ENGINE-MOUNTED SELF-STANDING TYPE FLIGHT DEVICE

To provide a self-standing type flight device of which a pay load and a continuous flight time can be largely assured, and of which a position attitude at the time of flight can be accurately adjusted.SOLUTION: A self-standing type flight device 10 comprises: a main rotor 14A and the like which give...

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Bibliographic Details
Main Authors KAYANUMA HIDETAKA, ISHIKAWA MITSURU
Format Patent
LanguageEnglish
Japanese
Published 18.04.2019
Subjects
AEROPLANES
AIRCRAFT
ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT
AVIATION
BLASTING
COMBUSTION ENGINES
COMBUSTION ENGINES IN GENERAL
COSMONAUTICS
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT
FLYING SUITS
HEATING
HELICOPTERS
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
INTERNAL-COMBUSTION PISTON ENGINES
LIGHTING
MECHANICAL ENGINEERING
PARACHUTES
PERFORMING OPERATIONS
TRANSPORTING
WEAPONS
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Summary:To provide a self-standing type flight device of which a pay load and a continuous flight time can be largely assured, and of which a position attitude at the time of flight can be accurately adjusted.SOLUTION: A self-standing type flight device 10 comprises: a main rotor 14A and the like which gives a main thrust; a sub-rotor 15A and the like which performs attitude control; an engine 30 which generates energy for rotation of the main rotor 14A and the like and the sub-rotor 15A and the like; and an arithmetic control device which controls rotation of the sub-rotor 15A and the like. Further, the main rotor 14A and the like is rotated in such manner that the same is drivingly connected with the engine 30, and on the other hand, the sub-rotor 15A and the like is rotated by a motor which is driven by electric power generated from an electric generator 16A and the like which is operated by the engine 30. Further, when performing attitude control for inclining an airframe, the arithmetic control device increases an output distribution ratio of the sub-rotor 15A compared to the time when performing hovering.SELECTED DRAWING: Figure 1 【課題】ペイロードおよび連続飛行時間を大きく確保すると共に、飛行時に於ける位置姿勢の調整を正確に行うことができる自立型飛行装置を提供する。【解決手段】本発明の自立型飛行装置１０は、主推力を与えるメインロータ１４Ａ等と、姿勢制御を行うサブロータ１５Ａ等と、メインロータ１４Ａ等およびサブロータ１５Ａ等が回転するためのエネルギを発生するエンジン３０と、サブロータ１５Ａ等の回転を制御する演算制御装置と、を具備する。また、メインロータ１４Ａ等は、エンジン３０と駆動的に接続されることで回転する一方、サブロータ１５Ａ等は、エンジン３０により運転される発電機１６Ａ等から発生する電力により駆動するモータにより回転する。更に、演算制御装置は、機体を傾斜させる姿勢制御を行う際には、ホバリングを行う際よりも、サブロータ１５Ａの出力配分比を大きくする。【選択図】図１
Bibliography:Application Number: JP20170185764