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.     

基于FPGA的DDR2缓存控制器在 无线链路图像跟踪系统中的应用

图像跟踪系统是机载光电吊舱的重要组成部分,其对目标捕捉的成功率直接决定了机载光电吊舱的性能.而作用于机载光电吊舱与地面站之间的无线链路系统,有着不可消除的的延时特性,这极大地降低了目标捕捉成功率.本文设计了一种基于FPGA的DDR2缓存控制器,通过缓存控制器可以轻松实现高清视频图像的快速存储和调用,从而实现图像跟踪算法对无线链路延时的补偿.该缓存控制器成功应用于某型机载光电吊舱图像跟踪系统,有效消除了无线链路延时的影响,提高了图像跟踪系统对目标捕捉的成功率.     

基于强跟踪EKF的组合导航系统故障检测方法

针对大方位失准角的机载SINS/GPS组合导航系统,为保证在高动态环境下实现高精度、高可靠的导航,利用强跟踪EKF滤波残差设计了一种基于残差统计特性的坏值检测算法,对导航信息进行估计和跟踪.仿真结果表明,该算法能够实时检测出GPS量测信息中的坏值信息,隔离后可显著提高组合导航精度,具有较高的可靠性、出色的容错能力和重要的工程应用价值.     

Nonlinear dynamic modeling of a helicopter planetary gear train for carrier plate crack fault diagnosis

Planetary gear train plays a significant role in a helicopter operation and its health is of great importance for the flight safety of the helicopter. This paper investigates the effects of a planet carrier plate crack on the dynamic characteristics of a planetary gear train, and thus finds an effec-tive method to diagnose crack fault. A dynamic model is developed to analyze the torsional vibra-tion of a planetary gear train with a cracked planet carrier plate. The model takes into consideration nonlinear factors such as the time-varying meshing stiffness, gear backlash and viscous damping. Investigation of the deformation of the cracked carrier plate under static stress is performed in order to simulate the dynamic effects of the planet carrier crack on the angular displacement of car-rier posts. Validation shows good accuracy of the developed dynamic model in predicting dynamic characteristics of a planetary gear train. Fault features extracted from predictions of the model reveal the correspondence between vibration characteristic and the conditions (length and position) of a planet carrier crack clearly.     

多飞行器再入段时间协同弹道规划方法

提出了一种多飞行器再入段时间协同弹道规划方法。首先,在纵向平面内规划满足航程与终端约束的纵向标称轨迹。随后,在采用轨迹跟踪律跟踪纵向标称轨迹的同时,运用考虑初始横侧向状态的多边界航向偏差角走廊策略控制飞行器的横侧向机动,以满足到达时间约束与终端约束,进而实现单枚飞行器到达时间约束下的轨迹规划。在此基础上,完成了飞行器的到达时间分布与飞行能力分析,给出了最小与最大到达时间的分析计算方法,并根据多飞行器协同再入的任务需求完成了协同飞行时间决策。最后,多飞行器协同再入与扰动条件下的仿真结果表明,该方法能够规划出满足到达时间与终端约束的协同再入轨迹,具备良好的计算精度与鲁棒性。     

Optimization and verification of free flight separation similarity law in high-speed wind tunnel

Based on the similarity of separation time, a similarity law optimization method for high-speed weapon delivery test is derived. The typical separation state under wind load is simulated by the numerical method. The real separation data of aircraft, separation data of previous test methods, separation data of ideal wind tunnel test of previous methods, and simulation data of the proposed optimization method are obtained. A comparison of the data shows that the method proposed can improve the performance of tracking. Similarity law optimization starts with the development of motion equations and dynamic equations in the windless state to address the problems of mismatching between vertical and horizontal displacement, and to address the problems of separation trajectory distortion caused by insufficient gravity acceleration of the scaling model of existing light model. The ejection velocity of the model is taken as a factor/vector, and is adjusted reasonably to compensate the linear displacement insufficiency caused by the insufficient vertical acceleration of the light model method, so as to ensure the matching of the vertical and horizontal displacement of the projectile, and to improve the consistency between the test results of high-speed projection and the actual separation trajectory. The optimized similarity law is applicable to many existing free-throwing modes of high-speed wind tunnels. The optimized similarity law is not affected by the ejection velocity and hanging mode of the projectile. The optimized similarity law is suitable not only for the launching of the buried ammunition compartment and external stores, but also for the test design of projectile launching and gravity separation.     

集成式随动装置目标引导信息动态校准方法研究

光电对抗系统在机动状态下搜索和跟踪目标时，必须用位置陀螺代替码盘来确定目标方位角。但是，由于搜索轴陀螺存在漂移和累积误差，导致跟踪转台按照引导信息调转到位后目标无法进入跟踪视场，而且陀螺的漂移和累积误差是随时间和温度非线性变化的，很难直接进行修正。为了解决这个问题，提出了一种对引导信息进行间接动态校准的方法。     

基于模拟退火粒子群算法的波浪发电系统最大功率跟踪控制

波浪发电系统最大功率点跟踪控制中,传统粒子群算法存在早熟收敛和局部搜索能力不足问题,为此提出基于模拟退火算法的粒子群优化方案。该算法每次更新粒子的速度和位置时,通过比较当前温度下各个粒子的适配值与随机数的大小,从所有粒子中确定全局最优解的替代值,从而使粒子群算法在发生早熟收敛时能够跳出局部最优并快速找到全局最优解。仿真结果表明,与传统粒子群优化算法相比,模拟退火粒子群算法可有效避免波浪发电系统陷入局部最大功率点,并快速实现全局最大功率跟踪,提高了波浪能捕获率。     

对某装备任务系统软件故障的研究

通过对任务系统软件故障进行定位和分析，提出了基于互斥信号量对获取数据进行现场保护及在任务管理区增加对时间的容错处理的解决措施，并对其进行了分析和验证。     

基于灰色补偿反步法的机动指令跟踪控制

基于三自由度飞行动力学模型和运动学模型,提出了一种带有灰色补偿的反步(Back-stepping)控制方法,以实现某些预定的战术机动动作。首先,将飞行动力学模型和运动学模型分解成3个轴方向的相对简单的子系统;然后,针对3个子系统采用反步法分别设计出模型中没有干扰时的控制律,并采用GM(0,N)预测模型对不确定部分的模型参数进行辨识,进一步根据估计出的参数设计灰色补偿控制律;最后,根据3个子系统设计出的控制律解算出同时满足3个子系统渐进稳定的控制输入,这样使得整个系统渐进稳定。仿真结果表明,GM(0,N)预测模型能精确预测不确定模型参数,该算法能够高效实现预定的战术机动动作。