火箭推进
火箭推進
화전추진
JOURNAL OF ROCKET PROPULSION
2012年
4期
55-59,80
,共6页
动态特性%有限元方法%喷管%模态试验
動態特性%有限元方法%噴管%模態試驗
동태특성%유한원방법%분관%모태시험
dynamic characteristic%finite element method%nozzle%modal test
为了获得某型号发动机的动态特性，采用有限元方法进行了发动机整机的模态分析。按照由组件到整机的思想，分别建立了各个组件的有限元模型。重点对推力室和喷管的建模方法进行了分析。将推力室按等效刚度法等效为单层壳，喷管按结构特性等效为正交各向异性壳，并将喷管计算结果同模态试验结果进行对比，验证了喷管建模方法的准确性。各组件模型组装为整机有限元模型，计算得到了整机的模态分布。数值计算结果同模态试验结果吻合较好。
為瞭穫得某型號髮動機的動態特性，採用有限元方法進行瞭髮動機整機的模態分析。按照由組件到整機的思想，分彆建立瞭各箇組件的有限元模型。重點對推力室和噴管的建模方法進行瞭分析。將推力室按等效剛度法等效為單層殼，噴管按結構特性等效為正交各嚮異性殼，併將噴管計算結果同模態試驗結果進行對比，驗證瞭噴管建模方法的準確性。各組件模型組裝為整機有限元模型，計算得到瞭整機的模態分佈。數值計算結果同模態試驗結果吻閤較好。
위료획득모형호발동궤적동태특성，채용유한원방법진행료발동궤정궤적모태분석。안조유조건도정궤적사상，분별건립료각개조건적유한원모형。중점대추력실화분관적건모방법진행료분석。장추력실안등효강도법등효위단층각，분관안결구특성등효위정교각향이성각，병장분관계산결과동모태시험결과진행대비，험증료분관건모방법적준학성。각조건모형조장위정궤유한원모형，계산득도료정궤적모태분포。수치계산결과동모태시험결과문합교호。
To obtain the dynamic characteristics of a certain rocket engine, a modal analysis for the engine is conducted with finite element method (FEM). According to the idea from components to integrate, the finite element model for each component is established. In addition, the modeling methods for nozzle and thrust chamber are analyzed emphatically. The thrust chamber is simplified to single-layer shell by stiffness equivalent, while the nozzle is simplified to orthotropic shell in accordance with its structural properities. The calculated result of nozzle is compared with that of modal experi- ment to verify the precison of the modeling method for nozzle presented in this paper. The finite element model of whole engine is assemblied by all the component models, and then its modal distribution is calculated. The result of numerical calculation agrees well with that of modal test.
