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aiaa modeling and simulation technologies conference, 2018

作者： Lopez, Guillermo Portapas, Vilius Dussart, Gaetan Lone, Mudassir Coetzee, Etienne Cranfield University Centre for Aeronautics School of Aerospace Transport & Manufacturing CranfieldMK43 0AL United Kingdom Airbus Operations BristolBS99 7AR United Kingdom

ISBN: (纸本)9781624105289

Integration of flight dynamic models, developed in the MATLAB®/Simulink® environment, with an engineering flight simulation platform allows rapid pilot-in-the-loop evaluation of new aircraft concepts at early stages of design. This paper aims to provide an overview of the integration activities needed to develop an engineering flight simulator capable of providing means to assess future concept aircraft, such as high aspect ratio wing configurations, where aeroelastic effects have a significant impact on rigid body flight dynamics. Details of the approach used to integrate an aeroelastic simulation framework with an engineering flight simulator are presented. The challenges of obtaining a real-time simulation capability and coding peculiarities of this approach are discussed. The paper expands on the discussion of integration and coding, and provides an example that demonstrates capabilities of such a framework for handling qualities assessment of a high aspect ratio wing aircraft. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Flight simulators

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Inverse simulation of symmetric flight of a guided gliding subsonic flying body

Inverse simulation of symmetric flight of a guided gliding s...

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aiaa modeling and simulation technologies conference, 2018

作者： Elsherbiny, A.M. Bayoumy, A.M. Elshabka, A.M. Abdelrahman, M.M. Aeronautical Department Military Technical College Cairo Egypt Mechatronics Department Aeronatuical department MSA University Giza Egypt Aeronautical Department Cairo university Cairo Egypt

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

Guided and smart ammunitions are getting interest in the last decades. This paper aims to obtain the time history of control surfaces deflections of a subsonic guided gliding flying body using an inverse dynamics technique in vertical plane motion. This flying body has a standoff capability and designed to attack fixed targets. A 2D trajectory is designed to achieve two requirements. The first is to achieve the maximum range during glide phase subjected to maximum available angle of attack. The second is to achieve the maximum impact angle and impact velocity during terminal phase subjected to maximum available pitch deflection angle. Then a three degree of freedom inverse simulation is performed to obtain the deflection angles time history along the generated trajectory trajectory. Finally, a three degree of freedom direct simulation is performed using these deflection angles. Comparing the inverse and direct trajectories validates the inverse simulation equations, methodology, and results where the difference between the two trajectories time history data can be neglected. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Angle of attack

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Application of Exactly Linearized Error Transport Equations to Sonic Boom Prediction Workshop

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JOURNAL OF AIRCRAFT 2019年第3期56卷 953-961页

作者： Derlaga, Joseph M. Park, Michael A. Rallabhandi, Sriram K. NASA Langley Res Ctr Computat AeroSci Branch 15 Langley BlvdMS 128 Hampton VA 23681 USA NASA Langley Res Ctr Aeronaut Syst Anal Branch 1 N Dryden StMS 442 Hampton VA 23681 USA

The computational fluid dynamics (CFD) prediction workshops sponsored by the aiaa have created invaluable opportunities to discuss the predictive capabilities of CFD in areas in which it has struggled, for example, sonic boom prediction. While there are many factors that contribute to disagreement between simulated and experimental results, such as modeling or discretization errors, quantifying the errors contained in a simulation is important for those who make decisions based on the computational results. The linearized error transport equations (ETE) combined with a truncation error estimate is a method to quantify one source of error. The ETE are implemented with a complex-step method to provide an exact linearization with minimal source code modifications to CFD and multidisciplinary analysis methods including atmospheric propagation of sonic boom signatures. Uniformly refined grids from the 2nd aiaa Sonic Boom Prediction Workshop demonstrate the utility of the linearized ETE for multidisciplinary analysis, capturing the general trends of the discretization error when flow features are resolved while also demonstrating issues related to error prediction near strong shocks or when under-resolved flow features are present.

关键词： Sonic Booms Computational Fluid Dynamics simulation FUN3D Fuselages Computational Aerodynamics Angle of Attack Finite Volume Scheme Fuselage Station Frequency Domain NASA Langley

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Overview of the DoD HPCMP hypersonic vehicle simulation initiative 22

Overview of the DoD HPCMP hypersonic vehicle simulation init...

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22nd aiaa International Space Planes and Hypersonics Systems and technologies conference, 2018

作者： Cummings, Russell M. Morton, Scott A. United States Air Force Academy Hypersonic Vehicle Simulation Institute Colorado SpringsCO80840 United States Eglin AFB FL32542 United States

ISBN: (数字)9781624105777

ISBN: (纸本)9781624105777

simulation of hypersonic vehicles requires the inclusion of multiple scientific aspects that are not currently modeled appropriately, or are not included at all, in most simulation codes. These aspects include: combustion physics, turbulence and transition, fluid-thermal-structural interactions, non-equilibrium chemistry, shock-boundary layer interactions, and ablation. Without the inclusion of these aspects of hypersonic flight (either through physics-based prediction or appropriate modeling), simulation of hypersonic vehicles is deficient and cannot properly provide support to the development and acquisition of hypersonic vehicles. In order to improve the national capability in hypersonic vehicle RDT&E, a Hypersonic Vehicle simulation Institute is being established by the DoD High Performance Computing Modernization Program. The institute will follow a multi-pronged, multi-year approach to address these shortcomings in hypersonic vehicle simulation. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Hypersonic vehicles

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A modeling and simulation tool for safe store separation envelope generation using monte carlo simulations

A modeling and simulation tool for safe store separation env...

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aiaa modeling and simulation technologies conference, 2018

作者： Unal, Kenan Baran, Ozgur Ugras Flight Mechanics Division TUBITAK-SAGE Ankara06261 Turkey Department of Mechanical Engineering TED University Ankara06420 Turkey

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

When an air released store is developed or undergoes substantial updates, integration to aircraft is realized through a certification process. One of the most important steps of the certification process is to determine safe separation envelope. For this process there are several approaches: full scale flight tests, computational fluid dynamics (CFD) simulation techniques and wind tunnel captive trajectory tests. Separation tests applied with flight tests is not only very costly, but it also contains high risks for the aircraft and the pilot. CFD solutions became popular as the computational power becomes achievable in recent years, however most of the time it is not considered as accurate and fast enough to be used for entire safe separation envelope. Most popular store separation analysis method is wind tunnel tests, which may provide accurate and flexible store separation analysis with a carefully designed test plan. The aim of this study is to develop a store separation modeling and simulation tool that will allow achieving the safe separation envelope of a store by performing Monte Carlo simulations to include uncertainties at initial conditions and at physical properties of the store. The new tool is based on six degree of freedom (6DOF) simulation tool based on freestream flight parameters and flow parameters at the vicinity of the aircraft flow field measured at the wind tunnel. This tool is verified with the results of the wind tunnel trajectory measured by Captive Trajectory System (CTS) at the same wind tunnel. The described system allows modeling, simulation and visualization of the store separation by customization of the store and motion parameters and integrates different stages of pre and post processing. Then the flight simulations are extended using Monte Carlo Method to improve confidence on the separation analysis at the actual flight conditions. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Wind tunnels

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Aerial combat simulation environment for one-on-one engagement

Aerial combat simulation environment for one-on-one engageme...

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aiaa modeling and simulation technologies conference, 2018

作者： Baspinar, Baris Koyuncu, Emre Aerospace Research Center Department of Aeronautics Engineering Istanbul Technical University Istanbul34469 Turkey Department of Aeronautics and Astronautics Engineering

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

This paper presents the methods to assist the decision making procedure in an air-to-air combat. It is mainly about engagement phase of the aerial combat for one-on-one scenario. It consists of the aircraft performance model that is implemented with F-16 performance parameters and air combat maneuvers. The basic fighter maneuvers (e.g. aileron roll, barrel roll, immelmann) and some advanced defensive (e.g. vertical spiral, spiral dive) and offensive maneuvers (e.g. low yo-yo, high yo-yo) are described as hybrid system models. These maneuvers are possible chooses of pilots in an air combat. In this study, preferences are defined by a game theoretic approach using some metrics that present the air superiority. These evaluation strategy and objective functions for air superiority are also presented. At the end, the models and decision process are verified through simulations. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Antennas

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modeling, simulation and hybrid optimization method as design tools for range extension kit of a subsonic flying body

Modeling, simulation and hybrid optimization method as desig...

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aiaa modeling and simulation technologies conference, 2018

作者： Elsherbiny, A.M. Bayoumy, A.M. Elshabka, A.M. Abdelrahman, M.M. Aeronautical Department Military Technical College Cairo Egypt Aeronatuical department Mechatronics Department MSA University Giza Egypt Aeronautical Department Cairo university Cairo Egypt

ISBN: (纸本)9781624105289

In this paper a hybrid optimization method is introduced to convert the aerodynamic shape of a conventional aerial subsonic flying body into a glide one by providing a range extension kit and fins. The selections of configuration and airfoils are described depending on the tactical requirements and flight regimes. The wing and fins sizing is obtained using four different methods subjected to geometric constraints. The first method is an iterative optimization method using linear aerodynamic coefficients and derivatives. The second method is a multi-objective function genetic algorithm aims to maximize stability, controllability and lift-drag ratio within certain weights using linear aerodynamic data. The third method is a genetic algorithm optimization function integrated with MISSILE DATCOM aims to maximize lift-drag ratio. The fourth method is a hybrid optimization method that integrate MISSILE DATCOM with both genetic algorithm and gradient-based optimization method. Then perform a direct uncontrolled six degree of freedom simulation for the four designs and the conventional flying body. Comparing the results of ranges for these bodies reveals that the hybrid optimization method has the best range over the other designs including the conventional flying body. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Genetic algorithms

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A mission optimization tool for air to ground tactical operations

A mission optimization tool for air to ground tactical opera...

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modeling and simulation technologies conference, 2018

作者： Akgül, Mehmet Aydın, Gunes Modeling and Simulation Department Roketsan Missile Industries Inc ElmadağAnkara06780 Turkey

ISBN: (数字)9781624105517

ISBN: (纸本)9781624105517

In most of the todays air forces around world have a wide variety guided missile/munition and aircraft systems in their inventory. Thanks to highly standardized munition-aircraft interfaces, these wide variety munitions can be easily integrated to wide variety aircrafts. This integration capability increases operational flexibility for the mission planner;however it brings complexity to match aircraft-munition alternative for a given specific operation regarding to mission success, time required and cost. For this reason there is a need for a tool in order to assist to solve mission planning complexity problem. This paper demonstrates that an optimization tool that utilizes genetic algorithm methods can handle the complexity problem and an optimal solution to single or multi objective mission profile can be obtained when combined with a mission simulation. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Genetic algorithms

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Space object trajectory simulation validation and computational efficiency analysis for adaptive algorithm execution

Space object trajectory simulation validation and computatio...

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aiaa modeling and simulation technologies conference, 2018

作者： Reynerson, Charles M. Raytheon Corporation AuroraCO80011 United States Raytheon ISS United States

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

When using propagation tools for estimating the states for large numbers of objects, it is important to know which orbital perturbations can be deemphasized to trade off computational speed with the state accuracy. Those algorithms that have the highest computational cost with the least impact in state accuracy will be identified. Some perturbation algorithms have more applicability to certain orbits as far as the relative impact of the applied forces on the trajectory. Therefore, particular object algorithms can be dynamically changed when particular perturbations are less relevant (and when the duration of the propagation interval is taken into account). By knowing this information, an adaptive algorithm scheme can be developed for more efficient overall computational environments. In this paper, a space object dynamic simulator was used to predict the future position and velocity of an object by integrating the net force applied to an object. The equations of motion are coded in the Python language, making it flexible for running the program on multiple platform operating systems (Windows, Linux, Mac). Multiple simulation runs are performed to examine which perturbations are the most significant at impacting execution speed and accuracy. A recommended algorithm approach is shown based on the altitude to help determine which perturbations are the most significant. Those perturbations with less significance are candidates to be excluded if the goal is to increase simulation speedup rather than to calculate the highest accuracy. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Adaptive algorithms

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A novel method to build a factor space for model validation

A novel method to build a factor space for model validation

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modeling and simulation technologies conference, 2018

作者： Fang, Ke Yang, Ming Zhou, Yuchen Control & Simulation Center Harbin Institute of Technology Harbin150001 China

ISBN: (纸本)9781624105517

Factor space is an indispensable part of the model validation. In order to provide an advantageous method to build factor space for model validation, this paper states the challenging problems of the factor space, and proposes a mathematical model of it. Further based on the model, this paper provides the graphic illustration, the factor decomposition, the credibility aggregation and the model defect tracing of the factor space, which construct a novel method to build a factor space for model validation. Finally, the paper provides a case study of an electromagnetic rail gun model validation to explain the usage of the method. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

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