外弹道非线性干扰与内弹道非稳态响应研究

Explore the basic law of the excitation, coupling and trigger of typically external ballistics nonlinear interference with the interior ballistic unsteady flow field which the aircraft encounters during the flight. Propose the methods of restrain coupling and enlarging with each other through the unsteady turbulent numerical calculation and experiment. Simplify the typical transient impact model which generated by the mutation external ballistic flight parameters, and carry out the engine experimental verification in the ground. Determine energy transfer and coupling methods of the unsteady flow field with the engine multilayer structure vibration, and present suppressing method of interior ballistics non-steady-state with engine structure vibration coupling. Research the influence of the aircraft thrust mutation to unsteady flow field characteristics of the engine through the numerical calculation and theoretical analysis. Reasonably simplify anisotropic tensor functions of propellant combustion surface mass injecting and tangential turbulence and response the true affecting extent of unsteady flow field by the boundary condition so that carry out the quantitative comparisons with the amplitude and frequency of chamber inner cavity, case and the outside interference. Finally find out the response characteristics of external ballistics nonlinear interference with the interior ballistics non-steady-state and the means to overcome.

探索飞行器在飞行过程中遭遇的外弹道典型非线性干扰对发动机内弹道非稳态流场触发、激励和耦合的基本规律，通过非稳态湍流场数值计算和设计相关的实验，提出抑制相互耦合放大的方法和途径。对外弹道飞行参数突变产生的典型瞬态冲击模式简化并进行地面发动机实验验证。确定非稳态内流场与发动机多层结构振动能量的传递与耦合方式，提出抑制内弹道不稳定与发动机结构振动耦合的方法。用数值计算和理论分析方法，研究飞行器推力突变对发动机的非稳态流场工作特性的影响。对装药燃烧表面质量注入与切向湍流各向异性张量函数进行合理简化，真实反映非稳态流场受边界状况影响的程度，以便和测量所得的燃烧室内腔、壳体的振幅频率以及外界干扰的关系进行定量比较，最终给出外弹道非线性干扰与内弹道非稳态响应特点和克服手段。

探索飞行器在飞行过程中遭遇的外弹道典型非线性扰动形式，探索对发动机内弹道非稳态流场的触发机理和影响程度，并提出抑制结构振动与内流场声涡相互耦合放大的方法和途径。探索内弹道声/涡耦合和非稳态内流场声与非声振荡增长条件。确定非稳态内流场与外弹道不稳定性，与发动机内部不同边界条件的耦合、反馈和放大机理，探索降低实际飞行中飞行器内/外弹道相互干扰耦合放大的基本规律。. 满足快速反应反弹道导弹需求，使其内弹道工作稳定不受外弹道突变和过载的影响。对在实际飞行过程中可能遇到的典型非线性触发脉冲进行分类定型，对其振幅、频率以及通过结构的传递特征给予定量描述。研究其引起的内弹道不稳定性规律和抑制手段。研究内外弹道通过结构传递过程中不稳定性耦合放大可能性及其后果，提高发动机在飞行过程中的抗干扰能力。. 战术导弹需要有强机动性，能够对目标进行快速响应，因此作为动力装置的SRM在工作过程中会遭遇各种各样的过载。过载会影响SRM的工作过程，对金属氧化物粒子的运动、推进剂的燃烧、燃烧室及喷管壳体的热防护、装药结构完整性等均会产生重要的影响。