物—伞系统运动稳定性初探

弹道－升力式再入飞行器常采用旋成体外形，但其质心偏离对称轴（纵轴）设置。这种飞行器在着陆前要采用降落伞作为主减速手段。研究质心偏离对称轴的旋成体与降落伞组成的系统的运动稳定性是一项有工程实践意义的课题。作为一种初步探索，在把降落伞视作刚体的条件下，按该系统平面运动方程考察其在平衡状态附近的稳定性，给出了运动稳定性判据。     

多个自由飞行空间机器人协调操作运动规划

本文提出了在空间微重力环境下多个自由飞行空间机器人协调操作运动规划算法，首先推导出多个自由飞行空间机器人协调操作的广义雅可比矩阵，其次给出了基于该矩阵的多个自由飞行空间机器人协调操作分解运动速度控制算法，最后用计算机仿真验证了该算法的正确性。     

基于模糊层次分析法的机场管制模拟机评价

采用模糊综合评判法与层次分析法相结合的评估方法,对机场管制模拟机仿真度进行评价.根据机场管制模拟机需求功能选取恰当的评估指标,用层次分析法建立机场管制模拟机仿真度评价指标体系.然后分层次进行模糊综合评判,得出综合评价结果.最后以某机场管制模拟机为例,对其仿真度进行评估.结果表明这种方法科学合理且容易实现,为实验室设备选型提供了合理的依据,具有实际的应用价值.     

Motion prediction of a non-cooperative space target

Capturing a non-cooperative space target is a tremendously challenging research topic. Effective acquisition of motion information of the space target is the premise to realize target capture. In this paper, motion prediction of a free-floating non-cooperative target in space is studied and a motion prediction algorithm is proposed. In order to predict the motion of the free-floating non-cooperative target, dynamic parameters of the target must be firstly identified (estimated), such as inertia, angular momentum and kinetic energy and so on; then the predicted motion of the target can be acquired by substituting these identified parameters into the Euler’s equations of the target. Accurate prediction needs precise identification. This paper presents an effective method to identify these dynamic parameters of a free-floating non-cooperative target. This method is based on two steps, (1) the rough estimation of the parameters is computed using the motion observation data to the target, and (2) the best estimation of the parameters is found by an optimization method. In the optimization problem, the objective function is based on the difference between the observed and the predicted motion, and the interior-point method (IPM) is chosen as the optimization algorithm, which starts at the rough estimate obtained in the first step and finds a global minimum to the objective function with the guidance of objective function’s gradient. So the speed of IPM searching for the global minimum is fast, and an accurate identification can be obtained in time. The numerical results show that the proposed motion prediction algorithm is able to predict the motion of the target.     

航天器分裂体或抛射物的轨道形成和演化

由卫星和碎片爆炸或相互间碰撞所产生的分裂体,或由在轨航天器向外抛射所产生的抛射物,对空间环境的影响正日益增大。对它们轨道形成和演化的研究可以为分析空间解体事件提供一种有效方法。本文利用Kep-ler运动积分以及受摄二体问题的分析解,建立了分裂体或抛射物的轨道形成及其演化与分裂或抛射速度之间的关系,从而为理解以各个方向、不同大小的速度分裂或抛射的物体的轨道演化特征提供理论依据。文章最后通过数值验证表明了该方法的有效性。     

Real-time trajectory planning for UCAV air-to-surface attack using inverse dynamics optimization method and receding horizon control

This paper presents a computationally efficient real-time trajectory planning framework for typical unmanned combat aerial vehicle (UCAV) performing autonomous air-to-surface (A/S) attack. It combines the benefits of inverse dynamics optimization method and receding horizon optimal control technique. Firstly, the ground attack trajectory planning problem is mathematically formulated as a receding horizon optimal control problem (RHC-OCP). In particular, an approximate elliptic launch acceptable region (LAR) model is proposed to model the critical weapon delivery constraints. Secondly, a planning algorithm based on inverse dynamics optimization, which has high computational efficiency and good convergence properties, is developed to solve the RHCOCP in real-time. Thirdly, in order to improve robustness and adaptivity in a dynamic and uncer- tain environment, a two-degree-of-freedom (2-DOF) receding horizon control architecture is introduced and a regular real-time update strategy is proposed as well, and the real-time feedback can be achieved and the not-converged situations can be handled. Finally, numerical simulations demon- strate the efficiency of this framework, and the results also show that the presented technique is well suited for real-time implementation in dynamic and uncertain environment.     

轻型飞行模拟器并联机构约束检验算法的研究

采用6-3UPS边置式座舱结构的轻型飞行模拟器,其工作空间受约束条件的限制。在数学描述的基础上,对影响工作空间的各项约束检验算法进行研究,并分析约束条件下轻型飞行模拟器的工作空间,为控制算法的研究提供依据。     

风挡玻璃加温系统功能试验方法优化设计

简述了风挡玻璃加温系统的工作原理,并结合飞机总装配阶段的生产特点,重点介绍了风挡玻璃加温系统功能试验的方法及其优化设计     

飞机座舱人机工效评定实验台研制

为解决飞机人机界面设计在新形势下面临的问题,研制了一套基于飞行模拟器的驾驶员工效评定实验台,以便在更加实际的飞行情况下对飞行员的认知特性进行研究.该实验台由飞机座舱、仿真软件、计算机系统和生理参数测量系统等组成,能开展座舱优化布局、界面信息显示适人性、脑力负荷的综合评定等研究.该实验台的研制为飞机人机界面的工效设计和评定提供了一种新的方法.     

一种基于COTS的SAR分布式目标模拟方法

针对目前合成孔径雷达(SAR)目标模拟器通常只能模拟点目标，且通用化程度和实时性较低的问题，提出了一种基于商用现成品或技术(COTS)的SAR分布式目标模拟方法。利用NI PXI平台构建了一个基于电磁仿真的SAR分布式目标模拟器，由电磁仿真软件模拟获取目标散射特性，并通过高速网口输入硬件设备进行采样及卷积操作得到仿真SAR回波数字信号，经数模转换模块完成对SAR数字信号的调制并输出模拟回波，可以直接用于SAR系统的数据验证。模拟器采用数字式一体化硬件设备，由NI PXIe-5646R和PXIe-5840进行信号的接收和发送，PXIe-7902作为系统核心进行高速实时数据运算。系统以现场可编程门阵列(FPGA)为核心，通过LabVIEW RT (Real Time)和FPGA模块直接进行访问，能实时、高速地采集和处理数据。经过测试，该目标模拟器可以生成分布式目标的射频回波信号，环路验证结果证明了本文提出方法的有效性。另外，本文提出的方法适用于多种雷达信号的模拟，通过设置不同的信号体制或接收外部信号输入，可以实现灵活的SAR目标模拟。