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以配装PW4000发动机的空客A330飞机曾出现的一起液压泵低压故障为案例,结合飞机主液压系统工作原理进行简要分析,逐步梳理故障源,拓宽排故思路,为同类故障的处理提供参考。 相似文献
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阐述了K8飞机从方案设计到设计定型整个过程重量重心的控制问题。由于控制方法适当、有效,使飞机重量控制致指标以下,飞机重心落在限制范围以内。 相似文献
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针对某小型飞机液压泵失效故障进行分析,找出电机碳刷过度磨损的原因,认为是由于液压油的异常浸入而加速了碳刷的磨损,并结合飞机日常维护要求和特点提出了维护建议。 相似文献
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K8飞机襟翼装配长期达不到设计要求,成为技术关键。本文从多方面分析了产生问题的原因,并详细介绍了改进方法及其效果。 相似文献
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简要介绍了一起PA44-180飞机液压泵跳开关弹出故障的排除过程,从液压收放系统的原理、结构和系统方面分析了故障原因.对主收放作动筒故障数据进行分析.获得了主作动筒的可靠性数据,为类似故障的排除提供了借鉴和参考。 相似文献
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K8飞机座舱盖有机玻璃破裂原因分析 总被引:2,自引:0,他引:2
通过对K8飞机座舱盖MYB-3^#有要玻璃断口进行宏观及微观分析,揭示了该座舱盖有机玻璃破裂的主要原因,并找到了划伤深度对有机玻璃疲劳寿命影响的规律。 相似文献
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通过对一起波音737NG飞机备用液压泵低压灯亮故障的分析,从宏观和整体的角度理解液压系统各部件之间的关联关系,为类似故障的排除提供参考。 相似文献
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介绍取消K8飞机配重的结构更改方案。并对方案的可行性作了分析,为改善K8飞机性能和提高飞机的操纵稳定性提供了一种可行的参考方法。 相似文献
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《中国航空学报》2020,33(1):16-30
The piston pump is the key power component in the civil aircraft hydraulic system, and the most common pump used in the aviation field is the pressure compensated variable displacement type. In this review paper, a basic introduction to the civil aircraft piston pump is presented, including the classification, structure, working principle, design features, and achievements by some research groups. Then, the future directions of the aircraft pump are reported from various perspectives. Further, the critical technologies are analyzed and summarized in detail from six thrust areas: friction couples, noise reduction, inlet boost, thermal management, fault diagnosis and health management, and mechanical seal. Finally, the challenges and limitations of the research on the aircraft pump are discussed to provide valuable insight for future scholars. 相似文献
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Fault diagnosis of an intelligent hydraulic pump based on a nonlinear unknown input observer 总被引:6,自引:6,他引:0
Hydraulic piston pumps are commonly used in aircraft. In order to improve the viability of aircraft and energy efficiency, intelligent variable pressure pump systems have been used in aircraft hydraulic systems more and more widely. Efficient fault diagnosis plays an important role in improving the reliability and performance of hydraulic systems. In this paper, a fault diagnosis method of an intelligent hydraulic pump system (IHPS) based on a nonlinear unknown input observer (NUIO) is proposed. Different from factors of a full-order Luenberger-type unknown input observer, nonlinear factors of the IHPS are considered in the NUIO. Firstly, a new type of intelligent pump is presented, the mathematical model of which is established to describe the IHPS. Taking into account the real-time requirements of the IHPS and the special structure of the pump, the mechanism of the intelligent pump and failure modes are analyzed and two typical failure modes are obtained. Furthermore, a NUIO of the IHPS is performed based on the output pressure and swashplate angle signals. With the residual error signals produced by the NUIO, online intelligent pump failure occurring in real-time can be detected. Lastly, through analysis and simulation, it is confirmed that this diagnostic method could accurately diagnose and isolate those typical failure modes of the nonlinear IHPS. The method proposed in this paper is of great significance in improving the reliability of the IHPS. 相似文献
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Traditional hydraulic brake systems require a complex system of pipelines between an aircraft engine driven pump (EDP) and brake actuators, which increases the weight of the aircraft and may even cause serious vibration and leakage problems. In order to improve the reliability and safety of more electric aircraft (MEA), this paper proposes a new integrated self-powered brake system (ISBS) for MEA. It uses a hydraulic pump geared to the main wheel to recover a small part of the kinetic energy of a landing aircraft. The recovered energy then serves as the hydraulic power supply for brake actuators. It does not require additional hydraulic source, thus removing the pipelines between an EDP and brake actuators. In addition, its self-powered characteristic makes it possible to brake as usual even in an emergency situation when the airborne power is lost. This paper introduces the working principle of the ISBS and presents a prototype. The mathematical models of a taxiing aircraft and the ISBS are established. A feedback linearization control algorithm is designed to fulfill the anti-skid control. Simulations are carried out to verify the feasibility of the ISBS, and experiments are conducted on a ground inertia brake test bench. The ISBS presents a good performance and provides a new potential solution in the field of brake systems for MEA. 相似文献
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《中国航空学报》2021,34(4):83-114
Vibrations in aircraft hydraulic pipeline system, due to multi-source excitation of high fluid pressure fluctuation and serious vibration environment of airframe, can cause the pipeline system vibration failures through overload in engineering field. Controlling the vibrations in hydraulic pipeline is a challenging work to ensure the flight safety of aircraft. The common vibration control technologies have been demonstrated to be effective in typical structures such as aerospace structures, shipbuilding structures, marine offshore structures, motor structures, etc. However, there are few research literatures on vibration control strategies of aircraft hydraulic pipeline. Combining with the development trend of aircraft hydraulic pipeline system and the requirement of vibration control technologies, this paper provides a detailed review on the current vibration control technologies in hydraulic pipeline system. A review of the general approaches following the passive and active control technologies are presented, which are including optimal layout technique of pipeline and clamps, constrained layer damping technique, vibration absorber technique, hydraulic hose technique, optimal pump structure technique, and active vibration control technique of pipeline system. Finally, some suggestions for the application of vibration control technologies in engineering field are given. 相似文献
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为了深入研究航空液压泵输出油液的脉动压力特性,以航空液压柱塞泵为研究对象,分析了柱塞泵运动和体积流量脉动的成因,推导了柱塞泵排油口的体积流量脉动函数表达式,建立了油液压力与体积流量脉动函数之间的联系,并采用傅里叶级数模拟了与实验数据吻合的多级脉动压力曲线。结果表明:模拟脉动压力曲线与实验数据基频、2倍频的相对误差均在5%以内,基频及2倍频处的压力幅值的相对误差均在1%以内,使用包含基频与2倍频的级数近似可以描绘航空液压柱塞泵出口处周期脉动压力的主要特征。研究结果为进行飞机液压系统管路结构的流固耦合振动仿真提供了载荷输入依据。 相似文献
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研究了民用飞机动力装置系统机械接口的设计技术,提出了动力装置系统机械接口的三种分类并总结了相应特点。根据民用飞机和动力装置系统的设计特点,总结了机械接口设计的主要内容,提出了一般设计流程,并以液压泵机械接口设计作为实例,详细描述了机械接口设计的内容和流程。为民用飞机动力装置系统安装集成设计提供了支持和技术积累。 相似文献
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辛东华 《民用飞机设计与研究》2019,(2):47-52
控制逻辑是机载系统的重要组成之一,对其进行仿真与验证有利于在飞机设计早期发现问题,从而提高系统的安全性。应用Matlab/Stateflow软件平台对民机液压控制逻辑进行了建模,通过控制信号设置和状态转移图的建立仿真实现了液压系统状态监控,泵源附件控制以及指示告警功能。结合液压控制面板的人机交互设计对逻辑模型进行了动态虚拟演示,提高了系统仿真的逼真度,验证了控制逻辑的有效性和准确性。 相似文献
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