检索结果-内蒙古大学图书馆

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

来源：评论

学校读者我要写书评

暂无评论

Conjunction Time and Collision Probability Calculation Based on Bayesian optimization

Conjunction Time and Collision Probability Calculation Based...

引用

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

来源：评论

学校读者我要写书评

暂无评论

Decentralized Trajectory optimization of Multiple Aircraft Using Intent-Based Coordination

Decentralized Trajectory Optimization of Multiple Aircraft U...

引用

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

来源：评论

学校读者我要写书评

暂无评论

Residential building energy consumption estimation: A novel ensemble and hybrid machine learning approach

引用

EXPERT SYSTEMS WITH APPLICATIONS 2024年 251卷

作者： Sadaghat, Behnam Afzal, Sadegh Khiavi, Ali Javadzade Tabriz Univ Fac Civil Engn Water Resources Engn Dept Tabriz Iran Univ Mohaghegh Ardabili Dept Mech Engn Ardebil Iran Univ Mohaghegh Ardabili Dept Civil Engn Ardebil Iran

In recent decades, there has been a substantial rise in both worldwide energy consumption and the accompanying increase in Carbon Dioxide (CO2) emissions, primarily propelled by population growth and the escalating demand for personal comfort. Operational energy consumption in buildings constitutes about 30% of the world's total final energy usage, underscoring the significance of predicting building energy usage for effective energy planning, management, and conservation. This study has enhanced the prediction of heating load (HL) and cooling loads (CL) for residential buildings using novel and dependable machine learning (ML) techniques. The study utilized two base models: Adaptive Boosting (ADA) and Extreme Gradient Boosting (XGBoost). An ensemble consisting of ADA and XGB was constructed to improve the model's performance, aligning with the principles of the Dempster-Shafer theory. To optimize the efficiency of ADA and XGB, five innovative optimizers, namely Victoria Amazonica optimization (VAO), Giant Trevally Optimizer (GTO), Covariance Matrix Adaptation Evolution Strategy (CMAES), Coyote optimization algorithm (COA), and Mountain Gazelle Optimizer (MGO), were integrated. Statistical analysis has been employed to evaluate the performance of the proposed models. The results highlight the effectiveness of CMAES in optimizing the XGB and ADA models for predicting HL and CL. The most accurate result was achieved by the XGCM hybrid model, as evidenced by the impressive total R2 value of 0.9934 in HL and 0.9911 in CL prediction. The experimental findings illustrate that the suggested approach exhibits superior predictive performance across various scenarios of building energy consumption.

关键词： Building Energy Heating load Cooling load Adaptive Boosting Extreme Gradient Boosting optimization algorithm

来源：评论

学校读者我要写书评

暂无评论

Compact Ultra-Wideband Wilkinson Power Divider in Parallel Stripline with Modified Isolation Branches

引用

SENSORS 2024年第11期24卷 3437页

作者： Go, Dong-Jae Min, Byung-Cheol Kim, Mun-Ju Choi, Hyun-Chul Kim, Kang-Wook Kyungpook Natl Univ Sch Elect & Elect Engn Daegu 41566 South Korea

An efficient design method for a compact and ultra-wideband multi-stage Wilkinson power divider in a parallel stripline (PSL) is proposed. To enhance the frequency bandwidth of the proposed power divider while reducing its size, the isolation branch is modified;that is, two capacitors are connected to both sides of a resistor at each isolation branch. For an efficient design process, the PSL power divider is equivalently represented by two microstrip power dividers, and the design equations are derived. Based on the design equations, an in-house algorithm is utilized to optimally determine the design parameters, including the line impedance, resistance, and capacitance of each stage. For example, a three-stage PSL power divider is designed with three lambda/4 transmission lines at a base frequency of 5 GHz. To verify the accuracy of the design procedure, 3D EM simulations and measurements are performed, and the results show good agreement. Compared with the conventional three-stage Wilkinson power divider, the proposed PSL power divider achieves a wider frequency bandwidth of 1.16 to 6.51 GHz (139.5%) and a 23% shorter transmission line length of 207 degrees, while exhibiting an insertion loss of 0.7 to 1.4 dB.

关键词： parallel stripline power divider/combiner ultra-wideband isolation branch optimization algorithm

来源：评论

学校读者我要写书评

暂无评论

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

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

引用

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

来源：评论

学校读者我要写书评

暂无评论

Study on thermal error modeling of high-speed motorized spindle inner

引用

CASE STUDIES IN THERMAL ENGINEERING 2024年 58卷

作者： Dai, Ye Pang, Jian Rui, Xukun Li, Weiwei Harbin Univ Sci & Technol Key Lab Adv Mfg Intelligent Technol Minist Educ Minist Educ Harbin 150080 Peoples R China Harbin Univ Sci & Technol Inst Digital Design & Automatic Machinery Prod Dev Harbin 150080 Peoples R China

In addressing the challenge of unattainable temperature data at critical heat source points in bearings, this study solves for the temperatures of the bearing inner ring and rollers by merging thermal resistance network calculations with experimental data, referencing finite element simulation outcomes. The impact of temperature data from various positions within bearings on model accuracy is assessed using a BP prediction model. Subsequently, the training dataset of the thermal error model is optimized to enhance its predictive performance. To further boost the predictive capabilities of the model, a whale optimization algorithm is employed to optimize the BP neural network, which is then compared against both the conventional BP model and the GPR model. The findings reveal that a model optimized with the input of inner ring temperatures and the WOA algorithm achieves an accuracy rate of 97.748 %, outperforming both the BP model and the GPR model. This study provides a new idea for the field of thermal error modeling of motorized spindle.

关键词： High-speed motorized spindle Thermal characteristic simulation analysis Thermal resistance network Thermal error prediction model optimization algorithm

来源：评论

学校读者我要写书评

暂无评论

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...

引用

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

来源：评论

学校读者我要写书评

暂无评论

Airplane Design optimization for Minimal Global Warming Impact

Airplane Design Optimization for Minimal Global Warming Impa...

引用

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

来源：评论

学校读者我要写书评

暂无评论

Aircraft Wing Design Through Concurrent Thickness and Material optimization

Aircraft Wing Design Through Concurrent Thickness and Materi...

引用

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

来源：评论

学校读者我要写书评

暂无评论

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案：

请选择收藏分类：

通借通还

建议与咨询 留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案： 新增检索档案 确定 取消

请选择收藏分类： 新增自定义分类 确定 取消

通借通还

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

请选择保存的检索档案：

请选择收藏分类：