公开(公告)号：US11919633B2

公开(公告)日：2024-03-05

申请号：US17786170

申请日：2020-12-17

Applicant: LEONARDO S.P.A.

Inventor： Riccardo Bianco Mengotti ,  Carlo Cassinelli ,  Alessandro Scandroglio ,  Andrea Bavetta ,  Paolo Brughera ,  Luca Sampugnaro

IPC: B64C29/00 ,  B64C1/20 ,  B64C1/22 ,  B64C3/52 ,  B64C9/14 ,  B64C27/22 ,  B64C39/12 ,  B64D27/24 ,  B64D29/00 ,  B64D35/04 ,  B64D35/08 ,  B64D27/02

CPC classification number: B64C29/0033 ,  B64C1/20 ,  B64C1/22 ,  B64C3/52 ,  B64C9/14 ,  B64C27/22 ,  B64C39/12 ,  B64D27/24 ,  B64D29/00 ,  B64D35/04 ,  B64D35/08 ,  B64D2027/026

Abstract: A convertiplane is described that comprises a fuselage, having a first longitudinal axis, with a nose and a tail portion; a pair of wings arranged on respective opposite sides of said fuselage, carrying respective rotors; a pair of engines operatively connected to respective said rotors; at least one first lifting surface arranged on said tail portion; and a pair of canards arranged on said nose of said fuselage and defining respective second lifting surfaces adapted to generate a third lift/negative lift value; each rotor comprising a mast rotatable about a second axis and about an relative third axis transversal to said second axis and with respect to the fuselage, so as to set said convertiplane between a helicopter configuration and an aeroplane configuration; each second axis, in use, being transversal to the first axis of said convertiplane in said helicopter configuration and being parallel to said first axis in said aeroplane configuration.

公开(公告)号：US20230025666A1

公开(公告)日：2023-01-26

申请号：US17786170

申请日：2020-12-17

Applicant: LEONARDO S.P.A.

Inventor： Riccardo Bianco Mengotti ,  Carlo Cassinelli ,  Alessandro Scandroglio ,  Andrea Bavetta ,  Paolo Brughera ,  Luca Sampugnaro

IPC: B64C29/00 ,  B64C27/22 ,  B64D35/04 ,  B64C9/14 ,  B64C1/20 ,  B64C1/22 ,  B64D27/24 ,  B64D35/08 ,  B64C3/52 ,  B64D29/00 ,  B64C39/12

Abstract: A convertiplane is described that comprises a fuselage, having a first longitudinal axis, with a nose and a tail portion; a pair of wings arranged on respective opposite sides of said fuselage, carrying respective rotors; a pair of engines operatively connected to respective said rotors; at least one first lifting surface arranged on said tail portion; and a pair of canards arranged on said nose of said fuselage and defining respective second lifting surfaces adapted to generate a third lift/negative lift value; each rotor comprising a mast rotatable about a second axis and about an relative third axis transversal to said second axis and with respect to the fuselage, so as to set said convertiplane between a helicopter configuration and an aeroplane configuration; each second axis, in use, being transversal to the first axis of said convertiplane in said helicopter configuration and being parallel to said first axis in said aeroplane configuration.