DIVERGENT FLAP ACTUATION SYSTEM FOR A TWO-DIMENSIONAL EXHAUST NOZZLE

摘要

A divergent flap actuation system for a two-dimensional exhaust nozzle for a gas turbine engine powered aircraft includes stationary sidewalls (2) with oppositely disposed movable divergent flaps (10) and (39) located therebetween, and flush mounted rotatable divergent disks (22) and (49) with drive pins (21) and (48) attached thereto for engaging the flaps. Each divergent disk (22) and (49) utilizes an individual actuator (25) and (52) to provide independent movement of the rearward edges (12) and (41) of the flaps (10) and (39) in response to disk rotation. Utilizing flush mounted disks (22) and (49) for controlling the position of the rearward edges (12) and (41) of the opposed flaps (10) and (39) minimizes sidewall thickness and allows use of full length,tapered sidewalls (2) to minimize drag and nozzle weight while maximizing flexibility in thrust control.