等离子涂层热疲劳失效模式及失效机理研究

开展了等离子涂层构件热疲劳实验研究,对失效过程及失效模式进行考察,分析了对失效起主导作用的应力分量.针对陶瓷层材料引入粘塑性本构模型,对涂层的热疲劳进行数值模拟研究.分析表明,氧化层厚度为2 μm时,陶瓷层波峰位置容易萌生Ⅰ型横向裂纹,界面中部偏上位置容易萌生Ⅱ型横向裂纹;氧化层厚度为8 μm时,陶瓷层内部法向应力主导横向裂纹的扩展;不同厚度的氧化层内部将形成较高的应变能密度.给出了等离子涂层内部裂纹形成过程及机理.      

一种新型滑模控制算法在挠性多体卫星姿态控制中的应用

针对一类挠性多体卫星的复合控制问题，提出一种新型滑模变结构控制算法。新型算法利用闭环系统Lyapunov函数的一阶导数估计值设计控制器，且控制器采用了递归学习控制结构，能够有效解决传统滑模控制技术的颤振问题。随后根据Lyapunov稳定性理论证明闭环系统轨迹可以快速收敛到滑模面，并且系统状态误差可在滑模面上渐近收敛到零。此外，设计的控制器能够有效抑制外部干扰，而且控制器只需要控制输入矩阵信息而不需受控系统和未知参数的其他先验信息，使得算法具有较强鲁棒性。最后通过数值仿真与现有文献中控制算法进行对比，结果充分验证了本文设计控制算法的有效性和实用性。     

机翼跨声速抖振数值模拟及模态分析

绕机翼的跨声速抖振流动是典型的复杂不稳定流动，对其非定常特性及失稳机制的研究具有重要的工程和学术价值。通过非定常雷诺平均Navier-Stokes（URANS）仿真方法和动模态分解（DMD）分析手段，研究了CRM（Common Research Model）等典型机翼的跨声速抖振流动特性及其主要失稳模态。数值仿真结果表明机翼的跨声速抖振表现为多失稳模式下的宽频特性。除了激波的弦向失稳，还会伴随发生激波的展向失稳，它们都表现为低频特性。翼梢处的高频响应可能是由激波诱导的低频失稳与翼尖涡相互耦合形成。DMD分析结果显示机翼展长和后掠因素诱导了激波展向失稳模态。本研究对抖振流动的物理建模、控制及理解相关的气动弹性现象具有指导意义。     

高超声速有攻角锥飞行工况下迎风面波包的演化

飞行工况下由于壁温与来流温度之比较低，Mack模态的不稳定性会得到显著增强，因此Mack模态占主导的有攻角锥迎风面相对侧面可能会提前转捩。本文采用高分辨率直接数值模拟研究了高超声速有攻角锥在飞行工况下迎风面Mack模态的演化规律，Mack模态由迎风中心线附近的一个短时局部壁面吹吸激发。波包的空间分布和不同模态幅值沿流向的演化过程表明在有攻角条件下，Mack模态的演化过程与零度攻角锥边界层中的类似，基频共振是Mack模态最可能的转捩形式。     

Fixed-time adaptive model reference sliding mode control for an air-to-ground missile

This paper addresses the fixed-time adaptive model reference sliding mode control for an air-to-ground missile associated with large speed ranges, mismatched disturbances and un-modeled dynamics. Firstly, a sliding mode surface is developed by the tracking error of the state equation and the model reference state equation with respect to the air-to-ground missile. More specifically,a novel fixed-time adaptive reaching law is presented. Subsequently, the mismatched disturbances and the un-modeled dynamics are treated as the model errors of the state equation. These model errors are estimated by means of a fixed-time disturbance observer, and they are also utilized to compensate the proposed controller. Therefore, the fixed-time controller is obtained by an adaptive reaching law and a fixed-time disturbance observer. Closed-loop stability of the proposed controller is established. Finally, simulation results including Monte Carlo simulations, nonlinear six-DegreeOf-Freedom(6-DOF) simulations and different ranges are presented to demonstrate the efficacy of the proposed control scheme.     

High precision dynamic model and control considering J2 perturbation for spacecraft hovering in low orbit

For spacecraft hovering in low orbit, a high precision spacecraft relative dynamics model without any simplification and considering J₂ perturbation is established in this paper. Using the derived model, open-loop control and closed-loop control are proposed respectively. Gauss's variation equations and the coordinate transformation method are combined to deal with the relative J₂ perturbation between the two spacecraft. The sliding mode controller is adopted as the closed-loop controller for spacecraft hovering. To improve the control accuracy, the relative J₂ perturbation is regarded as a known parameter term in the closed-loop controller. The external uncertainty perturbations except J₂ perturbation are estimated by numerical difference method, and the boundary layer method is used to weaken the impact of chattering on the sliding mode controller. The open-loop control of spacecraft hovering with the relative J₂ perturbation and without the relative J₂ perturbation are simulated and compared, and the results prove that the accuracy of open-loop control with relative J₂ perturbation has been significantly improved. Similarly, the simulation of the closed-loop control are presented to validate the effectiveness of the designed sliding mode controller, and the results demonstrate that the designed sliding mode controller including the derived relative J₂ perturbation can guarantee the high accuracy and robustness of spacecraft hovering in long-term mission.     

Finite-time relative orbit-attitude tracking control for multi-spacecraft with collision avoidance and changing network topologies

This paper addresses the relative position tracking and attitude synchronization control problem for spacecraft formation flying (SFF). Based on the derived relative coupled six-degree-of-freedom dynamics, a robust adaptive finite-time fast terminal sliding mode controller is proposed to achieve the desired formation in the presence of model uncertainties and external disturbances. It is shown that the designed controller is effective for changing information exchange topology making it robust to node failure. Then, the artificial potential function method is employed to generate collision avoidance schemes to modify the controller such that inter-agent collision avoidance can be ensured during the formation maneuver, which is critical for practical missions. The stability of the overall closed-loop system is proved by using Lyapunov theory. Finally, numerical examples for a given SFF scenario are presented to illustrate the performance of the controller.     

基于经验模态分解的有限阵元宽带自适应阵列DBF方法

针对有限阵元条件下宽带自适应阵列自由度不够和抗干扰性能下降的问题,提出一种基于经验模态分解(Empirical mode decomposition,EMD)的宽带自适应阵列数字波束形成(Digital beamforming,DBF)方法。该方法首先对阵元接收的快拍数据进行EMD处理,然后对各个模态函数矩阵应用线性约束最小方差(Linearlyconstrained minimum variance,LCMV)波束形成算法求解自适应权矢量,最后对信号进行重构。与传统的基于快速傅里叶变换(Fast Fourier transform,FFT)子带自适应阵列方法相比,该方法具有以下优势:适用于阵元数目受限的宽带自适应阵列,无需事先指定模态函数划分的频段,可以提高阵列处理的自由度。仿真验证了所提方法的有效性。     

捕获非合作目标后航天器的自主稳定技术研究

捕获非合作目标后航天器质量特性发生突变,这大大地增加了系统的不确定性,控制不当容易导致失稳.为避免控制过程中航天器出现较大系统干扰问题,提出了先识别捕获后的系统质量特性,而后合理摆放非合作目标的自主稳定策略.首先,对航天器捕获过程和自主稳定策略进行了描述;其次,依据动量矩定理建立了非合作目标与航天器组合系统的数学模型,推导了非合作目标位置与质量特性之间的关系;然后,基于航天器数学模型和姿态测量信息,采用非线性规划方法对质量特性进行了辨识;最后,利用滑模变结构理论设计了非合作目标的控制回路,采用Lyapunov理论对系统的稳定性进行了分析.仿真结果表明:本文提出的自主配平策略响应快、精度高,适合在轨服务.     

钡钨空心阴极等离子体放电模式实验研究

主要通过实验的手段,系统研究了钡钨空心阴极的等离子体放电特性及其工作模式。实验中,使空心阴极工作在三极管构型下,调节相应的放电参数,详细分析钡钨空心阴极放电特性的变化规律、存在的放电模式及其转化规律。最后得到结论：钡钨空心阴极放电表现为羽毛状、亮斑状和弥漫状等3种典型的工作模式;不同放电模式可以用放电电流、放电电压及其振荡特性进行判定和区分;随着放电参数的变化,几种放电模式之间可以相互转化。