摘要
根据主发动机在转子最大不平衡量作用下产生的激振力 ,应用动态分析有限元法计算了导弹飞行过程中弹体在发动机额定转速和巡航转速下的稳态响应 ,为进一步分析弹上仪器的响应及其可靠性提供理论依据。
According to the excitations generated by main engine under the largest imbalance of the rotor,the stable response of missile body is calculated at the specified speed and cruising speed of engine during the flying of guided missile using finite element method in dynamic analysis.The response data at some locations missile body are given in order to further analyze the responses and reliabilities of the instruments in missile.
出处
《振动与冲击》
EI
CSCD
北大核心
2003年第3期86-88,共3页
Journal of Vibration and Shock
