多级供油双模态燃烧室模态转换的动力学特性及控制研究

Dual-mode scramjet is one of the most promising hypersonic vehicle propulsion system in the atmosphere, the reliability and efficiency of the engine is highly rely on the thermodynamic control technology adopted in mode and mode transition. The thermodynamic control technology is also one of the key technologies in dual-mode scramjet engineering applications. To the study of thermodynamic control in dual-mode combustor with multi-staged fuel regulation, the time-frequency characteristics , freedom disturbance response characteristics and stability of flow field parameters in transition process are studied. Then the characteristics are compared with the single-staged fuel conditions. The control characteristics of mode transition are studied in multivariable control sensitivity, dynamic coupling modeling, coupling mechanism and the factors influence the characteristics. Finally, the combustor flow field parameters decoupling control verification tests are carried out under modal transition process. The research work can provide a useful reference for precise thermodynamic control mechanism and method in combustor mode transition.

双模态超燃冲压发动机是大气层内高超声速飞行器最具潜力的推进系统之一，其可靠高效的工作依赖于精确热力调节技术对模态及模态转换过程的控制，该技术也是解决双模态超燃冲压发动机实用性的关键技术之一。针对多级燃油调节条件下燃烧室模态转换的精确热力控制问题，研究模态转换过程流场参数的动力学特性和控制特性。首先，以试验结合一维稳态性能模型，研究多级供油对模态转换过程流场参数时频响应特性、自由扰动响应特性和稳定特性的影响，并与单级供油驱动的模态转换过程进行对比研究；在此基础上，研究多级燃油分布调节下模态转换流场参数的控制特性，包括流场参数的多变量控制灵敏度分析、动态耦合关系建模、耦合作用机理和影响因素研究，并进行燃烧室流场参数解耦控制试验验证。研究工作可为燃烧室模态转换过程的精确热力控制机理和方法提供有益的参考。

超燃冲压发动机模态的精确热力学调节问题是高超声速推进技术的关键问题之一。项目首先建立和完善了双模态燃烧室的多变量控制设备，为燃烧室动态特性和控制试验的实现打下了基础；并通过设计精确动态特性试验研究多级供油、燃烧模态和壁面压力分布之间的动力学关系，进而利用时域、频域、时频域分析和动态相关分析研究了多级燃油对壁压分布和模态转换动力学特征的耦合影响，最后在双模态燃烧室中实现了壁面压力分布的精确热力学控制试验验证，取得了较好的效果。项目共发表论文5篇，其中SCI检索1篇、EI检索4篇，项目协助培养博士生2名、硕士生2名。项目经费严格按照相关规定要求支出，剩余经费将用于后续研究。