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飞机结构 5

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倾转旋翼机；状态跟踪控制；线性切换系统；类时间依赖的多Lyapunov函数方法；光滑插值 1

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Design and applications of morphing aircraft and their structures

《机械工程前沿（英文）》 2023年第18卷第3期 doi: 10.1007/s11465-023-0750-6

摘要： Morphing aircraft can adaptively regulate their aerodynamic layout to meet the demands of varying flight conditions, improve their aerodynamic efficiency, and reduce their energy consumption. The design and fabrication of high-performance, lightweight, and intelligent morphing structures have become a hot topic in advanced aircraft design. This paper discusses morphing aircraft development history, structural characteristics, existing applications, and future prospects. First, some conventional mechanical morphing aircraft are examined with focus on their morphing modes, mechanisms, advantages, and disadvantages. Second, the novel applications of several technologies for morphing unmanned aerial vehicles, including additive manufacturing for fabricating complex morphing structures, lattice technology for reducing structural weight, and multi-mode morphing combined with flexible skins and foldable structures, are summarized and categorized. Moreover, in consideration of the further development of active morphing aircraft, the paper reviews morphing structures driven by smart material actuators, such as shape memory alloy and macro-fiber composites, and analyzes their advantages and limitations. Third, the paper discusses multiple challenges, including flexible structures, flexible skins, and control systems, in the design of future morphing aircraft. Lastly, the development and application of morphing structures in the aerospace field are discussed to provide a reference for future research and engineering applications.

关键词： morphing aircraft additive manufacturing lattice structure smart material flexible structure flexible skin

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基于飞机结构寿命包线的飞机结构单机寿命监控

何宇廷

《中国工程科学》 2006年第8卷第6期页码 23-27

摘要：

在分析基准使用条件下飞机结构寿命包线的基础上，给出飞机结构在非基准使用条件下的寿命包线的绘制方法，阐明了在非基准使用条件下对飞机结构进行单机寿命监控的原理与方法。最后以飞机首翻后进行第二次大修的大修间隔期监控为例进行了分析说明。

关键词：飞机结构寿命包线寿命监控大修间隔期

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Managing Coordination Complexity in the Remanufacturing of Aircraft Engines

Qing Yang,Lu Zheng

《工程管理前沿（英文）》 2016年第3卷第2期页码 158-164 doi: 10.15302/J-FEM-2016022

摘要： The complexity of communication and coordination stemming from teams responsible for adjusting interdependent parameters of components is a fundamental feature in the aircraft engine remanufacturing engineering project. To manage coordination complexity, the features of the remanufacturing process of aircraft engine are analyzed and a systematic method is presented to measure and optimize the dependency between coupled components. Furthermore, quantitative models are built based on Design Structure Matrix (DSM) models to measure dependency strengths related to the parameter features of the components. Also, a two-stage DSM clustering criteria is used to reduce the complexity of an organization. An industrial example is provided to illustrate the proposed models. The results showed that the proposed approach can reduce total coordination complexity.

关键词： remanufacturing engineering project aircraft engine coordination complexity organization optimization design structure matrix (DSM)

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Impact analysis of compressor rotor blades of an aircraft engine

Y B SUDHIR SASTRY, B G KIROS, F HAILU, P R BUDARAPU

《结构与土木工程前沿（英文）》 2019年第13卷第3期页码 505-514 doi: 10.1007/s11709-018-0493-3

摘要： Frequent failures due to foreign particle impacts are observed in compressor blades of the interceptor fighter MIG-23 aircraft engines in the Ethiopian air force, supplied by the Dejen Aviation Industry. In this paper, we made an attempt to identify the causes of failure and hence recommend the suitable materials to withstand the foreign particle impacts. Modal and stress analysis of one of the recently failed MIG-23 gas turbine compressor blades made up of the following Aluminum based alloys: 6061-T6, 7075-T6, and 2024-T4, has been performed, apart from the impact analysis of the rotor blades hit by a granite stone. The numerical results are correlated to the practical observations. Based on the modal, stress and impact analysis and the material properties of the three considered alloys, alloy 7075-T6 has been recommended as the blade material.

关键词： axial flow compressor rotor and stator blades aircraft engine stress and impact analysis aluminum alloys

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Risk evaluation for the task transfer of an aircraft maintenance program based on a multielement connection

《工程管理前沿（英文）》 doi: 10.1007/s42524-023-0282-0

摘要： This paper proposes a framework for evaluating the efficacy and suitability of maintenance programs with a focus on quantitative risk assessment in the domain of aircraft maintenance task transfer. The analysis is anchored in the principles of Maintenance Steering Group-3 (MSG-3) logic decision paradigms. The paper advances a holistic risk assessment index architecture tailored for the task transfer of maintenance programs. Utilizing the analytic network process (ANP), the study quantifies the weight interrelationships among diverse variables, incorporating expert-elicited subjective weighting. A multielement connection number-based evaluative model is employed to characterize decision-specific data, thereby facilitating the quantification of task transfer-associated risk through the appraisal of set-pair potentials. Moreover, the paper conducts a temporal risk trend analysis founded on partial connection numbers of varying orders. This analytical construct serves to streamline the process of risk assessment pertinent to maintenance program task transfer. The empirical component of this research, exemplified through a case study of the Boeing 737NG aircraft maintenance program, corroborates the methodological robustness and pragmatic applicability of the proposed framework in the quantification and analysis of mission transfer risk.

关键词： risk evaluation maintenance steering group analytic network process task transfer maintenance program

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中国直升机运输机的未来发展

张彦仲

《中国工程科学》 2002年第4卷第8期页码 1-7

摘要：

阐述了中国直升机、运输机的现状,未来发展思路和具体实施计划；介绍了中国在产的直升机、运输机，在产的直升机有直11（2吨级）、直9（4吨级）、直8（13吨级）系列，在产的运输机有运5、运7、运8、运12和农5系列；提出了改进生产一代、研制发展一代、预研攻关一代的发展思路，制定了直升机改进生产以直8、直9、直11为主，研制以6吨级直升机为主，预研以10吨级直升机为主的发展计划；运输机改进生产以运8、运12为主，研制以涡扇支线飞机为主，发展以大型运输机为主的实施计划；提出了突破直升机发动机、旋翼、传动、抗坠毁、复合材料关键技术的措施；指出直升机、运输机发展要坚持自主开发和国际合作、技术和贸易、军用和民用相结合，建议把直升机、运输机纳入国家长远发展规划。

关键词：中国直升机运输机发展

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民用支线飞机发展浅析

陈一坚

《中国工程科学》 2001年第3卷第2期页码 16-20

摘要：

高科技、高投入、高风险、长周期的航空产品是一个国家工业水平和经济发达程度的重要标志之一。由于种种历史原因，我国民用航空产业发展相对缓慢。在西部大开发方针指引下，充分发挥陕西航空工业的优势，集中全行业资源和人才，发挥"哑铃型"研制模式，两头集中在陕西，并组成符合市场经济规律的股份公司，有利于民用支线飞机尽早提供给用户，成为21世纪初中国航空人应肩负的历史使命。文章浅析了如何发展支线飞机，以引起各方重视。

关键词：民用支线飞机涡扇型支线飞机人公里数支线运输网

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大飞机气动总体技术的发展

张彦仲

《中国工程科学》 2009年第11卷第5期页码 4-17

摘要：

论述了大飞机常规气动布局的发展，客机机身技术以及新型气动布局——翼身融合体飞机(BWB)的发展。分析了气动总体技术对于大型飞机的安全性、经济性、舒适性和环保性等方面的作用, 并结合国内的研究现状提出我国加强气动总体技术研究，走自主创新道路的意见。

关键词：大飞机气动超临界翼型翼梢小翼层流技术翼身融合体 CFD 风洞试验气动噪音

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腐蚀环境下飞机结构疲劳寿命的分析方法

穆志韬

《中国工程科学》 2002年第4卷第3期页码 68-72

摘要：

依据海军现役飞机的腐蚀环境特点及结构件腐蚀损伤深度拟合规律，采用应力场强法和局部应力应变法分别对疲劳缺口系数K_f及疲劳寿命计算模型进行了分析，提出了一种腐蚀环境下飞机结构疲劳寿命的评定方法。该方法以室温大气环境下的寿命评定结论为依据，考虑了结构件腐蚀损伤后潮湿空气、盐雾、盐雾＋SO₂等环境介质对疲劳寿命的影响，并结合国产某型飞机机翼前梁缘条腐蚀损伤部位的疲劳寿命及剩余寿命估算实例进行了分析。

关键词：飞机结构疲劳寿命腐蚀环境疲劳缺口系数

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基于自动原位校准的大型飞机构件装配过程三维微位移监测系统 Article

贾振元, 梁冰, 刘巍, 刘坤, 马建伟

《工程（英文）》 2022年第19卷第12期页码 105-116 doi: 10.1016/j.eng.2021.02.023

摘要：

三维（3D）微位移监测在大型飞机装配中起着至关重要的作用。本文提出了一种广泛适用的基于接近传感器的高精度在线3D微位移监测方法和系统，以及相应的原位校准方法，可应用于飞机装配过程中遇到的各种极端工作条件，如紧凑和遮挡的空间。首先建立了一个3D监测模型，仅基于接近传感器测量的一
维距离实现3D微位移监测，该模型涉及传感器外部参数，如测量原点（PBP）和单位位移矢量（UDV）。然后，结合空间变换原理和加权优化校准方法，获得高精度外部参数。最后，针对尾翼装配过程开展了校准和监测实验。PBP 的校准精度在X、Y 方向优于±10 μm，在Z 方向优于±2 μm，UDV 的校准精度优于0.07°。此外，3D微位移监测系统的精度可达到±15 μm。总体而言，本文为基于接近传感器的3D微位移监测的建模和校准提供了新的见解，并为飞机装配过程中紧凑空间内的几何测量提供了一种高精度、高效率、低成本的技术手段。

关键词：飞机制造装配校准状态监测位移测量

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Design concepts of an aircraft wing: composite and morphing airfoil with auxetic structures

P R BUDARAPU,Sudhir Sastry Y B,R NATARAJAN

《结构与土木工程前沿（英文）》 2016年第10卷第4期页码 394-408 doi: 10.1007/s11709-016-0352-z

摘要： This paper is categorized into two parts. (1) A frame work to design the aircraft wing structure and (2) analysis of a morphing airfoil with auxetic structure. The developed design frame work in the first part is used to arrive at the sizes of the various components of an aircraft wing structure. The strength based design is adopted, where the design loads are extracted from the aerodynamic loads. The aerodynamic loads acting on a wing structure are converted to equivalent distributed loads, which are further converted point loads to arrive at the shear forces, bending and twisting moments along the wing span. Based on the estimated shear forces, bending and twisting moments, the strength based design is employed to estimate the sizes of various sections of a composite wing structure. A three dimensional numerical model of the composite wing structure has been developed and analyzed for the extreme load conditions. Glass fiber reinforced plastic material is used in the numerical analysis. The estimated natural frequencies are observed to be in the acceptable limits. Furthermore, the discussed design principles in the first part are extended to the design of a morphing airfoil with auxetic structure. The advantages of the morphing airfoil with auxetic structure are (i) larger displacement with limited straining of the components and (ii) unique deformation characteristics, which produce a theoretical in-plane Poisson’s ratio of −1. Aluminum Alloy AL6061-T651 is considered in the design of all the structural elements. The compliance characteristics of the airfoil are investigated through a numerical model. The numerical results are observed to be in close agreement with the experimental results in the literature.

关键词： wing design aerodynamic loads morphing airfoil auxetic structures negative Poisson’s ratio

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现役飞机结构腐蚀疲劳及寿命研究

穆志韬,金平,段成美

《中国工程科学》 2000年第2卷第4期页码 34-38

摘要：

文章分析研究了在环境腐蚀介质中飞机的疲劳损伤特性和基本破坏失效模式，阐述了现役军用飞机地面停放使用环境谱的编制以及在腐蚀环境条件下飞机腐蚀疲劳寿命的估算方法，并对未来几年我军飞机结构的腐蚀疲劳研究的发展提出了一些看法。

关键词：腐蚀飞机结构腐蚀疲劳疲劳寿命腐蚀环境谱

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军用飞机可发展性研究

张恒喜,江洋溢,王礼沅,解江

《中国工程科学》 2007年第9卷第1期页码 69-72

摘要：

在揭示军用飞机发展本质的基础上，提出了统领飞机发展的顶层综合特性———可持续发展性，给出了其定义和度量方式；进一步指出用可持续发展指数作为可发展性的表征参数能够更有效地进行评估，并在此基础上建立了可发展性的综合权衡模型。最后，将可发展性应用到某型歼击机改进方案的评估中。实例表明，可发展性是迄今为止最为合理的军用飞机顶层综合特性，可有效地使军用飞机发展纳入科学的发展轨道。

关键词：军用飞机可持续发展性可持续发展指数综合权衡