剪切理论与经典理论的对称角铺设方板弯曲解析研究

分别采用基于Reddy简化高阶剪切理论、一阶剪切理论和经典理论的对称角铺设矩形板横向弯曲一般解析解,计算分析四边固支对称角铺设层合方板在均布载荷下弯曲问题,讨论了横向剪切、铺设层数、铺设角、板厚对层合板内力矩和挠度的影响,概略分析了不同理论适用范围。引入了横向剪切效应参数,以反映横向剪切影响程度。文中给出数值算例,计算表明横向剪切效应与弯扭耦合效应存在交联。     

神经网络在发动机自适应建模中的应用研究

提出了一种新的基于神经网络的发动机自适应实时模型的建模方法。建模的思想是认为发动机的任何非额定工作都将导致其输出参数的变化,因而可以把这些参数偏离正常工作参数值的变化量,也就是输出偏离量,用来表征发动机的非额定工作情况。把它们作为增广的状态变量,设计卡尔曼滤波器对其进行最优估计,然后用这些输出偏离量的估计值,通过由BP神经网络训练出来的可测输出偏离量与未测输出偏离量的映射关系来校正机载发动机模型的计算输出,使之与真实发动机的输出一致,从而使实时机载模型获得对任何发动机非额定工况的自适应能力。      

用CPLD实现FIR数字滤波器的设计

针对在CPLD中实现FIR滤波器的关键一乘法运算的高效实现进行了研究，给出了将乘法化为查表的DA算法，并采用这一算法设计了FIR滤波器。其实现的滤波器的性能优于用DSP和传统方法实现FIR滤波。     

碳纤维复合材料方孔加工工艺

针对碳纤维复合材料大深度不贯通方孔提出了一种专用的加工工艺.通过试验对比,分析了磨削力、加工质量、刀具磨损、加工效率等因素.结果表明,先钻中心孔后磨削的方式适合于该方孔的加工.并对试验中出现的问题进行了工艺优化,初步解决了碳纤维复合材料大深度不贯通方孔的加工问题.     

一种航空噪声背景下的语音增强方法

依据航空噪声的频谱特性,提出将自适应滤波算法与改进的谱减法相级联的方法来增强语音。在强航空噪声背景下,处理后的语音不仅信噪比得到了很大提高,而且在有效抑制背景噪声和音乐噪声的同时,其清晰度和可懂度也得到了很大的改善。     

内重力波传播的3维传输函数模式研究

在考虑背景风场及大气耗散的条件下,建立了3维内重力波传输函数数值模式.分析了300 km高度3维传输函数在频率波数域的特性,并以近地面单位脉冲点源为激发源,得到了内重力波在3维空间中的时空分布.讨论了不同时空尺度地面方波源激发的内重力波在电离层高度的能量分布特征.结果表明,(1)对内重力波而言,背景大气相当于一个带通滤波器,只有波动周期和波长分别在15～30 min和200～400 km之间的重力波扰动最容易上传到300km高度;(2)在背景风场的作用下水平面上以同心圆扩散的波阵面以及垂直方向上成漏斗状的波阵面发生了变形,并且逆风方向比顺风方向更有利于声重力波由对流层向电离层高度传播;(3)300km高度对时间尺度和空间尺度分别在20～30 min和150～250 km之间的地面方波源响应的总能量最强.      

相控阵雷达长时跟踪波束调度与波形优化策略

针对相控阵雷达多目标跟踪波束调度和波形参数优化控制的问题，本文提出了一种基于马尔可夫决策过程（MDP）的相控阵雷达跟踪波束调度与波形参数优化策略，该方法以无迹卡尔曼滤波（UKF）算法为基础来估计目标的状态。首先将本文的序列决策问题建模为马尔可夫决策过程，定义了资源的效费比和长期回报率，然后与当前实际跟踪误差综合考虑作为MDP的回报函数，进而给出了调度的优化模型，最后将长时决策问题转化为动态规划算法结构进行求解，并且提出了一种并行混合遗传粒子群优化算法来求解各决策时刻的最优策略。仿真结果表明了长时策略的先进性以及寻优算法的优越性，与传统的短时策略相比，跟踪精度可提高11.17%。     

The attitude inversion method of geostationary satellites based on unscented particle filter

The attitude information of geostationary satellites is difficult to be obtained since they are presented in non-resolved images on the ground observation equipment in space object surveillance. In this paper, an attitude inversion method for geostationary satellite based on Unscented Particle Filter (UPF) and ground photometric data is presented. The inversion algorithm based on UPF is proposed aiming at the strong non-linear feature in the photometric data inversion for satellite attitude, which combines the advantage of Unscented Kalman Filter (UKF) and Particle Filter (PF). This update method improves the particle selection based on the idea of UKF to redesign the importance density function. Moreover, it uses the RMS-UKF to partially correct the prediction covariance matrix, which improves the applicability of the attitude inversion method in view of UKF and the particle degradation and dilution of the attitude inversion method based on PF. This paper describes the main principles and steps of algorithm in detail, correctness, accuracy, stability and applicability of the method are verified by simulation experiment and scaling experiment in the end. The results show that the proposed method can effectively solve the problem of particle degradation and depletion in the attitude inversion method on account of PF, and the problem that UKF is not suitable for the strong non-linear attitude inversion. However, the inversion accuracy is obviously superior to UKF and PF, in addition, in the case of the inversion with large attitude error that can inverse the attitude with small particles and high precision.     

In-plane corrugated cosine honeycomb for 1D morphing skin and its application on variable camber wing

A novel 0-Poisson’s ratio cosine honeycomb support structure of flexible skin is proposed. Mechanical model of the structure is analyzed with the energy method, finite element method (FEM) and experiments have been performed to validate the theoretical model. The in-plane characteristics of the cosine honeycomb are compared with accordion honeycomb through analytical models and experiments. Finally, the application of the cosine honeycomb on a variable camber wing is studied. Studies show that mechanical model agrees well with results of FEM and experiments. The transverse non-dimensional elastic modulus of the cosine honeycomb increases (decreases) when the wavelength or the wall width increases (decreases), or when the amplitude decreases (increases). Compared with accordion honeycomb, the transverse non-dimensional elastic modulus of the cosine honeycomb is smaller, which means the driving force is smaller and the power consumption is less during deformation. In addition, the cosine honeycomb can satisfy the deform- ing requirements of the variable camber wing.     

改进的平方根UKF在再入滑翔目标跟踪中的应用

针对临近空间高超声速再入滑翔目标跟踪问题，提出了一种基于新气动力模型的改进的平方根UKF滤波算法(ISR-UKF)。首先对气动力模型进行了变换。其次，在传统平方根UKF基础上，改用球形无迹变换来计算权系数以及sigma点；改进了平方根矩阵的分解方法；同时为解决矩阵求逆易出现奇异值使滤波失效的问题，提出在协方差矩阵更新中引入多重次稳定因子。最后将该算法分别与基于原气动力的ISR-UKF，基于新气动力的平方根UKF以及基于原气动力的平方根UKF进行仿真比较。仿真表明，该算法具有良好的滤波性能，而且能避免奇异值问题的出现，具有很好的可靠性。