非对称转捩对横向偏离稳定的影响  

Effect of Asymmetric Transition on Lateral Departure Stability

作　　者：徐国武[1] 李锋[1] 龚安龙[1] 刘周[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《宇航学报》2015年第9期995-1001,共7页Journal of Astronautics

基　　金：国家自然科学基金(11372040)

摘　　要：为研究非对称转捩对横向偏离稳定的影响,采用指定位置的强制转捩方法,对典型升力体外形进行非对称转捩的的数值模拟,包含全层流、全湍流及斜线转捩情况的计算与分析,得到非对称转捩对横向偏离稳定性影响的结论。结果表明:极端转捩会使飞行器航向稳定性变差,斜线转捩甚至会使飞行器航向稳定性的极性发生改变。In order to study the effect of asymmetric transition on lateral departure stability, a coercive transition method is used to do the research. The asymmetric transitions,including the laminar flow,turbulent flow and diagonal transitions, are numerically simulated for a typical lifting body configuration, and the conclusion of the effect of asymmetric transition on lateral departure stability is gained. The results indicate that extreme asymmetric transition makes lateral stability of vehicle become worse and that diagonal transition changes even the polarity of lateral stability.

关 键 词：升力体 非对称转捩 数值模拟 横向操纵偏离参数 航向稳定性 

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]