基于非旋弹体坐标系的面对称旋转导弹六自由度弹道模型  

Six Degree-of-freedom Trajectory Model of Plane-symmetry Rolling Missiles Based on Non-spinning Body Coordinate System

作　　者：高庆丰[1] 夏群力[1] 方蜀州[1] 陈罗婧[2] 

机构地区：[1]北京理工大学宇航学院,北京100081 [2]航天东方红卫星有限公司,北京100094

出　　处：《弹箭与制导学报》2010年第4期149-152,168,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了计算一定风洞试验方法下的面对称旋转导弹六自由度弹道，建立了相应的六自由度弹道模型，定义了模型中的坐标系并给出各个坐标系之间的转换关系，在此基础上得出了角度的计算公式，分析了风对旋转导弹运动的影响，在全攻角非旋弹体坐标系中计算了气动力和气动力矩，在非旋弹体坐标系下建立了质心运动的动力学方程和绕质心转动的动力学方程，给出了质心运动和绕质心转动的运动学方程，解决了面对称旋转导弹六自由度弹道计算问题。In order to calculate the six degree-of-freedom trajectory of plane-symmetry rolling missiles under a special wind tunnel test method, the six degree-of-freedom trajectory model was established. Based on the definition of coordinate systems and the transform relation of various coordinate systems, the computing formulas of angles were derived. The influence of wind on rolling missiles motion was analyzed. The aerodynamic forces and moments were calculated in the total angle of attack non-spinning body coordinate system. The dynamical equations of center of mass and rotation were established. The kinematical equations of center of mass and rotation were given. The problem of calculating the six degree-of-freedom trajectory of plane-symmetry rolling missiles was solved.

关 键 词：面对称 旋转 六自由度弹道模型 

分 类 号：TJ013[兵器科学与技术—兵器发射理论与技术]