关键词: 航空航天推进系统;球型收敛调节片喷管;矢量推力;内特性

Abstract: Numerical simulations were conducted on the 2-D convergent-divergent vector nozzles with spherical convergent flap to evaluate the static internal performance of vectored and unvectored nozzles.It was performed to analyze the effects of the geometric pitch and yaw vector angles on the discharge coefficient and resultant gross-thrust ratio,and the relationship between pressure ratios and the resultant thrust vector angle.All the nozzles have the same throat aspect ratio of 2.083.Results of the study indicate that the effect of geometric vector angles on Cv,and Cd was small(less than 3%).Because the pitch vectoring was accomplished by simultaneous deflection of the upper and lower divergent flaps,it caused lower resultant thrust ratio than the yaw vectoring did.A peak resultant vector angle which was larger than the geometric vector angle occurred at NPR below design,and the resultant vector angle was close to the geometric vector angle at NPR above design.But the resultant yaw thrust angles were nearly independent of NPR.

Key words: Aerospace propulsion system;Spherical convergent flap nozzle;Vector thrust;Internal performance