Active flow control system
An aircraft is provided and includes a fuselage including a top and a tail, a main rotor apparatus disposed at the top of the fuselage, which rotates one or more rotors to generate lift, and an active flow control (AFC) system. The AFC system includes plasma actuators configured to generate plasma at a location adjacent to the main rotor apparatus and/or at the tail of the fuselage.
1. An aircraft, comprising:
a fuselage comprising a top and a tail;
a main rotor apparatus disposed at the top of the fuselage which rotates one or more rotors to generate lift; and
an active flow control (AFC) system including plasma actuators configured to generate plasma at a location adjacent to the main rotor apparatus and at the tail of the fuselage.
2. The aircraft according to either of claim 1 , wherein the plasma actuators are elongate.
3. The aircraft according to claim 1 , wherein the plasma actuators are curved.
4. The aircraft according to claim 1 , wherein the main rotor apparatus comprises a sail fairing and coaxial sets of counter rotating rotor blades separated by the sail fairing, the fuselage comprises a hub fairing at the top of the fuselage adjacent to the main rotor blade, and the plasma actuators are disposed on one or both of the sail fairing of the main rotor apparatus and the hub fairing of the fuselage.
5. An aircraft, comprising:
a fuselage having a main portion, a top portion at an upper part of the main portion and a tail portion at an aft end of the main portion, the fuselage comprising a hub pylon at the top portion and an aft fuselage section at the tail portion;
a main rotor apparatus disposed at the top portion and comprising a sail fairing between upper and lower rotor hubs, upper blades extending from the upper rotor hub and lower blades extending from the lower rotor hub;
an auxiliary propulsor section disposed at the tail portion; and
an active flow control (AFC) system including plasma actuators configured to generate plasma at the tail portion and one or more of the main portion proximate to the hub pylon, the hub pylon, and the sail fairing.
6. The aircraft according to claim 5 , wherein the plasma actuators are curved along the lateral surfaces of the hub pylon.
7. The aircraft according to claim 5 , wherein the aft fuselage section comprises:
stabilizer elements; and
a pylon protruding from upper surfaces of the stabilizer elements and including an upper pylon surface,
wherein the plasma actuators are disposed on one or more of the upper surfaces of the stabilizer elements and the upper pylon surface.
8. The aircraft according to claim 5 , wherein the hub pylon comprises an upper surface and lateral surfaces extending from the main portion to the upper surface.
9. The aircraft according to claim 8 , wherein the plasma actuators are disposed on one or more of the upper and lateral surfaces of the hub pylon and on the main portion of the fuselage proximate to the hub pylon.
10. The aircraft according to claim 8 , wherein the plasma actuators are elongate and extend along the lateral surfaces of the hub pylon or along the main portion proximate to the hub pylon.
11. The aircraft according to claim 5 , wherein the sail fairing comprises a tapered trailing edge portion terminating aft of the upper and lower rotor hubs.
12. The aircraft according to claim 11 , wherein the plasma actuators are disposed on one or more of lateral and upper surfaces of the sail fairing.
13. The aircraft according to claim 12 , wherein the plasma actuators are elongate and extend along the lateral surfaces of the sail fairing.