conceptual phase of the aircraft development process. Traditionally, thermal analysis is conducted after the system architecture has already been defined. The aircraft system thermal environment evaluation may lead to late design changes that can have a significant impact on the development process. To reduce the risk of late design changes, thermal requirements need to be defined and validated in the conceptual design phase. This research paper introduces a novel multi-level modeling strategy based on a bottom-up approach. It proposes an automatic geometrical simplification procedure for Computational Fluid Dynamic (CFD) analysis, a methodology for the generation of analytical correlations based on highly detailed methods, and a thermal risk assessment approach based on dimensionless numbers. This methodology generates models with the right level of fidelity to conceptual and preliminary design, offers the possibility to assess thermal risk, and defines thermal requirements for the selection of aircraft and systems architectures. A proof-of-concept of the methodology for a simplified test case is presented to highlight the benefits…

A Methodology for Formal Requirements Validation and Automatic Test Generation and Application to Aerospace Systems

  • UTC Aerospace Systems-Eelco Scholte, Rob North
  • United Technologies Research Center-Orlando Ferrante, Simone Rollini, Luca Manica, Valerio Senni
  • Technical Paper
  • 2018-01-1948
Published 2018-10-30 by SAE International in United States
Automation on Validation and Verification (V&V) leveraging Formal Methods, and in particular Model Checking, is seeing an increasing use in the Aerospace domain. In recent years, Formal Methods have been used to verify systems and software and its correctness as a way to augment traditional methods relying on simulation and testing. Recent updates to the relevant Aerospace regulations (e.g. DO178C, DO331 and DO333) now have explicit provisions for utilization of models and formal methods. In a previous paper a compositional methodology for the verification of Aerospace Systems has been described with application to Electrical Power Generation and Distribution Systems. In this paper we present an expansion of the previous work in two directions. First, we describe the application of the methodology to the validation of Proximity Sensing Systems (PSS) requirements showing the effectiveness of the method to a new aerospace domain. Second, both the methodology and technology components have been expanded and applied to the PSS to enable automatic generation of test cases from the validated requirements models showing a novel application of formal models…

Reliability Case Analysis of an Autonomous Air Cooling System (AACS) for Aerospace Applications

  • IHI Corporation-Naoki Seki
  • University of Strathclyde-Chung Man Fong, Patrick Norman
  • Technical Paper
  • 2018-01-1916
Published 2018-10-30 by SAE International in United States
Current More Electric Aircraft (MEA) utilize Liquid Cooling Systems (LCS) for cooling on-board power electronics. In such LCS, coolant pipes around the structure of the aircraft are used to supply water glycol based coolant to sink heat from power electronics and other heat loads in the electronic bay. The extracted heat is then transferred to ram air through downstream heat exchangers.This paper presents a reliability examination of a proposed alternative Autonomous Air Cooling System (AACS) for a twin engine civil MEA case study. The proposed AACS utilizes cabin air as the coolant which is in turn supplied using the electric Environmental Control System (ECS) within the MEA. The AACS consists of electrical blowers allocated to each heat load which subsequently drive the outflow cabin air through the heat sinks of the power electronics for heat extraction. No additional heat exchanger is required after this stage in which the heated air is directly expelled overboard. One key advantage is the avoidance of liquid coolant leakage with the removal of liquid coolant from the MEA.It is necessary…

Safety Analysis of an Airship Which Loses Lifting Gas from the Hull

  • Sheffield Hallam University-Michele Trancossi
  • Universidade Da Beira Interior-Jose Pascoa
  • Show More
  • Technical Paper
  • 2018-01-1954
Published 2018-10-30 by SAE International in United States
This study investigates the physical phenomena that affect a high-altitude airship in the presence of lifting gas losses from the hull. General atmospheric thermodynamics and basic physical principles are adopted to describe the behavior of an airship with envelope failures that generate buoyant gas dispersion or depressurisation phenomena. Overpressure that could grant to maintain some controllability during a large part of the descent is assessed by mean of the thermodynamic model of the envelope in the presence of gas losses. Optimisation of the inflation parameters is provided and the conditions for avoiding dangerous crashes on the ground and the potential recovery of a damaged vehicle, people and its payload. In particular, the requirements for a slow depressurisation is computed by the equilibrium with the atmosphere and then how can it be possible to sustain controlled navigation are determined. A key factor for security relates directly to the capability of preserving some airship balloon overpressure for the longest time possible. This condition can extend much the range of control. Complete forfeit conditions will be determined to…

Analysis of the Effects of Modeling Depth and Parameter Uncertainties on the System Behavior of a Multifunctional High Lift Actuation System

  • German Aerospace Center (DLR)-Andreas Schäfer, Michael Schmid
  • Technical Paper
  • 2018-01-1918
Published 2018-10-30 by SAE International in United States
Modeling and simulation have become an important aspect of the design and development process of aircraft systems. During the design of high lift actuation systems for example, the dynamic loads in the transmission are estimated by simulation. Nevertheless huge development efforts and financial resources are still invested in physical testing. These integration and testing phases take place at a late stage in the design process. Therefore, identified malfunctions and development errors lead to undesired iterations and thus to high costs as well as to an increased development time. This issue is emphasized as system complexity is rises continuously in conjunction with an increase in the number of interconnections and functionality. Hence, early and continuous virtual testing activities on the overall system level become increasingly important. In order to establish such a process, this paper analyzes the effects of modeling depth and parameter uncertainties on the overall system behavior considering nominal operation as well as failure cases. It identifies which test cases can be performed in which development phase depending on the information required. The modeling…

Design, Manufacturing, Testing, and Analysis of a Highly-Constrained Single-Use UAV Wing

  • West Virginia University-Patrick H. Browning, Levi S. Hubbard, Philip Pennock
  • Technical Paper
  • 2018-01-1958
Published 2018-10-30 by SAE International in United States
Unmanned aerial vehicle (UAV) design aspects are as broad as the missions they are used to support. In some cases, the UAV mission scope can impose design constraints that can be difficult to achieve. This paper describes recent work performed at West Virginia University (WVU) to support repeated flight testing of a single-use UAV platform with emphasis on the highly specialized wings required to help meet the overall airframe mass properties constrained by the project sponsor. The wings were fabricated using a molded polyurethane (PU) foam as the base material which was supported by several different types of rigid and flexible substructures, skins, and matrix-infused fiber elements. Different ratios of infused fiber mass to PU foam were tested and additional tungsten masses were added to the wings to achieve the correct total mass and mass distribution of the wings. Expected accelerations were applied to the wing designs analytically and numerically to establish appropriate test limits and explore potential structural loading aspects, and static and dynamic experimental tests were employed to determine the suitability of the…

Feedback on Application of MBSE to an Avionics Subsystem

  • COMAC-Jian Tang, Shaofan Zhu
  • Samares-Engineering-Raphael Faudou, Jean-Marie Gauthier
Published 2018-10-30 by SAE International in United States
In avionics domain, currently most engineering efforts and costs come from integration, verification and validation activities. Each error found on requirements during product verification or validation requires a full engineering cycle to manage the change: impact analysis, design, realization, integration, verification and validation again. Hence, ensuring early and continuous validation of requirements in the engineering life cycle, becomes more and more crucial. In this paper, a Model-Based Systems Engineering (MBSE) approach is proposed. The proposed approach relies on SysML models and is composed of modelling tasks to capture requirements and to structure functional interfaces and functions. This approach has been applied in the frame of SAE ARP4754A aerospace recommended practices. This paper also provides feedback about the application of the proposed approach on an industrial avionic case study known as the Onboard Maintenance System by a team mainly used to document centric approach until recently. The feedback concerns the practical use of models to support functional part of the following processes: requirements capture, requirements validation, and top-level part of development of system architecture. After presenting…

Design, Development and Integration of a Wing-Morphing, Bimodal Unmanned Vehicle

  • RMIT University-Mark Simpson, Dian Guo
Published 2018-10-30 by SAE International in United States
This paper relates to the design and development of a multi-modal UAV capable of aerial flight and underwater propulsion. A novel hybrid propulsion system has been manufactured and tested. Consisting of folding blades, the propeller has been optimized for propulsion both in air and water. The critical water to air transition phase is achieved by an additional impulsive thruster powered by a C02 cartridge. To decrease the drag in underwater cruise and reduce the potential damage when the vehicle impacts the water, a morphing wing has been developed. This consists of foam-carbon fiber lay-up constructed wings in a variable sweep configuration. The actuation of the sweep is achieved by linear servos mounted on the sleeve shaped spar. An integrated prototype is constructed, using an unconventional, anhedral horizontal stabilizers to allow clearance for the morphing wing. Using a combination of data taken from wind tunnel testing, CFD simulation and analytic methods, models of the vehicles stability are developed with the aim of better understanding the dynamics of the vehicle during transition between the mediums. This will…

Multi-Layer Framework for Synthesis and Evaluation of Heterogeneous System-of-Systems Composed of Manned and Unmanned Vehicles

  • United Technologies Research Center-Jeffrey R. Peters, Ebad Jahangir, Amit Surana, Zohaib Mian
  • Technical Paper
  • 2018-01-1964
Published 2018-10-30 by SAE International in United States
The advancement of both sensory and unmanned technology, combined with increased utilization of autonomous platforms in complex teaming scenarios, has created a need for practical design space exploration tools to aid in the synthesis of effective System-of-Systems (SoS). The presented work describes a modular, flexible, and extensible framework, referred to herein as the Technologies and Teaming Evaluation (TATE) framework, for straightforward identification of high-quality SoS, which may include both manned and autonomous elements, through quantitative evaluation of system-level and SoS-level attributes against a set of user-defined reference tasks. More specifically, TATE combines a top-down (goal-driven) approach, which systematically decomposes mission-level goals into a set of relevant technology and teaming options, with a two-layer bottom-up (technology-driven) approach that compares and selects effective components and configurations both for individual systems and the overall team. The TATE framework serves as an extension to existing design space exploration tools that focus on individual system design and do not readily scale to SoS. A canonical example is used to illustrate the use of the TATE framework for synthesis and evaluation…