Dynamically tuned tail assemblies for rotorcraft
A tail assembly for a rotorcraft having a fuselage and a rotor assembly that generates first and second excitation frequencies. The tail assembly includes a stabilizer having an aft spar and a forward spar. An aft joint couples the aft spar to the fuselage and defines a pitch axis such that the aft joint allows the stabilizer to pivot about the pitch axis. A forward joint couples the forward spar to the fuselage. The forward joint has an axial stiffness configured to tailor a chordwise pivot mode of the stabilizer and a bending stiffness configured to tailor a beamwise bending mode of the stabilizer. The chordwise pivot mode of the stabilizer is below the first excitation frequency, the beamwise bending mode of the stabilizer is above the second excitation frequency and the chordwise pivot mode of the stabilizer is decoupled from the beamwise bending mode of the stabilizer.
1. A tail assembly for a rotorcraft having a fuselage and a rotor assembly that generates first and second excitation frequencies, the tail assembly comprising:
a stabilizer having an aft spar and a forward spar;
an aft joint coupling the aft spar to the fuselage, the aft joint defining a pitch axis such that the aft joint allows the stabilizer to pivot about the pitch axis; and
a forward joint coupling the forward spar to the fuselage, the forward joint having an axial stiffness configured to tailor a chordwise pivot mode of the stabilizer and a bending stiffness configured to tailor a beamwise bending mode of the stabilizer;
wherein, the chordwise pivot mode of the stabilizer is below the first excitation frequency;
wherein, the beamwise bending mode of the stabilizer is above the second excitation frequency; and
wherein, the chordwise pivot mode of the stabilizer is decoupled from the beamwise bending mode of the stabilizer.
2. The tail assembly as recited in claim 1 wherein, the aft joint further comprises a clevis fitting coupled to one of the aft spar or the fuselage and a lug fitting coupled to the other of the aft spar or the fuselage; and
wherein, the clevis fitting and the lug fitting are coupled together by at least one spherical bearing assembly such that the clevis fitting and the lug fitting allow the stabilizer to pivot about the pitch axis.
3. The tail assembly as recited in claim 1 wherein, the aft joint further comprises a clevis fitting coupled to one of the aft spar or the fuselage and a lug fitting coupled to the other of the aft spar or the fuselage; and
wherein, the clevis fitting and the lug fitting are coupled together by first and second spherical bearing assemblies such that the clevis fitting and the lug fitting allow the stabilizer to pivot about the pitch axis.
4. The tail assembly as recited in claim 1 wherein, the forward joint further comprises a shaft coupled to the forward spar by first and second outboard bearings and coupled to the fuselage by first and second inboard bearings, the shaft having an axis extending in an axial direction.
5. The tail assembly as recited in claim 4 wherein, the shaft is a generally cylindrical hollow shaft.
6. The tail assembly as recited in claim 4 wherein, the shaft is a generally cylindrical tapered hollow shaft.
7. The tail assembly as recited in claim 4 wherein, the shaft is formed from a metal.
8. The tail assembly as recited in claim 4 wherein, the first and second outboard bearings are spherical bearings and the first and second inboard bearings are elastomeric journal bearings.
9. The tail assembly as recited in claim 8 wherein, the elastomeric journal bearings define the axial stiffness of the forward joint and allow axial motion of the shaft relative to the fuselage when the stabilizer pivots about the pitch axis.
10. The tail assembly as recited in claim 9 wherein, the shaft and the elastomeric journal bearings define the bending stiffness of the forward joint and allow beamwise bending motion of the stabilizer.
11. The tail assembly as recited in claim 8 wherein, the axis of the shaft is tangent to an arc of rotation about the pitch axis at a location between the elastomeric journal bearings.
12. The tail assembly as recited in claim 4 wherein, the axis of the shaft is tangent to an arc of rotation about the pitch axis at a location between the first and second inboard bearings.
13. The tail assembly as recited in claim 4 wherein, the axis of the shaft is tangent to an arc of rotation about the pitch axis at a location inboard of the first and second outboard bearings.
14. The tail assembly as recited in claim 4 wherein, the first and second outboard bearings are elastomeric journal bearings and the first and second inboard bearings are spherical bearings.
15. The tail assembly as recited in claim 1 wherein, the first excitation frequency is a n/rev frequency, where n is a number of rotor blades of the rotor assembly.
16. The tail assembly as recited in claim 1 wherein, the first excitation frequency is a 3/rev frequency.
17. The tail assembly as recited in claim 1 wherein, the second excitation frequency is a 1/rev frequency.
18. A rotorcraft comprising:
a fuselage;
a rotor assembly rotatably coupled to the fuselage, the rotor assembly generating first and second excitation frequencies;
a tail assembly coupled to the fuselage, the tail assembly comprising:
a stabilizer having an aft spar and a forward spar;
an aft joint coupling the aft spar to the fuselage, the aft joint defining a pitch axis such that the aft joint allows the stabilizer to pivot about the pitch axis; and
a forward joint coupling the forward spar to the fuselage, the forward joint having an axial stiffness configured to tailor a chordwise pivot mode of the stabilizer and a bending stiffness configured to tailor a beamwise bending mode of the stabilizer;
wherein, the chordwise pivot mode of the stabilizer is below the first excitation frequency;
wherein, the beamwise bending mode of the stabilizer is above the second excitation frequency; and
wherein, the chordwise pivot mode of the stabilizer is decoupled from the beamwise bending mode of the stabilizer.
19. The rotorcraft as recited in claim 18 wherein, the tail assembly is a V-tail assembly.
20. A tiltrotor aircraft having a helicopter flight mode and an airplane flight mode, the tiltrotor aircraft comprising:
a fuselage;
a wing coupled to the fuselage;
first and second pylon assemblies rotatable coupled to the wing and configured to selectively operate the tiltrotor aircraft between the helicopter flight mode and the airplane flight mode, each pylon assembly including a proprotor assembly operable to generate first and second excitation frequencies;
a tail assembly coupled to the fuselage, the tail assembly comprising:
a stabilizer having an aft spar and a forward spar;
an aft joint coupling the aft spar to the fuselage, the aft joint defining a pitch axis such that the aft joint allows the stabilizer to pivot about the pitch axis; and
a forward joint coupling the forward spar to the fuselage, the forward joint having an axial stiffness configured to tailor a chordwise pivot mode of the stabilizer and a bending stiffness configured to tailor a beamwise bending mode of the stabilizer;
wherein, the chordwise pivot mode of the stabilizer is below the first excitation frequency;
wherein, the beamwise bending mode of the stabilizer is above the second excitation frequency; and
wherein, the chordwise pivot mode of the stabilizer is decoupled from the beamwise bending mode of the stabilizer.