WO1988006551A1 - Avion perfectionne - Google Patents

Avion perfectionne Download PDF

Info

Publication number
WO1988006551A1
WO1988006551A1 PCT/GB1988/000146 GB8800146W WO8806551A1 WO 1988006551 A1 WO1988006551 A1 WO 1988006551A1 GB 8800146 W GB8800146 W GB 8800146W WO 8806551 A1 WO8806551 A1 WO 8806551A1
Authority
WO
WIPO (PCT)
Prior art keywords
aftplane
aircraft
accordance
anhedral
wing
Prior art date
Application number
PCT/GB1988/000146
Other languages
English (en)
Inventor
Eric Blair Hall
Original Assignee
Eric Blair Hall
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
Priority claimed from GB878704942A external-priority patent/GB8704942D0/en
Priority claimed from GB878707261A external-priority patent/GB8707261D0/en
Application filed by Eric Blair Hall filed Critical Eric Blair Hall
Publication of WO1988006551A1 publication Critical patent/WO1988006551A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
    • B64C39/068—Aircraft not otherwise provided for having disc- or ring-shaped wings having multiple wings joined at the tips

Definitions

  • This invention relates to an improved aircraft and is an improvement in and modification to the aircraft disclosed and claimed in British Patent 2011848 and United States Patent 4336913..
  • an aircraft having swept back anhedral foreplane and forward swept aftplane, the outboard sections thereof forming a dihedral.
  • the aftplane has inboard sections which in combination with the outboard sections thereof form a 15 cranked wing.
  • the inboard sections of the aftplane have an anhedral configuration.
  • an aircraft having a swept back anhedral foreplane and a forward swept aftplane of which outboard sections at least thereof form a dihedral, the wing tips of the foreplane being connected to the wing tips of the aftplane through an articulated linkage.
  • the aftplane when cranked using an inboard anhedral portion provides lateral surfaces which can be used for directional, i.e. yaw, control of the aircraft.
  • Such surfaces may incorporate movable control surfaces forming effectively a rudder for directional control with the outboard sections of the aftplane having further movable surfaces forming aileron/elevator control.
  • FIG. 1 shows a side elevation
  • Figure 3 shows a rear perspective view
  • Figure 4 shows diagrammatically an articulated linkage joining the wing tips.
  • an aircraft is provided having no tail fin as such but employing a cranked forward swept wing as the main lifting surface in which the anhedral central section is intended to provide directional control and stability.
  • the forward swept wing is linked at or near the tips to a swept back canard foreplane by means of an articulated strut.
  • an aircraft has a fuselage 1 with a foreplane 2 mounted above the fuselage and having a swept back anhedral configuration.
  • An aftplane 3 is mounted below the fuselage and has an inboard cranked portion 4 of an anhedral configuration and an outboard portion 5 of dihedral configuration. The outboard portion 5 at least is forwardly swept.
  • High speed aileron control surfaces 6 may be provided on the trailing edge of the foreplane.
  • SUBSTITUTESHEET aftplane may include rudder control surfaces 7 and the dihedral outboard portions 5 of the aftplane may include an aileron/elevator control surface 8 together with augmentary low speed aileron control surfaces 9.
  • propulsion engines 10 mounted on the fuselage or mounted on the wing and the underside of the crank may include an undercarriage 11 being either fixed or retractable.
  • a nose wheel undercarriage 12 is provided at the forward end of the fuselage 1.
  • the foreplane and aftplane wing tips are connected through a strut member 13 which is articulated to allow wing flexing in the vertical plane.
  • the strut also permits the canard foreplane incidence to be varied in flight and the torsional tendency of the forward swept wing will at the same time be suppressed by the articulated strut which is secured in a system of bearings or bushes in a wing tip reinforcing member.
  • FIG. 4 A diagrammatic example of the articulated wing tip strut is shown in Figure 4 wherein the end of the foreplane 2 includes a universal joint or spherical bearing 14 bolted to a wing tip reinforcing member and carrying a titanium tubular strut 15 which has the other
  • the bearings 16 allow pivotal movement about a generally longitudinally extending axis whereas the bearing 14 allows universal movement. This arrangement reduces or minimises torsional effects occurring in the forward swept wing and in practice a fairing will be provided covering the actual tubular strut member 15 shown in the drawings.
  • the arrangement provides an efficient wing having low weight and cost and in addition there is inherent stability in roll and yaw. Stability is a problem associated with a forward swept wing which is otherwise of high efficiency.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Tires In General (AREA)

Abstract

Un avion a un fuselage (1) avec un plan avant (2) monté au-dessus du fuselage et ayant une configuration d'angle de dièdre latéral négatif en flèche. Un plan/arrière (3) est monté sous le fuselage et a une partie (4) coudée vers l'intérieur d'une configuration d'angle de dièdre lateral négatif, et une partie extérieure (5) d'une configuration d'angle dièdre. La partie extérieure (5), au moins, a une flèche avant. Les bouts d'aile respectifs sont en outre raccordés par des éléments de liaison (13) articulées.
PCT/GB1988/000146 1987-03-03 1988-03-01 Avion perfectionne WO1988006551A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
GB8704942 1987-03-03
GB878704942A GB8704942D0 (en) 1987-03-03 1987-03-03 Aircraft
GB878707261A GB8707261D0 (en) 1987-03-26 1987-03-26 Aircraft
GB8707261 1987-03-26

Publications (1)

Publication Number Publication Date
WO1988006551A1 true WO1988006551A1 (fr) 1988-09-07

Family

ID=26291970

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB1988/000146 WO1988006551A1 (fr) 1987-03-03 1988-03-01 Avion perfectionne

Country Status (3)

Country Link
EP (1) EP0348410A1 (fr)
GB (1) GB2203714B (fr)
WO (1) WO1988006551A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2208112B (en) * 1987-06-26 1991-04-17 Skywardens Limited An aircraft with paired aerofoils
US5899409A (en) * 1994-12-16 1999-05-04 Frediani; Aldo Large dimension aircraft
US6098923A (en) * 1998-03-13 2000-08-08 Lockheed Martin Corporation Aircraft structure to improve directional stability
DE19952024A1 (de) * 1999-10-28 2001-05-17 Schardt Friedrich Flugzeug
WO2016048211A1 (fr) * 2014-09-25 2016-03-31 Hernadi Andras Procédés pour des améliorations de la conception d'aile en structure caisson d'un aéronef et configuration d'aéronef correspondante
WO2020040671A1 (fr) 2018-08-19 2020-02-27 Hernadi Andras Procédés pour des améliorations de la conception d'aéronef à ailes en anneau et configurations d'aéronef correspondantes

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7841559B1 (en) 2006-02-16 2010-11-30 Mbda Incorporated Aerial vehicle with variable aspect ratio deployable wings

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4336913A (en) * 1979-10-02 1982-06-29 Hall Eric B Compound wing aircraft
FR2557065A1 (fr) * 1983-12-22 1985-06-28 Nguyen Manh Khanh Aerodyne a voilure polyedrique

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB949679A (en) * 1959-08-26 1964-02-19 Davide Velli Air and sea transport craft
GB2011848A (en) * 1977-10-05 1979-07-18 Hall E B Hang-Glider
GB8715073D0 (en) * 1987-06-26 1987-08-05 Skywardens Ltd Aircraft twin-wing configuration

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4336913A (en) * 1979-10-02 1982-06-29 Hall Eric B Compound wing aircraft
FR2557065A1 (fr) * 1983-12-22 1985-06-28 Nguyen Manh Khanh Aerodyne a voilure polyedrique

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2208112B (en) * 1987-06-26 1991-04-17 Skywardens Limited An aircraft with paired aerofoils
US5899409A (en) * 1994-12-16 1999-05-04 Frediani; Aldo Large dimension aircraft
US6098923A (en) * 1998-03-13 2000-08-08 Lockheed Martin Corporation Aircraft structure to improve directional stability
DE19952024A1 (de) * 1999-10-28 2001-05-17 Schardt Friedrich Flugzeug
WO2016048211A1 (fr) * 2014-09-25 2016-03-31 Hernadi Andras Procédés pour des améliorations de la conception d'aile en structure caisson d'un aéronef et configuration d'aéronef correspondante
WO2020040671A1 (fr) 2018-08-19 2020-02-27 Hernadi Andras Procédés pour des améliorations de la conception d'aéronef à ailes en anneau et configurations d'aéronef correspondantes

Also Published As

Publication number Publication date
EP0348410A1 (fr) 1990-01-03
GB2203714A (en) 1988-10-26
GB8804792D0 (en) 1988-03-30
GB2203714B (en) 1991-07-03

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