Search

CN-110446657-B - Aircraft capable of hovering

CN110446657BCN 110446657 BCN110446657 BCN 110446657BCN-110446657-B

Abstract

Disclosed is a rotor for an aircraft capable of hovering, comprising: fixing the support structure; a rotating element rotatable about an axis relative to the fixed support structure; at least one paddle operatively connected with the rotating element; a source of magnetic field that is fixed or driven to rotate at a first rotational speed; and a conductive element operatively connected to the rotational element and drivable to rotate at a second rotational speed different from the first rotational speed; the electrically conductive element is electromagnetically coupled with the source so as to magnetically induce an electromotive force in the electrically conductive element itself, with two rings extending radially inwards from the tubular body of the hub of the rotor, a first ring being connected to a plurality of thermally conductive rings of the deflector at the axial ends of the rotor, and a second ring supporting the electrically conductive element.

Inventors

  • Luigi botaso
  • Antonio Zoki
  • MASSIMO BRUNETTI
  • Luca Medic
  • WANG MING
  • George luki

Assignees

  • 列奥纳多股份公司
  • 列奥纳多股份公司

Dates

Publication Date
20220916
Application Date
20171229
Priority Date
20161230

Claims (11)

  1. 1. An aircraft (1) capable of hovering, comprising: -a fuselage (2); -a main transmission group (7); and -a main rotor (3, 3 ', 3' ', 3' '') connected to the main transmission group (7) and adapted to provide the aircraft (1) with a lift that makes it lift, said main rotor (3, 3 ', 3' ', 3' '') in turn comprising: -a fixed support structure (10) fixed to the fuselage (2); -a rotating element (11) rotatable with respect to said fixed support structure (10) about a first axis (a); -at least one blade (13) operatively connected with said rotating element (11); -a source (30) of magnetic field which is fixed or, in use, driven in rotation at a first rotation speed (ω 1); and -an electrically conductive element (32) operatively connected to the rotary element (11) and drivable in use to rotate at a second rotation speed (ω 2) different from the first rotation speed (ω 1), the conductive element (32) being electromagnetically coupled with the source (30) such that, in use, an electromotive force is magnetically induced in the conductive element (32) itself, said main rotor (3, 3 ', 3' ', 3' '') further comprising: -a hub (12) operatively connected to said rotating element (11), rotatable about said first axis (a) at said second rotation speed (ω 2) and on which said blades (13) are hinged (12); and -a support element (36, 36', 36 "), to which the source (30) is fixed and which is fixed or rotatable about the first axis (A) at the first rotation speed (ω 1), the conductive element (32) is fixed to the hub (12), characterized in that said main rotor (3, 3 ', 3 "') comprises a baffle (85) disposed at an axial end of said main rotor (3, 3 ', 3" ') rotatable integrally with said hub (12) about said first axis (A) and defining a compartment housing at least partially said support element (36, 36 '), the hub (12) comprises: -a tubular body (51) and a first ring (52) and a second ring (53) extending from the body (51) towards the first axis (A) and orthogonally thereto, said conductive element (32) being fitted to said second ring (53), the baffle (85) is made of metal and includes a plurality of thermally conductive rings (90) connected to the first ring (52, 52').
  2. 2. The aircraft of claim 1, characterized in that it is a helicopter or a thrust reverser.
  3. 3. The aircraft according to claim 1, characterized in that it comprises a first planetary gear (17), the first planetary gear (17) in turn comprises: -a sun gear (20) connectable to an output shaft of the main transmission group (7) of the aircraft (1); -a crown wheel (23) defined by a fixed support structure (10); -a plurality of planet gears (21) simultaneously meshing with said sun gear (20) and with said crown gear (23); and a first carrier (22) connected to the planet gear (21) and the rotary element (11, 151), the planet gears (21) are rotatable about respective second axes (E) parallel to and different from the first axis (A) and are mounted for rotation about the first axis (A).
  4. 4. The aircraft according to claim 3, characterized in that it comprises: -a connecting element (35) connected to said fixed support structure (10) and fixed with respect to said first axis (a); and -a second planetary gear train (37, 37 ') functionally interposed between said connection element (35) and said support element (36, 36').
  5. 5. The aircraft according to claim 4, characterized in that said support element (36, 36', 36 ") comprises a pair of third rings (39, 40) which support the respective sources (30) in positions in which they axially face each other along said first axis (A), the second ring (53) is interposed axially along the first axis (A) between the third rings (39, 40).
  6. 6. The aircraft of claim 5, wherein the second planetary gear train (37, 37') comprises: -a first gear wheel (45) defined by said support element (36, 36') and rotatable about said first axis (a); -at least one pair of third planet gears (46); and -a second carrier (47) connected with the third planet gears (46), wherein the hub (12) further comprises a fourth ring (48) extending from the main body (51) towards and orthogonal to the first axis (A), the fourth ring (48) being interposed axially between the second ring (53) and the third ring (39, 40), the fourth ring (48) comprising a radially internal toothing with respect to the first axis (A), said radially internal toothing meshing with a radially external toothing of the third planetary gear (46), the third planetary gears (46) are also simultaneously in mesh with the first gear (45), rotatable about respective third axes (F) parallel to and different from the first axis (A) and mounted for rotation about the first axis (A).
  7. 7. The aircraft of claim 6, characterized in that the second load bearing member (47) is connected to the fixed support structure (10) and is fixed with respect to the first axis (A).
  8. 8. The aircraft of claim 4, characterized in that the second epicyclic gear train (37 ') and the support element (36') are axially contained within the axial dimension of the hub (12).
  9. 9. The aircraft according to claim 6, wherein the second carrier (47) is connected to the sun gear (20) of the first planetary gear (17) and is rotatable about the first axis (A) at a third rotational speed (ω 0) different from the first and second rotational speeds (ω 1, ω 2).
  10. 10. The aircraft of claim 1, characterized in that the deflector (85) comprises an electrical storage device (89) electrically connected to the electrically conductive element (32) and/or a heat conduction ring (90) for dissipating heat generated, in use, by the source (30) and the electrically conductive element (32).
  11. 11. The aircraft according to claim 1, characterized in that it comprises electrical connection means (87) interposed between said conductive element (32, 169) and said blade (13, 154), the electrical connection means (87) are connected to an anti-icing system embedded in the blade (13).

Description

Aircraft capable of hovering Priority declaration This application claims priority from european patent application No. 16207524.6 filed on 30/12/2016, the disclosure of which is incorporated herein by reference. Technical Field The present invention relates to an aircraft capable of hovering, in particular a helicopter or a thrust reverser aircraft. Background A known helicopter includes a fuselage, a main rotor projecting upward from the fuselage, and a tail rotor provided at the tail of the fuselage. Furthermore, the known helicopter comprises a turbine, a main transmission group that transmits the motion from the turbine to the main rotor, and an additional transmission group that transmits the motion from the main transmission group to the tail rotor. The main rotor and the tail rotor each include: -a stationary housing; -a main shaft driven by the main transmission group or the additional transmission group to rotate around its own axis; -a hub driven in rotation by the main shaft; and -a plurality of blades, which are articulated with respect to the hub. There is a need in the art to provide electrical power to the rotating components of the main and tail rotors, i.e., the mast, hub and blades. For example, the electric power may be used to activate a de-icing or anti-icing system formed by a plurality of electric conductors embedded in the blade and adapted to heat the associated blade by the joule effect, or to activate some movable surface on the blade. In order to provide the necessary electrical power to the rotating parts of the main rotor, known helicopters usually comprise an electrical generator operated by a shaft connected to the main transmission group and to the collecting ring. Slip rings transmit electrical power from a stationary conductor electrically connected to the generator to a rotating conductor of the main or tail rotor by creating frictional contact. While performing well, the previously described solutions leave room for improvement. In fact, slip rings are complex to manufacture and maintain and are susceptible to wear. This drawback is more serious in particular in counter-torque tail rotors, which rotate at higher speeds than the main rotor. Furthermore, in the event of a lightning strike, the presence of the necessary conductive paths between the fixed conductors and the rotating conductors of the main and tail rotors may propagate dangerous current peaks from the fixed conductors to the rotating conductors, or vice versa. There is therefore a need in the industry to transmit electric power to the rotating parts of the main or tail rotor while eliminating the above-mentioned drawbacks in a simple, low-cost manner. Furthermore, there is a need to transmit electric power with a solution that is integrated within the limited dimensions of the rotor head so as to allow efficient heat dissipation and/or that can easily be retrofitted to existing main or tail rotors. EP- ｃA-2629407 discloses an aircraft. Disclosure of Invention It is an object of the present invention to provide a rotor for an aircraft capable of hovering that meets at least one of the above requirements. The above object is achieved by the present invention which relates to an aircraft capable of hovering. According to the invention, an aircraft capable of hovering comprises: a body; a main transmission set; and a main rotor connected to the main transmission group and adapted to provide lift to the aircraft. The main rotor in turn comprises: a fixed support structure fixed to the fuselage; a rotating element rotatable about a first axis relative to a fixed support structure; at least one paddle operatively connected with the rotating element; a source of magnetic field which is fixed or, in use, driven to rotate at a first rotational speed; and an electrically conductive element operatively connected to the rotational element and drivable in use to rotate at a second rotational speed different from the first rotational speed. The conductive element is electromagnetically coupled to the source such that, in use, an electromotive force is magnetically induced in the conductive element itself. The main rotor still includes: a hub operatively connected to the rotating element, rotatable about the first axis at a second rotation speed and on which the blades are hinged; and a support element to which the source is fixed and which is fixed or rotatable about a first axis at a first rotational speed. The conductive element is fixed to the hub. The main rotor comprises a baffle arranged at an axial end of the main rotor, rotatable integrally with the hub about the first axis and defining a compartment at least partially housing the support element. The hub includes: a tubular body and first and second rings extending from the body (51) towards and orthogonal to the first axis. The conductive element is fitted to the second ring. The baffle is made of metal and includes a plurality of thermally conductive rings conne