BR0302865A - Processo para diminuir amplitudes de oscilação laterais e/ou verticais na fuselagem de uma aeronave - Google Patents

Processo para diminuir amplitudes de oscilação laterais e/ou verticais na fuselagem de uma aeronave

Info

Publication number
BR0302865A
BR0302865A BR0302865-8A BR0302865A BR0302865A BR 0302865 A BR0302865 A BR 0302865A BR 0302865 A BR0302865 A BR 0302865A BR 0302865 A BR0302865 A BR 0302865A
Authority
BR
Brazil
Prior art keywords
aircraft
fuselage
lateral
determined
oscillation amplitudes
Prior art date
Application number
BR0302865-8A
Other languages
English (en)
Inventor
Detlef Schierenbeck
Original Assignee
Airbus Gmbh
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Gmbh filed Critical Airbus Gmbh
Publication of BR0302865A publication Critical patent/BR0302865A/pt

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2220/00—Active noise reduction systems

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Mechanical Engineering (AREA)
  • Vibration Prevention Devices (AREA)

Abstract

"PROCESSO PARA DIMINUIR AMPLITUDES DE OSCILAçãO LATERAIS E/OU VERTICAIS NA FUSELAGEM DE UMA AERONAVE". A presente invenção refere-se a um processo para a diminuição de amplitudes de oscilação laterais e/ou verticais na fuselagem de uma aeronave que são induzidas por dinâmicas de grupos propulsores da aeronave, para melhorar o comportamento de conforto de viagem na aeronave. Para este fim são utilizados um sistema de medição de sensor para a determinação das oscilações de grupos propulsores, e circuitos de conexão de regulação para a geração de sinais de controle e de ajuste que agem contra as amplitudes de oscilações. Para permitir de modo direto uma melhoria de amortecimento das oscilações da fuselagem induzidas pelos grupos propulsores de uma aeronave é previsto que por meio de um sensor redundante de aceleração é determinada ou são determinadas as acelerações lateral e/ou vertical em pelo menos um grupo propulsor ou em uma conexão mais dianteira de grupo propulsor/pilão, e de que os sinais de controle ou de ajuste são determinados de acordo com uma lei de regulação predeterminada para qualquer leme de inclinação lateral instalado na asa.
BR0302865-8A 2002-08-10 2003-08-08 Processo para diminuir amplitudes de oscilação laterais e/ou verticais na fuselagem de uma aeronave BR0302865A (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE10236815A DE10236815A1 (de) 2002-08-10 2002-08-10 Verfahren zur Verminderung von lateralen und/oder vertikalen Schwingungsamplituden im Rumpf eines Flugzeuges

Publications (1)

Publication Number Publication Date
BR0302865A true BR0302865A (pt) 2005-03-29

Family

ID=30775150

Family Applications (1)

Application Number Title Priority Date Filing Date
BR0302865-8A BR0302865A (pt) 2002-08-10 2003-08-08 Processo para diminuir amplitudes de oscilação laterais e/ou verticais na fuselagem de uma aeronave

Country Status (4)

Country Link
US (1) US20040104302A1 (pt)
BR (1) BR0302865A (pt)
CA (1) CA2436928A1 (pt)
DE (1) DE10236815A1 (pt)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7424989B2 (en) 2004-03-11 2008-09-16 The Boeing Company Intelligent multifunctional actuation system for vibration and buffet suppression
US8439299B2 (en) * 2005-12-21 2013-05-14 General Electric Company Active cancellation and vibration isolation with feedback and feedforward control for an aircraft engine mount
RU2401220C1 (ru) * 2009-08-17 2010-10-10 Александр Александрович Орлов Способ подавления боковых колебаний маневренного самолета на больших углах атаки
DE102011004386A1 (de) * 2011-02-18 2012-08-23 Airbus Operations Gmbh Verfahren und Vorrichtung zur Kalibrierung von Lastmesssensoren
ES2928656T3 (es) * 2016-09-26 2022-11-21 Subaru Corp Sistema de detección de daños y método de detección de daños
US10530696B2 (en) * 2017-06-12 2020-01-07 The Boeing Company Systems and methods for generating filtering rules
DE102018219179B3 (de) * 2018-11-09 2019-12-05 Siemens Aktiengesellschaft Böenlastminderung bei einem Flugzeug
EP4015362B1 (en) * 2020-12-18 2024-10-09 Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company Fan apparatus with lift fan and louvered cover

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4479620A (en) * 1978-07-13 1984-10-30 The Boeing Company Wing load alleviation system using tabbed allerons
US4725020A (en) * 1980-12-09 1988-02-16 The Boeing Company Control system incorporating structural feedback
US5082207A (en) * 1985-02-04 1992-01-21 Rockwell International Corporation Active flexible wing aircraft control system
US4796192A (en) * 1985-11-04 1989-01-03 The Boeing Company Maneuver load alleviation system
FR2656585B1 (fr) * 1989-12-28 1995-01-13 Aerospatiale Systeme pour diminuer les efforts appliques a la voilure et notamment a l'emplanture des ailes d'un aeronef en vol.
US5551650A (en) * 1994-06-16 1996-09-03 Lord Corporation Active mounts for aircraft engines
US6002778A (en) * 1996-08-07 1999-12-14 Lord Corporation Active structural control system and method including active vibration absorbers (AVAS)
DE19819341C2 (de) * 1998-04-30 2000-06-15 Daimler Chrysler Aerospace Verfahren zur Reduktion von an einem Flugzeug auftretenden Böenlasten unterhalb der Reiseflughöhe
US6493689B2 (en) * 2000-12-29 2002-12-10 General Dynamics Advanced Technology Systems, Inc. Neural net controller for noise and vibration reduction
US6402089B1 (en) * 2001-03-02 2002-06-11 General Dynamics Advanced Technology Services, Inc. System for control of active system for vibration and noise reduction
FR2841211B1 (fr) * 2002-06-21 2004-12-17 Airbus France Procede et dispositif pour reduire les mouvements vibratoires du fuselage d'un aeronef

Also Published As

Publication number Publication date
CA2436928A1 (en) 2004-02-10
US20040104302A1 (en) 2004-06-03
DE10236815A1 (de) 2004-02-26

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Legal Events

Date Code Title Description
B07A Application suspended after technical examination (opinion) [chapter 7.1 patent gazette]
B25D Requested change of name of applicant approved

Owner name: AIRBUS OPERATIONS GMBH (DE)

Free format text: NOME ALTERADO DE: AIRBUS DEUTSCHLAND GMBH

B09B Patent application refused [chapter 9.2 patent gazette]

Free format text: INDEFIRO O PEDIDO DE ACORDO COM O(S) ARTIGO(S) 24 DA LPI

B09B Patent application refused [chapter 9.2 patent gazette]

Free format text: MANTIDO O INDEFERIMENTO UMA VEZ QUE NAO FOI APRESENTADO RECURSO DENTRO DO PRAZO LEGAL.