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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。
By confirming the geometric meanings of concepts such as angle of attack, side slip angle and sweep angle, the relationship between the angles of attack is geometrically determined. On the basis of not changing the geometric meaning, Angle of attack formula for approximate treatment, and the use of the current prevailing method derives the slip caused by the slip-forward wing aircraft swept moment formula for backward-swept wing aircraft lateral stability analysis proposed a more accurate method . The geometric meaning of this method is clear, the use of analog methods, to avoid the complex geometric proof, so the formula is also relatively simple derivation process. Due to different understanding of the basic concepts and methods of approximate treatment, the variation of the resulting rolling moment is also different. However, in the case of low accuracy, the simplified results obtained by various methods are the same.