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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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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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Deformation analysis of shape memory polymer for morphing wing skin under airflow

Weilong YIN, Jingcang LIU, Jinsong LENG,

《机械工程前沿（英文）》 2009年第4卷第4期页码 447-449 doi: 10.1007/s11465-009-0062-5

摘要： The method for analyzing the out-of-plane deformation of a flexible skin under airflow is developed in this paper. The aerodynamic analysis is performed using the CFD software, and the structural analysis is performed using finite element method. The chief aim of the present study is to investigate the out-of-plane deformation of the shape memory polymer (SMP) skin at different temperatures. Numerical results show that the maximum out-of-plane displacement of the SMP skin increases with increasing temperature. When the SMP skin is heated to 53°C, the maximum out-of-plane displacement is about 7 mm. It decreases by 72%, when the SMP skin is applied with a uniform pre-strain of 0.1.

关键词： aircraft morphing skin shape memory polymer (SMP) deformation pre-strain

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Structural design of morphing trailing edge actuated by SMA

Qi WANG, Zhiwei XU, Qian ZHU

《机械工程前沿（英文）》 2013年第8卷第3期页码 268-275 doi: 10.1007/s11465-013-0261-y

摘要：

In this paper, the morphing trailing edge is designed to achieve the up and down deflection under the aerodynamic load. After a detailed and accurate computational analysis to determine the SMA specifications and layout programs, a solid model is created in CATIA and the structures of the morphing wing trailing edge are produced by CNC machining. A set of DSP measurement and control system is designed to accomplish the controlling experiment of the morphing wing trailing edge. At last, via the force analysis, the trailing edge is fabricated with four sections of aluminum alloy, and the arrangement scheme of SMA wires is determined. Experiment of precise control integral has been performed to survey the control effect. The experiment consists of deflection angle tests of the third joint and the integral structure. Primarily, the ultimate deflection angle is tested in these two experiments. Therefore, the controlling experiment of different angles could be performed within this range. The results show that the deflection error is less than 4% and response time is less than 6.7 s, the precise controlling of the morphing trailing edge is preliminary realized.

关键词： morphing wing trailing edge shape memory alloy digital signal processor PID algorithm

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Kinematical synthesis of an inversion of the double linked fourbar for morphing wing applications

J. AGUIRREBEITIA, R. AVILéS, I. FERNáNDEZ, M. ABASOLO

《机械工程前沿（英文）》 2013年第8卷第1期页码 17-32 doi: 10.1007/s11465-013-0364-5

摘要：

This paper presents the kinematical features of an inversion of the double linked fourbar for morphing wing purposes. The structure of the mechanism is obtained using structural synthesis concepts, from an initial conceptual schematic. Then, kinematic characteristics as instant center of rotation, lock positions, dead point positions and uncertainty positions are derived for this mechanism in order to face the last step, the dimensional synthesis; in this sense, two kinds of dimensional synthesis are arranged to guide the wing along two positions, and to fulfill with the second one some aerodynamic and minimum actuation energy related issues.

关键词： morphing wing structural synthesis dimensional synthesis geometrical kinematics

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Deformation characteristics of corrugated composites for morphing wings

Ruijun GE, Bangfeng WANG, Changwei MOU, Yong ZHOU,

《机械工程前沿（英文）》 2010年第5卷第1期页码 73-78 doi: 10.1007/s11465-009-0063-4

摘要： To meet the needs of morphing and withstand aerodynamic loads of a morphing wing skin, a corrugated glass fabric-epoxy laminated composite is prepared and investigated in this paper. This composite is flexible in the corrugated direction and stiff in the transverse direction to the corrugation. FEM models are established and solved to predict the characteristics of the composites by the commercial FEM software ANSYS. The relationship between the configuration of elongation and tensile load along the corrugation direction is obtained through numerical simulation. To reflect the stretching superiority of the configuration, the elongation of corrugated and flat composites is calculated and compared under the same tensile load. The linear cumulative effect of corrugated composites deformation is proved by calculating the elongation of the composites with several different corrugation numbers. Several corrugated composite specimens were manufactured and tested to verify the results of numerical analysis and the equivalent elastic modulus of the composites were also evaluated through the specimen tests. Results of simulation and experiments show that the corrugated composite provided in this paper can afford obviously larger deformation than the flat one. The corrugated composite can provide a possible choice for morphing wing skin.

关键词： corrugated composites deformation characteristic numerical analysis experiment

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Module-based method for design and analysis of reconfigurable parallel robots

Fengfeng XI, Yuwen LI, Hongbo WANG

《机械工程前沿（英文）》 2011年第6卷第2期页码 151-159 doi: 10.1007/s11465-011-0121-6

摘要：

This paper presents a method for the design and analysis of reconfigurable parallel robots. The inherent modularity in a parallel robot lends itself as a natural candidate for reconfiguration. By taking the branches as building blocks, many modular parallel robots can be constructed, from which a reconfigurable parallel robot can be realized. Among three types of reconfigurations, namely, geometry morphing, topology morphing, and group morphing, the method presented here is for the last two reconfigurations, thereby advancing the current research that is mainly limited to geometry morphing. It is shown that the module-based method not only provides a systematic way of designing a reconfigurable parallel robot, but also offers a unified modeling for robot analysis. Two examples are provided, one showing the topology morphing and the other showing the group morphing.

关键词： reconfigurable parallel robot topology morphing group morphing

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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