摘要
通过对迎角、侧滑角、后掠角等概念的几何意义进行确认,从几何上确定了各迎角间的关系,在不改变几何意义的基础上对有侧滑和无侧滑时的迎角关系式进行近似处理,并运用目前通行的方法推导了由侧滑导致的后掠翼飞机的滚转力矩公式,对后掠翼飞机横侧静稳定性的分析提出一种较准确的方法。这个方法几何意义明确,采用类比的方法后,避免了复杂的几何证明,因而公式的推导过程也比较简捷。 由于对基本概念的认识不同和近似处理的方法不同,所得滚转力矩的变化规律也是不同的。但在精度不高的情况下,各种方法所得的简化结果则相同。
Abstract In this paper, based on the affirming of the geometric meaning of several concepts, the relationship among several angles of attack is established. With no change in the geometric meaning, the relationship formula is handled simplified. Furthermore, with a universal method, it gives the derivation of a rolling moment formula caused by sideslip. The author put forward a more precise method on how to analyse the static rolling stability of a sweptwing aircraft. The advantage of this method is its clear geometric meaning, and by the use of analogism a complex geometry ?proving is avoided, thus makes the derivation more concise. For the different comprehension to the basic concepts and the different way of simplified handling, the principle of the alteration in rolling moments is not the same. Otherwise, without the requirement of exact precision, the simplified result is the same as the others.
出处
《飞行力学》
CSCD
北大核心
1996年第3期44-49,共6页
Flight Dynamics
关键词
迎角
侧滑角
后掠角
滚转力矩
后掠翼
飞机
Angle of attack Angle of sideslip Sweep angle Rolling moment
