摘要
将单独栅格翼气动特性的计算推广应用于计算栅格尾翼导弹在亚、跨、超音速流中的法向力、俯仰力矩和轴向力系数以及载荷分布。对于小的迎角和舵偏角 ,栅格尾翼的法向力特性在亚音速时用基于升力面理论的涡格法计算 ,在跨音速时用一维流理论计算 ,在超音速时用激波 -膨胀波法计算 ;弹体对尾翼的干扰 ,用尾翼处在弹体的横向上洗流场中来模拟。尾翼对弹体干扰所引起的附加载荷用镜像法计算。对于中等大的迎角和舵偏角 ,栅格尾翼的法向力用经验公式计算。单独弹体的法向力特性 ,在亚音速时采用 Jorgensen的理论与修正的细长体理论相结合的方法计算 ,在超音速时用 Aiello建立的数据相关法计算。通过实例计算 ,得到与实验数据吻合良好的满意结果。计算结果表明 ,栅格尾翼的空气动力有许多特有的性质 ,将它应用到导弹上作稳定面和控制面 。
The past successful experience in calculation single grid fin is extended to the calculation and analysis of normal force,pitching moment,axial force and load distribution of grid fin missile configurations in subsonic,transonic and supersonic flow.For small angles of attack and fin deflection angles, normal force of grid fin is calculated by using the vortex lattice method based on the lifting surface theory in subsonic flow,one dimension flow theory in transonic flow and shock expansion wave method in supersonic flow. Body fin interference is modeled by assuming the grid fins immersed in the body upward flow, and fin body interference is calculated by the mirror image method.For moderate angles of attack and fin deflection angles,the normal force of grid fin is calculated by an empirical formulation.The body alone aerodynamic coefficients are calculated by using a combination Jorggensen’s theory and a modified form of slender body theory in subsonic flow, and Aiello′s data correlated method in transonic or supersonic flow. The calculation results are quite well with the experimental data, and the results indicate that there are a lot of specific features of grid fin aerodynamic characteristics.The use of grid fins as aerodynamic stabilizers and control surfaces of missile seems much better than conventional planar fin in many aspects.
出处
《导弹与航天运载技术》
北大核心
2001年第3期7-12,共6页
Missiles and Space Vehicles
基金
国家自然科学基金资助项目
