[특허]Aircraft and aircraft control method

[미국특허] Aircraft and aircraft control method 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G05D-001/08 B64C-013/16 B64C-027/57 B64C-013/04 B64C-013/28 B64C-013/44 B64C-013/50
출원번호	US-0241232 (2012-10-12)
등록번호	US-9108722 (2015-08-18)
우선권정보	JP-2011-229201 (2011-10-18)
국제출원번호	PCT/JP2012/076390 (2012-10-12)
국제공개번호	WO2013/058173 (2013-04-25)
발명자 / 주소	Higuchi, Yosuke Matsuda, Takeshi
출원인 / 주소	MITSUBISHI HEAVY INDUSTRIES, LTD.
대리인 / 주소	Wenderoth, Lind & Ponack, L.L.P.
인용정보	피인용 횟수 : 1 인용 특허 : 24

초록 ▼

An aircraft is provided with a mechanical linkage that mechanically transmits an amount of manipulation of a control stick to a rudder controlling mechanism, an amount-of-manipulation sensor that detects the amount of manipulation, and an FBW control-law computing unit that calculates an FBW control-law command indicating an amount of control for a craft in accordance with the detected amount of manipulation. Also, with the aircraft, a high-pass filter outputs, among the control-stick manipulation amounts detected by the amount-of-manipulation sensor, an amount of change in the control-stick manipulation amounts; by subtracting the amount of change that has passed through the high-pass filter by means of the subtracting portion, the FBW control-law command serves as an SAS command; and the rudder controlling mechanism is driven by adding an amount of movement of an SAS actuator in accordance with the SAS command to the control-stick manipulation amount transmitted by the mechanical linkage.

대표청구항 ▼

1. An aircraft comprising: a control stick for a pilot to maneuver a craft;an amount-of-rudder-control transmitting part that mechanically transmits an amount of manipulation of the control stick to a rudder controlling part;a detecting part that detects the amount of manipulation;an amount-of-control calculating part that calculates an amount of control for the craft in accordance with the amount of manipulation detected by the detecting part;an amount-of-change outputting part that outputs, among the amounts of manipulation detected by the detecting part, an amount of change in the amounts of manipulation;a subtracting part that subtracts the amount of change output from the amount-of-change outputting part from the amount of control calculated by the amount-of-control calculating part; andan actuator that adds an amount of manipulation in accordance with a subtracted value output from the subtracting part to the amount of manipulation transmitted by the amount-of-rudder-control transmitting part. 2. An aircraft according to claim 1, wherein the amount-of-change outputting part attenuates, over time, the amount of manipulation to be output when the amount of manipulation has stopped changing. 3. An aircraft control method which is a method of controlling an aircraft provided with a control stick for a pilot to maneuver a craft, an amount-of-rudder-control transmitting part that mechanically transmits an amount of manipulation of the control stick to a rudder controlling part, a detecting part that detects the amount of manipulation, an amount-of-control calculating part that calculates an amount of control for the craft in accordance with the amount of manipulation detected by the detecting part, the aircraft control method comprising: a first step of outputting, among the amounts of manipulation detected by the detecting part, an amount of change in the amounts of manipulation;a second step of subtracting the amount of change from the amount of control calculated by the amount-of-control calculating part; anda third step of driving the rudder controlling part by adding an amount of movement of the actuator in accordance with a subtracted value obtained by the subtraction performed in the second step to the amount of manipulation transmitted by the amount-of-rudder-control transmitting part.

이 특허에 인용된 특허 (24) 인용/피인용 타임라인 분석

Adams ; Sr. Don L. (Fairfield CT) Wright Stuart C. (Woodbridge CT) Verzella David J. (Guilford CT) LaMontagne Troy J. (Wallingford CT), Adaptive control system input limiting.
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Najmabadi Kioumars ; Evans Monte R. ; Coleman Edward E. ; Bleeg Robert J. ; Breuhaus Richard S. ; Anderson Dorr Marshall ; Nelson Timothy A., Aircraft pitch-axis stability and command augmentation system.
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Fischer William C. (Monroe CT) Adams Don L. (Fairfield CT) Wright Stuart C. (Milford CT) Verzella David J. (Guilford CT), Aircraft trim actuator shutdown monitor system and method.
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Hirvonen, Jukka Matti, Apparatus and method for backup control in a distributed flight control system.
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Post Joseph A. (Huntington CT) Stiles Lorren (Boxbury CT), Arrangement for controlling the performance of bob-up/bob-down maneuvers by a helicopter.
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Einthoven,Pieter G.; Morse,Channing S., Constant vertical state maintaining cueing system.
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Murray James B. (New Brighton MN), Control augmentation system for flight vehicles.
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Laffisse Jean-Fran.cedilla.ois,FRX ; Woirin Eddy Gaston Jean,FRX, Device for assisting with retrimming an aircraft control.
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Takeshi Tomio JP; Hideki Shirasaya JP; Shigeru Tobari JP; Ikuo Sudo JP; Yoshiharu Kubo JP, Flight control apparatus for helicopters.
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Blight James D. (Redmond WA) Gangsaas Dagfinn (Bellevue WA), Flight control system and method.
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Koenig Herbert (Munich DEX), Flight control system especially for helicopters.
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Osder Stephen S., Flight control system for jet powered tri-mode aircraft.
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Hoh,Roger H., Helicopter force-feel and stability augmentation system with parallel servo-actuator.
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von Gersdorff Michael (Dietramszell DEX), Method and apparatus for trimming and stabilizing an aircraft.
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Allieta, Jean-Marie; Chaduc, Bruno; Lafisse, Jean-Francois; Honnorat, Olivier, Method of assisting piloting, piloting assistance means, and a piloting assistance device for a rotorcraft using said piloting assistance means to implement said piloting assistance method.
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Wright Stuart C. (Woodbridge CT) Dryfoos James B. (Wallingford PA), Model following control system.
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Cox Chadwick J. ; Lewis Carl E., Pilot-induced oscillation detection and compensation apparatus and method.
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Nixon John M. (Mineral Wells TX), Pitch/trim control.
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Clelford Douglas H. (Trumbull CT) Murphy Richard D. (Trumbull CT) Tefft Franklin A. (Killingworth CT), Preventing augmenting vertical load induced oscillations in a helicopter.
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Kaloust Joseph H., Stall and recovery control system.
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Hirvonen, Jukka Matti; Palfreyman, Gary, System and method for an integrated backup control system.
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Biest, Romuald; Gemmati, Bernard; Pruss, Julien, Variable damping of haptic feedback for a flight-attitude changing linkage of an aircraft.
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Gold Phillip J. (Shelton CT) Stiles Lorren (Roxbury CT) Post Joseph A. (Burke VA), Vertical control system for rotary wing aircraft.
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Lambregts Antonius A. (Renton WA), Vertical flight path steering system for aircraft.
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이 특허를 인용한 특허 (1) 인용/피인용 타임라인 분석

Carton, Mathieu; Debusschere, Pierre; Albugues, Laurent, Method and system for controlling the flight of an aircraft with respect to the pitch axis.
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A	생활필수품
A62	인명구조; 소방(사다리 E06C)
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[미국특허] Aircraft and aircraft control method 원문보기

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[미국특허] Aircraft and aircraft control method 원문보기

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이 특허에 인용된 특허 (24) 인용/피인용 타임라인 분석

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