CAJ | 학술논문

为研究导弹飞行速度对冲压式气动舵机自振参数的影响,采用数学建模和计算机仿真的方法,建立了舵机系统的数学模型和计算机仿真模型,通过仿真分析了气源压力和铰链力矩变化对自振参数的影响,揭示了舵机自振参数随飞行速度变化的内在机制,结果显示铰链力矩是影响自振荡参数的主要外在因素.分析表明,在总体设计中,应尽量减小导弹飞行速度的变化范围,以增强冲压式舵机自振荡参数的稳定性.
위연구도탄비행속도대충압식기동타궤자진삼수적영향,채용수학건모화계산궤방진적방법,건립료타궤계통적수학모형화계산궤방진모형,통과방진분석료기원압력화교련력구변화대자진삼수적영향,게시료타궤자진삼수수비행속도변화적내재궤제,결과현시교련력구시영향자진탕삼수적주요외재인소.분석표명,재총체설계중,응진량감소도탄비행속도적변화범위,이증강충압식타궤자진탕삼수적은정성.
In order to research the effect of missile flight speed on the vibration parameters of ram-air rudder, the mathematical and computer simulation models of the rudder system were created. On the basis of simulation, the effect of gas pressure and torque hinge on vibration parameters was analyzed, and the internal mechanism of the rudder vibration parameters varing with missile flight speed was revealed. The hinge moment is the main external effect factor of self-oscillation parameters. Analysis shows that the rate of change should be tried to reduce in the scope of missile flight in order to maintain the stability of ram-air rudder ' s self-oscillation parameters in the overall design of missile.