Anti-vibration moment generating aircraft actuation system
An aircraft is provided and includes an airframe, an engine, a drive portion driven by the engine, a rotor apparatus, which includes a rotor rotatable relative to the airframe and a fairing, a gearbox disposed to transmit rotational energy from the drive portion to the rotor to drive the rotor to rotate relative to the airframe and which generates a rotor rotation vibration, support members by which the gearbox is disposed on the airframe and an actuation system including actuation elements disposed at the fairing, the actuation system being configured to generate an anti-vibration moment using the actuation elements disposed at the fairing to counter the rotor rotation vibration.
1. An aircraft, comprising:
an airframe;
an engine;
a drive portion driven by the engine;
a rotor apparatus, which includes a rotor rotatable relative to the airframe and a fairing;
a gearbox disposed to transmit rotational energy from the drive portion to the rotor to drive the rotor to rotate relative to the airframe and which generates a rotor rotation vibration;
support members by which the gearbox is disposed on the airframe; and
an actuation system including actuation elements mounted to the fairing, and at least one of the gearbox and each of the support members, the actuation system being configured to generate an anti-vibration moment using the actuation elements disposed at the fairing to counter the rotor rotation vibration.
2. The aircraft according to claim 1 , wherein the actuation system comprises an active vibration control system configured to control operations of the actuation elements.
3. The aircraft according to claim 1 , wherein the actuation elements are controlled via wiring.
4. The aircraft according to claim 1 , wherein the actuation elements are wirelessly controlled, and the actuation elements disposed at the fairing further comprise a power source which powers the actuation elements disposed at the fairing.
5. The aircraft according to claim 1 , wherein the anti-vibration moment is adjustable in magnitude, phase and frequency.
6. The aircraft according to claim 1 , wherein the rotor comprises:
an upper rotor, which is rotatable relative to the airframe in a first direction; and
a lower rotor, which is rotatable relative to the airframe in a second direction opposite the first direction.
7. The aircraft according to claim 6 , wherein the fairing is disposed between the upper and lower rotors and is hollow.
8. The aircraft according to claim 1 , wherein the actuation elements comprise first, second and third single-point actuators disposed within the fairing.
9. The aircraft according to claim 8 , wherein the first, second and third single-point actuators are transversely oriented with respect to one another to drive respective anti-vibration loads in substantially orthogonal directions.
10. An actuation system of an aircraft comprising coaxial, counter rotating rotors rotatable relative to an airframe, a fairing disposed between the rotors, a gearbox disposed to transmit rotational energy to the rotors to drive rotor rotation and support members by which the gearbox is disposed on the airframe, the actuation system comprising:
actuation elements mounted to the fairing, and at least one of the gearbox and each of the support members; and
an active vibration control system configured to control the actuation elements at the fairing to generate an anti-vibration moment to counter rotor rotation vibration.
11. The actuation system according to claim 10 , further comprising an actuator disposed on at least one or both of the gearbox and one or more of the support members, wherein the active vibration control system is further configured to control the actuation elements at the gearbox and the support members to generate an anti-vibration moment to counter rotor rotation vibration.
12. The actuation system according to claim 10 , wherein the actuation elements are wirelessly controlled.
13. The actuation system according to claim 10 , wherein the actuation elements disposed at the fairing comprise first, second and third single-point actuators within the fairing.
14. The actuation system according to claim 13 , wherein the first, second and third single-point actuators are transversely oriented with respect to one another.