基于响应曲面车削加工表面粗糙度稳健性分析

随着现代科学技术的发展,对零件的表面加工质量提出了越来越高的要求。但由于机械加工过程较复杂,各种参数都不同程度地影响着表面粗糙度,表面粗糙度分析时,很难建立显式的解析模型。本文提出基于响应曲面法建立表面粗糙度可靠性指标对应刀具结构影响参数的灵敏度分析模型。结果表明,表面粗糙度对刀尖圆角半径r的变化最为敏感,对主偏角κ的变化敏感次之,对前角γ变化不敏感;刀尖圆角半径、主偏角和前角对表面粗糙度的贡献率分别为56.82%,27.84%和9.75%。     

一个时限信号采样定理及其在数据压缩中的应用

证明了一个时限信号采样定理，该定理指出：（１）对于一个带限信号，如果样点按照Ｎ阶Ｃｈｅｂｙｓｈｅｖ多项式的零点位置分布，则可在有限的时间长度之内获得信号的近似最佳一致逼近，在采样密度大于Ｎｙｑｕｉｓｔ率２．１３５倍的条件下，截断误差的上界随着样点个数的增加呈指数衰减；（２）若用Ｃｈｅｂｙｓｈｅｖ多项式的线性组合形式进行内插，内插过程稳定。将此结果用于数据压缩可得到一个结合非均匀采样的ＤＣＴ方法。计     

非均匀弹性地基上梁横向振动的渐近解法

研究非均匀弹性地基上梁的横向振动，提供了一种既能保证较高精度、计算又非常简单的固有频率的渐近解法，作为算例，给出了非均匀弹性地基上悬臂梁固有频率的一级近似计算公式并将计算结果与连续质量有限元素法的计算结果作了比较。     

置信分布的贝塔分布近似及其在可靠性统计中的应用

在复杂系统可靠性综合评估方法研究中,利用β分布来近似区间[0,1]上的各种概率分布是一种常用的工程方法,并被许多系统可靠性综合评估方法所采用。工程中常用的β分布近似方法有二阶矩法和点估计下限法。为了减少近似误差,本文在文献[1]的基础上,对文献[1]中提出的β分布近似的两点法进行了深入研究,证明了两点法解的存在性和唯一性,并在这一结果的基础上设计出有效的算法。通过模拟计算可以看出,两点法与目前普遍使用的二阶矩法和点估计下限法相比,近似的精确性明显提高,尤其在小子样情形下效果更为显著。     

Reachable set estimation for spacecraft relative motion based on bang-bang principle

For spacecraft formation flight, the information of relative motion reachable set is very important, which can be used to predict the operating boundary of adjacent spacecraft and thus to ensure the safety of spacecraft operation. In this paper, we aim at developing a numerical method to approximate the reachable set for spacecraft relative motion. In particular, we focus on the quality of the approximation and the computational cost. Based on the bang-bang control principle, a polyhedral approximation algorithm is proposed to compute the reachable set of a relative motion spacecraft system. An inner approximation and an outer approximation of the reachable set for the system can be obtained. We prove that the approximation quality measured in Hausdorff distance can be guaranteed. The method is easy to implement and has low computational cost. Finally, the effectiveness of the algorithm is demonstrated by experimental simulation.     

A methodology for constructing the aircraft design schema

Aircraft collaboration design is based on a unified set of schemas containing data and model representations and interfaces across disciplines. The aircraft design schema is a central data model that specifies the paradigm for the representation of a full lifecycle model of aircraft design. The construction of the schema currently lacks theoretical guidance. This paper designs a novel methodology to construct the aircraft design schema, a fully functional, logical, and self-consistent methodology. The methodology defines a schema matrix that includes implementation strategies, principles, processes, meta-object facility, views, scenarios, and products. The aircraft conceptual design schema is constructed according to the methodology, which is a hands-on approach to help understand the concept and implementation. The features of the methodology are analyzed, and the methodology and the aircraft conceptual design schema are presented to address the pain points of multiple solution trade-offs, multiple iterations, and multidisciplinary coupling in aircraft conceptual collaboration design.     

基于响应曲面法的成型CBN砂轮高频感应钎焊温度均匀性研究

成型砂轮在高频感应钎焊过程中存在温度分布不均匀导致钎焊质量无法满足使用要求，这是长期困扰超硬磨料砂轮高频感应钎焊技术的难题。针对该问题，提出温度均匀性的表征方法，以温度均匀度和平均温度为响应值，基于有限元仿真数据获得了响应曲面法模型。基于该模型，采用方差分析成型砂轮感应钎焊温度均匀性的影响因素显著程度由大到小依次为加热间隙、感应电流、导磁体长度。以平均温度值和温度均匀度为优化目标，基于响应曲面法优化线圈结构和工艺参数，开展了感应加热试验，证明响应曲面法模型优化结果的误差在6.94%以内。高频感应钎焊的成型立方氮化硼（cubic boron nitride，CBN）砂轮宏观形貌显示，钎料在成型面各处铺展的一致性好，表明钎焊过程中在成型面的温度分布具有较好的均匀性。     

An architecture decomposition method of pneumatic catapult system based on OPM and DSM

The architecture strategy of the Unmanned Aerial Vehicle (UAV) pneumatic launch system should continue to evolve to adapt to complex and variable operating environments. Architecture representation, decomposition perspective, and cluster analysis play a vital role in the early phase of system architecture development. In order for the system to emerge anticipated and desirable intrinsic functional properties, an architecture decomposition method based on the Object-Process Methodology (OPM) and Design Structure Matrix (DSM) is put forward in this paper. The OPM is proposed to model the UAV launch process formally, and the matrix representation of the architecture of the pneumatic launch system is established. After the extension of the definition and operations of DSM, with the Idicula-Gutierrez-Thebeau Algorithm plus (IGTA + ) clustering algorithm, the transformation of the pneumatic launch system architecture from process decomposition to function decomposition is demonstrated in this paper. The analysis shows that the architecture decomposition of the pneumatic launch system meets the functional requirements of stakeholders.     

Stark broadening parameters of the singly ionized sulfur: S II

Stark broadening parameters are useful in solving various problems e.g., in astrophysics, opacity calculations, design of lasers, laser-produced plasma and for the evaluation of the physical conditions in stellar atmospheres. Our objectives in this research work are to obtain, for electron collisions, new atomic data for Stark broadening of astrophysically important S II lines using semi-classical perturbation (SCP) and modified semi-empirical (MSE) theory with the needed energy levels and oscillator strengths from NIST database. After calculating the Stark broadening data, we compared them with experimental and theoretical data.     

Optimum alternate material selection methodology for an aircraft skin

Weight penalty has been a challenge for design engineers of aerospace vehicles. Today’s high-efficiency combat aircraft undergoes intense stress and strain during flying missions, which require stronger and stiffer materials to retain structural integrity. Though metallic materials have been successfully used for the construction of aircraft structures and components, metals still have a low strength-to-weight ratio. This paper aims to develop an alternate optimised material selection methodolog...