细长体飞行器气动伺服弹性稳定性分析对比研究  

Comparative study on the aeroservoelastic stability analysis for slender body aircraft

作　　者：严晓雪 许云涛[1,2] 李长文 Yan Xiaoxue;Xu Yuntao;Li Changwen(Beijing Electro-mechanical Engineering Institute,Beijing 100074,China;Beihang University,Beijing 100083,China)

机构地区：[1]北京机电工程研究所,北京100074 [2]北京航空航天大学,北京100083

出　　处：《战术导弹技术》2024年第3期11-16,共6页Tactical Missile Technology

摘　　要：为有效避免飞行器设计过程中面临的非定常气动力、机体结构及控制系统耦合引发的闭环系统失稳问题,针对细长体飞行器气动伺服弹性稳定性分析需求,建立了基于气动导数法与工程面元法的气动伺服弹性稳定性分析手段,对比了不同方法气动伺服弹性稳定性分析的适用性。针对某细长体飞行器的研究发现,亚声速和超声速状态两种方法计算偏差在2 dB以内,偏差较小,使用两种方法评估均可;高超声速状态两种方法偏差达到10 dB,此时建议采用精度更高的气动导数法。In order to effectively avoid the closed-loop system instability problem caused by the coupling of unsteady aerodynamics,body structure,and control system in the aircraft design process,and to meet the requirements of aeroservoelastic stability analysis for slender body aircraft,an aeroservoelastic stability analysis method for slender body aircraft is established based on aerodynamic derivative method and engineering panel method.Taking a slender body aircraft as research object,the deviation of two methods at subsonic state and supersonic state are within 2 dB.The deviation of two methods at hypersonic state are over 10 dB.It is recommended to adopt aerodynamic derivative method to achieve higher accuracy at hypersonic state.

关 键 词：细长体飞行器 气动伺服弹性 稳定性 气动导数法 工程面元法 亚声速 高超声速 

分 类 号：TP761.3[自动化与计算机技术—检测技术与自动化装置]