碟形飞行器是一种新颖的,采用翼身融合布局的飞行器.为获得碟形飞行器在低速条件下的总体特性,对其进行了风洞测力和动导数测量试验,结合稳定性分析和模型试飞研究了其总体性能.研究结果表明:碟形飞行器最大升阻比为12.2,失速迎角28°,全机纵向模态稳定,横航向滚转模态和荷兰滚模态稳定,螺旋模态发散,具有良好的飞行品质和综合性能. As a new type of aircraft with fuselage and fuselage layout, the aircraft is tested by wind tunnel dynamometer and dynamic derivative in order to obtain the overall characteristics of the aircraft under low speed. Combining the stability analysis and the model The test results show that the maximum lift-drag ratio of the aircraft is 12.2, the angle of attack is 28 °, the longitudinal mode of the whole machine is stable, the roll mode of lateral direction and the roll mode of Netherlands are stable, and the helical mode Divergent, with good flight quality and overall performance.