IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0057280
(2009-06-26)
|
등록번호 |
US-8556207
(2013-10-15)
|
우선권정보 |
IT-RM2008A0424 (2008-08-04) |
국제출원번호 |
PCT/IT2009/000282
(2009-06-26)
|
§371/§102 date |
20110203
(20110203)
|
국제공개번호 |
WO2010/016080
(2010-02-11)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
3 |
초록
▼
An aircraft with preferably coaxial counter-rotating sustaining rotors includes in combination: elements for variation of the collective pitch, i.e., for applying simultaneously one and the same variation to the incidence of all the blades of the rotors; and elements for controlling the attitude and
An aircraft with preferably coaxial counter-rotating sustaining rotors includes in combination: elements for variation of the collective pitch, i.e., for applying simultaneously one and the same variation to the incidence of all the blades of the rotors; and elements for controlling the attitude and direction of flight, which by generating appropriate aerodynamic forces via the sustaining rotor wind eliminate the need for the presence of elements for variation of the cyclic pitch of the blades of the rotors themselves.
대표청구항
▼
1. An aircraft with counter-rotating sustaining rotors (4, 5), comprising: a rotor control head, said rotors operatively connected to the rotor control head; a collective pitch variation control (9) operatively connected to said rotors (4, 5), said collective pitch variation control, via the rotor c
1. An aircraft with counter-rotating sustaining rotors (4, 5), comprising: a rotor control head, said rotors operatively connected to the rotor control head; a collective pitch variation control (9) operatively connected to said rotors (4, 5), said collective pitch variation control, via the rotor control head, simultaneously applying an equivalent variation to an incidence of all blades of said rotors (4, 5) varying the collective pitch of said rotors, said rotors (4, 5) being counter-rotating sustaining coaxial rotors; andan attitude and direction flight control generating aerodynamic forces via sustaining rotor wind from said blades of said rotors (4, 5), the aircraft being free of elements for variation of cyclic pitch of the blades of the rotors,the attitude and direction flight control comprising governing surfaces including two governing surfaces (2, 3) placed in a back part of the aircraft, and a control element (8) operatively connected to said two governing surfaces functioning to move said two governing surfaces with respect to each other in order to produce a pitching movement of the whole aircraft,the rotor has a fixed substantially vertical axis,said governing surfaces are substantially constituted by three governing surfaces defined by three ailerons (1, 2, 3), andeach of the three ailerons move independently to control the yaw. 2. The aircraft according to claim 1, wherein said counter-rotating rotors comprise a top rotor (4) and a bottom rotor (5), said top and bottom rotors (4, 5) sharing a common axis, andsaid collective pitch variation control (9) comprises a collective-pitch control lever (9) operatively connected to said top and bottom rotors (4, 5) and only and exclusively controlling the simultaneous and equivalent variation of the incidence of the blades of both of the sustaining rotors. 3. The aircraft according to claim 2, wherein said collective pitch variation control (9) comprises two rotating, but non-oscillating, disks (27, 31), arranged to vary inclination of the blades of the rotors (4, 5), said rotating, but non-oscillating, disks (27, 31) being located in the rotor control head. 4. The aircraft according to claim 3, further comprising: a collective-pitch control kinematic chain originates from the collective-pitch control lever (9) and is movable upwards or downwards by the collective-pitch control lever (9),said collective-pitch control lever (9) being fixed with respect to an arm (12), arranged to move a tie rod (13), which causes rotation of a lever (15), pivoted on a pin (16) governing an articulated tie rod (17), arranged to move axially upwards and downwards to govern displacement upwards and downwards of a control head (18), wherein,the control head (18) is equipped with two bearings (19, 20) that roll on a bottom flange (21) fixed with respect to a sleeve (22), andsaid sleeve (22) being free to slide axially on an outer coaxial shaft (23) turning fixedly with respect thereto, and drawn along by longitudinal rods (24, 25) fixed with the respect to the sleeve (22). 5. The aircraft according to claim 4, wherein, said longitudinal rods (24, 25) traverse freely a head (26) of the bottom rotor (5) fixed rigidly to said outer shaft (23),said longitudinal rods (24, 25) sliding freely in an axial direction within said head (26) and being drawn along thereby in rotation,said head (26) of the bottom rotor (5) comprises a first of said two non-oscillating disks (27) fitted rigidly on the sleeve (22) so as to follow bothi) rotation of the sleeve (22), governed by the outer coaxial shaft (23) by means of the rods (24, 25) via the head (26) of the bottom rotor (5), andii) axial translation of the sleeve (22), governed by the control head (18),articulated tie rods (28, 29) anchored, in an articulated way, on the first non-oscillating disk (27) and to a trailing edge of the bottom rotor (5), the articulated tie rods (28, 29) arranged to move the trailing edge of the respective blades of the bottom rotor (5) to turn the respective blades of the bottom rotor in perfect synchronism with the first non-oscillating disk (27) under control of said outer coaxial shaft (23),the blades of the bottom rotor (5) are fitted to shafts that join the blades of the bottom rotor to the head (26) with exactly one degree of freedom that enables variation of the collective pitch thereof, andthe articulated tie rods (28, 29) apply translational movement of the disk (27) to provide a displacement to the trailing edge of the respective blade of the bottom rotor (5) and thereby producing a corresponding variation of the incidence of each of the blades of the bottom rotor (5). 6. The aircraft according to claim 5, wherein, said longitudinal rods (24, 25) undergo axial movement, and said axial movement of said longitudinal rods (24, 25) is transmitted to change a pitch of the top rotor (4),an inner disk (30) is associated with a second of said rotating, but non-oscillating, disks (31), said second non-oscillating disk (31) being an outer disk (31), both said inner disk (30) and said outer ring (31) being non-oscillating,a thrust bearing (33) is located between the inner disk (30) and the outer disked (31),said longitudinal rods (24, 25) transmit their axial translation to the inner disk (30) andthe outer disk (31), in response to the transmission of the axial translation of the longitudinal roads (24, 25) to the inner disk (30), turns in a direction opposite to the disk (30), on account of a decoupling action provided by the thrust bearing (33). 7. The aircraft according to claim 6, wherein, within said inner disk (30), an inner shaft (32) turns freely and in an opposite direction to said inner disk (30), without any mechanical interference,the translational movement of the outer ring (31) remains always identical to the translational movement of the bottom flange (21),further articulated tie rods (34, 35) anchored to the outer ring (31), the further articulated tie rods (34, 35) actuated by the first non-oscillating disk (27) and following both rotation and axial translation of the first non-oscillating disk (27) to simultaneously bring about an identical displacement on trailing edge of the blades of the top and bottom rotors (4, 5). 8. The aircraft according to claim 2, wherein,said collective pitch variation control (9) produces the simultaneous and equivalent variation of the incidence of all the blades of the rotors (4, 5) for positive incidence of leading angles of the blades reaches values greater than or equal to 12° , and for negative incidence of the leading angles reaches values higher than 45° ,said collective pitch variation control (9) comprises a collective-pitch control lever (9) and two rotating, but non-oscillating, disks (27, 31), arranged to vary inclination of the blades of the rotors (4, 5), said rotating, but non-oscillating, disks (27, 31) being positioned in proximity of the rotors,said rotating, but non-oscillating, disks (27, 31) sliding on respective shafts by transmissions coming from the control lever (9). 9. The aircraft according to claim 2, wherein, the blades of the rotors (4, 5) are each equipped with a corresponding and separate end mass having an aerodynamic shape,the end masses each having i) a first end and ii) a second, opposite end, the first and second ends corresponding to edges of the corresponding blade,the end masses stiffened the blades by centrifugal force during rotation,the end masses enabling the rotors to accumulate a greater amount of kinetic energy duration rotation. 10. The aircraft according to claim 1, wherein, said two governing surfaces (2, 3) placed in the back part of the aircraft connected to control element (8) are defined by two lateral rear ailerons (2 and 3) arranged in a rear part of the fuselage, symmetrically with respect to a longitudinal axis of the aircraft, with respective axes of rotation lying in horizontal plane passing through a center of a gravity of the aircraft,the third governing surface is defined by a third, front aileron (1) positioned at a prow of the aircraft, on the longitudinal axis of the aircraft, the third aileron (1) having an axis of rotation lying in the horizontal plane passing through the center of gravity of the machine,the control element (8) is a joystick (8) and movement of the two lateral rear ailerons (2, 3) is governed by the pilot through the joystick (8), which joystick performs only the function to move said two lateral rear ailerons with respect to each other in order to produce a pitching movement of the whole aircraft,the attitude and direction flight control further comprises two pedals (10-11) operatively connected to said front aileron (1), said front aileron being actuated by the pilot by operation of the pedals (10-11), the pedals performing the single and specific function of actuating said front aileron,said three ailerons (1, 2, 3) are placed underneath the rotors (4, 5), in a horizontal plane parallel to a fixed plane of rotation of the rotors and passing through the center of gravity of the aircraft, andin conditions of fixed-point stationary flight a wing chord of said ailerons is kept parallel to the axis of rotation of the rotors (4, 5). 11. The aircraft according to claim 10, wherein, a kinematic control chain connects the control lever (8) and the two rear ailerons (2, 3),management of the lateral attitude is controlled by the two rear ailerons (2, 3), andinstantaneous position of the two rear ailerons (2, 3) is determined by the pilot moving the control lever (8) through the kinematic control chain. 12. The aircraft according to claim 11, wherein, the kinematic control chain connecting the control lever (8) and the two rear ailerons (2, 3) comprises two specular kinematic control chains actuated by the control lever (8) via a respective right-hand half-shaft (41) and left-hand half-shaft (42), each of the right-hand half-shaft (41) and left-hand half-shaft (42) rigidly connected to a corresponding outer bevel gear (43, 44),movement applied by the pilot on the control lever (8) reaches the ailerons (2, 3) through the two specular kinematic control chains actuated by the control lever (8),the control lever (8) is fixed to a vertical L-shaped bracket (36), on which L-shaped bracket (36) a central bevel gear (38) is fixed via a shaft that freely traverses a horizontal C-shaped bracket (37),the C-shaped bracket (37) having a central bevel gear (38) that always meshes with two lateral bevel gears (39, 40), which are coaxial and opposed to one another,the control lever (8) is turnable forwards and backwards about an axis of rotation of the two lateral bevel gears (39, 40), about an axis of the central bevel gear (38),said lateral bevel gears (39, 40) are fixed with respect to an end of the respective right-hand half-shaft (41) and left-hand half-shaft (42), the lateral bevel gears (39, 40) meshing with the central bevel gear (38) being ensured by said C-shaped bracket (37),the right-hand and left-hand half-shafts (41, 42) are free to turn with respect to the C-shaped bracket (37). 13. The aircraft according to claim 12, wherein, said outer bevel gears (43, 44) in turn move transmission bevel gears (45, 46) respectively, governing longitudinal rods (47, 48),the longitudinal rods (47, 48), via constant-velocity universal joints (49, 50) and further transmission rods (51, 52), transmit, respectively, to the right-hand aileron (2) and left-hand aileron (3), commands generated by the control lever (8),by movement of the control lever (8) forwards and backwards longitudinally, the respective top leading edges of the rear ailerons (2, 3) approach one another and move away from one another and the bottom leading edges of the rear ailerons (2, 3) move away from one another and approach one another,by movement of the control lever (8) to the right/left transversely the two rear ailerons (2, 3) move with concordant motion but in the opposite direction to the direction in which the lever itself is moved, and other movement of the control lever (8) being a vector sum of components of the displacement along longitudinal and transverse reference axes. 14. The aircraft according to claim 10, wherein, said two pedals comprise a right-hand pedal (10) and a left-hand pedal (11), the pedals (10, 11) moved by the pilot's feet,said pedals connected to corresponding L-shaped brackets (49, 50) and transverse arms (51, 52) of a pantograph parallelepiped;a central bevel gear (53) is provided, fixed with respect to one of the transverse arms (52),the central bevel gears moves a bevel gear (54) and thereby a shaft (55) for rotation of the front aileron (1),i) pushing the right-hand pedal (10) forward inclines the top leading edge of the front aileron (1) to the right, and ii) pushing the left-hand pedal (11) forward inclines the top leading edge of the front aileron (1) to the left, thus obtaining when the control lever (8) is kept at center, turning of the aircraft on the aircraft's axis of yaw on the side of the pedal that is pushed forward. 15. The aircraft according to claim 1, wherein the blades of the rotors (4, 5) are equipped with additional end masses having an aerodynamic shape corresponding to a cross-section shape of the blades and opposite ends corresponding to edges of the blades, which, enable the rotors to accumulate a greater amount of kinetic energy. 16. The aircraft according to claim 1, further comprising:two counter-rotating coaxial shafts, each of the coaxial shafts controlling a respective one of the rotors (4, 5),one engine,one transmission,a decoupling chain present between the engine and the coaxial shafts for controlling the rotors, andone train of gears that reverses a direction of rotation of the coaxial shafts. 17. The aircraft according to claim 1, wherein,said collective pitch variation control (9) produces the simultaneous and equivalent variation of the incidence of all the blades of the rotors (4, 5) for positive incidence of leading angles of the blades reaches values greater than or equal to 12° , and for negative incidence of the leading angles reaches values higher than 45°,said collective pitch variation control (9) comprises a collective-pitch control lever (9) and two rotating, but non-oscillating, disks (27, 31), arranged to vary inclination of the blades of the rotors (4, 5), said rotating, but non-oscillating, disks (27, 31) being positioned in proximity of the rotors,said rotating, but non-oscillating, disks (27, 31) sliding on respective shafts by transmissions coming from the control lever (9).
※ AI-Helper는 부적절한 답변을 할 수 있습니다.