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Real-time simulation infrastructure for model-based design of helicopter flight control system

Real-time simulation infrastructure for model-based design o...

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aiaa modeling and simulation technologies conference, 2018

作者： Aydemir, Hakan Zengin, Ugur TAI – Turkish Aerospace Industries Inc Ankara06980 Turkey Helicopter Group KazanAnkara06980 Turkey

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

Model Based Design (MBD) tools help to simplify and accelerate process of designing highly complex systems such as automatic flight control systems. MBD also provides the opportunity to follow an iterative design process. Every iteration needs software in the loop, hardware in the loop and pilot in the loop testing to verify algorithms and logics step by step according to the project specific Software Test Procedures. Software in the loop testing environment is relatively easy to establish and not expensive to maintain compared to the other testing environments which may need complex system architectures and extra hardware integration such as actuators, control grips, visual environment, flight control computer and etc. Engineering simulators are growing to be a good option to verify system design and complete necessary testing in a realistic environment by using different hardware options. Further, engineering simulators provide the capability for designers to conduct detailed run-time analysis and to evaluate the design against real flight scenarios. Software in the loop testing can be realized by using a standard MS Windows Personal Computer (PC) environment however hardware in the loop and pilot in the loop testing requires establishment of a real-time environment to perform accurate analyses. This paper represents an affordable and easy way to develop a real-time infrastructure solution in an engineering simulator for MBD of an automatic flight control system. Idea behind this infrastructure is transforming MS Windows into a real-time operating system by installing a symmetric multiprocessing-enabled real-time software to a multi core enabled PC. Unlike traditional architectures, this infrastructure utilizes MS Windows based Human Machine Interface (HMI) benefits and real-time system in same PC environment and makes communication easy between HMI services and real-time system. Using MS Windows and real-time software in same commercial off the shelf hardware (St

关键词： Real time systems

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Shimmy simulation and virtual verification for amphibious aircraft’s landing gear airworthiness certification

Shimmy simulation and virtual verification for amphibious ai...

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modeling and simulation technologies conference, 2018

作者： He, Xufei Song, Zhitao Ai, Jianliang Shanghai Aircraft Airworthiness Certification Center of CAAC Shanghai200335 China Department of Aerospace Fudan University Shanghai200443 China

ISBN: (数字)9781624105517

ISBN: (纸本)9781624105517

Landing gear shimmy is an important problem related to the safety of taxiing for large aircrafts. Shimmy simulation study is of great significance to the airworthiness certification of modern civil aircrafts. For the complex nose landing gear (NLG) of an amphibious aircraft, a three-dimensional (3-D) rigid-flexible coupling dynamic model is developed and shimmy characteristic parameters of the flexible structure are obtained under simulated shimmy flight testing scenarios-typical taxiing speed, weight/center of gravity, and runway plank excitation. The landing gear stability in normal operation configuration is validated. Effects of shimmy damping, tire relaxation length, and cornering stiffness on shimmy stability are analyzed respectively. Applicable Chinese Civil Aviation Regulations for shimmy are identified and interpreted. Through landing gear shimmy airworthiness certification practice, a reasonable airworthiness verification "Building Block Model," which includes airworthiness requirements capture, simulation, virtual tests, and physical testing (equipment qualification testing, landing gear system laboratory testing, and shimmy flight testing), is proposed. Shimmy characteristics of an amphibious aircraft under different test scenarios are thoroughly investigated. Study results demonstrate the potential of virtual verification technology to prevent the occurrence of shimmy and assist compliance finding. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Amphibious aircraft

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Unstructured large eddy simulation of a turboshaft ejector on rotorcraft 36th

Unstructured large eddy simulation of a turboshaft ejector o...

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36th aiaa Applied Aerodynamics conference, 2018

作者： Tamm, Patrick Q. Spyropoulos, John T. Philips, David A. NAVAIR Propulsion and Power Patuxent RiverMD United States Cascade Technologies Inc. Palo AltoCA United States

ISBN: (数字)9781624105593

ISBN: (纸本)9781624105593

Turboshaft engines typically operate in confined rotorcraft compartments and are subject to environments of extremely complex and transient flow, particularly in multi-engine installations. Cooling demands for these engines and associated accessories are typically addressed by the use of nozzle ejectors to increase the supply of exterior air to the engine compartments. modeling and simulation of rotorcraft ejector physics—particularly in a design environment—is a significant challenge due to the complex installation geometries and highly transient nozzle and external flowfields. Wall Modeled Large Eddy simulation (WMLES) has proved to be an adept Computational Fluid Dynamics (CFD) method for accurately representing highly separated and shear driven wall-bounded flows. This study employs WMLES to realistically simulate the transient physics of rotorcraft ejector applications over long simulation times to examine predominant system behavior and evolving unsteady phenomena. The effectiveness of a Voronoi grid generation methodology bespoke for WMLES is also demonstrated in a production environment by analyzing two geometry configurations and assessing the effects of these design changes on ejector system performance. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Computational fluid dynamics

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A multifidelity framework to support the design of more-electric actuation 19th

A multifidelity framework to support the design of more-elec...

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19th aiaa/ISSMO Multidisciplinary Analysis and Optimization conference, 2018

作者： Garriga, Ana Garcia Ponnusamy, Sangeeth S. Mainini, Laura United Technologies Research Center CorkT23XN53 Ireland

ISBN: (数字)9781624105500

ISBN: (纸本)9781624105500

The push towards reducing the impact of aviation on the environment motivates the development of collaborative frameworks that enable the more integrated design of aircraft and their systems. The ModellIng and simulation tools for Systems IntegratiON on Aircraft (MISSION) project aims to develop one such integrated modelling and simulation framework. This paper focuses on some recent advancements in the MISSION project and presents a design framework that combines a filtering process to down-select feasible architectures, a modeling platform that simulates the power system of the aircraft, and a clustering and optimization module. This framework enables the designer to prioritize different designs at system level and offers traceability on the optimal choices. In addition, it enables the integration of models at multiple levels of detail depending on the size of the design space and the level of detail required. It is demonstrated for the electrification of the Primary Flight Control System (PFCS) using different electric actuation technologies. The performances of different architectures are analyzed with respect to key performance indicators. The optimization process benefits from a localization step to identify sets of similar architectures. The framework demonstrates the capability of optimizing across multiple, different system architectures in an efficient way that is scalable for larger design spaces and larger dimensionality problems. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Benchmarking

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simulation of cavitating venturi flows using a 1d flow solution 54th

Simulation of cavitating venturi flows using a 1d flow solut...

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54th aiaa/SAE/ASEE Joint Propulsion conference, 2018

作者： Tiwari, A. Harrison, J. Gamma Technologies LLC WestmontIL60446 United States

ISBN: (数字)9781624105708

ISBN: (纸本)9781624105708

Cavitating venturis are used in many space fueling applications to regulate pressure in propellant feed lines. The flow in cavitating venturis is complex, and often involves simulation with 3D CFD to be predictive, and accurately capture the performance of these devices. However, there is a need to do faster simulation with 1D flow solvers in order to explore the design space faster than 3D CFD. This paper presents a framework for solving these complex cavitating venturi flows with a commercial multi-physics system-level simulation software called GT-SUITE. Cavitation dynamics are challenging to simulate because of large gradients in dynamic flow properties that arise due to sharp transition in thermodynamic properties at the phasic interfaces, particularly during phase transition, which if not correctly solved, generate large spurious oscillations at the interfaces. Therefore, for such flows, it is imperative for a simulation tool to capture multiphase interfaces in a stable fashion that preserves their integrity. This paper will demonstrate the capturing of such interfaces using GT-SUITE. Further, validation of the modeling approach will be presented by showing good comparison with analytical solutions, and experimental results. © 2018, American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Computational fluid dynamics

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Automating Intra-Links and Node Analysis

Automating Intra-Links and Node Analysis

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conference on Disruptive technologies in Information Sciences

作者： Smith, Anthony Smith, Kaleb Aved, Alex J. Florida Inst Technol 150 W Univ Blvd Melbourne FL 32901 USA Air Force Res Lab 525 Brooks Rd Rome NY 13441 USA

ISBN: (数字)9781510618169

ISBN: (纸本)9781510618169

In this work, we investigate and compare centrality metrics on several datasets. Many real-world complex systems can be addressed using a graph-based analytical approach, where nodes represent the components of the system and edges are the interactions or relationships between them. Different systems such as communication networks and critical infrastructure are known to exhibit common characteristics in their behavior and structure. Infrastructure networks such as power girds, communication networks and natural gas are interdependent. These systems are usually coupled such that failures in one network can propagate and affect the entire system. The purpose of this analysis is to perform a metric analysis on synthetic infrastructure data. Our view of critical infrastructure systems holds that the function of each system, and especially continuity of that function, is of primary importance. In this work, we view an infrastructure as a collection of interconnected components that work together as a system to achieve a domain-specific function. The importance of a single component within an infrastructure system is based on how it contributes, which we assess with centrality metrics.

关键词： modeling and simulation Node Analysis Graphical Analysis Course of Action Analysis Visualization Graph Theory

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Large-eddy simulations of co-annular turbulent jet using a voronoi-based mesh generation framework

Large-eddy simulations of co-annular turbulent jet using a v...

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aiaa/CEAS Aeroacoustics conference, 2018

作者： Brès, Guillaume A. Bose, Sanjeeb T. Emory, Michael Ham, Frank E. Schmidt, Oliver T. Rigas, Georgios Colonius, Tim Cascade Technologies Inc. Palo AltoCA94303 United States California Institute of Technology PasadenaCA91125 United States Dept. of Mechanical Engineering United States

ISBN: (数字)9781624105609

ISBN: (纸本)9781624105609

Large eddy simulations are performed for a cold ideally-expanded dual-stream jet issued from cylindrical co-axial nozzles, with supersonic primary stream (Mach number M1 = 1.55) and subsonic secondary stream (M2 = 0.9). The geometry includes the internal screw holes used to fasten the two nozzles together and to the plenum chamber. These slanted cylindrical holes over which the secondary stream flows were not covered in the experiment and were seamlessly captured in the computational mesh thanks to a novel grid generation paradigm based on the computation of Voronoi diagrams. A simulation with the screw holes covered is also performed and the preliminary results tends to indicate that these features have minimal impact on the flow and acoustic fields for the present operating conditions. As expected, the present dual-stream configuration with subsonic annular stream surrounding the primary supersonic stream features a reduced shear-layer growth, a longer potential core and a lack of strong Mach wave radiation. A long LES database is currently being collected for analysis and modeling of wavepackets and noise sources in such complex turbulent jets. © 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Large eddy simulation

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Parallelization of a six degree of freedom entry vehicle trajectory simulation using openMP and openACC

Parallelization of a six degree of freedom entry vehicle tra...

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modeling and simulation technologies conference, 2018

作者： Green, Justin S. Williams, Robert Anthony Gutierrez, Julian Dept. of Mechanical and Aerospace Engineering NASA Langley Research Center University of Virginia CharlottesvilleVA22903 United States Atmospheric Flight and Entry Systems Branch NASA Langley Research Center HamptonVA23681 United States Dept. of Mathematics and Statistics NASA Langley Research Center Old Dominion University NorfolkVA23529 United States High Performance Computing Incubator and Atmospheric Flight and Entry Systems Branch NASA Langley Research Center HamptonVA23681 United States Dept. of Electrical and Computer Engineering Northeastern University BostonMA02115 United States

ISBN: (数字)9781624105517

ISBN: (纸本)9781624105517

The art and science of writing parallelized software, using methods such as Open Multi-Processing (OpenMP) and Open Accelerators (OpenACC), is dominated by computer scientists. Engineers and non-computer scientists looking to apply these techniques to their project applications face a steep learning curve, especially when looking to adapt their original single threaded software to run multi-threaded on graphics processing units (GPUs). There are significant changes in mindset that must occur;such as how to manage memory, the organization of instructions, and the use of if statements (also known as branching). The purpose of this work is twofold: 1) to demonstrate the applicability of parallelized coding methodologies, OpenMP and OpenACC, to tasks outside of the typical large scale matrix mathematics;and 2) to discuss, from an engineer’s perspective, the lessons learned from parallelizing software using these computer science techniques. This work applies OpenMP, on both multi-core central processing units (CPUs) and Intel® Xeon Phi™ 7210, and OpenACC on GPUs. These parallelization techniques are used to tackle the simulation of thousands of entry vehicle trajectories through the integration of six degree of freedom (DoF) equations of motion (EoM). The forces and moments acting on the entry vehicle, and used by the EoM, are estimated using multiple models of varying levels of complexity. Several benchmark comparisons are made on the execution of six DoF trajectory simulation: single thread Intel® Xeon® E5-2670 CPU, multi-thread CPU using OpenMP, multi-thread Xeon Phi™ 7210 using OpenMP, and multi-thread NVIDIA® Tesla® K40 GPU using OpenACC. These benchmarks are run on the Pleiades Supercomputer Cluster at the National Aeronautics and Space Administration (NASA) Ames Research Center (ARC), and a Xeon Phi™ 7210 node at NASA Langley Research Center (LaRC). © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Program processors

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Recent advances in enhanced oil recovery technologies for unconventional oil reservoirs

Recent advances in enhanced oil recovery technologies for un...

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Offshore Technology conference, OTC 2018

作者： Balasubramanian, S. Chen, P. Bose, S. Alzahabi, A. Thakur, G.C. University of Houston United States

ISBN: (纸本)9781510862531

Unconventional resources have significantly transformed the landscape of the oil and gas industry. The primary recovery factor ranges anywhere from 2% to 8% for the various shale plays throughout the United States. Hence, it is imperative to exploit the vast potential of unconventional reservoirs and increase the recovery factors beyond primary depletion by implementing improved and enhanced oil recovery (IOR/EOR) methods. This paper presents detailed review of the advances in IOR/EOR technologies applied to unconventional oil reservoirs. A thorough review of the pertinent published literature on IOR/EOR was performed. Results of EOR application to unconventionals shared by various operators in their investor presentations and press reports were also analyzed. The IOR/EOR studies were classified into laboratory experiments, numerical modeling and field laboratory trials (pilots). In addition, the field trials were also analyzed based on the representative shale plays. Most of the studies performed for the application of EOR technologies to unconventional oil reservoirs have been limited to experimental investigations and numerical simulation studies. The research revealed that miscible gas injection (produced gases, CO2, etc.) is the most promising method among the EOR techniques (miscible gas, water flooding, surfactant, chemical and polymer). Experimental studies showed that CO2 injection had the highest potential of improved recovery in unconventionals followed by produced gas injection and that diffusion was the most predominant mechanism. Surfactant injection showed the next best potential to increase oil recovery by altering the wettability of rock in laboratory experiments. The gas injection pilots showed that sufficient injectivity was achieved mainly due to the injection induced fractures and did not exhibit any significant effect of diffusion. Conformance control remains a big challenge especially due to the channeling of the gas through the fractures. Pro

关键词： Enhanced recovery

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modeling and simulation of Aerobee-150A sounding rocket

Modeling and simulation of Aerobee-150A sounding rocket

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aiaa modeling and simulation technologies conference, 2017

作者： Akcal, Mehmet U. Yukseky, Burak Ure, Nazim K. Department of Aeronautical and Astronautical Engineering Istanbul Technical University Istanbul34469 Turkey

ISBN: (数字)9781624104510

ISBN: (纸本)9781624104510

This paper presents modeling and simulation studies for an Aerobee-150A sounding rocket. The model consists of 6 degree of freedom motion model accompanied with various subsystems such as yo-yo despin model, cold gas thruster model, and recovery system model. A pulse-width pulse-frequency (PWPF) modulator is employed for attitude control. A large portion of the model parameters are obtained from the publicly shared NASA reports. simulation results show that the performance parameters (e.g. burn-out velocity and apogee etc.) of the sounding rocket model introduced in this study match closely with the data presented in NASA reports. © 2017, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： NASA

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