摘要
在考虑各种影响因素的基础上，增加了交叉惯性积对稳定尾旋的影响，从而导出了分析稳定尾旋的有关公式。为了避免遗漏解的可能性，采用不需选择初值的求解方法，给出了稳定尾旋的判据。应用该方法对某型飞机的尾旋进行了预测计算，求出了一个陡尾旋解和一个平尾旋解，计算结果与该飞机尾旋试飞结果吻合较好，表明计算方法是正确的，计算结果可用于指导飞机的尾旋试飞。
On the basis of considering all kinds of factors, it is added how the cross inertia moment effects the steady spin characteristics. The equations are deduced, using which to analyze the steady spin characteristics. The solving method is gived which doesn't required selecting the initial values. The criterion is presented which is suitable to judge whether there is steady spin. Using this method to predict a plane characteristics, the solutions of a step spin and a flat spin are obtained. The result can be used to guide the spin test fly and coincides with that of the flying test.
出处
《飞行力学》
CSCD
北大核心
1998年第2期56-60,共5页
Flight Dynamics
关键词
大迎角
尾旋
稳态解
飞机失速
High angle of attack Spin Steady solution
