针对动态偏离稳定判据C_nβDYN和侧向操纵偏离判据LCDP不能准确预测飞行器高机动状态下偏离稳定性的不足,基于高超声速飞行器耦合动力学模型,采用小扰动原理与系数冻结方法,推导了适用于飞行器全通道耦合的偏离稳定判据,新的稳定判据适用于更多的飞行状态。总结了不同飞行状态下适用的稳定判据,并应用新的偏离稳定判据对实际飞行器进行了偏离失稳分析。结果表明,在高机动状态下飞行器三通道间的耦合对稳定性影响较大,全通道偏离稳定判据能够更精确地反映飞行器的偏离稳定特性。

The dynamic departure stability criteria C_nβDYN and lateral control departure criteria LCDP cannot accurately predict the deviation stability characteristics of aircraft under high maneuverability. Based on the coupled dynamics model of hypersonic vehicle, the small-disturbance principle and the method of freezing coefficient are adopted to deduce the departure stability criteria of the whole channel coupling, which is applicable to more flight states. The applicable stability criteria are summarized under various flight conditions, and the departure stability analysis of the actual aircraft is carried out. It is pointed out that the coupling between the three channels cannot be neglected when the vehicle is in high maneuvering state, and the whole channel deviation stability criterion can reflect the deviation stability of the aircraft more accurately.