折叠机翼变体飞机纵向操纵性与稳定性研究

Study on longitudinal maneuverability and stability of folding wing morphing aircraft

针对一种飞翼布局折叠机翼变体飞机方案,建立了相应的研究模型,使用涡格估算方法计算出机翼折叠角度对全机纵向静稳定性的影响。利用飞机纵向小扰动运动方程,分别得到了机翼展开和折叠状态的长、短周期模态,并对其动稳定性进行了讨论。结合工程估算方法和风洞试验方法,计算出内段机翼折叠过程全机力矩系数、升降舵操纵导数以及升降舵配平偏角的变化量。通过对计算结果分析和验证机试飞验证,发现机翼折叠后纵向操纵性存在的问题,并提出了相应的改进措施。

A morphing aircraft could enhance its behavior and performance by varying its state. In this paper,a kind of tailless folding wing morphing aircraft research model was built. Based on this model, the change of folding wing longitudinal static stability in wing folding process was calculated by using the Vortex Lattice Method （VLM）. Through aircraft longitudinal disturbulance equations, the states of wing folded and unfolded of short period mode and phugoid mode were obtained, and then their longitudinal dynamic stabilities were discussed. Integrating the estimations of the engineering and wind tunnel test method, the variation of moment coefficient, elevator control derivatives and the elevator trimangle in wing folding process of the whole aircraftwas calculated. The analysis results and the verification aircraft fly test showthat the longitudinal controllability has some problems when the wing is folded. Against these problems, improvement measures were proposed.