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A modeling, simulation and control framework for small unmanned multicopter platforms in urban environments

A modeling, simulation and control framework for small unman...

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aiaa modeling and simulation technologies conference, 2018

作者： Ippolito, Corey A. Krishnakumar, Kalmanje Hening, Sebastian Sankararaman, Shankar NASA Ames Research Center Moffett Field CA94035 United States Stinger Ghaffarian Technologies Inc Moffett Field CA94035 United States Stinger Ghaffarian Technologies Inc. NASA Ames Research Center Moffett Field CA94035 United States

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

The market for small unmanned multicopter vehicle platforms has been growing rapidly, and as demand for using these vehicles grows, there is a pressing need for higher-fidelity simulation frameworks with accurate and validated dynamic models to ensure safe operation in complex environments, such as urban city-scapes, to support regulatory decision-making. In this paper we present a modeling, control, and simulation framework to support autonomy research on small unmanned multicopters. This framework includes dynamics based on a forward flight aircraft model derived from aerodynamic coefficients, an extensible mode-based flight management system, a flexible automatic flight control system, and an interactive environment model for urban environments. The system is built on the modular Reflection Architecture that facilitates development and testing of new research components for autonomous vehicle systems in both hardware and software. This paper presents an overview of the framework, derivation of models, overview of the flight hardware, and initial results. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Decision making

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simulation of integrated approach for aircraft turnaround process

Simulation of integrated approach for aircraft turnaround pr...

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aiaa modeling and simulation technologies conference, 2018

作者： Jin, Hyunjee Garcia, Elena Mavris, Dimitri Georgia Institute of Technology AtlantaGA30332-0150 United States Aerospace System Design Laboratory Georgia Institute of Technology United States

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

To handle the high volume of increasing air traffic demands, a more efficient operational strategy is necessary due to capacity limitations. Reducing inefficiencies in ground space workflow can greatly reduce extra costs for airlines and airports as well as improve passenger comfort by increasing the number of on-time flights. Thus, this paper will focus on improving the aircraft turnaround process with the goal of increasing the number of on-time flights and decreasing the total delay time. It will proceed to introduce an integrated approach for the aircraft turnaround process and analyze the performance of the approach with a case study. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Aircraft

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Applying the DASE protocol to a high-speed engine performance analysis

Applying the DASE protocol to a high-speed engine performanc...

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aiaa modeling and simulation technologies conference, 2018

作者： Henderson, Ryan O. Snyder, Sharon E. Ward, Christopher A. C. Hurst, Terril N. Raytheon Missile Systems TucsonAZ85756 United States Advanced Systems Development Center TucsonAZ85756 United States Guidance Navigation and Control Center TucsonAZ85756 United States Modeling Simulation and Analysis Center TucsonAZ85756 United States

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

A 7-step protocol called Design and Analysis of simulation of Experiments (DASE) was applied to a high-speed engine study. Two multivariate surrogate model types were compared for engine performance sensitivity analysis: a polynomial regression model and a regression tree. The polynomial regression model produced imprecise results. The regression tree model produced significantly more precise results, with almost all data falling within the discernible (practical) difference declared for the simulation experiment. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Sensitivity analysis

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modeling and inverse simulation of generic helicopter maneuvers

Modeling and inverse simulation of generic helicopter maneuv...

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aiaa modeling and simulation technologies conference, 2018

作者： Hassan, Hassan Shahat Bayoumy, Amgad M. El-Bayoumi, Gamal M. Abdelrahman, Mohamed Madbouly Aerospace engineering-Cairo University Cairo Egypt Military Technical College Cairo Egypt

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

Inverse simulation is a computational method that determines the control inputs required for a dynamic system to achieve a desired output. In case of helicopter dynamics, inverse simulation is used to obtain the pilot control inputs required for the helicopter to accomplish a desired maneuver. Complex configuration of helicopter makes its model inversion is significantly more difficult than fixed wing aircrafts. In this paper, a general method, used to define any helicopter maneuver in earth axes system, is introduced. An algorithm, for solving the helicopter inverse simulation problem at a given maneuver by using the differentiation approach, is presented. This method is based on converting the model nonlinear differential equations to algebraic difference equations which can be solved at each time step by an iterative scheme. The accuracy of this technique is improved by increasing the order of the finite difference scheme and decreasing the time step. The verification of the inverse simulation results is achieved by supplying the resultant control inputs to the direct simulation code and the helicopter flies in the desired maneuver. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Nonlinear equations

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simulation study for the comparison of 3 & 4 fin controlled air vehicles

Simulation study for the comparison of 3 & 4 fin controlled ...

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aiaa modeling and simulation technologies conference, 2018

作者： Yavuzturk, Nabi Vefa Bent, Mustafa Kucuk, Umut Can Flight Mechanics Division TUBITAK-SAGE Ankara06261 Turkey Aerodynamic Division TUBITAK-SAGE Ankara06261 Turkey

ISBN: (纸本)9781624105289

In this paper, effects of the fin configurations are studied for air vehicles controlled by 3 & 4 fins. Moreover, fin mixing for untraditional configuration of 3-fin controlled air vehicles is derived. Afterwards, 3 & 4 fin controlled missiles with same fin area on sample geometry are compared in terms of lift, drag, static margin, control effectiveness and trim performance. Finally, a simulation study is carried out to compare the performance of 3 & 4 fin controlled air vehicles. In simulation study, at first, a basic fin actuator model is built and responses of both systems to the doublet input are examined. At the last step of simulation study, the instantaneous turn performance for both air vehicles is compared. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Fins (heat exchange)

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Online trimming of flight dynamics models using the 2simulate realtime simulation framework

Online trimming of flight dynamics models using the 2simulat...

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aiaa modeling and simulation technologies conference, 2018

作者： Gotschlich, Jürgen Jones, Michael Institute of Flight Systems Flight Dynamics and Simulation Lilienthalplatz 7 Braunschweig38108 Germany Institute of Flight Systems Rotorcraft Department Lilienthalplatz 7 Braunschweig38108 Germany

ISBN: (纸本)9781624105289

Real-time simulation requires the definition of scenarios, which may be defined on the ground or in the air. In-flight scenarios usually begin in a trimmed flight condition, so that the simulation model is in a steady state. At the German Aerospace Center (DLR), the Air Vehicle Simulator (AVES) is operated for flight research and simulator studies. Research simulators require a high degree of flexibility to modify scenarios. Moreover, the flexibility to modify the simulation model poses a challenge to both the user interface and the trim procedure. Therefore, an adjustable user interface is required to allow the user to run the trim calculation online for immediate operation in a simulation run. This paper presents an implementation of a generic approach to trim flight dynamic models for use in research flight simulators. This implies both the implementation of a graphical user interface as well as the trim algorithm and their interaction. An example is demonstrated for a helicopter model used for research activities at DLR. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Flight simulators

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Adapting scenario definition language for formalizing uas concept of operations

Adapting scenario definition language for formalizing uas co...

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aiaa modeling and simulation technologies conference, 2018

作者： Torens, Christoph Durak, Umut Nikodem, Florian Dauer, Johann Adolf, Florian-Michael Dittrich, Joerg Institute of Flight Systems Braunschweig Germany Flight Dynamics and Simulation Safety Critical Systems and Systems Engineering

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

Recent regulatory efforts from EASA introduced the new concept of a specific category that allows a stepwise adaptation of certification requirements. Based on a specific operation risk assessment, this category enables new aircraft system architectures and mission designs. The concept allows for operational restrictions, defined in the concept of operations, to maintain overall operation safety. Therefore, the description of the concept of operations is one of the key elements for the approval of a UAS operation. This description will be used by pilots, operators, certification authorities and possibly additional stakeholders, e.g., for publishing operation into databases. Standardization of this document seems mandatory. In addition to this, we discuss the formalization of this document for easy distribution amongst stakeholders and establishment of tool support. To support this, we use recent developments regarding standardization of simulation modeling. The American Institute of Aeronautics and Astronautics modeling and simulation Technical Committee recently launched a working group towards the development of a standard scenario definition language for aviation. In this paper, we extend this language specification in order to define specific operation safety boundaries of a system. Thereby, we aim at creating a dialect of the simulation scenario definition language that can be used to describe safe scenarios for a particular system of interest. We further discuss the challenges and benefits of such a formalization of the concept of operations by adapting the simulation scenario definition language. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Standardization

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Model-in-the-loop simulation of experimental flight control software

Model-in-the-loop simulation of experimental flight control ...

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aiaa modeling and simulation technologies conference, 2018

作者： Zollitsch, Alexander W. Schatz, Simon P. Mumm, Nils C. Holzapfel, Florian Technical University of Munich Garching85748 Germany Institute of Flight System Dynamics Boltzmannstrasse 15 Garching85748 Germany

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

This paper describes a model-in-the-loop simulation in Simulink to design and test experimental flight control software of a general aviation research aircraft, specifically a modified Diamond Aircraft Industries DA42 M-NG. The aircraft offers an experimental fly-by-wire system with access to all axes of the mechanical flight controls. The experimental software model subject to testing is developed using model-based design in Simulink. The simulation is highly flexible and scalable due to its modularity, which is essential for experimental software. The model-in-the-loop environment provides cost- and time-efficient development and testing, which accelerates the path towards flight test experiments. The core components of the simulation include the flight control computer model, actuation models, a flight dynamics model, sensor models, and numerous command and feedback interfaces. Interfaces to the control software are stimulated in the simulation environment, which allows manual interaction in soft real-time, automatic test case execution, and application of Monte Carlo methods. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Research aircraft

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Model predictive control for path tracking of a VTOL tail-sitter UAV in an HIL simulation environment

Model predictive control for path tracking of a VTOL tail-si...

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aiaa modeling and simulation technologies conference, 2018

作者： Li, Boyang Zhou, Weifeng Sun, Jingxuan Wen, Chih-Yung Chen, Chih-Keng The Hong Kong Polytechnic University Hong Kong National Taipei University of Technology Taipei Taiwan Department of Mechanical Engineering Department of Vehicle Engineering

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

This paper investigates the application of Model Predictive Control (MPC) for path tracking of a vertical takeoff and landing (VTOL) tail-sitter unmanned aerial vehicle (UAV) in hovering. In this work, the nonlinear dynamic model of a quad-rotor tail-sitter UAV including the aerodynamic effect of the wing, propellers, and slipstream was developed. The cascaded MPC controllers were then built upon linearized dynamic models. Path tracking simulations were conducted in a hardware-in-loop (HIL) environment where the UAV model and controllers were running on a PC and a flight computer independently. The simulation results show that the proposed MPC controllers are capable to perform good path tracking and the ability of disturbance rejection under limited on-board computation resource. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Model predictive control

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Overview of studies using the numerical propulsion system simulation at UT-Arlington

Overview of studies using the numerical propulsion system si...

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aiaa modeling and simulation technologies conference, 2018

作者： Vu, Long N. Vijayakumar, Nandakumar Wilson, Donald R. Department of Mechanical and Aerospace Engineering University of Texas at Arlington ArlingtonTX76019 United States Mechanical and Aerospace Engineering Department Aerodynamics Research Center Box 19018 United States

ISBN: (数字)9781624105289

ISBN: (纸本)9781624105289

The progress in the development of computational simulation tools has opened a more efficient and economical way of engine design and manufacturing, in which the number of redesign, rebuild and retest cycles is significantly reduced. The Numerical Propulsion System simulation (NPSS) is one such tool with the ability of performing multidisciplinary and multifidelity analysis. A number of research projects at the University of Texas at Arlington (UTA) have been done using NPSS, covering various topics not limited to the aerospace discipline. This paper aims to provide an overview of these studies. An introduction to NPSS is first given, continuing with a description of its structure and components. A literature study of several prominent works that have been carried out utilizing NPSS are highlighted, followed by a consolidated overview of studies involving NPSS at UTA together with several recommendations for future application of NPSS are presented. Emphasis is placed on how NPSS is utilized in the aforementioned research studies. © 2018, American Institute of Aeronautics and Astronautics Inc, aiaa. All rights reserved.

关键词： Machine design

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