Tilting duct compound helicopter
A rotorcraft that utilizes both a main compound rotor and a plurality of tiltrotors is disclosed. The main rotor and the thrusters can provide vertical lift for vertical take-off and landing of the rotorcraft. The thrusters of the rotorcraft can articulate to a horizontal position to facilitate horizontal flight. The main rotor of the rotorcraft can continue to provide vertical lift for the rotorcraft in horizontal flight, as well as operate in an autorotation mode. In the event of a failure of the main power source of the rotorcraft, the main rotor in autorotation mode can safety land the rotorcraft. In the autorotation mode, the main rotor can create electrical energy that is stored in a battery and can be used to power the plurality of thrusters. The rotorcraft can also be configured in an anti-torque mode, where the thrusters cancel out the torque of the main rotor.
1. A compound rotorcraft, comprising:
an airframe structure;
a plurality of thrusters operably coupled to the airframe structure, the thrusters operably rotatable between a vertical lift position and a horizontal cruise position, the thrusters configured to provide vertical thrust in the vertical lift position and horizontal thrust in the horizontal cruise position at a cruise speed; and
a main rotor operably coupled to the airframe structure, the main rotor configured to operate in an autorotation mode when the rotorcraft reaches the cruise speed in horizontal flight, the main rotor configured to generate electrical energy while operating in autorotation mode,
wherein, in the event of a failure of a primary energy source, the main rotor is configured to continue in the autorotation mode and generate electrical energy driving the plurality of thrusters.
2. The rotorcraft of claim 1 , further comprising a battery configured to store the electrical energy generated by the main rotor assembly.
3. The rotorcraft of claim 2 , wherein the electrical energy stored by the battery is configured to power the plurality of thrusters.
4. The rotorcraft of claim 1 , wherein the plurality of thrusters are ducted fans.
5. The rotorcraft of claim 1 , wherein the main rotor is further configured to generate vertical lift.
6. The rotorcraft of claim 1 , wherein the main rotor is further configured to generate vertical lift when operating in the autorotation mode.
7. The rotorcraft of claim 1 , further comprising a primary energy source configured to power the plurality of thrusters.
8. The rotorcraft of claim 7 , wherein the primary energy source is a battery.
9. The rotorcraft of claim 1 , wherein the airframe structure is a fuselage.
10. The rotorcraft of claim 1 , wherein the main rotor mechanically disengages a drive system in the autorotation mode.