公开(公告)号：US20240092484A1

公开(公告)日：2024-03-21

申请号：US18450097

申请日：2023-08-15

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Jun Ho CHO ,  Myeong Kyu LEE ,  Seong Wook CHOI

IPC: B64C29/00 ,  B64C13/30 ,  B64C13/34

CPC classification number: B64C29/0033 ,  B64C13/30 ,  B64C13/34

Abstract: A tilt prop aircraft is provided, including a first longeron and a second longeron capable of tilting relatively to each other, a tilt actuator disposed on the second longeron, a first power transmission member rotated by the tilt actuator, a second power transmission member fixed to the first longeron and coupled to the first power transmission member to transmit a rotational movement of the first power transmission member by turning 90 degrees in different planes, a crank fixed to the second longeron and extending through a slot in the first longeron and protruding inwardly from the first longeron, and a connecting rod connected to the crank so as to be relatively rotatable to the crank, and connected to the pitch control rod.

公开(公告)号：US20240166333A1

公开(公告)日：2024-05-23

申请号：US18511423

申请日：2023-11-16

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Youngshin KANG ,  Am CHO ,  Seongwook CHOI ,  Yushin KIM ,  Jongmin BAE ,  Junho CHO ,  Haneul YUN ,  Myeong Kyu LEE

IPC: B64C11/30 ,  B64C13/50 ,  B64D35/04

CPC classification number: B64C11/305 ,  B64C13/503 ,  B64D35/04 ,  B64C27/52

Abstract: An apparatus for controlling a tilt rotor is provided. The apparatus includes a thrust command generator configured to generate a first collective pitch angle based on a throttle command, a rotation speed compensator configured to generate a compensation value based on a rotation speed of the motor, a compensation weight generator configured to generate weight values according to a flight speed, a collective pitch angle command generator configured to generate a collective pitch angle adjustment command of the rotor blade of the motor, based on the first collective pitch angle and a first compensation value being obtained by multiplying the compensation value by a preset conversion ratio and a first weight value, and a motor controller configured to generate a motor control command based on a second compensation value being obtained by multiplying the compensation value by a second weight value and the first collective pitch angle.

公开(公告)号：US20180155019A1

公开(公告)日：2018-06-07

申请号：US15820787

申请日：2017-11-22

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Myeong Kyu LEE ,  Seong Wook CHOI ,  Deog-Kwan KIM

IPC: B64C29/00 ,  B64D35/04

CPC classification number: B64C29/0033 ,  B64C27/28 ,  B64C27/46 ,  B64C27/59 ,  B64D35/04 ,  Y02T50/44

Abstract: A tilt-prop aircraft is configured to operate in a vertical take-off and landing (VTOL) mode or a forward flight mode by adjusting a tilt angle of a rotor connected to a wing. The tilt-prop aircraft includes: a blade included in the rotor and configured to rotate to produce lift and thrust; and a tilt center shaft configured to connect the rotor and the wing to each other and adjust the tilt angle of the rotor with respect to a flight plane of the tilt-prop aircraft, wherein when the tilt angle of the rotor is adjusted, a pitch angle of the blade is varied by a power transmission unit mechanically interlocked with the tilt center shaft.