尾翼稳定火箭弹高空气动力与弹道特性研究

The Research on Aerodynamic Characteristics and Ballistic Characteristics of Fin-stabilized Rocket at High Altitude

针对新型弹箭的射程增大和飞行空域的大幅度提高,文中研究了尾翼稳定弹箭的主要气动力特性随海拔高度增大的变化规律以及对飞行弹道特性的影响。结果表明,随海拔高度增大阻力系数增大及压心系数减小对弹道特性的影响应该引起重视,在飞行弹道高度大于30km的远程弹箭飞行动力设计和弹道仿真计算中应该考虑空气动力系数随高度的变化。

In view of the range extended and flight space enhanced substantially of new rockets, the varying law of the major aerodynamic characteristics of the fin stabilized rocket following accretion of altitude above sea level and it＇s influence to the ballistic characteristic were studied in this paper. The conclusion shows that more attention should he paid to the influences applied hy the drag coefficient increase and the center of pressure coefficient decrease following the accretion of the altitude above sea level to the ballistic characteristics, For the long range rocket with flight trajectory high than 30km, the aerodynamic coefficient varying following accretion of the altitude should be considered in power design and ballistic simulation.