检索结果-内蒙古大学图书馆

您好，读者！请登录

内蒙古大学图书馆

首页
概况
党建
资源
服务
科研支持
- 论文收录引用证明
- 科技查新
知识产权
档案馆
帮助

咨询与建议

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

您的常用邮箱：*

您的手机号码：*

问题描述：

当前已输入0个字，您还可以输入200个字

全部搜索
期刊论文
图书
学位论文
标准
纸本馆藏
外文资源发现
数据库导航
超星发现

高级检索

时间限定

出版年份：

文献类型

图书期刊文献学位论文多媒体

馆藏选择

电子馆藏纸本馆藏

核心期刊

全部期刊 SCI 收录期刊 SSCI 收录期刊 EI 收录期刊 CSCD 收录期刊 CSSCI 收录期刊

语言

中文英文

文献类型

期刊文献图书学位论文标准纸本馆藏

帮助

文字说明：

T=题名（书名、题名），A=作者（责任者），K=主题词，P=出版物名称，PU=出版社名称，O=机构（作者单位、学位授予单位、专利申请人），L=中图分类号，C=学科分类号，U=全部字段，Y=年（出版发行年、学位年度、标准发布年）

检索规则说明：

AND代表“并且”；OR代表“或者”；NOT代表“不包含”；(注意必须大写,运算符两边需空一格)

检索范例：

范例一：(K=图书馆学 OR K=情报学) AND A=范并思 AND Y=1982-2016
范例二：P=计算机应用与软件 AND (U=C++ OR U=Basic) NOT K=Visual AND Y=2011-2016

分类表

所选分类

>> <<

限定检索结果

文献类型

935 篇 期刊文献
240 篇 会议
5 篇 学位论文

馆藏范围

1,180 篇 电子文献
0 种 纸本馆藏

日期分布

学科分类号

959 篇 工学
- 333 篇 航空宇航科学与技...
- 184 篇 计算机科学与技术...
- 160 篇 电气工程
- 157 篇 机械工程
- 141 篇 仪器科学与技术
- 99 篇 控制科学与工程
- 84 篇 力学（可授工学、理...
- 75 篇 石油与天然气工程
- 64 篇 软件工程
- 40 篇 动力工程及工程热...
- 35 篇 信息与通信工程
- 30 篇 材料科学与工程（可...
- 30 篇 土木工程
- 26 篇 化学工程与技术
- 25 篇 交通运输工程
- 17 篇 电子科学与技术（可...
- 13 篇 建筑学
- 9 篇 水利工程
- 8 篇 光学工程
- 7 篇 环境科学与工程（可...
351 篇 理学
- 248 篇 数学
- 73 篇 物理学
- 15 篇 统计学（可授理学、...
- 14 篇 系统科学
- 12 篇 生物学
- 7 篇 化学
- 7 篇 地球物理学
295 篇 管理学
- 289 篇 管理科学与工程(可...
10 篇 经济学
- 9 篇 应用经济学
10 篇 医学
6 篇 农学
1 篇 法学
1 篇 教育学

主题

1,180 篇 sequential quadr...
125 篇 nonlinear progra...
76 篇 genetic algorith...
67 篇 trajectory optim...
62 篇 optimization
58 篇 optimal control
49 篇 earth
44 篇 genetic algorith...
42 篇 quadratic progra...
41 篇 particle swarm o...
36 篇 model predictive...
36 篇 numerical optimi...
35 篇 constrained opti...
33 篇 propellant
30 篇 aerodynamic shap...
29 篇 lagrange multipl...
29 篇 global convergen...
27 篇 shape optimizati...
27 篇 sensitivity anal...
25 篇 structural optim...

机构

17 篇 natl yunlin univ...
16 篇 hazara univ dept...
15 篇 comsats inst inf...
9 篇 comsats univ isl...
8 篇 univ michigan de...
7 篇 natl univ def te...
7 篇 univ calif san d...
6 篇 beijing inst tec...
6 篇 comsats univ isl...
6 篇 univ bristol dep...
6 篇 int islamic univ...
6 篇 univ gujrat dept...
5 篇 northwestern uni...
5 篇 univ glasgow dep...
5 篇 comsats inst inf...
5 篇 harbin inst tech...
5 篇 natl yunlin univ...
5 篇 tongji univ dept...
5 篇 johns hopkins un...
5 篇 univ bayreuth de...

作者

55 篇 raja muhammad as...
18 篇 sabir zulqurnain
16 篇 shoaib muhammad
13 篇 izmailov a. f.
10 篇 ahmad iftikhar
10 篇 luo ya-zhong
9 篇 kluever ca
9 篇 robinson daniel ...
8 篇 qi hong
7 篇 allen c. b.
7 篇 samar raza
7 篇 zameer aneela
6 篇 tits al
6 篇 martins joaquim ...
6 篇 long kai
6 篇 solodov m. v.
6 篇 ren ya-tao
6 篇 wright sj
6 篇 nisar kottakkara...
6 篇 umar muhammad

语言

1,118 篇 英文
51 篇 其他
8 篇 中文
2 篇 德文
1 篇 法文
1 篇 克罗地亚文
1 篇 日文

检索条件"主题词=sequential Quadratic Programming"

共 1180 条记录，以下是991-1000 订阅

全选清除本页清除全部题录导出标记到"检索档案"

详细简洁

排序：

Efficient Global Optimization with Gradient Finish for Design Under Uncertainty

Efficient Global Optimization with Gradient Finish for Desig...

引用

AIAA SciTech Forum

作者： DiGregorio, Nicholas J. Wright, Aaron H. NASA Langley Res Ctr Vehicle Anal Branch Syst Anal & Concepts Directorate Hampton VA 23681 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

The Efficient Global Optimization (EGO) algorithm is extended to include a gradient-descentbased finish upon reaching a threshold value of the expected improvement function. Emphasis is placed on efficient evaluation of local gradients using Kriging models during the gradientbased finish to enable application to design under uncertainty (DUU) problems. The modified algorithm is applied to both the well-known Rosenbrock function and a more challenging hypersonic inlet design under uncertainty problem. Results demonstrate improvement in locating the global optimum compared to the classical implementation of EGO, as well as a reduced number of true function evaluations compared to pure gradient-based algorithms. For the Rosenbrock function, a global optimum is returned using an average of 12% fewer function calls than a gradient-based optimizer with comparable tolerances. For the design under uncertainty problem, a global optimum is found using an average of 75% fewer function calls than a gradient-based optimizer. Global Pareto fronts of multiobjective DUU problems are obtained at little additional cost after a single optimization is complete.

关键词： Cumulative Distribution Function Hypersonic Inlets Uncertainty Quantification sequential quadratic programming Freestream Mach Number Space Exploration Multidisciplinary Design and Optimization Angle of Attack Thermodynamics Oblique Shock Wave

来源：评论

学校读者我要写书评

暂无评论

Predictive Path-Following Control for Fixed-Wing UAVs Using the qLMPC Framework in the Presence of Wind Disturbances

Predictive Path-Following Control for Fixed-Wing UAVs Using ...

引用

AIAA SciTech Forum

作者： Samir, Ahmed Calderon, Horacio Martinez Werner, Herbert Herrmann, Benjamin Thielecke, Frank Hamburg Univ Technol Inst Control Syst Hamburg Germany Hamburg Univ Technol Inst Aircraft Syst Engn Hamburg Germany

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

This paper presents a cascaded approach for a predictive path-following scheme using quasi-linear parameter-varying model predictive control (qLMPC) applied to a 25 kg unmanned aerobatic aircraft. The quasi-linear parameter-varying (qLPV) representation provides a semi-linear model of the nonlinear system, while fast solvers are utilized to solve quadratic optimization problems (QOPs) in milliseconds. To incorporate integral action and overcome wind disturbances, a velocity-based linearization of the model is employed. Two scenarios with nine waypoints each are evaluated using a hybrid strategy that combines arc-length parameterization with cubic splines and a synthetic waypoint path-planner. The path-following strategy is applied to both simplified kinematic and high-fidelity models of the aircraft, with constant wind in the first scenario and time-varying wind in the second scenario. The algorithm achieves good performance in both scenarios with short computation times. Lastly, a performance analysis of the strategy with the two path-planning techniques is presented.

关键词： Proportional Integral Derivative Path Planning Aerobatic Aircraft Nonlinear Systems Airspeed sequential quadratic programming Ailerons Fixed Wing Aircraft Control Moment Gyroscope Remotely Piloted Aircraft

来源：评论

学校读者我要写书评

暂无评论

A Suboptimal Control Strategy for the Start-up of the Open Plate Reactor

A Suboptimal Control Strategy for the Start-up of the Open P...

引用

10th International Conference on Control, Automation, Robotics and Vision

作者： Kaya, Sener A. Attia, S. A. Raisch, J. Dalarna Univ Dept Elect Engn Borlange Sweden Tech Univ Berlin Control Syst Grp Berlin Germany

ISBN: (纸本)9781424422869

In this paper the application of Nonlinear Model Predictive Control (NMPC) to a chemical reactor, namely the Open Plate Reactor(OPR), is considered. A control strategy which allows a safe start-up operation of the reactor and provides an easy handling of system restrictions and nonlinearities, is proposed. An efficient open-loop parameterization of the control signals is used to further reduce the size of the optimization variables. It is shown that the NMPC algorithm developed gives satisfactory operation and the reduced open loop parameterization results in a sufficiently rich closed loop behavior.

关键词： chemical reactor heat exchange plate reactor start-up control nonlinear model predictive control efficient open loop parameterization sequential quadratic programming

来源：评论

学校读者我要写书评

暂无评论

Nonlinear Optimization for Human-Like Movements of a High Degree of Freedom Robotics Arm-Hand System

Nonlinear Optimization for Human-Like Movements of a High De...

引用

11th International Conference on Computational Science and Its Applications (ICCSA)

作者： Costa e Silva, Eliana Costa, Fernanda Bicho, Estela Erlhagen, Wolfram Univ Minho Dept Ind Elect P-4719 Braga Portugal Univ Minho Dept Math Appl P-4719 Braga Portugal

ISBN: (纸本)9783642219306;9783642219313

The design of autonomous robots, able to closely cooperate with human users in shared tasks, provides many new challenges for robotics research. Compared to industrial applications, robots working in human environments will need to have human-like abilities in their cognitive and motor behaviors. Here we present a model for generating trajectories of a high degree of freedom robotics arm-hand system that reflects optimality principles of human motor control. The process of finding a human-like trajectory among all possible solutions is formalized as a large-scale nonlinear optimization problem. We compare numerically three existing solvers, IPOPT, KNITRO and SNOPT, in terms of their real-time performance in different reach-to-grasp problems that are part of a human-robot interaction task. The results show that the SQP methods obtain better results than the IP methods. SNOPT finds optimal solutions for all tested problems in competitive computational times, thus being the one that best serves our purpose.

关键词： anthropomorphic robotic system reach-to-grasp human-like collision-free arm movements large-scale nonlinear optimization interior-point methods sequential quadratic programming

来源：评论

学校读者我要写书评

暂无评论

High-Order Implicit Shock Tracking for Finite-Source Spherical Blast Waves

High-Order Implicit Shock Tracking for Finite-Source Spheric...

引用

AIAA Aviation Forum

作者： Naudet, Charles Taylor, Brian Zahr, Matthew J. Univ Notre Dame Dept Aerosp & Mech Engn 321 Cushing Hall Notre Dame IN 46556 USA Air Force Res Lab Eglin AFB FL 32542 USA Univ Notre Dame Dept Aerosp & Mech Engn 300B Cushing Hall Notre Dame IN 46556 USA

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

Implicit shock tracking is a class of numerical methods to approximate solutions of conservation laws with non-smooth features, e.g., contact lines, shock waves, and rarefactions. These methods align elements of the computational mesh with non-smooth features to represent them perfectly, allowing high-order basis functions to approximate smooth regions of the solution without the need for nonlinear stabilization, which leads to accurate approximations on traditionally coarse meshes. In this work, we use the High-Order Implicit Shock Tracking method to simulate a finite-source spherical blast wave.

关键词： Blast Wave Discontinuous Galerkin Method Shock Waves Rankine Hugoniot Conditions Weighted Essentially Non Oscillatory Flow Characteristics Gas Constant sequential quadratic programming Atwood Number Compressible Fluid

来源：评论

学校读者我要写书评

暂无评论

Iteratively feasible optimal spacecraft guidance with non-convex path constraints using convex optimization

Iteratively feasible optimal spacecraft guidance with non-co...

引用

AIAA Science and Technology Forum and Exposition (AIAA SciTech)

作者： Misra, Gaurav Bai, Xiaoli Rutgers State Univ Dept Mech & Aerosp Engn Piscataway NJ 08854 USA

ISBN: (数字)9781624105951

ISBN: (纸本)9781624105951

In this paper, a convex optimization based approach is proposed for solving the relative spacecraft guidance problem with non-convex obstacle avoidance constraints akin to sequential convex programming approaches proposed in literature, which require solving a sequence of simpler convex programs. However, contrary to existing approaches, the method proposed in this paper ensures that the iterates remain feasible as long as the first iterate is feasible and achieves monotonic convergence of the objective function. Significantly, the proposed methodology leads to anytime solutions, i.e., the computation can be aborted whenever needed and still return a quality solution, which is highly desirable for real-time operations due to potential unexpected situations and limited computation resources. However, most existing methods only guarantee the correctness of the solution when they converge, whereas preconvergence solution obtained can be useless or even dangerous when applied. The underlying methodology assumes linear dynamics with polynomial path constraints and relies on the convex-concave procedure and sum-of-squares programming to obtain tractable inner convex approximations. To validate the efficacy of the proposed method, a relative spacecraft fuel optimal guidance problem under Clohessy-Hill-Wiltshire (CHW) dynamics is studied under plume impingement, keep-out zones, and obstacle avoidance constraints.

关键词： Nonlinear programming Spacecraft Trajectory Optimization Model Predictive Control Optimal Control Algorithms Convergence sequential quadratic programming Pseudo Spectral Method Boundary Value Problems Guidance Laws Rockets

来源：评论

学校读者我要写书评

暂无评论

A B-Spline-based Generative Adversarial Network Model for Fast Interactive Airfoil Aerodynamic Optimization

A B-Spline-based Generative Adversarial Network Model for Fa...

引用

AIAA Science and Technology Forum and Exposition (AIAA SciTech)

作者： Du, Xiaosong He, Ping Martins, Joaquim R. R. A. Univ Michigan Dept Aerosp Engn Ann Arbor MI 48109 USA

ISBN: (数字)9781624105951

ISBN: (纸本)9781624105951

Airfoil aerodynamic optimization is of great importance in aircraft design;however, it relies on high-fidelity physics-based models that are computationally expensive to evaluate. In this work, we provide a methodology to reduce the computational cost for airfoil aerodynamic optimization. Firstly, we develop a B-spline based generative adversarial networks (BSplineGAN) parameterization method to automatically infer design space with sufficient shape variability. Secondly, we construct multi-layer neural network (MNN) surrogates for fast predictions on aerodynamic drag, lift, and pitching moment coefficients. The BSplineGAN has a relative error lower than 1% when fitting to UIUC database. Verification of MNN surrogates shows the root means square errors (RMSE) of all aerodynamic coefficients are within the range of 20%-40% standard deviation of testing points. Both normalized RMSE and relative errors are controlled within 1%. The proposed methodology is then demonstrated on an airfoil aerodynamic optimization. We also verified the baseline and optimized designs using a high-fidelity computational fluid dynamic solver. The proposed framework has the potential to enable web-based fast interactive airfoil aerodynamic optimization.

关键词： Airfoil Databases Generative Adversarial Network Aerodynamic Shape Optimization Cumulative Distribution Function Aircraft Design Surrogate Model Computational Fluid Dynamics Lift Coefficient Shape Control sequential quadratic programming

来源：评论

学校读者我要写书评

暂无评论

Error Analysis of Optimization Algorithms in Ultrasonic Parameter Estimation 9

Error Analysis of Optimization Algorithms in Ultrasonic Para...

引用

9th IEEE International Conference on Computational Intelligence and Computing Research (ICCIC)

作者： Aditya, N. Ram Abhijeeth, K. Sri Anuraj, K. Poorna, S. S. Amrita Vishwa Vidyapeetham Dept Elect & Commun Engn Amritapuri India

ISBN: (纸本)9781538615072

The back scattered ultrasonic echo carries several valuable information in its amplitude, bandwidth, delay in time, phase and time of flight. This information is capable of characterizing properties of the material from which it is reflected. In order to model the reverberations, white Gaussian noise is added to Gaussian echo. The required set of parameters are estimated from the noise altered echo using Maximum Likelihood Estimation. This reduces to least square curve fitting, due to additive white gaussian noise. For optimizing the estimated parameters from the back-scattered signal, different algorithms such as Levenberg- Marquardt, Trust-Region Reflective, Active Set, Quasi Newton and sequential quadratic programming are used. The proposed work aims at the error analysis of estimated signals using the above-mentioned optimization algorithms for different SNR values viz. 0-20dB. Further the noise added signals are subjected to wavelet denoising, prior to parameter estimation. The experimental result shows that the lowest mean square error is obtained for the echo parameters optimized using Levenberg-Marquardt algorithm, for both noisy and de-noised cases.

关键词： Ultrasonic Echo Error analysis MLE LM Trust-Region Reflective Active Set Quasi Newton sequential quadratic programming wavelet denoising MSE SNR

来源：评论

学校读者我要写书评

暂无评论

Slotted Waveguide Stress Concentration Factor

Slotted Waveguide Stress Concentration Factor

引用

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

作者： Brooks, Joseph Canfield, Robert A. Virginia Polytech Inst & State Univ Kevin T Crofton Dept Aerosp & Ocean Engn Randolph Room 215460 Old Turner St Blacksburg VA 24061 USA Virginia Polytech Inst & State Univ Kevin T Crofton Dept Aerosp & Ocean Engn 460 Old Turner StMS 0203 Blacksburg VA 24061 USA

ISBN: (数字)9781624106095

ISBN: (纸本)9781624106095

Sharp turns or corners within a structure lead to local failures well before the rest of the structure due to the creation of stress concentrations. For a load-bearing waveguide, these occur at the corners of the slots. After modeling a test waveguide, a bivariate curve fit was created to model these stress concentrations, based on four configurations for a single slot length, then refined into a trivariate form based on an expanded eight cases across two slot lengths. Once properly formatted, the integration of the bivariate function into an optimization allowed stress concentration to be estimated at the slot corners within a coarse low-fidelity model, rather than the high-fidelity model otherwise required, following the expected behavior and acting as a verification case. Implementation of the full trivariate form into a design optimization enabled use of the concentration factor to estimate the critical stress. The study showed that the inset copper waveguide could not be loaded from the outset, and that an offset of the copper waveguide could avoid overloading it.

关键词： Stress Concentration Finite Element Modeling Compressive Stress sequential quadratic programming Yield Stress MATLAB Numerical Modeling Comsol Multiphysics Linear Elasticity Structural Modeling

来源：评论

学校读者我要写书评

暂无评论

Particle-Based Optimization of a Conceptual Wing with Gradient Information

Particle-Based Optimization of a Conceptual Wing with Gradie...

引用

AIAA Science and Technology (SciTech) Forum and Exposition

作者： Dettwiller, Ian D. England, William Foster, Justin Garon, Elyse Freeman, Elton US Army Engineer Res & Dev Ctr ERDC Informat Technol Lab Vicksburg MS 39180 USA

ISBN: (数字)9781624105784

ISBN: (纸本)9781624105784

A new, particle-based optimization strategy for global optimization is presented. The new approach is used for minimizing weight through sizing optimization of the interior components of a conceptual wing subject to Von Mises stress constraints. The goal of the particle-based optimization scheme is to produce a methodology for high-dimensional global optimization. Performance of the new optimization scheme is compared to particle swarm optimization, differential evolution, and sequential quadratic programming with multiple starting points on a pair of global optimization benchmark problems. The particle-based strategy is shown to rapidly converge to global solutions to the unconstrained problems, even as dimensionality is increased. Finally, the particle-based optimization strategy is shown to be capable of successfully optimizing the conceptual wing.

关键词： Global optimization Wings stress constraints conceptual Benchmark testing sequential quadratic programming Point pairs Particle swarm optimization

来源：评论

学校读者我要写书评

暂无评论

没有更多数据了...

全选清除本页清除全部题录导出标记到“检索档案”

共118页 << < 96 97 98 99 100 101 102 103 104 105 > >>

检索报告对象比较合并检索0

隐藏清空

合并搜索

回到顶部

执行限定条件

内容：

评分：

请选择保存的检索档案：

请选择收藏分类：

订阅名称：

通借通还

温馨提示：

图书名称：

借书校区：

取书校区：

手机号码：

邮箱地址：

一卡通帐号：

电话和邮箱必须正确填写，我们会与您联系确认。

联系人：

所在院系：

联系邮箱：

联系电话：

内蒙古自治区呼和浩特市赛罕区大学西街235号邮编: 010021

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：