Mixing enhancement mechanism of combined H2–Water jets in supersonic crossflows in a combustor with an expanded section

To obtain the mixing enhancement mechanism of H₂–Water combined jets in supersonic crossflows in a combustor with expanded section for rotating detonation ramjet, the flow field shape and spray structure were studied by experimental and numerical methods. The Eulerian–Lagrangian method was used to investigate the diffusion mechanism and H₂–Water interaction law of combined jets with different sequences. At the same time, high-speed photography and the schlieren technique were used to capture the flow field. The effects of jet pressure drop, orifice diameter, orifice spacing, incoming Mach number, and other parameters on the penetration depth of water jets were studied. The results of experiment and simulation show that using H₂–Water combined jets, the penetration depth of the jet spray can be greatly increased and the jet mixing effect can be significantly improved, which will contribute to the engine's ignition and stable combustion. In the case of pre-water/post-H₂, the penetration depth of the hydrogen jet is greater. In the case of pre-H₂/post-water, the hydrogen jet raises the water spray mainly by protecting the integrity of the water column.     

BTT－固冲导弹总体一体化设计方法研究

从BTT-固冲导弹的特点:固冲发动机、导弹外形及控制系统具有强耦合的性质出发,分析了相互影响因素及建立计算模型时的特点。提出了一种BTT-固冲导弹总体一体化设计方法。     

基于响应面的变复杂度气动分析模型

结合变复杂度和响应面近似建模方法，采用CFD和工程估算气动分析方法，构建了基于响应面校准的变复杂度气动分析模型。以冲压发动机导弹为例，采用拉丁超方取样技术，选取6个CFD计算状态，建立了差值和比值校准响应面，并比较校准后的气动性能与CFD分析。结果显示，基于差值校准响应面的变复杂度方法具有较好的逼近能力和计算效率，适合于飞行器多学科设计优化过程的气动分析。     

冲压增程炮弹外弹道理论分析及数值仿真

简述了冲压增程炮弹增程原理,建立了进气道、发动机一体化外弹道计算模型,通过数值仿真得到了155 mm增程弹弹道曲线。通过对仿真结果进行分析,得到了射程随部分设计变量变化的关系曲线,为增程弹总体优化设计奠定了理论基础。     

国外低特征信号富燃料推进剂的研究进展

综述了国外低特征信号富燃料推进剂的研究进展,归纳了研究低特征信号富燃料推进剂的技术途径。认为碳氢富燃料推进剂具有低特征信号的特点,是研究低特征信号富燃料推进剂的基础,采用非金属燃料是降低推进剂一次烟烟雾特征信号的有效途径,通过添加剂消除HCl是降二次烟的有效手段。对我国低特征信号富燃料推进剂的发展提出了几点建议。     

固体火箭冲压发动机在空空导弹上应用的优势

通过对采用固体火箭冲压发动机和固体火箭发动机的导弹在不同高度下的弹道性能计算和分析,得出采用固体火箭冲压发动机的导弹在射程、速度、机动性等方面都比采用固体火箭发动机的导弹具有很大的优越性,希望能够为我国今后发展固体火箭冲压发动机技术提供一些理论支撑。     

轴对称凹腔燃烧室点火影响因素的试验研究

对采用凹腔作为火焰稳定器的亚燃燃烧室进行了点火试验研究.通过考察不同的凹腔结构及其组合方式、煤油喷注方式,分析了凹腔大小、火焰的轴向、周向传播对点火性能的影响.结果表明,点火瞬间的凹腔有效储能大小来源于轴向容积比率;凹腔内的轴向火焰传播是火焰发展的主要机制;在凹腔前方壁面以使喷油能使凹腔内维持合适的燃油浓度分布,是可靠点火的前提.     

Research status of key techniques for shock-induced combustion ramjet(shcramjet) engine

As one of the most promising propulsion systems in the future,shock-induced combustion ramjet engine can remedy the disadvantages in the integrated design of scramjet engine and airframe.It can shorten the length of the combustor,lighten the structure weight of the engine and keep better performance in a broad range of flight Mach number.The elementary principle of shock-induced combustion ramjet engine is introduced.The key technologies of this kind of propulsion system are described,while their research s...     

整体式液体冲压发动机动力特性研究

综合导弹和整体式冲压发动机的相互影响，从导弹总体设计的观点出发，对整体式液体冲压发动机的性能进行了研究，分析讨论了设计参数对发动机性能的影响及发动机设计的特殊问题。本文法可用于导弹总体方案设计阶段参数的选择和性能分析。     

含侧向支柱冲压增程弹用进气道复杂流场数值模拟

采用块结构网格与二阶精度流场分区求解技术,对含侧向支柱冲压增程弹丸进气道内外复杂流场进行了数值模拟。通过数值模拟得到了对应于不同来流马赫数和攻角情况下,临界工况时,超声速进气道内外粘性流场复杂的波系结构。当进气道扩压段有侧向支柱存在时,进气道总压恢复系数和动能系数均有所降低,而流场畸变指数则显著增大。由于攻角的存在,进气道总压恢复系数和动能系数均有所降低,而流场畸变指数则明显增大。