轴对称推力矢量喷管载荷变形的控制补偿  

Load deformation compensation of the axisymmetric vectoring exhaust nozzle

作　　者：王玉新[1] 王仪明 李雨桐[3] 

机构地区：[1]浙江大学机械与能源学院,杭州310027 [2]北京图形与传媒学院,北京100014 [3]同济大学机械学院,上海200092

出　　处：《航空动力学报》2007年第10期1685-1689,共5页Journal of Aerospace Power

基　　金：国家自然科学基金资助项目(50375111/50675148)

摘　　要：研究了温度场和气动载荷联合作用下的轴对称矢量喷管出口面积和偏转角度误差的补偿问题.建立了扩张调节片位姿参数与其悬挂机构尺度之间的关系,导出了悬挂机构关节角位移增量与构件长度增量之间的微分方程,得到喷管出口面积误差和矢量偏转角误差与负载变形之间的解析表达式.利用矢量偏转角度和面积与轴对称矢量喷管转向驱动机构动平台位姿之间的关系,建立了受温度场和气动载荷联合作用下的动平台位姿补偿方程.研究表明,补偿后的矢量偏转角度和面积的相对误差不大于1%.　The compensation of the load deformations for axisymmetric vectoring exhaust nozzle（AVEN） under heat field and aerodynamic forces was analyzed.The correlation between expansion plates and suspension kinematic chains was set up,while a differential equation for the joint displacement increments and length increments of suspension kinematic chains was introduced.Then,the analytical expression for the deviations of the area/vector deflection angle of the exhaust nozzle caused by the load deformations was expressed analytically.With the aid of the relationship among the deviations of the nozzle and the pose parameters of the driving platform of the AVEN,the dynamic compensation equation for correcting the deviations of the AVEN caused by the heat field and forces was deduced.The research results show that,the relative error of the area and deflection angle of AVEN is less than 1% after compensation.

关 键 词：航空、航天推进系统 轴对称推力矢量喷管(AVEN) 变形补偿 温度载荷 气动载荷 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]