Rotorcraft anti-torque system
There is provided a rotorcraft, including a body, including a front portion and a tail portion; a main rotor system coupled to the front portion of the body, the main rotor system operable to provide a lifting force on the body; and an anti-torque system coupled to the tail portion of the body, the anti-torque system including a primary tail rotor system and a secondary tail rotor system; wherein the primary tail rotor system and the secondary tail rotor system are operable to provide a first anti-torque force and a second anti-torque force. In other aspects, there are methods of providing anti-torque force in a rotorcraft.
1. A rotorcraft, comprising:
a body, including a front portion and a tail portion having a shroud including a primary duct and a secondary duct disposed adjacent to the primary duct, each of the primary duct and the secondary duct extend transversely through the shroud;
a main rotor system coupled to the front portion of the body, the main rotor system operable to provide a lifting force on the body;
an anti-torque system coupled to the tail portion of the body, the anti-torque system comprising a primary tail rotor system disposed in the primary duct and a secondary tail rotor system comprising a first tail rotor assembly disposed in the secondary duct, the first tail rotor assembly having a diameter less than the diameter of the primary tail rotor system;
a powertrain coupled to the body, the powertrain including an engine and a tail rotor drive shaft coupled to the engine, the tail rotor drive shaft being connected to provide mechanical power to the primary tail rotor system; and
an electrical power supply coupled to the body, the electrical power supply being conductively connected to the secondary tail rotor system to provide electrical power thereto;
wherein the primary tail rotor system and the secondary tail rotor system are operable to provide a first anti-torque force and a second anti-torque force.
2. The rotorcraft of claim 1 , wherein the secondary tail rotor system has a faster response time than the primary tail rotor system.
3. The rotorcraft of claim 1 , wherein the first tail rotor assembly is disposed in at least one of the following: a top region of the shroud, a bottom region of the shroud, a leading edge region of the shroud, and a trailing edge region of the shroud.
4. A rotorcraft comprising:
a body, including a front portion and a tail portion having a shroud including a primary duct, a secondary duct disposed adjacent to the primary duct, and a third duct disposed adjacent to the primary duct, each of the primary duct, the secondary duct, and the third duct extend transversely through the shroud;
a main rotor system coupled to the front portion of the body, the main rotor system operable to provide a lifting force on the body;
an anti-torque system coupled to the tail portion of the body, the anti-torque system comprising a primary tail rotor system disposed in the primary duct and a secondary tail rotor system comprising a first tail rotor assembly disposed in the secondary duct and a second tail rotor assembly disposed in the third duct, the first tail rotor assembly and the second tail rotor assembly having a diameter less than the diameter of the primary tail rotor system;
a powertrain coupled to the body, the powertrain including an engine and a tail rotor drive shaft coupled to the engine, the tail rotor drive shaft being connected to provide mechanical power to the primary tail rotor system; and
an electrical power supply coupled to the body, the electrical power supply being conductively connected to the secondary tail rotor system to provide electrical power thereto;
wherein the primary tail rotor system and the secondary tail rotor system are operable to provide a first anti-torque force and a second anti-torque force.
5. The rotorcraft of claim 4 , wherein at least one of the first tail rotor assembly and the second tail rotor assembly is disposed in at least one of the following: a leading edge region of the shroud and a trailing edge region of the shroud.
6. The rotorcraft of claim 4 , wherein at least one of the first tail rotor assembly and the second tail rotor assembly is disposed in at least one of the following: a top region of the shroud and a bottom region of the shroud.
7. The rotorcraft of claim 1 , wherein the secondary tail rotor system comprises at least one of: a plurality of variable pitch secondary blades and/or a plurality of fixed pitch secondary blades.
8. The rotorcraft of claim 1 , further comprising a control system for selectively controlling the operation of each of the primary tail rotor system and the secondary tail rotor system.
9. The rotorcraft of claim 1 , wherein the secondary tail rotor system is configured to selectively provide supplemental anti-torque force to the rotorcraft.