Propulsive anti-torque system for rotorcraft

A rotorcraft having an engine for driving a rotor system comprising:

• a plurality of wings disposed on the side of the rotorcraft to provide lift compounding;
• and
• a pneumatic propulsive anti-torque system comprising:
• a tail boom disposed at the aft end of the rotorcraft;
• a fan module disposed in the tail boom and driven by the engine for producing a flow of compressed air through the tail boom;
• adjustable spillage doors disposed near the aft end of the tail boom for selectively releasing excess airflow from within the tail boom and for selectively controlling a temperature within the duct system;
• and
• a thrust nozzle disposed at the end of the tail boom for selectively producing anti-torque thrust and forward thrust, wherein the thrust nozzle comprises:
• a plurality of articulating control vanes which pivot about an axis that is generally vertical relative to the tail boom and disposed at the aft end of the tail boom for selectively controlling the anti-torque thrust and forward thrust. wherein the control vanes articulate between a left-thrust mode in which the control vanes are pivoted relative to the tail boom and to one another so as to direct the air flow from to the left of the tail boom, thereby producing left thrust;
• a right-thrust mode in which the control vanes are pivoted relative to the tail boom and to one another so as to direct the air flow to the right of the tail boom, thereby producing right thrust;
• and a forward thrust mode in which the control vanes are aligned longitudinally so as to direct the air flow out the aft end of the tail boom, thereby producing forward thrust.

A rotorcraft, comprising:

• a tail boom disposed at the aft end of the rotorcraft;
• an engine disposed in the tail boom for providing torque to a rotor system of the rotorcraft;
• a fan module disposed in the tail boom and driven by the engine for producing a flow of compressed air through the tail boom;
• a thrust nozzle disposed at the end of the tail boom for selectively producing anti-torque thrust and forward thrust;
• and
• a plurality of sets of control vanes configured so that the control vanes within each set are located adjacently in a longitudinal direction, such that adjacent control vanes within each set are pivotally connected to each other;
• wherein each control vane within a set of control vanes is configured to pivot on a generally vertical axis;
• and
• wherein the fan module is located in relation to the engine, such that the compressed air flow from the fan module is mixed with exhaust from the engine to cool the exhaust from the engine.