铸铝薄壁件高速钻深孔技术研究

为解决铸铝薄壁件进气机匣的深孔加工，针对麻花钻加工深孔的难点，在加工中心上研究了用枪钻和GT深孔麻花钻高速加工深孔的方案和工艺参数，并探讨了雾化高压气体强制排屑加工深孔的技术，获得了典型薄壁箱体零件的高速钻深孔的经验。     

涡轮叶片精铸模CAD／CAM原型系统开发与应用

将并行工程的思想和方法运用于航空发动机涡轮叶片精铸模具设计与制造的全过程,以ＩＭＡＮ 作为信息集成平台,开发出的ＣＡＤ／ＣＡＭ 原型系统真正实现了精铸模设计与制造的无纸化,使涡轮叶片精铸模具的设计周期缩短了６０ ％ ,数控编程周期缩短了５０ ％ 。     

论加速可靠性增长试验(I)新方向的提出

在分析总结加速寿命试验 (ALT)及可靠性增长试验 (RGT)的基础上 ,首次提出了加速可靠性增长试验 (ARGT)这个新方向 ,并指出了在研究ARGT时将会遇到的主要问题以及解决这些问题的途径     

航空电液伺服系统阀套珩磨材料去除体积预测研究

针对珩磨加工阀套孔生产率低、加工精度难控制等问题,开展了内孔珩磨技术研究,通过分析9Cr18不锈钢珩磨过程中材料去除率的变化规律,提出一套适用于珩磨加工的材料去除体积理论公式。同时为使珩后孔不同轴向位置处的孔径趋近一致,需要在上下越程处增设停留时间,以此改进初始模型。基于初始模型与优化模型分别开展单因素珩磨试验,结果表明,往复速度和珩磨压强是影响珩磨材料去除体积的显著因素,针对珩磨材料去除体积与珩后孔径差,优化模型与初始模型的预测结果分别与对应的试验结果对比,可发现优化模型预测精度相较于初始模型分别提高25%～30%。在越程段增设停留时间并不会降低加工效率,可提高珩后孔尺寸精度,实现材料去除体积的准确预测。     

天基激光清除空间碎片方案与可行性研究

介绍了激光烧蚀驱动机理和空间碎片降轨清除原理,通过分析计算确立了空间碎片降轨清除判据和2 种降轨清除模式。理论计算给出了清除1200、800 和500 km 三个典型低地球轨道上空间碎片所必须的速度增量、激光器功率、单脉冲能量、激光发射镜直径等主要参数值。对比分析显示现有的硬件指标和条件能够满足清除低地球轨道上空间碎片的设计要求,因此,天基激光清除空间碎片方案从技术角度是可行的。     

Dynamics and control for contactless interaction between spacecraft and tumbling debris

Tumbling debris has become a great threat to orbit activities. Contactless interaction is a novel concept for active debris removal, through which the tumbling debris no longer rotates freely but is under control. The contactless interaction method aims to de-tumble the debris and then maintain desired relative states between the spacecraft and debris. The spacecraft is simultaneously stabilized through three-axis attitude control, which makes the de-tumbling and capture operation much safer, more effective and accurate. The dynamics and control for the contactless interaction have been little studied in the past years. This paper considers a generic dynamics and control problem for contactless interaction between a spacecraft and debris. A translational and rotational dynamics model of contactless interaction is proposed and the 6-DOF equations are established. The contactless interaction control law is designed with the backstepping method, and the spacecraft three-axis control law is designed with the PD control. Simulation results show that the angular momentum is transferred from the debris to the spacecraft and the debris is thus de-tumbled. The desired relative states are achieved efficiently. Significantly, the spacecraft and debris no longer rotate in the inertial frame and, hence, the safety and accuracy for capture operation are guaranteed.     

地基激光清除椭圆轨道空间碎片特性的计算分析

空间碎片对人类航天活动的危害很大,用高能激光减缓其危害性已受到广泛关注.针对地基激光清除椭圆轨道空间碎片问题,提出了单脉冲变轨和多脉冲变轨两种计算分析方法.仿真计算结果表明,碎片初始真近角在100°～150°附近降轨效果最佳;从激光器在地球表面可供布站的区域讲,在碎片真近角180°附近,布站区域最大;当推进激光总作用时间较短或作用距离较小时,单脉冲变轨计算模型和多脉冲变轨计算模型计算结果接近,因此可采用单脉冲变轨计算模型计算结果近似表示多脉冲作用效果.     

A novel stability prediction approach for thin-walled component milling considering material removing process

The milling stability of thin-walled components is an important issue in the aviation manufacturing industry,which greatly limits the removal rate of a workpiece.However,for a thin-walled workpiece,the dynamic characteristics vary at different positions.In addition,the removed part also has influence on determining the modal parameters of the workpiece.Thus,the milling stability is also time-variant.In this work,in order to investigate the time variation of a workpiece's dynamic characteristics,a new computational model is firstly derived by dividing the workpiece into a removed part and a remaining part with the Ritz method.Then,an updated frequency response function is obtained by Lagrange's equation and the corresponding modal parameters are extracted.Finally,multi-mode stability lobes are plotted by the different quadrature method and its accuracy is verified by experiments.The proposed method improves the computational efficiency to predict the time-varying characteristics of a thin-walled workpiece.     

大型飞机气源起动装备供气流程设计与计算

为了研发具有自主知识产权的气源起动装备,立足于大型飞机较高压力、超大流量的特殊气源起动保障需求,设计了以双级无油螺杆压缩为核心技术的供气流程,对其中涉及的级间压力、散热量、除水量等关键参数进行了分析与计算,为解决超大流量气源的二次升压、风冷散热、高温除水等核心技术难题奠定了基础。     

Orbital debris–debris collision avoidance

We focus on preventing collisions between debris and debris, for which there is no current, effective mitigation strategy. We investigate the feasibility of using a medium-powered (5 kW) ground-based laser combined with a ground-based telescope to prevent collisions between debris objects in low-Earth orbit (LEO). The scheme utilizes photon pressure alone as a means to perturb the orbit of a debris object. Applied over multiple engagements, this alters the debris orbit sufficiently to reduce the risk of an upcoming conjunction. We employ standard assumptions for atmospheric conditions and the resulting beam propagation. Using case studies designed to represent the properties (e.g. area and mass) of the current debris population, we show that one could significantly reduce the risk of nearly half of all catastrophic collisions involving debris using only one such laser/telescope facility. We speculate on whether this could mitigate the debris fragmentation rate such that it falls below the natural debris re-entry rate due to atmospheric drag, and thus whether continuous long-term operation could entirely mitigate the Kessler syndrome in LEO, without need for relatively expensive active debris removal.