摘要
针对高速飞行器存在横侧向耦合易失控问题,建立了基于部件组合思想的CST几何外形参数化建模方法,以升力体外形为例,采用拉丁超立方试验设计方法和高速气动特性快速分析方法,分析了升力体主要布局参数对横侧向耦合稳定性参数开环动态偏离稳定判据(C_(nβ,dyn))和闭环横向控制偏离判据(LCDP)的影响规律.升力体外形主导布局参数对横向操纵滚转反逆参数LCDP是二次非线性影响,横侧向稳定性的主导布局参数随着攻角变化有明显变化.文章为耦合稳定性影响规律研究建立了有效的分析方法,研究结论可为高超声速升力体式飞行器总体抗失控设计提供规律建议.
Aiming at the problem that the hypersonic vehicle is easy to lose control due to lateral coupling,the methods of CST parametric modeling based on part combination were established in this paper.Taking the lifting body as an example,the Latin Hypercube design method and the fast analysis method of hypersonic aerodynamic properties were used.The influence of the lifting-body′s main shape parameters on the lateral coupling stability parameters was analyzed,such as dynamic directional stability parameter(C_(nβ,dyn))and lateral control departure parameter(LCDP).The dominant shape parameter had a quadratic nonlinear effect on LCDP.The lateral coupling stability parameters changed significantly with the angle of attack.This paper established an effective analysis method for the study of the lateral coupling stability.It can provide regular suggestions for the overall anti-runaway design of hypersonic lifting-body vehicles.
作者
张青青
张石玉
赵俊波
赵力宁
ZHANG Qing-qing;ZHANG Shi-yu;ZHAO Jun-bo;ZHAO Li-ning(China Academy of Aerospace Aerodynamics, Beijing 100074, China)
出处
《气体物理》
2021年第6期20-28,共9页
Physics of Gases
关键词
横侧向稳定性
外形参数化
类型形状函数法
升力体
高超声速
lateral-direction stability
shape parameterization
class function/shape function
lifting-body configuration
hypersonic
