Modeling and experiment of grinding wheel axial profiles based on gear hobs

Hobbing is one of the crucial gear manufacturing processes with high precision and high efficiency. In order to improve the accuracy of hobbing and hob relief grinding, more precise grinding wheels are demanded for relief grinding in the production of gear hobs. In this paper, a new and accurate mathematical method for calculating the axial profile of grinding wheel based on the corresponding gear hob to be ground is proposed. Considering that most researches have been conducted to focus on the optimization of hob geometric feature and only can be applied to a specific type of hand of helix and rake angle of gear hobs. The method in this paper can be served as a general algorithm for generating axial profile of grinding wheels on the basis of the spatial envelope theory, the principle of coordinate system transformation, and studies on normal profile of single-tooth. The accuracy of grinding hobs is based on applying the approach in practical manufacturing. Taking two typical different kinds of pre-grinding gear hobs as examples for calculation and experiment, the results of tooth profile errors strengthen the position that the validity and feasibility of this method, it can be employed for gear hob design and grinding processing.     

Influence of leading edge with real manufacturing error on aerodynamic performance of high subsonic compressor cascades

To investigate the influence of real leading-edge manufacturing error on aerodynamic performance of high subsonic compressor blades, a family of leading-edge manufacturing error data were obtained from measured compressor cascades. Considering the limited samples, the leading-edge angle and leading-edge radius distribution forms were evaluated by Shapiro-Wilk test and quantile–quantile plot. Their statistical characteristics provided can be introduced to later related researches. The parameterization design method B-spline and Bezier are adopted to create geometry models with manufacturing error based on leading-edge angle and leading-edge radius. The influence of real manufacturing error is quantified and analyzed by self-developed non-intrusive polynomial chaos and Sobol’ indices. The mechanism of leading-edge manufacturing error on aerodynamic performance is discussed. The results show that the total pressure loss coefficient is sensitive to the leading-edge manufacturing error compared with the static pressure ratio, especially at high incidence. Specifically, manufacturing error of the leading edge will influence the local flow acceleration and subsequently cause fluctuation of the downstream flow. The aerodynamic performance is sensitive to the manufacturing error of leading-edge radius at the design and negative incidences, while it is sensitive to the manufacturing error of leading-edge angle under the operation conditions with high incidences.     

FC-AE-1553网络传输性能评价

为了提高航天航空网络传输性能,提出一种通用的FC-AE-1553网络传输效率计算方法并研制高性能FC-AE-1553节点卡.首先,对FC-AE-1553网络的消息传输过程进行详细分析,分析信息类型,给出传输帧的格式建议,通过分析FC-AE-1553协议中各类消息传输的时间参数,结合FC标准中对通信时间的要求,提出FC-AE-1553网络交换中各种消息类型的通信时间计算公式.然后, 针对无差错传输和有差错传输两种情况,给出了网络传输效率的计算方法.最后,通过仿真分析数据帧净荷长度、节点处理时间、交换中序列数量、传输误码率、丢包率等参数对FC-AE-1553网络传输效率的影响,给出了网络优化设计的建议.依托某航天工程任务,研制了基于XC5VFX100T和MPC8536E的FC-AE-1553节点卡.实验结果表明:丢包对传输效率的影响可忽略;数据帧净荷为2 048 B,数据帧数量为16时,传输效率可达到77.2%.      

等效原理算法在不同等效面下的误差分析

等效原理算法(EPA)借鉴了区域分解的思想,并基于惠更斯等效原理实现了对大规模散射问题的计算.本文对EPA中的等效原理算子(EPO)进行了误差分析,选取了立方体、球体和进行了光滑处理的立方体等作为等效面寻找误差来源,并提出了误差改进的建议.根据计算结果,等效磁流在等效面上描述的误差一般集中在等效面表面的几何不连续处,且主要受等效面上的法向向量不连续性和基函数的选取的影响.故在选取等效面时应尽量考虑使用平滑的等效面,而不是直接使用立方体等效面.      

一种星间设备系统偏差的标定方法

针对Ka波段测距体制中星间测距设备系统偏差标定困难从而影响自主导航精度的问题,提出用星地无线电双向时间比对的方法标定星间设备系统偏差。通过两条星地双向链路并在这两颗卫星间建立一条星间双向链路进行标定。结果表明：该方法能够标定星间设备系统偏差,其RMS优于1ns,从而起到提高星间时间同步精度的目的。     

姿态角幅值约束下的太阳帆Lissajous轨道保持控制

太阳帆航天器以两姿态角作为轨道控制输入时, 其轨道动力学方程具有非仿射非线性特性. 通过人工平动点处线性化获得的线性系统可完成太阳帆航天器轨道保持控制器的分析与设计. 由于线性近似模型为有误差模型, 存在近似有效范围约束, 表现为轨道高度约束和姿态角幅值约束. 本文研究了姿态角幅值约束对线性近似模型有效性的影响, 通过计算给出满足近似误差要求的姿态角幅值约束. 当控制输入存在幅值约束时, 控制器轨道修正能力受到束缚. 通过研究姿态角幅值约束下的最大允许入轨误差, 设计了最大允许入轨误差下线性二次型调节器(LQR)用于轨道保持控制, 并将控制器应用于太阳帆日地三体系统非线性模型中, 实现了日地人工L₁点Lissajous轨道最大允许入轨误差的控制收敛和良好精度下的轨道保持控制.      

基于三维最小二乘方法的空间直线度误差评定

空间直线度误差是评定机械产品精度的一项重要指标,实际工程中对空间直线度误差评定算法的精度要求越来越高.为了准确评定空间直线度误差,参照国家标准(GB/T 11336—2004),采用三维最小二乘方法建立了空间直线拟合的数学模型,并给出了该数学模型的精确解.基于最小二乘拟合中线,采用空间投影、坐标变换和格点法求得最小二乘中线包容圆柱面直径.采用数值算例验证了新方法的有效性.提出的空间直线度误差评定方法精度高、鲁棒性好且易于编程实现.     

基于LS-DYNA滚动轴承使役可靠度计算方法

利用软件LS-DYNA对滚动轴承使役过程进行了动态有限元计算,基于响应面法（RSM）建立6408滚动轴承输入参数与输出响应的函数关系方程,设定各类随机误差分布,利用矩阵试验法确定抽样点在输入变量抽样空间的位置,进行一系列确定性拟合试验.每次试验借助LS-DYNA进行精确求解,运用求解数据对方程进行最小二乘法回归分析确定方程的组成项及系数.最后利用函数关系方程计算轴承任意时刻的使役可靠度.结果表明:计算得出该轴承在0.020008s时的使役可靠度为97.062%.      

航母运动对舰载飞机着舰安全性的影响

总结了舰载飞机的着舰安全性分类等级,研究了航母的航行运动以及随海浪的摇晃和振荡运动对舰载机着舰安全性的影响规律,并给出了与舰载机进舰速度适配的最优航母航行速度.研究结果表明:由于航母的航行方向与舰载机的进舰方向存在一定的夹角,驾驶员在进舰过程中必须协调操纵副翼和方向舵才能保证舰载机安全准确地着舰;航母航行速度越大,驾驶员操纵量越大,着舰偏差也越大.海况越恶劣,着舰信号指挥官对航母运动的预报和补偿效果越差,着舰失败概率越大.因此,为保证舰载机的着舰安全,必须选择合适的航母航行速度,同时应尽量选择在平稳的海况下进舰着舰.      

基于自相关及相位差法的高精度频率估计算法

为提高高斯白噪声背景中正弦信号的频率估计精度,对基于自相关运算的频率估计算法的相关长度m进行了推导,得到了m的优化值与信噪比的关系式.当信噪比较高时,m的最优值为N/3(N为信号采样点数);信噪比较低时,m的最优值为N/2.通过对自相关法及分段FFT(Fast Fourier Transforms)相位差法特性的分析,提出了一种性能更优的频率估计综合算法. Monte Carlo仿真实验表明:新算法吸收了两种算法的优点,克服了其不足,在更大的信噪比范围内具有较高的频率估计精度,且计算量也较小.