Method and computer program for controlling tilt angle of main rotor on basis of pitch attitude control signal low-speed flight state, and vertical take-off and landing aircraft
US11809203B2 · kind B2 · utility
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20Claims
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Key dates
| Filing date | May 12, 2020 |
| Grant date | Nov 7, 2023 |
| Priority date | — |
| Expiry date | May 23, 2042 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64U2201/00
- WIPO fieldTransport
- WIPO sectorMechanical engineering
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.