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KR-102963897-B1 - Convertible airplane

KR102963897B1KR 102963897 B1KR102963897 B1KR 102963897B1KR-102963897-B1

Abstract

The present specification discloses a convertible airplane (1, 1', 1"), which comprises a fuselage (2) having a first longitudinal axis (A) and, in turn, a nose (12) and a tail section (13); a pair of wings (3) disposed on each opposing side of the fuselage (2) to carry each rotor (5) and generate lift; and a pair of engines (4) operatively connected to each rotor (5); each rotor (5) comprises a mast (9) rotatable about a second axis (B) between the helicopter configuration and the airplane configuration; and each rotor (4) is positioned between the fuselage (2) and the associated rotor (5) along the extension direction of the associated wing (3).

Inventors

  • 비안코 멘고티 리카르도
  • 브루게라 파올로
  • 삼푸냐로 루카
  • 카시넬리 카를로

Assignees

  • 레오나르도 에스.피.에이.

Dates

Publication Date
20260513
Application Date
20201217
Priority Date
20191217

Claims (13)

  1. As a convertible airplane (1, 1', 1"), - A body (2) having a first axis (A) and including a nose (12) and a tail section (13) in sequence; - A pair of wings (3) disposed on each opposing side of the fuselage (2), each carrying a rotor (5) and generating a lift value; - A pair of engines (4) of thermal type and operatively connected to the rotor (5); - A pair of electric motors (52) operatively connected to each of the above rotors (5) and suitable for driving the rotation of the rotors (5); - A pair of generators (51) electrically connected to each of the above-mentioned electric motors (52) and operably connected to each of the above-mentioned engines (4); and - Includes an interconnecting shaft (11) positioned between the engines (4) and disposed within the fuselage (2) for a larger portion of its length; Each of the above rotors (5) includes a mast (9) that is rotatable around a second axis (B) in turn; The mast (9) of each of the above rotors (5) can be tilted integrally with the second axis (B) with respect to the fuselage (2) and around a third axis (E) transversal of the second axis (B) so as to set the convertible airplane (1, 1', 1") between the helicopter configuration and the airplane configuration; Each of the above-mentioned second axis (B) traverses the first axis (A) of the convertible airplane (1, 1', 1") in the helicopter configuration when in use, and is parallel to the first axis (A) in the airplane configuration when in use; The above engine (4) is positioned between the rotors (5) along the extension direction of the blade (3); When in use, the engine (4) is connected and positioned below the lower surface (49) of the wing (3) based on the normal operation configuration of the convertible airplane (1, 1', 1") set in the airplane configuration; The engine (4) is positioned at the connection interface between the fuselage (2) and the wing (3); Each of the above-mentioned engines (4) is positioned at the root portion of the wing (3); The engine (4) is characterized by being located within each interface corner between the fuselage (2) and each of the wings (3) and connected to each side of the fuselage (2). Convertible airplane.
  2. In Article 1, Each of the above wings (3) in turn: - A first part (20) fixed to the above body (2); - A tip portion (21) that can be tilted integrally with the mast (9) around the third axis (E); and - Includes a third intermediate part (22) located between each of the first part (20) and each of the tip part (21); A convertible airplane characterized in that the third intermediate part (22) of each wing (3) is hinge-connected to the first part (20) of each wing (3) around the fourth axis (I).
  3. In Article 2, The above-mentioned fourth axis (I) is characterized by being incident to each other within the longitudinal plane (P) of the convertible aircraft (1) including the first axis (A); or The above-mentioned fourth axis (I) is characterized by converging with each other; or A convertible airplane characterized in that the above-mentioned fourth axis (I) is skewed.
  4. In Paragraph 3, A convertible airplane characterized in that the generator (51) is positioned between the engines (4) along the third axis (E).
  5. In Article 3 or Article 4, The above electric motor (52) is characterized by being able to tilt integrally with each rotor (5) around each of the above third axes (E).
  6. In Paragraph 3, In each of the above rotors (5): - An engine room (10) accommodating the rotor (5) and each of the electric motors (52); and - A convertible airplane characterized by including a hub (7) which is operatively connected to each of the above-mentioned masts (9) and mechanically connected to each of the above-mentioned electric motors (52).
  7. In Paragraph 3, A convertible airplane characterized in that each of the above-mentioned engines (4) is operationally connected to both of the two above-mentioned generators (51) and has a size to provide the mechanical power level necessary to power both of the two above-mentioned generators (51) in the event of a failure of the other engine (4).
  8. In Paragraph 3, Each of the above generators (51) is operationally connected to both of the two electric motors (52) and is characterized by having a size to provide the power level required to power both of the two electric motors (52) in the event of a failure of the other generator (51).
  9. In Paragraph 3, A convertible airplane characterized by including an electric energy source (56) that is operable to be operationally connected to at least one of the generators (51) and capable of providing additional power to at least one of the generators (51) for a predetermined time.
  10. In Article 1, The above-mentioned fuselage (2) includes a cargo compartment (60) and at least one panel (66, 80') defining the cargo compartment (60); The above panels (66, 80') are: - A closing position for closing the above cargo room (60); and - An open position that allows access to the cargo compartment (60) from the outside; Optionally movable between; The above-described convertible airplane (1, 1', 1") further includes a support element (70, 70') that is accommodated inside the cargo compartment (60) in a retracted position when the panel (66, 80') is in the closed position and is movable to an extraction position outside the cargo compartment (60); The above support element (70, 70') includes an equipment station (71, 71'); and when the above support element (70, 70') is in the above withdrawal position, the station (71, 71') is between the rotor (5) along the third axis (E) and offset from the fuselage (2) along the first axis (A), characterized by a convertible airplane.
  11. In Article 10, The support element (70) is constrained to slide inside the cargo compartment (60) and, when in use, is movable along a linear translational path along the fifth axis (Z) between the retracted position and the extended position when the panel (66) is in the open position; The above-mentioned fifth axis (Z) is characterized by traversing the above-mentioned first axis (A) and third axis (E); Or, when the panel (80') is positioned in the open position and the convertible aircraft (1, 1', 1") is on the ground during use, the panel (80') defines a loading ramp; The above support element (70') is constrained to the panel (80') in a movable manner; The support element (70') and the station (71') can slide integrally relative to each other along a translational path for the panel (80') between an initial position and an intermediate position when the panel (80') is in the open position; The above station (71') is positioned outside the cargo compartment (60) at the above intermediate location and is positioned behind the panel (80') when in use; A convertible airplane characterized in that the station (71') is hinged to the support element (70') and is rotatable around the support element (70') between the intermediate position and the final position in which the station (71') is positioned outside the cargo compartment (60) and is positioned under the panel (80') when in use, when the panel (80') is in the open position.
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Description

Convertible airplane This patent application claims priority to European patent application no. 19217218.7 filed on December 17, 2019, the entire disclosure of which is incorporated herein by reference. The present invention relates to a convertiplane. In the aviation industry, aircraft are generally used at high cruising speeds, particularly at speeds higher than 150 knots, at altitudes higher than, for example, 30,000 feet. For high cruising speeds and altitudes, aircraft use fixed wings to generate the lift necessary to maintain them in the air. A sufficient amount of this lift can only be obtained when accelerating the aircraft on a relatively long runway. Such a runway is also required to enable the aircraft to land. Conversely, helicopters generally have lower cruising speeds than airplanes and generate the necessary lift through the rotation of the main rotor blades. As a result, helicopters can take off and land without the need for horizontal speed and, in particular, utilize small surfaces. Furthermore, because helicopters can hover and fly at relatively low altitudes and speeds, they are particularly easy to handle and suitable for difficult maneuvers such as mountain or maritime rescue operations. Nevertheless, helicopters have inherent limitations regarding a maximum operating altitude of approximately 20,000 feet and a maximum operating speed that cannot exceed 150 knots. Convertible aircraft are known to meet the demand for aircraft capable of possessing the same maneuverability and flexibility as helicopters while overcoming the unique limitations mentioned above. An example of a convertible airplane is described in patent application US 10,011,349 B. More specifically, the convertible aircraft described in the aforementioned application is basically: - A fuselage extending along the first longitudinal axis; - A wing formed by a pair of wings that project in a cantilevered manner, are positioned on each opposing side of the fuselage and have each free end facing the fuselage and are aligned along a second transverse axis substantially orthogonal to a first longitudinal axis; and - Includes a V-shaped tail section protruding from the fuselage in a rearward position relative to the wing. Convertible airplanes also: - A pair of engine rooms housing each engine; and - Includes a pair of rotors that are rotatable around each third axis and are operatively connected to each engine. The rotor may preferably be tilted relative to the blades with respect to a fourth axis parallel to the second axis. Each rotor comprises a mast rotatable about a third axis associated in a known manner and a plurality of blades hinged to the mast, in particular, a plurality of blades angularly spaced along the circumference of the free end of the mast protruding from each engine room. More specifically, each rotor blade extends along each longitudinal axis that is transverse to the associated third axis. The rotors are connected together by interconnecting shafts to ensure the operation of both rotors in the event of a failure in one of the engines. Additionally, the engines are mounted on each wing facing each other relative to the fuselage. More specifically, the engines are positioned with each rotor, that is, at an equal distance from each rotor relative to the body. In the embodiment described in the aforementioned patent application, the engine is fixed to the fuselage and wings. As a result, the convertible aircraft described in the aforementioned patent application includes a pair of transmissions, each transmission being located between each engine and each rotor. In particular, each transmission includes a fixed part connected to each engine and a movable part connected to each rotor. Convertible airplanes can also optionally assume the following: - A "plane" configuration in which the rotor is substantially parallel to the first axis of the convertible airplane and arranged on a respective third axis coaxial to each engine; or - A "helicopter" configuration in which rotors are arranged along a third axis that is substantially perpendicular to the first axis of the convertible aircraft, transverse, and orthogonal to each engine. Due to the possibility of tilting the rotor, the convertible aircraft can take off and land like a helicopter, that is, in a direction substantially perpendicular to the first longitudinal axis of the convertible aircraft without the need for a runway. In addition, convertible aircraft can take off and land on rough terrain or on ground that is generally not prepared for such maneuvers. In addition, the convertible aircraft can hover in the air when in "helicopter" configuration. The convertible aircraft can also reach and maintain a cruising speed of approximately 250-300 knots and a flight altitude of approximately 20,000 feet when in "airplane" configuration. This cruising speed is much higher than the value of approximately 150 knots that defines the maximum cruising speed of a he