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Nonlinear state estimation for aeroelastic multi-body models

Nonlinear state estimation for aeroelastic multi-body models

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aiaa modeling and simulation technologies conference, 2016

作者： Benoit, Tuur Lemmens, Yves Desmet, Wim Simulation and Test Solutions Siemens PLM Interleuvenlaan 68 LeuvenVlaams-Brabant3001 Belgium KU Leuven LeuvenVlaams-Brabant3000 Belgium Section Celestijnenlaan 300 - box 2420 Leuven3001 Belgium

ISBN: (数字)9781624104299

ISBN: (纸本)9781624104299

This paper discusses the use of aeroelastic multi-body models in a discrete extended Kalman filter. An FMI-based co-simulation approach is proposed to transform the multi-body differential-algebraic continuous-time equations into a set of discrete ordinary differential equations, for use in an ODE type of state estimator such as the extended Kalman filter. The proposed approach is validated numerically with an industrial-size high-fidelity model of a fixed-wing aircraft, which contains a flexible airframe and detailed multi-body models of the nose and main landing gear, for a hard landing case. It is expected that this approach will improve health monitoring applications by providing a method for virtually observing unmeasurable quantities such as internal structural loads. © 2016 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Extended Kalman filters

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Global simulation of aviation operations

Global simulation of aviation operations

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aiaa modeling and simulation technologies conference, 2016

作者： Sridhar, Banavar Sheth, Kapil Ng, Hok K. Morando, Alex Li, Jinhua NASA Ames Research Center Moffett Field CA94035-1000 United States University of California Santa Cruz Moffett Field CA94035-1000 United States SGT Inc. Moffett Field CA94035-1000 United States Air Transportation Systems Aviation Systems Division United States Systems Modeling and Optimization Branch MS 210-15 United States U.C. Santa Cruz MS 210-8 United States Stinger Ghaffarian Technologies

ISBN: (数字)9781624103872

ISBN: (纸本)9781624103872

The simulation and analysis of global air traffic is limited due to a lack of simulation tools and the difficulty in accessing data sources. This paper provides a global simulation of aviation operations combining flight plans and real air traffic data with historical commercial city-pair aircraft type and schedule data and global atmospheric data. The resulting capability extends the simulation and optimization functions of NASA’s Future Air Traffic Management Concept Evaluation Tool (FACET) to global scale. This new capability is used to present results on the evolution of global air traffic patterns from a concentration of traffic inside US, Europe and across the Atlantic Ocean to a more diverse traffic pattern across the globe with accelerated growth in Asia, Australia, Africa and South America. The simulation analyzes seasonal variation in the long-haul wind-optimal traffic patterns in six major regions of the world and provides potential timesavings of wind-optimal routes compared with either great circle routes or current flight-plans if available. © 2016, American Institute of Aeronautics and Astronautics Inc. All rights reserved.

关键词： NASA

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simulation framework for incorporating sensor systems in UAS conceptual design

Simulation framework for incorporating sensor systems in UAS...

引用

aiaa modeling and simulation technologies conference, 2016

作者： Jerath, Kshitij Langelaan, Jack W. Washington State University PullmanWA99164 United States The Pennsylvania State University University ParkPA16802 United States School of Mechanical and Materials Eng Washington State University United States Department of Aerospace Engineering United States

ISBN: (纸本)9781624103872

Sensor systems typically have not played a significant role in the aircraft conceptual design process. However, with the proliferation of unmanned aerial systems (UAS), the role of sensor systems on vehicle conceptual design can no longer be ignored. This is-sue is accentuated at smaller scales, where the sensing equipment may place significant constraints on the size, weight and power requirements of the aircraft. In this paper, we present a novel method that incorporates sensor systems into vehicle conceptual design and mission capability analysis. The presented method relies on a simulation framework in which the Blender Game Engine is used to generate complex cluttered ight environments. The MORSE simulator is used to y vehicles with varying sensor configurations in these cluttered environments in order to assess mission capabilities. Results show that this ap-proach has the potential to assess mission capabilities as a function of sensor configurations and specifications. © 2016, American Institute of Aeronautics and Astronautics Inc. All rights reserved.

关键词： Conceptual design

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Formal scenario definition language for aviation: Aircraft landing case study

Formal scenario definition language for aviation: Aircraft l...

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aiaa modeling and simulation technologies conference, 2016

作者： Jafer, Shafagh Chhaya, Bharvi Durak, Umut Gerlach, Torsten Embry-Riddle Aeronautical University 600 S Clyde Morris Blvd Daytona BeachFL32114-3900 United States Institute of Flight Systems Flight Dynamics and Simulation Lilienthalplatz 7 Braunschweig38108 Germany

ISBN: (数字)9781624104299

ISBN: (纸本)9781624104299

Although the importance of scenarios in modeling and simulation has long been well known, there still exists a lack of common understanding and standardized practices in simulation scenario development. This paper proposes a Domain-Specific Language (DLS) to provide a standard scenario specification that will lead to a common mechanism for verifying and executing aviation scenarios, effective sharing of scenarios among various simulation environments, improve the consistency among different simulators and simulations, and even enable the reuse of scenario specifications. Following DSL design practices, the proposed Aviation Scenario Definition Language (ASDL) will provide a well-structured definition language to formally specify complete aircraft landing scenarios. In order to capture the necessary constructs for a simulation scenario, simulation Interoperability Standards Organization (SISO) Base Object Model (BOM) is adopted as the baseline metamodel. This baseline is extended using the fundamentals of aircraft landing that cover all the domain-related concepts and terminology as constructs. By taking a formal approach in defining aviation scenarios, ASDL aims at providing consistency and completeness checking, and model-to-text transformations capabilities for various targets in the aviation scenario definition domain. The results of this work will be used to develop a graphical modeling environment and automatic means to transform scenario models into executable scenario scripts. The work presented here is the first stepping stone in formal scenario definition in aviation domain. © 2016 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Specifications

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ISS Double-Gimbaled CMG subsystem simulation using the agile development method

ISS Double-Gimbaled CMG subsystem simulation using the agile...

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aiaa modeling and simulation technologies conference, 2016

作者： Inampudi, Ravi Lockheed Martin HoustonTX77058 United States

ISBN: (纸本)9781624103872

This paper presents an evolutionary approach in simulating a cluster of 4 Control Moment Gyros (CMG) on the International Space Station (ISS) using a common sense approach (the agile development method) for concurrent mathematical modeling and simulation of the CMG subsystem. This simulation is part of Training systems for the 21st Century simulator which will provide training for crew members, instructors, and flight controllers. The basic idea of how the CMGs on the space station are used for its non-propulsive attitude control is briefly explained to set up the context for simulating a CMG subsystem. Next different reference frames and the detailed equations of motion (EOM) for multiple double-gimbal variable-speed control moment gyroscopes (DGVs) are presented. Fixing some of the terms in the EOM becomes the special case EOM for ISS’s double-gimbaled fixed speed CMGs. CMG simulation development using the agile development method is presented in which customer’s requirements and solutions evolve through iterative analysis, design, coding, unit testing and acceptance testing. At the end of the iteration a set of features implemented in that iteration are demonstrated to the flight controllers thus creating a short feedback loop and helping in creating adaptive development cycles. The unified modeling language (UML) tool is used in illustrating the user stories, class designs and sequence diagrams. This incremental development approach of mathematical modeling and simulating the CMG subsystem involved the development team and the customer early on, thus improving the quality of the working CMG system in each iteration and helping the team to accurately predict the cost, schedule and delivery of the software. © 2016, American Institute of Aeronautics and Astronautics Inc. All rights reserved.

关键词： Space stations

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modeling liners for engine exhaust applications 22

Modeling liners for engine exhaust applications

引用

22nd aiaa/CEAS Aeroacoustics conference, 2016

作者： Naïr, M. Detandt, Y. Yannic, B. Binet, D. Cordaro, T. De Brye, B. Mosson, A. Free Field Technologies Mont-Saint-Guibert Belgium Airbus France Toulouse France

ISBN: (数字)9781624103865

ISBN: (纸本)9781624103865

The rear fan noise from jet engines corresponds to a significant noise source at aircraft level. The aeroacoustic simulation solving this problem requires an accurate physical modeling of the acoustic propagation in complex mean flows, but also a stable and realistic modeling of liners conditions applied in the exhaust to reduce the rear fan noise level. In the present paper, a Linearized Euler solver is used to tackle this problem and a specific section discusses the modeling of the boundary layer refraction above the liner. The classical Myers term is compared to a new approach. The discussion involves the physical and stability aspects of the boundary layer modeling which are important for a robust and accurate industrial process. © 2016, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Exhaust systems (engine)

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Non-intrusive flight test instrumentation using video recognition: Reducing the cost and time to market for certified flight simulation devices

Non-intrusive flight test instrumentation using video recogn...

引用

aiaa modeling and simulation technologies conference, 2016

作者： Riccardi, Joseph Minwalla, Cyrus Flight Research Laboratory National Research Council Canada 1200 Montreal Rd OttawaONK1A 0R6 Canada

ISBN: (纸本)9781624103872

The National Research Council of Canada has conducted feasibility studies into the development of non-intrusive flight test instrumentation methods with the goal of reducing the cost and time-to-market for certified aerospace products. Video recognition for the collection of flight test time history data was one such non-intrusive method. The advantages of using machine vision for flight data collection are many. One video camera can be used to extract data for many in-flight parameters, reducing instrumentation time, the airworthiness effort, the overall aircraft schedule and associated costs. This paper details the development of flight test video recognition software, calibration algorithms, hardware, and the accuracy of data collected by video via full flight simulator data benchmarks. Video recognition is a convenient means of collecting cockpit flight test data for model development and certification of full flight simulator devices. © 2016, American Institute of Aeronautics and Astronautics Inc. All rights reserved.

关键词： Video cameras

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An overview of model-based development verification/validation processes and technologies in the aerospace industry

An overview of model-based development verification/validati...

引用

aiaa modeling and simulation technologies conference, 2016

作者： Allen, Jace L. Simulation and Test Systems dSPACE Inc. WixomMI48393 United States

ISBN: (数字)9781624103872

ISBN: (纸本)9781624103872

Due to the rapid rate of increase in product complexity and need to shorten delivery times, the Model-based Development (MBD) process has been adopted to help manage the complexity of these systems while making product development more efficient. Adopting MBD has resulted in tool-chains that allow for efficient rapid controls prototyping, automatic code generation, and advanced validation and verification techniques, such as Hardware-in-the-loop (HIL). Managing these MBD tool chains and testing processes is a demanding task for many organizations. New technologies and standards advancements are providing key enablers for solving the complex issues faced in product development and validation. This paper describes some of the latest advancements for MBD development and HIL simulation, and how they address demanding system Validation and Verification (V&V) requirements. Model-based Systems Engineering (MBSE) is a basis for product engineering processes that utilize various modeling and simulation systems. Going from the system to component domain requires management of the product development process, the necessary MBD artifacts, and all MBD tools used. New standards have been introduced, such as the Functional Mockup Interface (FMI), to provide capabilities for multi-domain simulation and testing, enabling models and tools to be more effectively used earlier in the design process and re-used throughout the V&V cycle. This paper addresses the above technologies and a novel V&V HIL hardware/software architecture that was designed to address these needs, resulting in a test system that provides more effective flexibility, adaptability and process efficiency to the embedded software development and testing process. The paper also addresses "virtual" controller testing, with a process that uses the same tools and workflows that can later be used later in the V-cycle. This improves synergy in the testing processes and increases the speed of deployment for testing with HIL s

关键词： Chains

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Design and simulation of F/A-18a automatic carrier landing guidance controller

Design and simulation of F/A-18a automatic carrier landing g...

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aiaa modeling and simulation technologies conference, 2016

作者： Yue, Liuming Liu, Gang Hong, Guanxin Beijing University of Aeronautics and Astronautics School of Aeronautic Science and Engineering 37 Xueyuan Rd Haidian Dist BeijingBJ10 China

ISBN: (数字)9781624104299

ISBN: (纸本)9781624104299

The purpose of this paper is to design automatic carrier landing guidance controller for F/A-18A to facilitate subsequent further research. Airwake and deck motion are main factors introduced to the automatic carrier landing system. Airwake model is based on the MIL-F-8785C definitions and the deck motion comes from ESSEX class aircraft carrier. The F/A-18A model and its flight control system are built with some efforts based on exiting data in some published papers. This paper designs three kinds of automatic carrier landing guidance controller for F/A-18A, namely, PID, Fuzzy-PID, PIDDD controller, to find the most reliable in different disturbances. Parameters of controllers are optimized with different methods, respectively, PID tuning in MATLAB, self-optimization and progressive optimization algorithm. Guidance and control effects are mainly presented with images. This paper finds that PIDDD controller is the most reliable to adapt to diferent disturbances and proposes corresponding ideas about design of guidance controller. Design and simulation analysis are processed by MATLAB software. © 2016 by Liuming YUE. Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Controllers

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Human-in-the-loop simulation analysis of conict resolution maneuvers using an air traffic control simulation

Human-in-the-loop simulation analysis of conict resolution m...

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aiaa modeling and simulation technologies conference, 2016

作者： Oh, Hyeju Jeong, Sehun Choi, Keeyoung Lee, Hak-Tae Jung, Hyun-Tae Moon, Woo-Choon Inha University Incheon22212 Korea Republic of Korea Aerospace University Goyang-SiGyeonggi-Do10540 Korea Republic of Department of Aerospace Engineering India School of Air Transport Transportation and Logistics School of Air Transport Transportation and Logistics and Air and Space Law

ISBN: (纸本)9781624103872

As the technologies and demands of Remotely Piloted Aircraft Systems (RPASs) growing rapidly, integration of RPAS into the existing airspace system is becoming an issue in many countries. To establish rules and regulations for RPAS integration, it is important to understand the impacts of RPAS, which have different flight performances, communication characteristics, separation assurance mechanisms, and human machine interfaces from manned aircraft, on the airspace system. A simulation system that integrates manned aircraft, air traffic control, and RPASs is developed in Inha University to investigate these impacts through Human-in-The-Loop (HiTL) simulations. For the initial test, a scenario with communication delays between the controller and the pilot of the RPAS was constructed. HiTL simulations were performed with several trainee controllers in Korean Aerospace University. Metrics such as Loss of Well Clear (LOWC), delay, and NASA Task Load Index were investigated to analyze the relation between safety, efficiency, and work- load respectively. The results show that the introduction of RPASs with communication delay generally causes other manned aircraft to maneuver, which leads to increased delay and workload. Meanwhile, safety is not significantly impacted. © 2016, American Institute of Aeronautics and Astronautics Inc. All rights reserved.

关键词： Air traffic control

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