全动舵铰链力矩计算的CFD数值仿真  

CFD Numerical Simulation of All-Movable Panel Hinge Moment Calculation

作　　者：段晓亮[1] 吴颂平[1] 

机构地区：[1]北京航空航天大学CFD国家重点实验室,北京100083

出　　处：《计算机仿真》2008年第10期46-49,共4页Computer Simulation

摘　　要：在飞行器设计初期,舵面铰链力矩的预测主要依靠理论估算和试验测量的方法取得,随着CFD技术的发展,运用数值模拟方法预测舵面铰链力矩成为现实。使用二阶精度的Harten-Yee空间离散格式和LU-SGS隐式时间推进方法计算了单独舵面以及弹身-舵面组合体外形的超音速绕流流场特性,并通过积分计算了单独舵面以及舵体组合体的压心位置和铰链力矩。考察了在不同来流马赫数、攻角和舵偏角状态下的压心位置和铰链力矩的变化。计算铰链力矩时用了两种不同的方法,第一种是直接对铰链轴进行压强积分计算,第二种方法是先求出压心位置和法向力,然后再计算铰链力矩,并对两种方法进行了对比分析。计算结果表明两种计算方法所得结果比较接近,验证了数值仿真的可行性,对舵面铰链力矩预测有很好的指导意义。At the beginning of aircraft design, prediction of hinge moment depends on theoretical method and experiment. With the development of CFD technology, numerical simulation becomes an important method in hinge moment prediction. This paper calculates the supersonic flow characteristic by Harten - Yee two order spatial discretization format and LU - SGS implicit time discretization format, calculates the center of press location and hinge moment of the tail and body - tail combination by numerical integral, and calculates the center of press location and hinge moment at different Mach number, angle of attack and angle of tail deflection. Two methods are used for calculating the hinge moment, the first method is direct numerical integral, the second method is that the hinge moment is a product of the normal force multiplied by its perpendicular distance from the reference chord. The computational result indicates that the two methods are equal in prediction of hinge moment, so CFD method is proved to be a significant guide for hinge moment prediction.

关 键 词：全动舵 铰链力矩 压力中心 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]