中文摘要：

通过建立轴对称推力矢量喷管（AVEN）的构型分岔方程,运用连续同伦方法,研究了AVEN装置驱动机构和扩张调节片导引机构的构型分岔特性,发现,无论推力矢量喷管是否发生偏转,当以喷口面积作为分岔参数时,AVEN装置都存在转向点奇异位置;当以矢量偏转角为分岔参数时,AVEN装置不存在奇异位置。当AVEN装置处于非矢量状态时,扩张调节片导引机构处于多重奇异位置状态。转向点奇异位置和扩张调节片导引机构多重奇异位置,将导致AVEN装置的运动输出具有不确定性,影响含AVEN装置飞机的空中飞行安全。

英文摘要：

Setting up the configuration bifurcation equation of the axisymmetric vectoring exhaust nozzle （AVEN） and utilizing the homotopy tracing approach, the configuration bifurcation behaviors of the AVEN driving parallel mechanism and the driving kinematic chains of the divergent flaps were analyzed. It is found that whether deflecting or not, the turning points will exist corresponding to the bifurcation parameter of the area exhaust nozzle, and the turning points will disappear corresponding to the bifurcation parameters of the deflecting angle. While the AVEN is in non-vector status, the driving kinematic chain of di vergent flaps is at its multi-singular position. Both the turning points and multi singular positions will lead the motion of the AVEN uncertain. This kind of motion uncertainty is harm ful to the safety of aircrafts equipped with the AVEN.