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。 Aiming at a scheme of flying wing layout folding wing variant aircraft, a corresponding research model was established and the influence of wing folding angle on the whole machine longitudinal static stability was calculated by using the method of estimation of the squiggle. The long and short period modes of the unfolded and folded states of the wings were obtained respectively by using the small perturbed equations of motion of the aircraft, and the dynamic stability of the wings was discussed. Combined with the engineering estimation method and the wind tunnel test method, the variation factors of full-machine moment coefficient, elevator steering derivative and elevator declination are calculated. Through the analysis of the calculation results and verification test flight test, the problems of longitudinal maneuverability after wing folding are found, and the corresponding improvement measures are put forward.