Experimental Study of Effects of Tail Wings on Submunition Aerodynamic Characteristics

Aimed at the needs of deceleration of submunitions dispensed from the ballistic missile, wind tunnel tests were performed on the submunitions with different tail wing sizes at the Mach number range from 0.7 to 3.0 and the angle of attack range from 0° to 14°. Experimental data about the variance of aerodynamic coefficients with the Mach number and angle of attack were obtained systemically. The effects of the tail wing sizes on the drag coefficients and the center of pressure coefficients were discussed. Analyzed results show the arc tail wings designed are beneficial to both the deceleration effect and static stability. These results are significant to the tail wing design and its applications to the submunitions deceleration..     

Wind Tunnel Experimental Investigation on the Aerodynamic Characteristics of the Multifin Rockets and Missiles

The transonic-supersonic wind tunnel experiment on the aerodynamics of the rockets and missiles that have four, six, eight flat or wrap-around fins is introduced. The experimental results show, while M∞〈2.0, with the increase of the fins＇number, the derivative of lift coefficient is increasing, the pressure center is shifting backwards, and the longitudinal static stability is augmenting. On the contrary, while the Mach number exceeds a certain supersonic value, the aerodynamic effectiveness of the eight-fin missiles would be lower than that of the six-fin missiles. For the low speed short-range missiles, by adopting six, eight or ten flat fins configuration, the lift effectiveness can be greatly increased, the pressure center can be shifted backwards, the static and dynamic stability can be obviously enhanced. For the high speed long-range large rockets and missiles launched from multi-tube launcher, the configuration adopting more than six fins can not be useful for increasing the stability but would make the rolling rate instable during the flight.     

前掠翼鸭式布局中鸭翼的气动特性

本文根据低速风洞所取得的测力、油流观察及旋涡测量结果,研究了前掠翼鸭式布局的鸭翼平面形状及其位置对气动性能影响的机理。研究表明,前掠翼布局大迎角气动性能的提高取决于鸭翼、主翼前缘涡的相对位置及其相互控制,也就是它们间的相互干扰。文中根据前掠及后掠鸭翼与主翼组合的实验结果,提出了采用鸭式布局时鸭翼应具有的平面形状及合适的位置选择范围。文中还对双前掠翼布局提出了一些看法。解释了加鸭翼后精侧气动性能出现反常变化的原因。     

Decoupling of BTT Missile Using Rolling Actuator

In order to reduce the coupling between pitch, yaw and roll channels of the bank -to-turn (BTT) missile caused due to missile body roll. A new structure actuat or for reducing the coupling of BTT missiles is studied. The new structure actua tor can roll independently along the longitudinal axis of the missile. The actua tor instead of airframe needs to steer when controlling BTT missile roll. So the rolling speed of main airframe and thus the coupling of missile introduced by a irframe rolling are reduced. ...     

长扁圆形烟囱风致振动风洞模拟试验研究

由于长扁圆形烟囱外形特殊,风荷载规范中没有其体型系数。为了确定长扁圆形烟囱的体型系数,作者借助风洞试验方法。本文主要阐述了长扁圆形烟囱气动弹性风洞试验情况：试验模型采用完全弹性模型,主要考虑了几何相似、动力相似、来流条件相似等几个主要的相似性条件,用热线风速计测量风速,用激光测振仪测量烟囱振动速度和位移,实测了烟囱根部的应变以及横风向风振情况,此结果可用于推求烟囱体型系数,可供此类烟囱设计时参考。     

整体式冲压超音速飞航导弹的自适应控制

采用导弹总体、气动、动力、控制和弹道一体化设计方法，研究了超音速整体式冲压发动机飞航导弹的控制问题。引入了自适应控制规律，利用该规律，可全面满足发射高度在大范围内变化时的所有战术技术要求．     

正、余弦指令控制方式旋转导弹气动特性分析

为了研究正、余弦控制式鸭舵对旋转导弹气动特性的影响,在CFD软件中采用嵌套网格方法模拟导弹的旋转和鸭舵的偏转。在与风洞试验结果进行对比,验证了数值模拟准确性基础之上,对不同转速、迎角、马赫数下正、余弦控制方式旋转导弹的气动特性进行数值模拟,得出如下结论:当采用相同最大舵偏角时,导弹进行正、余弦控制时其法向力系数要比静态条件下小,其侧向力系数和偏航力矩系数要比静态条件下大;导弹进行正、余弦控制时的偏航力矩系数大小要比不控时小;转速的变化对全弹法向力、侧向力特性以及鸭舵提供的法向力影响相对较小;亚声速条件下导弹的侧向力系数和偏航力矩系数数值比超声速条件下大;导弹做锥进运动时,合成迎角Г的变化对周期平均升力系数和侧向力系数影响较小,Г的变大会使周期平均偏航力系数、周期平均阻力系数数值变大;旋转效应是正、余弦控制方式旋转导弹产生侧向力的原因,并且鸭舵、尾翼产生的侧向力占主导地位。     

高速线材生产吐丝尾部控制

通过高速高速线材生产过程中吐丝尾部的控制,解决尾部"乱丝"的问题。     

炮射导弹反武装直升机可行性仿真研究

研究通过炮射反坦克导弹赋予坦克有限反武装直升机能力的可行性 .建立了一种炮射导弹与武装直升机对抗的仿真模型 ,并在各种情况下进行了系统仿真与导弹控制系统参数优化 .经参数优化的炮射导弹在给定的武装直升机各种航迹下 ,均可直接命中 ,脱靶量均小于 1m ,最大过载不超过可用过载 .仿真结果表明炮射导弹是坦克对抗武装直升机的一种可行的选择 .     

喇叭型隧道入口的空气动力学特性的试验研究

为了研究高速列车进入隧道时在隧道内所产生的压力波和向外辐射出去的微压波的规律,开发了一套以压缩空气作为动力来驱动列车模型的缩尺模型试验装置。通过模型试验系统对高速列车突入带喇叭型入口隧道产生的复杂压力场进行模拟,通过分析模型试验结果中的压力及压力梯度曲线所表现的规律,对喇叭型入口削减隧道入口处的最大压力和最大梯度值的效果进行了研究,结果表明:喇叭型隧道入口能够有效地减小压缩波和微压波的影响,其削减效果依赖于入口长度。     

激光驾束反坦克导弹控制系统优化设计

在尽可能短的时间内设计出激光驾束反坦克导弹的控制系统 .采用最优化技术 ,通过建立被优化系统的数学模型和选择合适的最优化求解方法 ,利用计算机的高速计算能力和逻辑能力寻找最佳控制器 .仿真结果表明 ,设计出的该型导弹控制系统具有良好的动静态性能 ,很好地满足了战技要求 ,证明最优化技术和计算机技术的结合可以在短时间内设计出性能优良的控制系统 .     

中厚板轧机的板形控制

国内普通四辊中板轧机板形控制手段较少,控制质量精度不高。针对某中板改造项目,分析各种板形控制手段,建立适用于中厚板在线应用的板形和板凸度控制模型。根据这些模型,在考虑弯辊等多种板形控制手段的情况下,给出了适合现场应用的负荷分配流程图。应用结果表明：合理的规程分配、适当的弯辊力设定、良好的辊形和辊凸度配合,能使中厚板的板形得到最佳控制。     

新型IDC棒材连轧控制模式初探

针对引进的IDC控制系统在棒材连轧系统中的运用,通过与常规微张力控制等在控制原理、控制方法、控制效果方面做比较。描述了IDC这种新型控制手段的优缺点。     

无横滚控制导弹目标记忆

对无横滚控制导弹,目标方位会随着随机性横滚很难“记忆”,本文讨论一个集角度传感,同步信号产生及转子跟踪为一体的三自由度角度陀螺记忆装置的技术可能性。     

反辐射导弹惯性制导段拉制参数的优化

本文采用变步长加速法对反辐射导弹惯性制导段的控制参数进行了优化,并针对变步长加速法收敛慢的问题提出了一种改进方法,取得了满意的结果。     

堆石区填筑料碾压试验质量控制在除险加固水库工程中的应用

通过不同组合参数的碾压试验,从而合理地选择施工压实参数,也为设计提供可靠的试验成果,并从堆石料铺筑、碾压等方面总结出碾压试验质量控制方法,指导堆石区填筑料施工质量控制,提出了“双控”相结合的质量控制手段,也作为工程质量监督与检测、工程质量评定的依据之一。     

热带轧机全数字电控改造

介绍攀钢西昌分公司带钢分厂热带轧机全数字系统 ,电控系统的改造过程     

Short Stroke Control with Gaussian Curve and PSO Algorithm in Plate Rolling Process

The precision width control is vital for product quality and production economy in plate width control process, so short stroke control method was used in plate rolling by opening or closing edger gap so as to avoid head end necking. Head end necking on different broadening ratio was analyzed, and sections of different elongations at edger roiling was calculated; based on the law of volume constancy, the adjustment functions were described by parabolic functions. Control curves were developed with three Gaussian curves by means of additional combining; SSC control curve was changed with different weights of those curves, w1 effect one-third of SSC length, w2 effect two-third of SSC length, w3 effect all three parts of SSC length. In order to adjust the amount of weights for precise quantification, PSO algorithm was used to build sufficiency function so as to obtain best rectangular degree by global optimization. Practical applications showed that the method proposed is available to improve the product rolling yields by 1.0% -2. 0% and worthy to apply to plate rolling.     

ZR轧机液压压下油源

分析森吉米尔轧机主机液压压下各机构的特殊工艺特点,提出了油源的构成方案及主要参数的确定原则,同时侧重探讨：1．蓄能器参数的确定;2．防止恒压变量泵压力设定点偏移的措施。