D-Q方法求实系数高次代数方程的全部根

本文介绍了一种求实系数高次代数方程全部根的新方法。提出一种求根精度的新标准。     

Initiation characteristics of oblique detonation waves from a finite wedge under argon dilution

In this paper, the flow field characteristics of Oblique Detonation Waves (ODWs) induced by a finite wedge under argon dilution are studied by solving the Euler equations with a detailed chemical model of hydrogen and air. First, the effects of the expansion waves, argon concentration, geometric parameters, and Mach number on the ODW are discussed. The results show that the changes of these parameters may make the oblique detonation not be initiated. Then, the ODW initiation criterion of the finite wedge is summarized, as the characteristic length of the induction zone L_C and the characteristic length of the oblique wedge L_W meet the condition L_C/L_W < 1, the initiation of the ODW occurs; otherwise, it does not occur. What’s more, the Constant Volume Combustion (CVC) theory is applied to study the characteristic length of induction zone. It is found that CVC theory is more suitable for the “smooth transition” type of ODW flow field, the theoretical and numerical characteristic length in induction regions are in good agreement. This work is of great significance for the design of oblique detonation engines for hypersonic vehicles.     

Maximal admissible mode decision delay in terminal guidance

Mode decision-maker is a critical component in the logic-based Integrated Estimation and Guidance(IEG) system. For the best possible estimation and guidance performance, the mode decision delay of the mode decision-maker should be limited to a range as small as possible. This paper presents a numerical method for computing the maximal admissible mode decision delay that varies with time-to-go. Particular attention has been paid to highly maneuvering target interception in terminal guidance. The results of this research offer useful guidelines for the design of the mode decision-maker in IEG systems.     

碳纳米管阵列推力器放电特性的数值模拟研究

基于直接蒙特卡洛(DSMC)算法、浸入式有限元算法(IFE)、粒子云及蒙特卡洛碰撞(PIC-MCC)算法以及Ammosov-Delone-Krainov(ADK)隧穿电离模型建立了碳纳米管阵列推力器工质气体和CNT场电离过程的三维仿真模型。利用文献中的实验数据对本文仿真模型的有效性进行了验证,结果表明本文仿真模型与实验结果基本一致。针对碳纳米管阵列推力器的放电特性进行了研究,并重点分析了离子与原子碰撞过程对碳纳米管阵列推力器放电特性的影响。结果表明CNT可以极大地增强局部电场,稳态时场增强因子约为1308;与原子的碰撞使得离子在CNT附近更加集中,降低了局部电场,进而降低了其场增强能力。     

Mechanism analysis of hysteretic aerodynamic characteristics on variable-sweep wings

Variable-sweep wings have large shape-changing capabilities and wide flight envelops, which are considered as one of the most promising directions for intelligent morphing UAVs. Aerodynamic investigations always focus on several static states in the varying sweep process, which ignore the unsteady aerodynamic characteristics. However, deviations to static aerodynamic forces are inevitably caused by dynamic sweep motion. In this work, first, unsteady aerodynamic characteristics on a typical variable-sweep UAV with large aspect ratio were analyzed. Then, deep mechanism of unsteady aerodynamic characteristics in the varying sweep process was studied. Finally, numerical simulation method integrated with structured moving overset grids was applied to solve the unsteady fluid of varying sweep process. The simulation results of a sweep forward-backward circle show a distinct dynamic hysteresis loop surrounding the static data for the aerodynamic forces. Compared with the static lift coefficients , at the same sweep angles, dynamic  lift coefficient in sweep forward process are all smaller, while dynamic sweep backward  lift coefficient are all larger. In addition, dynamic deviations to static  lift coefficient are positively related with the varying sweep speeds. Mechanism study on the unsteady aerodynamic characteristics indicates that three key factors lead to the dynamic hysteresis loop in varying sweep process. They are the effects of additional velocity caused by varying sweep motion, the effects of flow hysteresis and viscosity. The additional velocity induced by sweep motion affects the transversal flow direction along the wing and the effective angle of attack at the airfoil profile. The physical properties of flow, the hysteresis and viscosity affect the unsteady aerodynamic characteristics by flow separation and induced vortexes.     

C/C复合材料喷管烧蚀壁面退移流固耦合仿真研究

为了保障固体火箭发动机C/C喷管的可靠性,建立了一套正确反映发动机喷管烧蚀过程的流固耦合计算模型,以实现对喷管烧蚀率的高精度预估。依据热化学烧蚀理论以及喷管内燃气与喷管结构体界面的质量平衡和能量平衡关系,建立并验证了考虑壁面退移的C/C喷管流固耦合方法,实现了燃气流动、异相化学反应、结构体传热三者间的耦合。通过实验发动机喷管的烧蚀计算,论证了模型的正确性,并分析了不同金属铝含量对烧蚀率的影响,计算所得的烧蚀率与实验值最大相对误差为4.3%,与不考虑壁面退移的耦合算法计算结果对比,计算精度最高可提升46%。计算结果表明：C/C喷管在喉部附近烧蚀最为严重;推进剂中Al含量的增加导致燃气中氧化组分浓度降低,进而减少了烧蚀速率,这些结论与C/C喷管烧蚀相关研究结果一致。     

超临界碳氢燃料蒸汽重整一维模型研究

为了获得关键参数对超临界碳氢燃料蒸汽重整化学热沉分布特性的影响,建立了超临界碳氢燃料蒸汽重整非稳态一维计算模型,通过与实验数据的对比验证了模型的准确性,并基于该模型采用RP-3的四组分替代模型对RP-3蒸汽重整过程中入口流速、压力和含水量等关键参数对热沉沿流向分布特性的影响进行了研究。结果表明：随着入口流速的增加,蒸汽重整反应化学热沉的峰值减小,且出现峰值的位置逐渐向出口移动。随着压力的升高,相同位置处的化学热沉都减少,但是出现峰值的位置不变。在入口含水量由5%增大到12%的过程中,微通道同一位置处的化学热沉增大,且化学热沉的最大值也是增大的,峰值出现的位置向微通道出口移动。     

中心锥对旋转爆轰发动机内外流场影响的三维数值模拟研究

为探究中心锥对旋转爆轰发动机(Rotating Detonation Engine,简称RDE)内外流场结构与推进性能的影响,本文设计了90°、60°、45°、30°、20°、14°锥角与无中心锥7种构型,对燃烧室内径为78mm、外径为88mm、长度为100mm的RDE进行三维数值模拟,推导了适用于带中心锥RDE的推力公式,获得了各构型下详尽的流场参数。结果表明：在本文构型下中心锥对内流场影响很小,各构型的内流场参数与结构基本一致;中心锥对外流场的爆轰产物有轴向加速与径向吸附作用,能够调控尾部区域的流场特性;中心锥对由压差项产生的推力具有显著的提升效果,最佳推力性能出现在20°中心锥构型中,RDE总推力增益达22.8%。研究结果揭示了中心锥对RDE推力影响的作用机理,阐明了锥角对推进性能的影响规律,对带锥形构型的尾喷管设计工作提供了参考。     

碳氢燃料超声速燃烧的化学动力学研究 (Ⅰ)甲烷超声速燃烧的简化化学动力学模型

采用雷诺平均Ｎ－Ｓ方程对碳氢燃料甲烷（ＣＨ４） 在超声速流动中混合燃烧过程进行了数值研究, 提出了简化的甲烷燃烧的反应机理及反应动力学模型, 建立了Ｂａｌｄｗ ｉｎ－Ｌｏｍ ａｘ 代数涡粘性湍流模型, 采用了高精度的ＴＶＤ隐式格式和化学源项隐式解法, 计算结果和氢气／空气超燃的计算结果进行了比较, 表明所采用的反应机理及计算模型合理, 算法可行, 就算例结果而言,碳氢化合物作为一种超燃燃料有其独特的优势, 值得进一步深入研究     

双燃式冲压发动机中超燃燃烧室冷态流场数值模拟

采用Ｍａｃ Ｃｏｒｍ ａｃｋ 矢通分裂格式, 求解雷诺平均的Ｎ－Ｓ方程组, 采用Ｂａｌｄｗ ｉｎ－Ｌｏ－ｍ ａｘ 代数湍流模型和混合长度模型, 模拟超燃燃烧室内两股平行超声速来流的冷态流场, 取得了与试验相一致的结果, 计算表明回流区和射流流动参数对超燃燃烧室流场内波系的变化有着较大的影响。