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AIAA Science and Technology Forum and Exposition (AIAA SciTech Forum)

作者： Yokoyama, Nobuhiro Natl Def Acad Dept Aerosp Engn 1-10-20 Hashirimizu Yokosuka Kanagawa 2398686 Japan

ISBN: (数字)9781624106095

ISBN: (纸本)9781624106095

The present paper proposes a decentralized trajectory optimization method for air traffic flow including conflict resolution. The proposed method does not need explicit communication of tactical intent information with neighboring aircraft, such as going directly to a waypoint or conflict resolution with neighboring aircraft, but rather infers it by solving the inverse optimal control problem based on observed trajectories and calculates the coordinated velocities of all the involved aircraft reflecting their inferred intent. Based on these coordinated velocities, the proposed method then solves a decentralized model predictive control (MPC) problem to compute the optimal trajectory of each aircraft. Moreover, to make the calculation of the resulting non-convex MPC problem tractable, a novel convexification technique for quadratic equalities/inequalities is introduced. Through several numerical simulations, the effectiveness of the proposed method is confirmed in terms of the validity of the obtained conflict-free trajectories and the computational efficiency.

关键词： Trajectory optimization Model Aircraft Model Predictive Control Numerical Simulation Air Traffic Management System Closest Point of Approach optimization algorithm Lagrange Multipliers Flight Planning Airspace

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Enhanced Flexible algorithm for the optimization of Slot Filling Factors in Electrical Machines

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ENERGIES 2020年第5期13卷

作者： Dietz, Armin Di Tommaso, Antonino Oscar Marignetti, Fabrizio Miceli, Rosario Nevoloso, Claudio Tech Hsch Nurnberg Inst ELSYS D-90489 Nurnberg Germany Univ Palermo Dipartimento Ingn Viale Sci I-90128 Palermo Italy Univ Cassino & South Lazio Dept Elect & Informat Engn DIEI Via G Di Biasio 43 I-03043 Cassino Italy

The continuous development in the field of industrial automation and electric mobility has led to the need for more efficient electrical machines with a high power density. The improvement of electrical machines' slot filling factors is one of the measures to satisfy these requirements. In recent years, this topic has aroused greater interest in the industrial sector, since the evolution of the winding technological manufacturing processes allows an economically sustainable realization of ordered winding arrangements, rather than random ones. Moreover, the manufacture of electrical machines' windings must be preceded by an accurate design phase in which it is possible to evaluate the maximum slot filling factor obtainable for a given wire shape and for its dimensions. For this purpose, this paper presents an algorithmic approach for the evaluation of maximum slot filling factors in electrical machines under an ideal geometric premise. In particular, this algorithm has a greater degree of flexibility with respect to the algorithm approaches found in the literature, since the study has been extended to round, rectangular and hexagonal wire sections. Furthermore, the slot filling factor calculation was carried out both for standard and non-standard slots. The algorithmic approach proposed can be considered as an additional useful tool for the fast design of electrical machine windings.

关键词： electrical motors sot filling factor optimization algorithm windings magnetic wire filling factor optimization

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Aerodynamic Shape optimization of an S-Duct Intake for a Boundary Layer Ingesting Engine

Aerodynamic Shape Optimization of an S-Duct Intake for a Bou...

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AIAA Aviation Forum and Exposition

作者： Chiang, Christopher Koo, David Zingg, David W. Univ Toronto Inst Aerosp Studies Toronto ON M3H 5T6 Canada

ISBN: (数字)9781624106101

ISBN: (纸本)9781624106101

Ahigh-fidelity aerodynamic shape optimization framework based on the Reynolds-Averaged Navier-Stokes equations is applied to the optimization of a boundary layer ingesting S-duct designed for embedded engines on a high-subsonic, unmanned flight vehicle. The optimizations initially target a cruise operating condition and are further extended to single-point and multi-point optimizations considering descent and climb. Two different composite objective functions are used. The first combines distortion and swirl at the fan interface plane as well as total pressure recovery, with user-defined weights for each objective, while the second involves pressure recovery, fan blade load variation, and fan blade incidence variation. Pareto fronts show the trade-offs between objectives. The results indicate that compared to the baseline geometry, a simultaneous improvement in all objectives contained in the composite objective function can be obtained, depending on the priorities of each objective pre-assigned by the user. It was also found that if swirl can be ignored, then fan-face distortion can be greatly reduced while simultaneously reducing total pressure loss in the S-duct. Similarly, fan blade load variation and fan blade incidence variation can be significantly reduced while reducing total pressure loss. Finally, the multipoint optimization results show that a single S-duct geometry can perform well during cruise, climb, and descent conditions.

关键词： Momentum Boundary Layer Aerodynamic Shape optimization Reynolds Averaged Navier Stokes Fan Blades Flight Vehicle Blade Loading Aerodynamic Performance Flow Conditions optimization algorithm Sparse Nonlinear Optimizer

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Airplane Design optimization for Minimal Global Warming Impact

Airplane Design Optimization for Minimal Global Warming Impa...

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AIAA Science and Technology Forum and Exposition (AIAA SciTech Forum)

作者： Proesmans, P. Vos, R. Delft Univ Technol Fac Aerosp Engn Kluyverweg 1 NL-2629 HS Delft Netherlands

ISBN: (数字)9781624106095

ISBN: (纸本)9781624106095

This paper presents a method to assess the key performance indicators of aircraft designed for minimum direct operating cost and aircraft designed for minimum global-warming impact. The method comprises a multidisciplinary aircraft optimization algorithm capable of changing wing, engine and mission design variables while including constraints on flight and field performance. The presented methodology uses traditional Class-I methods augmented with dedicated Class-II models to increase the sensitivity of the performance indicators to relevant design variables. The global-warming impact is measured through the average temperature response caused by several emission species, including CO2, NOx and contrail formation, over a prolonged period of one hundred years. The analysis routines are verified against experimental data or higher-order methods. The design algorithm is subsequently applied to a single-aisle, medium-range aircraft, demonstrating that a 45% reduction in average temperature response can be achieved by flying at 8.64 km and Mach 0.61, and by reducing the engine overall pressure ratio to 34 when compared to an aircraft optimized for minimal operating costs or fuel burn. However, if the total productivity of the aircraft fleet is to be maintained, the potential reduction shrinks to 38%.

关键词： Aircraft Design Condensation Trails Overall Pressure Ratio Aircraft Operating Costs Depreciation Costs optimization algorithm Narrow Body Aircraft Zero Lift Drag Coefficient Aircraft Configurations High Aspect Ratio

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Aircraft Wing Design Through Concurrent Thickness and Material optimization

Aircraft Wing Design Through Concurrent Thickness and Materi...

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AIAA Science and Technology Forum and Exposition (AIAA SciTech Forum)

作者： Kashanian, Kiarash Kim, Il Yong Queens Univ Dept Mech & Mat Engn Kingston ON K7L 2N8 Canada

ISBN: (数字)9781624106095

ISBN: (纸本)9781624106095

Existing optimization algorithms do not allow for simultaneous thickness optimization and material selection of non-laminate shell structures. The proposed concurrent thickness and material optimization (CTMO) scheme fills this niche, with a focus on practical, industry-style problems. A complex aircraft wing model is developed and optimized through CTMO. An extensive parameter sweep is conducted for this model, generating 384 results with different designable thickness limits and masses. These results are analyzed to show overall trends in compliance based on problem constraints. Selected results are presented qualitatively to study material selection and optimized thickness. Finally, the relevance of this work to real-world engineering studies is discussed, along with some areas for future improvement of CTMO.

关键词： Aircraft Wing Design optimization algorithm Finite Element Modeling Light Sport Aircraft Topology optimization Numerical Stability Composite Laminates Material Properties Structural Load Poisson's Ratio

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Multi-criteria Multi-constrained Aerodynamic optimization of Civil Tiltrotor Empennage Surfaces

Multi-criteria Multi-constrained Aerodynamic Optimization of...

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AIAA Aviation Forum and Exposition

作者： Battiston, A. Ponza, R. Benini, E. Bernini, G. Pecoraro, M. HIT09 Srl I-35127 Padua Italy Univ Padua Dept Ind Engn I-35131 Padua Italy Leonardo SpA Helicopter Div I-21017 Cascina Costa Di Samarat Italy

ISBN: (数字)9781624106101

ISBN: (纸本)9781624106101

The present work describes the overall optimization strategy that has been adopted for the enhancement of the aerodynamic performance of a civil tiltrotor empennage surfaces. The optimization process has been designed around GeDEA-II, a Multi-Objective Evolutionary algorithm developed at University of Padua. The optimization algorithm has been used in two different cases: a two-dimensional optimization of the empennage airfoil and a threedimensional optimization of the empennage winglets, patented by Leonardo Helicopters under the name of finlets. Results demonstrate the effectiveness of the optimization strategies for both the cases. A parametric study of the empennage planform has also been conducted with the aid of an artificial neural network, in order to assess the variations in aerodynamic performance for different geometries.

关键词： Tiltrotor Airframes Aerodynamic Performance Symmetric Airfoil Artificial Neural Network optimization algorithm Multi Objective Evolutionary algorithms Leonardo Helicopters Aerodynamic Coefficients Aspect Ratio

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Image Non-significant Target Detection Based on Depth Metric Particle Swarm optimization

Image Non-significant Target Detection Based on Depth Metric...

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International Conference on Computer, Control and Robotics (ICCCR)

作者： Song, Xinxin Dou, Quansheng Shandong Technol & Business Univ Sch Informat & Elect Engn Yantai Peoples R China Shandong Technol & Business Univ Sch Comp Sci & Technol Yantai Peoples R China

ISBN: (纸本)9781728190358

In the problem of target detection, the degree of discrimination between the target area and the background area will directly affect the detection result. The existing target detection algorithms relies too much on the difference between the target area and the background area. When the boundary between the target region and the background region is fuzzy or even intersects, the detection effect is not good. In order to overcome this problem, this paper proposes a depth measurement particle swarm optimization method for target detection of blurred images. By constructing a depth measurement model, the similarity between the target and the detection area is solved, combined with PSO (particle swarm search algorithm). Search the target area. Compared with the existing target detection algorithms, the proposed in this paper is more effective in dealing with medical image target detection problems.

关键词： optimization algorithm target detection deep neural network similarity measure

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Conjunction Time and Collision Probability Calculation Based on Bayesian optimization

Conjunction Time and Collision Probability Calculation Based...

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AIAA Science and Technology Forum and Exposition (AIAA SciTech Forum)

作者： Jia, Bin Xing, Ming Aptiv Agoura Hills CA 91301 USA Univ Missouri Dept Mech & Aerosp Engn Columbia MO 65211 USA

ISBN: (数字)9781624106095

ISBN: (纸本)9781624106095

Collision probability calculation is critical to space situational awareness or space traffic management. To determine the collision probability, the conjunction time is required first. In this paper, the continuous representation of the polynomial chaos is used to describe the uncertainty of space objects along with time. Based on this representation, the Bayesian optimization is employed to find the conjunction time and then the collision probability. The polynomial chaos representation and Bayesian optimization do not require Gaussian assumption and are computationally more efficient than the Monte Carlo sampling-based method to calculate collision probability and time. The effect of the order of polynomial chaos as well as the sampling period is also analyzed. Two numerical experiments are used to show the effectiveness of the proposed algorithm.

关键词： Bayesian optimization Space Situational Awareness Space Traffic Management Numerical Integration Monte Carlo Method Probability Density Functions Graphics Processing Unit optimization algorithm Maximum Likelihood Estimation Aerospace Engineering

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A Local Area Segmentation algorithm for the Underwater Transponder Calibration 7

A Local Area Segmentation Algorithm for the Underwater Trans...

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7th International Conference on Robotics and Automation Engineering (ICRAE)

作者： Zhang, Haixu Xu, Xiaosu Southeast Univ Sch Instrument Sci & Engn Minist Educ Key Lab Microinertial Instrument & Adv Nav Techno Nanjing Peoples R China

ISBN: (纸本)9781665489188

The accuracy in depth estimation of the transponder calibration algorithms based on Long Baseline (LBL) technology needs to be improved, especially in the case of no Depth Gauge (DG), poor depth estimation will directly affect the spatial positioning accuracy. In order to comprehensively improve the solution accuracy of transponder calibration, this paper proposes a calibration algorithm based on Local Area Segmentation (LAS) method. According to the simulation results, LAS performs the best in depth estimation, horizontal positioning solution and spatial positioning accuracy.

关键词： transponder calibration TOA optimization algorithm underwater positioning LBL

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Robust Pole Assignment via State Feedback for Uncertain High-order System 4

Robust Pole Assignment via State Feedback for Uncertain High...

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4th International Conference on Control and Robotics (ICCR)

作者： Gao, Yajun Duan, Guang-Ren Harbin Inst Technol Ctr Control Syst & Guidance Technol Harbin Peoples R China Southern Univ Sci & Technol Ctr Control Sci & Technol Shenzhen Peoples R China

ISBN: (纸本)9781665486415

The problem of robust pole assignment for the uncertain high-order system is formulated. On the strength of a previous eigenstructure assignment result for the high-order system, by introducing the sensitivity of uncertain parameters in the system model to the closed-loop poles, the parametric expression of the state feedback gain matrix to the problem of robust pole assignment is obtained. The robust optimal solution can be derived by a simple independent optimization algorithm. The closed-loop poles can be fixed or chosen within certain desired regions on the complex plane, which further improves the robustness. The example illustrates robust state feedback controller obtained by the proposed algorithm has better robustness.

关键词： Robust pole assignment Uncertain high-order system Complete parametric solution optimization algorithm

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