重复使用天地往返运载器飞行弹道计算研究

介绍了应用于吸气式重复使用天地往返运载器的RBCC动力,根据动力学和运动学方程及地球物理方程式,利用数值积分方法,计算并比较了采用RBCC动力水平起飞、垂直起飞及纯火箭动力垂直起飞的运载器飞行弹道。计算结果表明,相比于纯火箭动力,RBCC动力有效地降低了运载器的燃料消耗量,但热环境明显要恶劣。     

YAG激光焊接钛合金TA15熔池特征

利用高速摄像,对YAG激光焊接钛合金TA15时的熔池特征以及动态过程进行了深入研究,结果表明,整个熔池可以分为3部分:(a)金属蒸气/等离子体区,它是一个以1kHz以上频率波动的过程;(b)温度超过2 000K的液态熔池区域;(c)半固态熔池区域,这是熔池的主要部分,其温度虽有一定的梯度,但基本保持在熔点温度.     

Prediction of combined cycle fatigue life of TC11 alloy based on modified nonlinear cumulative damage model

The nonlinear cumulative damage model is modified to have high prediction accuracy when the high-low cycle stress frequency ratio m is large (m ≥ 500). The low cycle fatigue (LCF) tests, high cycle fatigue (HCF) tests and combined high and low cycle fatigue (CCF) tests of TC11 titanium alloy were carried out, and the influencing factors of CCF life were analysed. The CCF life declines with the decrease of the ratio of high-low cycle stress frequency m. Both linear and nonlinear cumulative damage models are used to predict the CCF life. The CCF life prediction error of the linear cumulative damage model is great and the predictions tend to be overestimated, which is dangerous for engineering application. The accuracy is relatively high when the high-low cycle stress frequency ratio m ≤ 500. The accuracy of nonlinear cumulative damage model is higher than that of linear model when the high-low cycle stress frequency ratio m ≥ 500. Based on the relationship between high cycle average stress σ_major and material yield limit σ_p,0.2, a correction term is added to the nonlinear cumulative damage model and verified, which made the modified model more accurate when m ≥ 500.     

不同冲击角度外物损伤对TC4钛合金高循环疲劳强度的影响

基于空气炮冲击试验装置在不同冲击角度下进行了TC4钛合金平板试件的外物损伤模拟试验,采用逐级加载试验方法测试获得了光滑和冲击损伤试件的高循环疲劳(high cycle fatigue,HCF)强度,研究了冲击角度、冲击位置以及冲击损伤宏观几何尺寸与HCF强度的关系.结果表明:不同冲击角度下的损伤对HCF强度的影响程度不同.冲击损伤在试件边缘时,30°冲击使试件HCF强度的下降幅度最大;冲击损伤在试件表面时,60°冲击使试件HCF强度的下降幅度最大.试件边缘产生的缺口使HCF强度的下降幅度一般大于试件表面产生弹坑的影响.但在60°冲击时,冲击缺口损伤的影响要小于冲击弹坑损伤的影响.冲击损伤宏观几何尺寸一定程度上可以表征损伤试件HCF强度下降的严重程度.      

补燃循环发动机推力调节过程建模与仿真研究

以补燃循环液氧煤油发动机为研究对象,对其推力调节特性进行了研究.建立了描述补燃循环发动机瞬变过程的数学模型,提出了求解供应系统管路内液体瞬变流控制方程的Chebyshev伪谱方法,应用该模型对补燃循环液氧煤油发动机的推力调节特性进行了仿真计算,并将计算结果与试验数据进行了对比分析,验证了模型和算法的合理性.研究结果表明：对于所研究的补燃循环发动机系统而言,通过调节发生器中较少组元的流量,改变涡轮泵的功率,可很好地实现调节推力的目的,且该推力调节系统具有良好的动态调节品质和很强的抗干扰性.     

Evolution of Dst index,cosmic rays and global temperature during solar cycles 20–23

We have studied conditions in interplanetary space, which can have an influence on galactic cosmic ray (CR) and climate change. In this connection the solar wind and interplanetary magnetic field parameters and cosmic ray variations have been compared with geomagnetic activity represented by the equatorial Dst index from the beginning 1965 to the end of 2012. Dst index is commonly used as the solar wind–magnetosphere–ionosphere interaction characteristic. The important drivers in interplanetary medium which have effect on cosmic rays as CMEs (coronal mass ejections) and CIRs (corotating interaction regions) undergo very strong changes during their propagation to the Earth. Because of this CMEs, coronal holes and the solar spot numbers (SSN) do not adequately reflect peculiarities concerned with the solar wind arrival to 1 AU. Therefore, the geomagnetic indices have some inestimable advantage as continuous series other the irregular solar wind measurements. We have compared the yearly average variations of Dst index and the solar wind parameters with cosmic ray data from Moscow, Climax, and Haleakala neutron monitors during the solar cycles 20–23. The descending phases of these solar cycles (CSs) had the long-lasting solar wind high speed streams occurred frequently and were the primary contributors to the recurrent Dst variations. They also had effects on cosmic rays variations. We show that long-term Dst variations in these solar cycles were correlated with the cosmic ray count rate and can be used for study of CR variations. Global temperature variations in connection with evolution of Dst index and CR variations is discussed.     

RBCC-RKT两级入轨飞行器飞行轨迹优化方法

针对火箭基组合循环（RBCC）发动机比冲和推进剂质量流量随飞行条件改变而不断变化的特点,提出了通过增广拉格朗日遗传算法优化飞行器飞行轨迹的方法,在飞行器气动参数和发动机比冲已知、最大飞行动压给定等条件下,进行了火箭基组合循环发动机-液体火箭（RKT）发动机推进的水平起飞两级入轨（TSTO）飞行器飞行轨迹优化计算。研究结果表明：在飞行俯仰角和发动机推进剂质量流量变化范围已知的情况下,利用该方法能够在较好满足给定约束条件的情况下,优化得到飞行俯仰角和发动机流量随时间的变化关系,为飞行轨迹初步设计提供参考。     

一类含小参数微分方程鸭解的存在性

本文应用微分方程定性理论、 渐进分析方法、 隐函数定理以及不动点理论的方法研究一类单参数二维奇异摄动系统.给出了当系统的奇点在破坏点的小邻域时鸭解和鸭极限环存在的充分条件.证明了存在参数值a=a\-c(ε),使得对a\-c(ε)小邻域中的所有参数a, 系统存在鸭极限环.并给出了鸭解和鸭极限环的渐近估计式以及鸭极限环随参数变化的规律.本文推广了文献[1]和文献[2]的结果.     

全流量补燃循环液氧/甲烷发动机系统分析

对全流量补燃循环液氧,甲烷发动机系统进行了分析研究。确定了初步的发动机系统方案,对发动机的系统参数、结构质量进行了分析计算。     

低周疲劳寿命的试验研究

用GH33A钢制成圆柱形棒、鼓形平板和带中心孔平板3种试件进行拉-拉低循环试验。试验测定的疲劳寿命与采用局部应力-应变法预测的寿命结果符合较好。随着应力集中系数的增加,试验寿命与预测寿命之比有所增大。实验中,一次超载造成较大的寿命降低。由于较厚板缺口处存在双向应力-应变状态,较厚试件的疲劳寿命比较薄平板的寿命长。