飞机大部件自动对接同步调姿方法

提出了飞机大部件自动对接同步调姿方法,实现了大部件调姿基准点的连续自动跟踪测量和位姿连续调整.在此基础上开发了集测量场构建、大部件位姿解算和调整等功能于一体的大部件自动对接集成控制软件,并在ARJ21飞机翼身自动对接现场进行了应用试验,结果证明该方法能有效完成飞机翼身自动对接过程,提高测量和对接效率.     

飞机装配质量数字化检测技术研究及应用

针对飞机装配过程质量评价对数字化测量技术的需求,开展了面向飞机装配的数字化测量特征设计、测量方案设计、多系统异构测量场构建、测量误差分析与修正等技术研究,并以表面类、内部结构特征、大部件对接和活动部件装配质量的控制为例,阐述了测量设备选型、整体测量场的构建方法及其应用效果.     

基于响应面法的齿轮容差设计方法研究

随着附件传动系统不断向高速、重载方向发展,齿面接触可靠性问题越来越受关注.为提高齿轮可靠性,分析了齿轮传动系统常见误差类型及影响,开展了齿轮容差设计初步探讨.根据齿轮制造、加工及系统动态误差的产生原理和作用方式,基于齿轮接触应力仿真结果,确定了影响齿轮接触应力随机性的5种主要误差形式及其特征量分布规律,提出了基于响应面法的齿轮容差设计方法,给出了齿轮系统公差设计的改进方向:在进行齿轮公差设计时,重点控制H、V方向的轴向平行度公差.     

基于离散粒子群算法的航空发动机总装工艺优化方法

为了提高航空发动机总装工作的效率与质量,加强对总装工序和总装机件的管控,量化不同总装人员工作任务量,提高发动机总装的一致性和可追溯性,提出了1种发动机总装分区优化方法。以改进的2进制粒子群算法为基础,平衡了发动机总装各区域的工作内容,最小化各总装区域的工作差异,增强了每个区域装配机件的关联度,提高了总装工作的并行度,从而提高了装配质量。以某型发动机总装区域划分工作为实例,通过上述算法进行了总装区域划分,量化了所有装配区域每一工序的具体装配内容,减小了不同装配区域间的机件差异,杜绝了缺件、剩件等装配问题。     

突加不平衡下GTF发动机转子系统瞬态响应分析

针对GTF发动机低压转子系统突加不平衡瞬态响应问题,基于有限元法建立了考虑啮合单元、行星架单元、膜盘联轴器单元的多体接触、多转子耦合动力学模型,介绍了考虑非线性因素下突加不平衡瞬态响应计算方法,求解了低压转子系统的突加不平衡瞬态响应,并分析了关键部件刚度对突加不平衡的影响规律。结果表明：当风扇转子发生突加不平衡时,各部件均表现为振动幅值突增,后迅速趋于稳定,低压涡轮转子发生明显拍振,突加不平衡载荷主要由行星架结构和第1.5支点刚性支承承担;行星架刚度主要影响风扇转子突加不平衡响应、第1.5支点和行星架处的外传力;膜盘联轴器刚度主要影响增压级突加不平衡响应、转子在突加不平衡之后稳定运转情况。     

Downsizing an orbital space robot: A dynamic system based evaluation

Small space robots have the potential to revolutionise space exploration by facilitating the on-orbit assembly of infrastructure, in shorter time scales, at reduced costs. Their commercial appeal will be further improved if such a system is also capable of performing on-orbit servicing missions, in line with the current drive to limit space debris and prolong the lifetime of satellites already in orbit. Whilst there have been a limited number of successful demonstrations of technologies capable of these on-orbit operations, the systems remain large and bespoke. The recent surge in small satellite technologies is changing the economics of space and in the near future, downsizing a space robot might become be a viable option with a host of benefits. This industry wide shift means some of the technologies for use with a downsized space robot, such as power and communication subsystems, now exist. However, there are still dynamic and control issues that need to be overcome before a downsized space robot can be capable of undertaking useful missions. This paper first outlines these issues, before analyzing the effect of downsizing a system on its operational capability. Therefore presenting the smallest controllable system such that the benefits of a small space robot can be achieved with current technologies. The sizing of the base spacecraft and manipulator are addressed here. The design presented consists of a 3 link, 6 degrees of freedom robotic manipulator mounted on a 12U form factor satellite. The feasibility of this 12U space robot was evaluated in simulation and the in-depth results presented here support the hypothesis that a small space robot is a viable solution for in-orbit operations.     

永磁同步电机驱动太阳翼扰动力矩建模与仿真

建立太阳翼驱动机构(SADA)永磁同步电机的电磁方程,并利用固定界面模态综合法建立SADA驱动太阳翼耦合系统的振动方程;设计模拟柔性负载,对SADA驱动该柔性负载的扰振力矩进行仿真分析。结果表明,SADA驱动柔性负载运行过程中所产生扰振力矩主要由两个原因引起：1)电流噪声引起的力矩波动;2)控制参数选取不当引起的转角波动。     

基于模因算法的飞机装配序列规划

针对飞机制造的装配序列规划问题,提出一种基于模因算法的飞机部件装配序列规划方法。在装配优先约束矩阵和非正交干涉矩阵的基础上构建装配规划模型,以飞机零部件间的装配方向和装配工具的差异性来构建适应度函数。在非干涉解空间中进行全局搜索,获得较优的装配规划方案,通过二叉树中序遍历法将较优的方案转化为可行解,再经过交叉操作和变异操作后,在可行解空间内进行局部搜索,最终获取较优的装配方案。以某型号的飞机舱门装配为例,通过与传统遗传算法对比,证实模因算法在飞机装配序列规划中的可行性和有效性。     

Hypervelocity impact induced shock acoustic emission waves for quantitative damage evaluation using in situ miniaturized piezoelectric sensor network

Manmade debris and natural meteoroids, travelling in the Low Earth Orbit at a speed of several kilometers per second, pose a severe safety concern to the spacecraft in service through the HyperVelocity Impact(HVI). To address this issue, an investigation of shock Acoustic Emission(AE) waves induced by HVI to a downscaled two-layer Whipple shielding structure is performed,to realize a quantitative damage evaluation. Firstly a hybrid numerical model integrating smoothparticle hydrodynamics and finite element is built to obtain the wave response. The projectiles, with various impact velocities and directions, are modelled to impact the shielding structure with different thicknesses. Then experimental validation is carried out with built-in miniaturized piezoelectric sensors to in situ sense the HVI-induced AE waves. A quantitative agreement is obtained between numerical and experimental results, demonstrating the correctness of the hybrid model and facilitating the explanation of obtained AE signals in experiment. Based on the understanding of HVI-induced wave components, assessment of the damage severity, i.e., whether the outer shielding layer is perforated or not, is performed using the energy ratio between the regions of ‘‘high frequency" and ‘‘low frequency" in the acquired AE signals. Lastly, the direct-arrival fundamentalsymmetric wave mode is isolated from each sensing signal to be input into an enhanced delay-andsum algorithm, which visualizes HVI spots accurately and instantaneously with different sensor network configuration. All these works demonstrate the potential of quantitative, in situ, and real time HVI monitoring using miniaturized piezoelectric sensor network.     

基于联系度的雷达导引头综合能力评估

雷达导引头是反舰导弹的重要组成部分,对其综合能力的评估是一个多因素综合评判问题。文章分析了影响雷达导引头综合能力的主要因素,建立了雷达导引头综合能力评估指标体系和基于联系度的雷达导引头综合能力评估模型,并提出了联系度的比较规则。最后,评估得出了国外几种典型的雷达导引头综合能力的优劣排序。