CONTROL DEVICE OF AIRCRAFT

To suppress increase in the weight of an airframe.SOLUTION: When a first power generator 46a stops, an electric motor control part reduces output power of a VTOL electric motor 20V and a cruise electric motor 24C operated by power supplied from the first power generator 46a, and increases the output...

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Bibliographic Details
Main Authors YAMAMOTO YOSHIFUMI, NAKANO RITSU, KITA AKINORI
Format Patent
LanguageEnglish
Japanese
Published 13.10.2023
Subjects
AEROPLANES
AIRCRAFT
ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT
AVIATION
CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTINGELECTRIC POWER
CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
COSMONAUTICS
ELECTRICITY
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT
FLYING SUITS
GENERATION
HELICOPTERS
PARACHUTES
PERFORMING OPERATIONS
SYSTEMS FOR STORING ELECTRIC ENERGY
TRANSPORTING
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Summary:To suppress increase in the weight of an airframe.SOLUTION: When a first power generator 46a stops, an electric motor control part reduces output power of a VTOL electric motor 20V and a cruise electric motor 24C operated by power supplied from the first power generator 46a, and increases the output power of the VTOL electric motor 20V and a cruise electric motor 24C operated by power supplied from a second power generator 46b.SELECTED DRAWING: Figure 2 【課題】機体の重量の増加を抑制する。【解決手段】第１発電機４６ａが停止した場合、電動モータ制御部は、第１発電機４６ａから供給される電力により動作していたＶＴＯＬ電動モータ２０Ｖ及びクルーズ電動モータ２４Ｃの出力パワーを減少させ、第２発電機４６ｂから供給される電力により動作するＶＴＯＬ電動モータ２０Ｖ及びクルーズ電動モータ２４Ｃの出力パワーを増加させる。【選択図】図２
Bibliography:Application Number: JP20220054782