公开(公告)号：US11591077B2

公开(公告)日：2023-02-28

申请号：US17334311

申请日：2021-05-28

申请人： SUBARU CORPORATION ,  Japan Aerospace Exploration Agency

发明人： Wataru Kobayashi ,  Hirotaka Hayashi ,  Mizuki Nakamura ,  Masafumi Sasaki ,  Yasutada Tanabe ,  Noboru Kobiki ,  Hideaki Sugawara

IPC分类号： B64C27/26 ,  B64C27/00 ,  B64C13/50

摘要： Provided is a vibration control system for a compound helicopter with a rotor and a fixed wing. The fixed wing includes a movable flap that is mounted on a rear edge of the fixed wing. The vibration control system periodically moves the movable flap so as to periodically change lift of the fixed wing such that vibration aerodynamically generated by the fixed wing is in anti-phase with vibration caused by rotation of the rotor.

公开(公告)号：US11685512B2

公开(公告)日：2023-06-27

申请号：US17307421

申请日：2021-05-04

申请人： SUBARU CORPORATION

发明人： Wataru Kobayashi ,  Hirotaka Hayashi ,  Mizuki Nakamura ,  Masafumi Sasaki

IPC分类号： B64C9/18 ,  B64C3/50 ,  B64C9/34

CPC分类号： B64C9/18 ,  B64C3/50 ,  B64C9/34

摘要： A lift-changing mechanism is configured to change generated by a wing of an aircraft and includes a slit and an opening and closing member. The slit extends in a wingspan direction inside the wing and forms openings on the lower surface of the wing and on the upper surface of the wing respectively. A part of airflow below the lower surface is allowed to flow toward the upper surface through the slit. The opening and closing member is configured to open and close the slit. When the opening and closing member opens the slit, lift generated on the wing is decreased compared with when the slit is closed.

公开(公告)号：US11738860B2

公开(公告)日：2023-08-29

申请号：US17307409

申请日：2021-05-04

申请人： SUBARU CORPORATION

发明人： Wataru Kobayashi ,  Hirotaka Hayashi ,  Mizuki Nakamura ,  Masafumi Sasaki

IPC分类号： B64C27/26

CPC分类号： B64C27/26

摘要： A compound helicopter includes a fuselage, a fixed wing, a rotary wing, and a barrier member. The fixed wing is fixed to the fuselage. The rotary wing is rotatably coupled to the fuselage. The barrier member is attached to a part, of the fuselage, that is above the fixed wing and is between the rotary wing and the fixed wing. The barrier member is configured to generate no lift upon forward flight.

公开(公告)号：US11267567B2

公开(公告)日：2022-03-08

申请号：US16435862

申请日：2019-06-10

申请人： SUBARU CORPORATION

发明人： Wataru Kobayashi ,  Hokuto Yamane ,  Hirotaka Hayashi ,  Hiroshi Taguchi

IPC分类号： B64C27/46 ,  B64C27/473 ,  B64C23/06 ,  F04D29/38 ,  F04D29/66

摘要： A rotor blade for an aircraft includes first and second blade tips, a blade body, and a vortex-generating blade. The blade body has an end forming the first blade tip of the rotor blade and an airfoil section configured such that during rotation, pressure acting on a lower surface of the blade body is greater than pressure acting on an upper surface of the blade body. The vortex-generating blade is disposed at an end of the rotor blade and forms the second blade tip. The vortex-generating blade also has an airfoil section configured such that during rotation, pressure acting on a lower surface of the vortex-generating blade is smaller than pressure acting on an upper surface of the vortex-generating blade.