FR2374209A1 - Avion-canard - Google Patents

Avion-canard

Info

Publication number
FR2374209A1
FR2374209A1 FR7737573A FR7737573A FR2374209A1 FR 2374209 A1 FR2374209 A1 FR 2374209A1 FR 7737573 A FR7737573 A FR 7737573A FR 7737573 A FR7737573 A FR 7737573A FR 2374209 A1 FR2374209 A1 FR 2374209A1
Authority
FR
France
Prior art keywords
fuselage
longitudinal axis
axis
respect
empennage
Prior art date
Legal status (The legal status 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 status listed.)
Withdrawn
Application number
FR7737573A
Other languages
English (en)
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm AG
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 Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Publication of FR2374209A1 publication Critical patent/FR2374209A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/12—Canard-type aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Tires In General (AREA)
  • Emergency Lowering Means (AREA)
  • Mechanical Control Devices (AREA)

Abstract

Avion-canard dont l'empennage avant s'intègre à la surface de la voilure, cet empennage étant monté rotatif autour d'un axe formant un angle aigu par rapport à l'axe longitudinal du fuselage. L'empennage 1, dans la zone de contact avec la structure de l'avion, est réalisé à deux arêtes formant un angle obtu, l'arête arrière, située à angle aigu par rapport à l'axe longitudinal du fuselage 6, contenant l'axe de rotation 2, tandis que l'autre arête, située parallèlement à l'axe longitudinal du fuselage, vient s'appliquer étroitement, mais de façon déplaçable sur le fuselage 6.
FR7737573A 1976-12-15 1977-12-13 Avion-canard Withdrawn FR2374209A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2656692A DE2656692C2 (de) 1976-12-15 1976-12-15 Entenflugzeug

Publications (1)

Publication Number Publication Date
FR2374209A1 true FR2374209A1 (fr) 1978-07-13

Family

ID=5995543

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7737573A Withdrawn FR2374209A1 (fr) 1976-12-15 1977-12-13 Avion-canard

Country Status (7)

Country Link
US (1) US4161300A (fr)
JP (1) JPS5375700A (fr)
DE (1) DE2656692C2 (fr)
FR (1) FR2374209A1 (fr)
GB (1) GB1595442A (fr)
IT (1) IT1088993B (fr)
SE (1) SE7713035L (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2430884A1 (fr) * 1978-07-15 1980-02-08 Messerschmitt Boelkow Blohm Gouvernes pour avion
EP2081821A2 (fr) * 2006-10-18 2009-07-29 Aerion Corporation Aile à écoulement laminaire supersonique très efficace

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2751361C2 (de) * 1977-11-17 1984-09-27 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Verfahren zur Flugzeugsteuerung durch Steuerung abgelöster Flügelvorderkanten-Wirbelströme
US4485992A (en) * 1981-09-10 1984-12-04 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Leading edge flap system for aircraft control augmentation
US4569494A (en) * 1982-12-23 1986-02-11 The Boeing Company Pitch control of swept wing aircraft
US4697768A (en) * 1985-11-12 1987-10-06 Grumman Aerospace Corporation Flight control system employing complementary filter
US4797829A (en) * 1986-12-11 1989-01-10 Grumman Aerospace Corporation Flight control optimization system for multi-control surface aircraft
US4786009A (en) * 1987-01-05 1988-11-22 Vigyan Research Associates, Inc. Yaw and pitch control of air vehicles at high angles of attack
US4848700A (en) * 1987-04-16 1989-07-18 Lockheed John A Canard control system for aircraft
US5094411A (en) * 1990-10-19 1992-03-10 Vigyan, Inc. Control configured vortex flaps
US5348256A (en) * 1992-05-13 1994-09-20 The Boeing Company Supersonic aircraft and method
US5398888A (en) * 1993-05-12 1995-03-21 Northrop Grumman Corporation Skewed hinge control surface
US5366180A (en) * 1993-06-30 1994-11-22 Northrop Corporation High-lift device for aircraft
DE4422152C2 (de) * 1994-06-27 2000-02-03 Daimler Chrysler Aerospace Verfahren und Anordnung zum Optimieren der aerodynamischen Wirkung eines Tragflügels
US5875998A (en) * 1996-02-05 1999-03-02 Daimler-Benz Aerospace Airbus Gmbh Method and apparatus for optimizing the aerodynamic effect of an airfoil
US5992796A (en) * 1997-03-13 1999-11-30 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Secondary wing system for use on an aircraft
US6634594B1 (en) 2002-05-03 2003-10-21 The Boeing Company Hypersonic waverider variable leading edge flaps
US7870334B2 (en) * 2003-11-12 2011-01-11 International Business Machines Corporation Distributed task queues in a multiple-port storage system
US6935592B2 (en) * 2003-08-29 2005-08-30 Supersonic Aerospace International, Llc Aircraft lift device for low sonic boom
US20050045764A1 (en) * 2003-08-29 2005-03-03 Supersonic Aerospace International, Llc Canard position and dihedral for boom reduction and pitch/directional control
US6921045B2 (en) 2003-10-30 2005-07-26 Supersonic Aerospace International, Llc Supersonic aircraft with channel relief control
US6824092B1 (en) * 2003-10-30 2004-11-30 Supersonic Aerospace International, Llc Aircraft tail configuration for sonic boom reduction
US7216835B2 (en) * 2005-02-25 2007-05-15 Northrop Grumman Corporation Aircraft with extendable leading edge of fuselage and wings
US7246770B2 (en) * 2005-02-25 2007-07-24 Northrop Grumman Corporation Aircraft with rotatable leading edge of fuselage and wings
US7204454B2 (en) * 2005-02-25 2007-04-17 Northrop Grumman Corporation Aircraft with articulated leading edge of fuselage and wings
FR2951434B1 (fr) * 2009-10-20 2012-03-09 Airbus Operations Sas Empennage horizontal d'aeronef muni d'un apex de bord d'attaque
US10384796B2 (en) 2012-04-04 2019-08-20 Commercial Aerospace Plane Pty Limited Aerospace plane system
WO2014176622A1 (fr) * 2012-04-04 2014-11-06 Commercial Aerospace Plane Pty Limited Système d'avion aérospatial
USD887949S1 (en) * 2018-06-19 2020-06-23 Christopher R. Beskar Aircraft
RU2735107C1 (ru) * 2019-06-06 2020-10-28 Общество с ограниченной ответственностью "Альбатрос" (ООО "Альбатрос") Конструкция крепления стреловидных крыльев с фюзеляжем беспилотного летательного аппарата самолетного типа
RU195661U1 (ru) * 2019-06-27 2020-02-03 Алексей Завенович Бабаян Элемент механизации передней кромки крыла
RU194250U1 (ru) * 2019-06-27 2019-12-04 Петр Алексеевич Розин Крыло малого удлинения для дозвукового летательного аппарата
USD942321S1 (en) * 2019-09-13 2022-02-01 The Boeing Company Unmanned aircraft

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2783956A (en) * 1952-05-09 1957-03-05 English Electric Co Ltd Variable-incidence sweptback wing for aircraft
FR1304839A (fr) * 1961-10-31 1962-09-28 English Electric Co Ltd Avion supersonique
US3270989A (en) * 1965-03-30 1966-09-06 Edward C Polhamus Variable sweep aircraft
US3478989A (en) * 1966-11-14 1969-11-18 Hamburger Flugzeugbau Gmbh Supersonic aircraft

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2981504A (en) * 1959-03-13 1961-04-25 Gen Dynamics Corp Fuselage blade sealing using conical surfaces
US3104079A (en) * 1960-10-07 1963-09-17 William H Phillips Variable-geometry winged reentry vehicle
DE1456048A1 (de) * 1965-11-04 1968-11-14 Hamburger Flugzeugbau Gmbh Flugzeug mit Ausgleich der Neutralpunktwanderung
US3447761A (en) * 1967-06-12 1969-06-03 Boeing Co Supersonic airplane variable-sweep integrated airfoil system
DE2012243C2 (de) * 1970-03-14 1975-01-23 Vereinigte Flugtechnische Werke Fokker Gmbh, 2800 Bremen Flugzeug mit Deltaflügel

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2783956A (en) * 1952-05-09 1957-03-05 English Electric Co Ltd Variable-incidence sweptback wing for aircraft
FR1304839A (fr) * 1961-10-31 1962-09-28 English Electric Co Ltd Avion supersonique
US3270989A (en) * 1965-03-30 1966-09-06 Edward C Polhamus Variable sweep aircraft
US3478989A (en) * 1966-11-14 1969-11-18 Hamburger Flugzeugbau Gmbh Supersonic aircraft

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2430884A1 (fr) * 1978-07-15 1980-02-08 Messerschmitt Boelkow Blohm Gouvernes pour avion
EP2081821A2 (fr) * 2006-10-18 2009-07-29 Aerion Corporation Aile à écoulement laminaire supersonique très efficace
EP2081821B1 (fr) * 2006-10-18 2016-01-27 Aerion Corporation Avion supersonique

Also Published As

Publication number Publication date
JPS5375700A (en) 1978-07-05
IT1088993B (it) 1985-06-10
US4161300A (en) 1979-07-17
GB1595442A (en) 1981-08-12
DE2656692C2 (de) 1982-07-29
DE2656692A1 (de) 1978-06-22
SE7713035L (sv) 1978-06-16

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Legal Events

Date Code Title Description
ST Notification of lapse