【摘要】 针对近年来大长径比战术导弹续航发动机与弹体发生的共振现象，基于天上飞行试验遥测数据对其基本规律进行了总结，并进行了发生机理方面的分析探讨和解释。分析认为，几十千帕以下的压力振幅是燃烧表面和声场的相互作用所致；100 kPa以上的压力振幅是燃烧表面和声场还有弹体结构共同激励的耦合共振所致，此时发动机内部以声场基频和倍频振荡的振幅可以达到100～600 kPa,同时导弹全弹也在以发动机内部声场基频和倍频振动，加速度计振幅显示陡然增大，而振动幅度从弹体后端发动机位置一直向弹体头部传递并逐渐减弱。对战术导弹发动机内流动适用的流体力学基本理论进行了简述，并提出了飞行状态下抑制耦合共振与发动机非线性压力突升需要研究的问题。更多还原

【Abstract】 In view of the resonance phenomenon occurring between the sustainer motor and the body of tactical missiles with large aspect ratio in recent years, and based on telemetry data from flight tests, the basic laws was summarized, moreover the mechanism was analyzed and discussed.It is believed that the pressure amplitude below tens of kilopascals results from the interaction between combustion surface and sound field, and those above 100 kPa result from the coupling resonance jointly excited by combustion surface, sound field and projectile structure.For the latter case, the fundamental frequency and multiple frequency oscillation in motor sound field can reach an amplitude of 100～600 kPa, and meanwhile the whole missile body also vibrate with the same frequency level.As the accelerometer amplitude shows a sudden increase, it is found that the vibration is transmitted from the rear end to the head of the missile body and its amplitude gradually decreases.After the basic theory of fluid dynamics applicable to the flow in tactical missile motors is briefly reviewed, the problems to suppressing coupling resonance and motor nonlinear pressure steep in flight are also put foward.更多还原