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| 1 | 柔性飞艇主气囊干湿模态分析与影响因素显示文摘为了掌握柔性飞艇无约束状态下的模态特性,以25m平流层验证飞艇为基本分析对象,对其自振特性进行研究.根据充气膜结构的力学特点,基于柔性飞艇主气囊初始形状,通过充气压力静力非线性分析得到充气平衡形态位形和应力,利用兰索斯法进行模态数值分析.分析表明,影响柔性飞艇模态特性的主要因素为:壳单元与膜单元模型、拼接缝、不均匀质量分布、内外压差、尺寸、飞艇周围空气附加质量,且最后三者为重要影响因素;壳单元和膜单元模型频率相近且振型一致.对柔性平流层飞艇结构设计具有参考价值. | 陈宇峰 陈务军 何艳丽 张大旭 | 2014 | 上海交通大学学报2014，48，2： | 17 |
| 2 | 临近空间大型柔性充气囊体结构特性分析显示文摘以临近空间平流层飞艇柔性充气囊体为研究对象,根据充气结构设计理论对充气囊体结构的最小压差和应力进行计算,建立平流层飞艇充气囊体结构有限元模型。在模型验证的基础上,采用非线性有限元方法对平流层飞艇充气囊体结构特性进行仿真分析,得到了囊体结构在不同压差和吊舱载荷作用下应力和变形分布及变化规律,并分析了结构加强配置对囊体应力和变形的影响,为平流层飞艇结构设计提供技术支撑和参考依据。 | 麻震宇 侯中喜 杨希祥 | 2015 | 国防科技大学学报2015，37，4： | 8 |
| 3 | Multi-disciplinary design optimization with variable complexity modeling for a stratosphere airship显示文摘This paper proposes a hybrid architecture based on Multi-disciplinary Design Optimization(MDO) with the Variable Complexity Modeling(VCM) method, to solve the problem of general design optimization for a stratosphere airship. Firstly, MDO based on the Concurrent SubSpace Optimization(CSSO) strategy is improved for handling the subsystem coupling problem in stratosphere airship design which contains aerodynamics, structure, and energy. Secondly, the VCM method based on the surrogate model is presented for reducing the computational complexity in high-fidelity modeling without loss of accuracy. Moreover, the global-to-local optimization strategy is added to the architecture to enhance the process. Finally, the result gives a prominent stratosphere airship general solution that validates the feasibility and efficiency of the optimization architecture. Besides, a sensitivity analysis is conducted to outline the critical impact upon stratosphere airship design. | Shi YIN Ming ZHU Haoquan LIANG | 2019 | Chinese Journal of Aeronautics2019，32，5： | 7 |
| 4 | Structural Design Conception and Analysis for the Structural System of Large Flexible Airship显示文摘Nine kinds of structure systems were proposed for the flexible airship according to the inherent structural characteristics. On the basis of equilibrium configuration of the oating airship subjected to the ascent helium buoyancy and gravity,the structural analysis procedure was developed and the computation models were presented for the airship. Then the systematic numerical analysis was carried out for a 25 m long airship,the comparison of principal stress of envelope was performed between the nonlinear numerical analysis result and the engineering elastic theory result. The structural performances were evaluated thoroughly. Finally,the reasonable structural systems were proposed. Accordingly,the results herein were valuable to structural design for flexible airship especially for large flexible airship. | 高海健 陈务军 付功义 | 2010 | Journal of Shanghai Jiaotong university(Science)2010，15，6： | 5 |
| 5 | 柔性飞艇主气囊不稳定构型阶段力学性能分析显示文摘为了揭示柔性飞艇主气囊不稳定构型阶段的力学性能,首先基于迭代薄膜性能法(IMP)编制可分析薄膜褶皱的子程序,通过对比不同单元类型充气管变形结果,找出一种合理的单元类型进行不稳定构型主气囊模拟.在此基础上,以9m柔性飞艇主气囊简化模型为对象,对简化模型在不同约束状态下不稳定构型阶段外形及应力进行分析.研究表明:气压梯度和模型约束是柔性飞艇主气囊在不稳定构型阶段力学性能的重要影响因素,模型从稳定构型到不稳定构型阶段开始的一段时间,形状变化不大,中间阶段模型发生较大的形状改变.不稳定构型阶段在约束部位较稳定构型时更容易发生强度破坏.研究结果对柔性平流层飞艇主气囊结构设计具有参考价值. | 陈宇峰 陈务军 邱振宇 | 2015 | 上海交通大学学报2015，49，9： | 4 |
| 6 | 柔性飞艇及其悬挂屏体系结构力学性能分析显示文摘为研究大型柔性飞艇及其悬挂屏结构体系力学性能,以25 m验证飞艇(ZY-1)放大3倍的模型为对象,分析了仅考虑内外压差自平衡体系和考虑浮力、重力的平衡体系结构性能。基于柔性飞艇主气囊初始形状,通过充气压力静力非线性分析得到充气平衡形态位形和应力。利用兰索斯法分析了含悬挂屏飞艇结构在2种平衡体系中不同气压下的自振特性;探讨了悬挂屏悬索制作误差对自振特性影响。分析表明:悬挂屏悬索与囊体连接部位是飞艇的薄弱部位,囊体的内外压差和压力梯度的大小对悬挂屏力学性能影响显著;悬挂屏悬索制作误差导致囊体局部形变,从而改变悬挂屏力学性能。 | 陈宇峰 陈务军 何艳丽 张大旭 | 2014 | 哈尔滨工程大学学报2014，35，7： | 2 |
| 7 | Vibration Characteristic Analysis and Experiment of Non-Rigid Airship with Suspended Curtain显示文摘In order to evaluate the vibration characteristics of non-rigid airship with suspended curtain,we introduce vibration characteristic analysis method of the inflatable membrane structure.Modal numerical method of the inflatable membrane structure under the pressure difference is validated by the model testing of the inflatable cantilever tube.The finite element model of 75 m airships is established to simulate the vibration characteristics subjected to only pressure difference and the resultant force of weight and buoyancy.The nonlinear static deformation and stress analysis are investigated for two kinds of equilibrated configurations with various pressure differences,as well as the vibration characteristics.The structural efficiency of the suspended curtain is investigated through the force transfer ratio at the assumed equilibrated point.The effects of manufacture error of the suspended cable length on the structural behavior are analyzed.The results indicate that the local area of airship envelope connected to the suspended cable is a weak part.Various pressures and pressure gradients have significant effects on the global airship structure and the suspended curtain.The suspended curtain is effective to transfer the equilibrated force from the bottom to the top of airship envelope.Manufacture error of the suspended cable length could result in obvious deformation of local airship envelope.The presented work is valuable to the structural engineering design of stratospheric airship. | 陈宇峰 陈务军 何艳丽 张大旭 | 2015 | Journal of Shanghai Jiaotong university(Science)2015，20，5： | 0 |
| 8 | 海泰电子最新推出HTPXI4284振动和噪声测量模块显示文摘陕西海泰电子有限责任公司(以下简称“海泰电子”)近日发布了一款基于PXI总线高性价比的8通道、24位振动和噪声测量模块——HTPX14284。 | | 2014 | 电子测量与仪器学报2014，28，2： | 0 |
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