基于WVD的防空雷达直升机信号特征分析

基于直升机目标旋转部件的调制模型，本文针对防空雷达提出了分析直升机信号特征的一种新方法——WVD法，并对直升机目标旋转部件调制回波信号在不同噪声情况下加以仿真分析，结果表明：用WVD分析雷达回波中直升机信号特征是一种非常有效的方法。     

悬停直升机的雷达探测技术

首先对直升机旋翼的雷达回波进行建模与分析,在此基础上分析了雷达探测悬停直升机的可能性,提出了一种适用于所有直升机类型的多扫描周期积累检测系统方案,讨论了可能影响其检测性能的因素.     

全站仪在直升机悬停测试中的应用

介绍了如何将改造后的全站仪应用于直升机悬停性能测试的方法。经真实飞行试验检验，该方法理论严密，方案合理，改装简单，操作方便，成本低廉。较之原始的摄影测量法有无法替代的优点。     

Lowering the erosion wear of long blades of the last stages by optimum hanging

Problems of optimum hanging of long rotor blades of the last stages of steam turbines are considered. Causes of nonuniform erosion wear of the inlet edges connected with inaccurate location of holes for the external damper coupling on the chord of the profile are determined. Methods for optimizing the hanging of blades for raising the reliability of the last stages are suggested. Main results of hanging performed with the help of a specially developed “LIBRA” soft hardware are presented. __________ Translated from élektricheskie Stantsii, No. 11, November 2006, pp. 36–41.     

FINITE ELEMENT ANALYSIS OF THE FLOW INDUCED BY ROTATING BLADES IN AN INCOMPRESSIBLE VISCOUS FLUID

Aerodynamic loads on a multi-bladed helicopter rotor in hovering flight were calculated by solving the three-dimensional incompressible Navier-Stokes equations. The rotor wake effects were accounted by the correction of local geometric angle of attack according to a free-wake modeling in addition to an empirical modification for the tip flow effect. The validity and efficiency of the present method were verified by the comparisons between numerical results and experimental data.     

直升机发动机超转实验系统的测频设计

本文采用FPGA技术测量直升机发动机转速,介绍了双通道等精度测频的原理,设计了信号调理电路,并在FPGA上设计了Verilog代码,在实际应用中测量直升机发动机转速表现了良好的系统实时性能。     

65Mn钢CCT曲线及圆锯片淬火工艺

用全自动相变测定仪测定了圆锯片常用６５Ｍｎ钢的连续冷却转为曲线，研究了不同连续冷却速度下得到的组织，为合理制订圆锯片的淬火工艺提供了依据，得到了最佳淬火工艺曲线。     

导叶叶片数对多相混输泵内能量损失的影响北大核心

为了提高混输泵的做功性能,降低能量损失,在不同导叶叶片数下,对多相混输泵的外特性及其内部能量损失进行分析。结果表明:当导叶叶片数为10时混输泵的外特性明显比导叶叶片数为7和8时更差,且最高效率偏向小流量工况;不同流量下,导叶叶片数为8时混输泵叶轮内的收缩损失和湍流耗散损失最小,而导叶叶片数对导叶进口的冲击损失影响很小,可不考虑其影响;在所选3组导叶叶片数下,当导叶叶片数等于8时混输泵的性能最优且流道内能量损失最小。     

主旋翼升力和机身姿态受限的模型直升机非线性控制（英文）

A nonlinear control is proposed for trajectory tracking of a 6-DOF model-scaled helicopter with constraints on main rotor thrust and fuselage attitude. In the procedure of control design, the mathematical model of helicopter is simplified into three subsystems: altitude subsystem, longitudinal-lateral subsystem and attitude subsystem. The proposed control is developed by combining the sub-controls for the corresponding subsystems. The sub-controls for altitude subsystem and longitudinal-lateral subsystem are designed with hyperbolic tangent functions to satisfy the constraints; the sub-control for attitude subsystem is based on backstepping technique such that fuselage attitude tracks the virtual control for longitudinallateral subsystem. It is proved theoretically that tracking errors are ultimately bounded, and control constraints are satisfied.Performances of the proposed controller are demonstrated by simulation results.