A drive link assembly includes a case having a spherically formed inner ring. A clevis is affixed to a surface of the case such that is disposed horizontally between a first end and a second end of the clevis. A spacer having a spherical inset portion is positioned on the surface horizontally between the clevis and the spherically formed inner ring, such that the spherical inset portion is aligned with the spherically formed inner ring. A spherical bearing is seated within the spherically formed inner ring. A rod is affixed to an outer surface of the spherical bearing.

Aspects of the disclosure are directed to a system of an aircraft, comprising: at least one fairing, a liner, and an actuator configured to cause the at least one fairing to be translated relative to the liner in order to obtain a modulation of a metering area between the liner and the at least one fairing.

An articulating exhaust nozzle thrust reverser includes an outer articulating panel comprising an outer skin and an outer thrust reverser door and an inner articulating panel comprising a forward inner skin, an aft inner skin, and an inner thrust reverser door. The outer articulating panel is configured to pivot to vary a nozzle exit area. The forward inner skin is configured to pivot to vary a nozzle throat area. The outer thrust reverser door is pivotally coupled to the outer skin. The inner thrust reverser door is pivotally coupled to the aft inner skin. The outer articulating panel and the inner articulating panel may be individually operated to independently vary the exhaust nozzle throat area and/or the exhaust nozzle exit area.

A thrust reverser includes an outer articulating panel and an inner articulating panel. The outer articulating panel includes an outer thrust reverser door pivotally coupled to the outer articulating panel. The outer thrust reverser door is movable between an outer door stowed position and an outer door deployed position with respect to the outer articulating panel. The inner articulating panel includes an inner thrust reverser door pivotally coupled to the inner articulating panel. The inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel. The inner thrust reverser door and the outer thrust reverser door are configured to redirect exhaust gasses to generate reverse thrust to an aircraft when the thrust reverser doors are in the deployed positions.