According to one embodiment, an empennage attachment system features an aft attachment mechanism and a forward attachment system. The aft attachment mechanism is configured to be coupled to a tail section of a body of an aircraft and to an empennage proximate to an aft spar of the empennage. The aft
According to one embodiment, an empennage attachment system features an aft attachment mechanism and a forward attachment system. The aft attachment mechanism is configured to be coupled to a tail section of a body of an aircraft and to an empennage proximate to an aft spar of the empennage. The aft attachment mechanism defines a pitch axis such that the aft attachment mechanism allows the empennage to rotate about the pitch axis. The forward attachment system is configured to be coupled to the tail section of the body and to the empennage proximate to a forward spar of the empennage. The forward attachment system is configured to restrict rotation of the empennage about the pitch axis to an allowable range of motion.
대표청구항▼
1. A tiltrotor aircraft, comprising: a body;a wing member;a power train coupled to the body and comprising a power source and a drive shaft in mechanical communication with the power source;a plurality of rotor blades comprising a first rotor blade, a second rotor blade, and a third rotor blade;a ro
1. A tiltrotor aircraft, comprising: a body;a wing member;a power train coupled to the body and comprising a power source and a drive shaft in mechanical communication with the power source;a plurality of rotor blades comprising a first rotor blade, a second rotor blade, and a third rotor blade;a rotor system coupled to the wing member and in mechanical communication with the drive shaft, at least part of the rotor system being tiltable between a helicopter mode position and an airplane mode position;an empennage, the empennage comprising an aft spar and a forward spar;an aft attachment mechanism coupled to a tail section of the body and to the empennage proximate to the aft spar, the aft attachment mechanism defining a pitch axis such that the aft attachment mechanism allows the empennage to rotate about the pitch axis; anda forward attachment system coupled to the tail section of the body and to the empennage proximate to the forward spar, the forward attachment system configured to restrict rotation of the empennage about the pitch axis to an allowable range of motion, the forward attachment system comprising: an outer member;an inner member disposed at least partially within the outer member; andat least one pad configured to restrict the movement of the inner member relative to the outer member. 2. The tiltrotor of claim 1, wherein the aft attachment mechanism comprises an elongated pin defining the pitch axis and a receiver portion coupled at least partially about the elongated pin and configured to rotate about the elongated pin. 3. The tiltrotor of claim 1, wherein the at least one pad is comprised of a material selected from the group consisting of elastomer materials, silicone, and composite materials. 4. The tiltrotor of claim 1, wherein the at least one pad is an elastomer material bonded to both the inner member and to the outer member. 5. The tiltrotor of claim 1, wherein the at least one pad is disposed between the inner member and the outer member such that the at least one pad prevents the inner member from contacting the outer member. 6. The tiltrotor of claim 1, wherein the inner member is coupled to the forward spar, and the outer member is coupled to the fuselage. 7. The tiltrotor of claim 1, wherein the inner member is configured to travel along a curved path within the outer member. 8. The tiltrotor of claim 7, wherein an inner chamber of the outer member is symmetrical about a straight-line axis, and the curved path passes through the inner chamber. 9. An aircraft, comprising: a body;an empennage, the empennage comprising an aft spar and a forward spar;an aft attachment mechanism coupled to a tail section of the body and to the empennage proximate to the aft spar, the aft attachment mechanism defining a pitch axis such that the aft attachment mechanism allows the empennage to rotate about the pitch axis; anda forward attachment system coupled to the tail section of the body and to the empennage proximate to the forward spar, and configured to restrict rotation of the empennage about the pitch axis to an allowable range of motion, the forward attachment system comprising: an outer member;an inner member disposed at least partially within the outer member; andat least one pad configured to restrict the movement of the inner member relative to the outer member. 10. The aircraft of claim 9, wherein the aft attachment mechanism comprises an elongated pin defining the pitch axis and a receiver portion coupled at least partially about the elongated pin and configured to rotate about the elongated pin. 11. The aircraft of claim 9, wherein the at least one pad is comprised of a material selected from the group consisting of elastomer materials, silicone, and composite materials. 12. The aircraft of claim 9, wherein the at least one pad is an elastomer material bonded to both the inner member and to the outer member. 13. The aircraft of claim 9, wherein the at least one pad is disposed between the inner member and the outer member such that the at least one pad prevents the inner member from contacting the outer member. 14. The aircraft of claim 9, wherein the outer member is coupled to the forward spar, and the inner member is coupled to the fuselage. 15. The aircraft of claim 9, wherein the inner member is configured to travel along a curved path within the outer member. 16. The aircraft of claim 15, wherein an inner chamber of the outer member is symmetrical about a straight-line axis, and the curved path passes through the inner chamber. 17. An empennage attachment system, comprising: an aft attachment mechanism configured to be coupled to a tail section of a body of an aircraft and to an empennage proximate to an aft spar of the empennage, the aft attachment mechanism defining a pitch axis such that the aft attachment mechanism allows the empennage to rotate about the pitch axis; anda forward attachment system coupled to the tail section of the body and to the empennage proximate to the forward spar, and configured to restrict rotation of the empennage about the pitch axis to an allowable range of motion, the forward attachment system comprising: an outer member;an inner member disposed at least partially within the outer member; andat least one pad configured to restrict the movement of the inner member relative to the outer member. 18. An aircraft, comprising: a body;an empennage, the empennage comprising a first spar and a second spar;a rotational attachment mechanism coupled to a tail section of the body and to the empennage proximate to the second spar, the rotational attachment mechanism defining a pitch axis such that the rotational attachment mechanism allows the empennage to rotate about the pitch axis; anda limiting attachment system coupled to the tail section of the body and to the empennage proximate to the first spar, and configured to restrict rotation of the empennage about the pitch axis to an allowable range of motion, the limiting attachment system comprising: an outer member;an inner member disposed at least partially within the outer member; andat least one pad configured to restrict the movement of the inner member relative to the outer member. 19. The aircraft of claim 18, wherein the rotational attachment mechanism comprises an elongated pin defining the pitch axis and a receiver portion coupled at least partially about the elongated pin and configured to rotate about the elongated pin. 20. The aircraft of claim 18, wherein the at least one pad is comprised of a material selected from the group consisting of elastomer materials, silicone, and composite materials. 21. The aircraft of claim 18, wherein the at least one pad is an elastomer material bonded to both the inner member and to the outer member. 22. The aircraft of claim 18, wherein the at least one pad is disposed between the inner member and the outer member such that the at least one pad prevents the inner member from contacting the outer member. 23. The aircraft of claim 18, wherein the inner member is coupled to the first spar, and the outer member is coupled to the fuselage. 24. The aircraft of claim 18, wherein the inner member is configured to travel along a curved path within the outer member. 25. The aircraft of claim 24, wherein an inner chamber of the outer member is symmetrical about a straight-line axis, and the curved path passes through the inner chamber.
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이 특허에 인용된 특허 (10)
Reed ; III Wilmer H. (Hampton VA), Active control device for aircraft tail buffet alleviation.
Ross, Brent C.; Bockmiller, David R.; McCullough, John R.; Carlson, David G., Fixed engine and rotating proprotor arrangement for a tiltrotor aircraft.
Kuczynski William A. (Branford CT) Marshall ; II ; deceased John (late of Cheshire CT by Ruth Ann D. Marshall ; administratrix), Helicopter with stabilator detuned in antisymmetric vibration modes from main rotor wake excitation frequency.
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