升力式面对称运载器大攻角颤振分析方法研究  

Research on the Analysis Method of High Angle of Attack Flutter of Lifting Symmetric Carrier

作　　者：蔡巧言[1] 吕计男 郭力[3] 王昕江 CAI Qiaoyan;LV Jinan;GUO Li;WANG Xinjiang(China Academy of Launch Vehicle Technology,Beijing 100076,China;Beijing institute of aerospace systems engineering,Beijing 100076,China;China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]北京宇航系统工程研究所,北京100076 [3]中国航天空气动力技术研究院,北京100074

出　　处：《强度与环境》2023年第6期41-47,共7页Structure & Environment Engineering

基　　金：民用航天项目(D020504)。

摘　　要：升力式运载器采用面对称气动布局,结构频率低,易与气动耦合发生气动弹性问题,舵翼面颤振特性的准确分析对型号飞行的成败具有重要意义。当前针对经典颤振的数值分析方法发展较为成熟,对亚声速及超声速域内小攻角飞行状态下的颤振特性预示具有较高精度。然而,对处于大攻角气动干扰下气动控制面的颤振特性分析,工程气动力模型的颤振分析方法难以给出准确的预示结果。本文分别采用工程气动力模型方法和CFD方法对升力式布局面对称运载器颤振特性进行分析,对传统工程方法在此类飞行器大攻角颤振分析中的不足进行了分析,并采用CFD/CSD耦合方法准确预示运载器大攻角飞行时的颤振特性。Due to its low structural frequency and aerodynamic coupling,the lift-type shuttle is prone to aeroelastic problems.The accurate analysis of flutter characteristics of the rudder/wing is of great significance to the success of the flight tests.At the present,the numerical analysis methods for classical flutter are relatively mature and have high accuracy in predicting flutter characteristics under low angle of attack in subsonic and supersonic domains.However,for analysis of wing flutter,which may under the complex aerodynamic interference,the method based on the engineering aerodynamic model is often difficult to give accurate predicting results.In present paper,engineering aerodynamic model and CFD method were under used to analyze the flutter characteristics of lift-type shuttle,the misjudge and shortcoming of engineering method in this type vehicle flutter analysis was demonstrated,which at the same time testifies the necessity and feasible of the CFD/CSD method in this flight profile.

关 键 词：大攻角 颤振 数值分析 

分 类 号：V417.3[航空宇航科学与技术—航空宇航推进理论与工程] TJ06[兵器科学与技术—兵器发射理论与技术] O348.5[理学—固体力学]