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公开(公告)号：US11809203B2
公开(公告)日：2023-11-07
申请号：US16872825
申请日：2020-05-12
Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
Inventor： Youngshin Kang , Am Cho , Seongwook Choi , Yushin Kim , Sung Ho Chang
CPC classification number: G05D1/102 , B64C27/52 , B64C27/82 , G05D1/0858 , B64C2027/8254
Abstract: Provided is a vertical take-off/landing aircraft controlling a tilt angle of a main rotor, based on a vertical posture control signal during low-speed flight, wherein, when an aircraft steering signal including a vertical posture control signal for changing the pitch posture angle of the vertical take-off/landing aircraft by a first pitch posture angle is obtained, a flight controller determines a tilt angle of the main rotor with reference to the first pitch posture angle and generates a tilt angle control signal for the main rotor based on the determined tilt angle.
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公开(公告)号：US11505315B2
公开(公告)日：2022-11-22
申请号：US17040896
申请日：2019-04-12
Applicant: Korea Aerospace Research Institute
Inventor： Sung Ho Chang , Yu Shin Kim , Seong Wook Choi , Young Shin Kang , Am Cho
Abstract: The flying object according to one embodiment comprises: a main body; a main wing formed on a side surface of the main body; a duct-shaped first propulsion part which is provided outside the main wing and can be tilted; a second propulsion part arranged behind the main body; horizontal tail wings formed on both side surfaces of the second propulsion part; and a control part for controlling the movement of the first propulsion part, second propulsion part, and horizontal tail wings, wherein the control part controls the second propulsion part and the horizontal tail wings according to the tilt angle of the first propulsion part.
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3.发明授权公开(公告)号：US12234005B2
公开(公告)日：2025-02-25
申请号：US17757357
申请日：2020-11-26
Applicant: KOREA AEROSPACE RESEARCH INSTITUTE
Inventor： Youngshin Kang , Am Cho , Bumjin Park , Seongwook Choi , Sam Ok Koo , Chang Sun Yoo , Yushin Kim
Abstract: Provided is a system for controlling an RPM of a propeller and a rotor of a flight vehicle having multiple power units including: a collective pitch angle command generating unit generating a collective pitch angle command upon receiving a thrust control command from a pilot or an automatic controller; a disturbance factor compensating unit for generating an RPM compensation electronic speed control (ESC) command for compensating for an RPM error, and an electronic speed adjustment command generating unit generating a final ESC command upon receiving a collective command input or derived in the process of generating the collective pitch angle command by the collective pitch angle command generating unit and the RPM compensation ESC command generated by the disturbance factor compensating unit. RPMs of motors of a flight vehicle having a plurality of propellers and rotors may be maintained to be the same.
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公开(公告)号：US20210009264A1
公开(公告)日：2021-01-14
申请号：US17040896
申请日：2019-04-12
Applicant: Korea Aerospace Research Institute
Inventor： Sung Ho Chang , Yu Shin Kim , Seong Wook Choi , Young Shin Kang , Am Cho
Abstract: The flying object according to one embodiment comprises: a main body; a main wing formed on a side surface of the main body; a duct-shaped first propulsion part which is provided outside the main wing and can be tilted; a second propulsion part arranged behind the main body; horizontal tail wings formed on both side surfaces of the second propulsion part; and a control part for controlling the movement of the first propulsion part, second propulsion part, and horizontal tail wings, wherein the control part controls the second propulsion part and the horizontal tail wings according to the tilt angle of the first propulsion part.
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