Numerical investigation of the impact of asymmetric fuel injection on shock train characteristics

Numerical simulations are carried out to investigate the impact of asymmetric fuel injection on shock train characteristics using the commercial-code FLUENT. The asymmetry of fuel injection is examined by changing the fuel flow rates of the upper and lower wall fuel injectors. The numerical approach solves the two-dimensional Reynolds-averaged Navier–Stokes (RANS) equations, supplemented with a k-ω model of turbulence. As a result, different ways of fuel injections will always lead to shock train transitions, with the variations of shock train structure, strength and leading edge position. For symmetric fuel injection, the flowfield of the isolator is quite asymmetric with the boundary layer of the upper wall side developing much stronger than that of the lower wall, which is due to the heterogeneity of the incoming flow. Regarding to asymmetric fuel injection with more of lower wall side, though the pressures in the combustor are nearly the same, the first shock of the shock train converts between ‘Distinct symmetric X type shock’ and ‘Obscure and weaker asymmetric shock’ and the shock train leading edge moves upstream with the increase of the asymmetry level. With regard to asymmetric fuel injection with more of upper wall side, ‘incomplete asymmetric X type shock’ occurs and the shock train structures keep nearly the same with low level of fuel injection asymmetry. Unexpected results like unstart will happen when increasing the level of fuel injection asymmetry. And the isolator will come back to normal state by decreasing the differential of upper and lower wall sides fuel injections.     

Experimental study of a flush wall scramjet combustor equipped with strut/wall fuel injection

In this study a flush wall scramjet combustor is tested in a supersonic incoming air flow with the Mach number of 3 which is generated by an air vitiation heater producing the stagnation temperature of 1505 K. Using liquid kerosene as the fuel, the flame is stabilized by means of a centrally mounted O₂ pilot strut after being ignited by a plasma torch. During experimental measurements, the fuel is injected with a constant equivalence ratio of 0.8 according to specified strut/wall injection ratios, i.e., a portion of the fuel amount is injected from the strut while the rest is injected from the wall. The strut and wall injectors are arranged at the same axial position. The combustion performance and wall temperature gradients are evaluated with various fuel feeding ratios between the wall and the strut. Experimental results show, when the equivalence ratio is constant and the axial injection position is fixed, the combustion characteristics vary significantly with the strut/wall fuel feeding ratio, especially when this ratio is close to its lowest and highest limits. Among the four fuel feeding ratios examined, the strut only injection mode and the average distributed strut/wall injection mode show the best combustion performance. However, the strut/wall injection mode produces a smaller wall temperature gradient compared to the strut only injection mode, which is due to the significant film cooling effect caused by the wall injected liquid kerosene.     

求解结构可靠度的直接积分方法

针对一类极限状态函数为随机变量的和差积商的有理函数形式,提出了求解结构可靠度的直接积分方法。给出了一些基本函数的概率密度函数。通过定义中间变量将这类特殊的极限状态函数转化为基本函数的函数,进而求出中间变量的概率密度函数,最终求出极限状态函数的概率密度函数.用积分的方法求出结构可靠度。该方法不用考虑随机变量服从何种概率分布,且计算结果为精确解。     

单音干扰下扩频测控信号伪码跟踪性能研究

扩频测控信号的伪码跟踪性能直接关系到测控系统的测距精度。以伪码跟踪环中鉴相曲线平衡点的过零偏移为研究对象,推导了音频干扰条件下扩频测控信号伪码跟踪的干扰最大误差;并针对干扰最大误差需考虑具体鉴相算法的特点,提出基于相关曲线主瓣的二阶中心矩扩展因子的性能评价方法。该方法利用伪码相关曲线主瓣在干扰前后的畸变情况,反映干扰对伪码跟踪性能的影响。仿真分析表明,干扰最大误差的理论及仿真结果和二阶中心矩扩展因子所得结论一致,从而验证了干扰最大误差理论的正确性以及所提性能指标的有效性。     

基于多级维纳滤波器的树型WSN分布式线性约束最小方差波束形成方法

为减少树型无线传感器网络(Wireless sensor network,WSN)中分布式线性约束最小方差(Linearly constrained minimum variance,LCMV)波束形成器的计算量,将多级分解技术用于WSN分布式波束形成技术中,提出基于多级维纳滤波器(Multistage Wiener filter,MSWF)的分布式LCMV波束形成器方法。该方法通过有效引入MSWF技术避免本地协方差矩阵估计及求逆运算,能以更少的计算量获得分布式LCMV波束形成器相同的输出性能,说明新方法继承了MSWF和分布式LCMV波束形成器的优点。计算机仿真结果验证了算法的优良性能。     

空气节流对煤油燃料超燃燃烧室燃烧性能影响

采用非定常数值模拟方法研究了空气节流对煤油燃料超燃冲压发动机燃烧性能的影响,并研究了节流流量和节流撤去时间对节流效果的影响。在发动机入口马赫数2.0、静温656.5K、静压0.125MPa的条件下,无空气节流时发动机下壁面稳焰失败,壁面压力较低;有空气节流时发动机下壁面燃料稳定燃烧,壁面压力较高。空气节流可以有效地提高发动机的推力性能,可以改变发动机的燃烧模态。随着节流流量和节流撤去时间的增加,燃烧越来越剧烈,壁面压力逐渐升高,可能影响进气道的起动。节流可能促使流场产生振荡现象,通过改变节流流量也可以消除振荡现象。     

构建有理函数逼近式的一种新方法

为超越函数提出一种构建有理函数逼近式的方法.与Pad′e法不同,这种新方法利用超越函数的值与其逼近式的值相互逼近这个条件,较少地依赖超越函数的泰勒展开式.以两个超越函数为例,叙述了用这种方法构建的逼近式与Pad′e逼近式的不同.用这种方法构建了一系列适合在单片机上运行的超越函数的有理函数逼近式.     

陀螺经纬仪在北向基准检测中的应用研究

利用高端精密仪表——陀螺经纬仪,确定与检测棱镜、转台、地标北向基准准确度。在说明了陀螺经纬仪寻北原理、使用方法的基础上,描述了棱镜、转台、地标等检测方法和技术要求。     

火星探测器进入阶段稳定性分析

文章针对＂火星探路者＂,对火星探测器在进入火星大气减速过程中的运动稳定性问题进行了研究,分析了质心位置、进入条件、大气参数等因素对火星探测器运动稳定性的影响。分析结果表明,在马赫数大于1.2时,探测器处于一个比较稳定的状态。     

不确定广义时滞系统的参数依赖指数镇定

研究了具有凸多面体不确定广义时滞系统的时滞相关型指数镇定问题。首先,利用Lyapunov稳定性定理和线性矩阵不等式工具,给出了标称的广义时滞系统正则、无脉冲和指数稳定的时滞相关型充分条件。在此基础上,采用参数依赖Lyapunov函数方法,设计了使闭环系统正则、无脉冲和指数稳定的时滞相关型状态反馈控制器,并给出了相应控制器的显式表示。