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一、引言本文是发表在本刊1986年第3期中的“大迎角时的附加偏航导数对飞机稳定性的影响”一文的继续。在前文中曾指出,在大迎角时由于绕流出现非对称分离,将必须计及小迎角时常予忽略的附加纵横向交叉导数。前文中已分析了偏航交叉导数 C_(nα)、C_(?)、C_(?)和 C_(?)对飞行稳定性的严重影响。本文继续分析附加滚转导数 C_1_a、C(?)、C_1_q和 C(?)对飞机运动稳定性的影响以及横侧运动引起的纵向导数 C_m_p、C_(mγ)、和 C(?)。
I. INTRODUCTION This article is the continuation of the article “The Influence of Additional Yaw Derivatives on Aircraft Stability at High Angle of Attack”, published in Issue 3, 1986. It has been pointed out in the foregoing that due to the asymmetric separation of the flow around the high angle of attack, it will be necessary to take account of the additional vertical and horizontal cross-derivatives that are often overlooked at small angles of attack. In the previous section, the severe influence of the yaw cross-derivatives C_ (nα), C_ (?), C_ (?) And C_ (?) On flight stability has been analyzed. In this paper, the influence of additional roll derivatives C_1_a, C_ (), C_1_q and C (Δ) on the stability of aircraft and the longitudinal derivatives C_m_p, C_ (mγ) and C (?) Caused by lateral motion are analyzed.