CAJ | 학술논문

为研究大展弦比巡航导弹在弹性振动时的侧向动态特性,采用NASTRAN软件计算了结构的固有模态,分析了弹性振动时的附加非定常气动力,建立了刚体扰动运动方程组,将弹性振动引起的附加非定常气动力作为干扰输入项代入扰动运动方程组,得到了弹性振动下的动态响应.结果表明,大展弦比巡航导弹的弹性振动主要为翼面的振动;在满足气动与结构稳定的前提下,弹性振动引起的侧滑角偏量非常微小;倾斜角偏量比较大,各姿态角都在做微幅高频振荡,对弹上惯性器件的测量将造成不利影响,必须采取滤波等方式将此不利因素消除.
위연구대전현비순항도탄재탄성진동시적측향동태특성,채용NASTRAN연건계산료결구적고유모태,분석료탄성진동시적부가비정상기동력,건립료강체우동운동방정조,장탄성진동인기적부가비정상기동력작위간우수입항대입우동운동방정조,득도료탄성진동하적동태향응.결과표명,대전현비순항도탄적탄성진동주요위익면적진동;재만족기동여결구은정적전제하,탄성진동인기적측활각편량비상미소;경사각편량비교대,각자태각도재주미폭고빈진탕,대탄상관성기건적측량장조성불리영향,필수채취려파등방식장차불리인소소제.
To study the lateral dynamic characteristics of large-aspect-ratio cruise-missile vibrating in flight,the natural mode was calculated by using NASTRAN.The additional unsteady aerodynamics derived from vibration was investigated.The lateral perturbation motion equations were established by the linearization theory.The additional unsteady aerodynamics were induced to the equations as disturbance variables,and the dynamic response was obtained.The results indicate that the elastic vibration of large-aspect-ratio cruise-missile is mainly the vibration of airfoil surface,and the deflection of sideslip angle is very small while the aerodynamics and structure stability are satisfied,but the deflection of bank angle is large.All the attitude angles vibrate with micro amplitude and high frequency;the micro-vibration has bad influence on the survey of inertial components,so the filtering method must be applied to eliminate the disadvantage.