应用惯性释放方法的静气动弹性发散分析

翼面发散作为静气动弹性的重点分析对象，传统的分析方法通常将翼面根部固支约束，不考虑刚体模态的影响。根据咨询通告AC 25.629-1B 的要求，刚体模态或短周期模态也可能会造成发散。因此，在民用飞机静气动弹性分析及适航符合性验证中，要计及刚体模态对发散的影响。通过对惯性释放方法的研究，在发散分析中计及刚体模态，给出考虑刚体模态的模态法发散分析方法；以某型民用飞机为例，应用本文方法分别计算空机状态、不同燃油和商载的静气动弹性发散结果，并和不考虑刚体模态的模态法、考虑/不考虑刚体模态的颤振法的发散计算结果进行对比分析。结果表明：考虑刚体模态后的发散速度有所提高，临界发散模态不变，发散速度随燃油和商载的增加而降低。

Aeroelastic dynamic divergence analysis by introducing inertia relief method

Lifting surface divergence plays an important role in static aeroelasticity analysis.Traditional static aeroelasticity analysis of airplane lifting surface makes the root part fixed without considering the influence of rigid mode. According to AC 25.629-1B, divergence may occur for a structural mode or the short period mode. Inertia relief method is studied and used to take rigid mode into account in divergence analysis. The method is used to compute the divergence results of empty airplane and different payload and fuel for certain airplane. Results are compared with that calculated by flutter method and mode method. Furthermore, results of empty airplane are compared with that gotten by SOL 144 of NASTRAN. Comparison shows divergence results with rigid mode are larger and divergence speed decreases with the increase of payload and fuel.