EP0348410A1 - Avion perfectionne - Google Patents

Avion perfectionne

Info

Publication number
EP0348410A1
EP0348410A1 EP19880901899 EP88901899A EP0348410A1 EP 0348410 A1 EP0348410 A1 EP 0348410A1 EP 19880901899 EP19880901899 EP 19880901899 EP 88901899 A EP88901899 A EP 88901899A EP 0348410 A1 EP0348410 A1 EP 0348410A1
Authority
EP
European Patent Office
Prior art keywords
aircraft
aftplane
accordance
wing
anhedral
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Withdrawn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
EP19880901899
Other languages
German (de)
English (en)
Inventor
Eric Blair Hall
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of EP0348410A1 publication Critical patent/EP0348410A1/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Withdrawn legal-status Critical Current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
    • B64C39/06—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.
EP19880901899 1987-03-03 1988-03-01 Avion perfectionne Withdrawn EP0348410A1 (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
EP0348410A1 true EP0348410A1 (fr) 1990-01-03

Family

ID=26291970

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19880901899 Withdrawn EP0348410A1 (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)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8715073D0 (en) * 1987-06-26 1987-08-05 Skywardens Ltd Aircraft twin-wing configuration
EP0716978B1 (fr) * 1994-12-16 2002-03-20 Aldo Frediani Avion de grandes dimensions
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
US7841559B1 (en) 2006-02-16 2010-11-30 Mbda Incorporated Aerial vehicle with variable aspect ratio deployable wings
CN107000841B (zh) * 2014-09-25 2019-08-16 安德拉斯·海尔纳迪 用于改进盒式机翼飞行器概念的方法以及对应的飞行器构造
CN112533824A (zh) 2018-08-19 2021-03-19 安德拉斯·海尔纳迪 用于改进封闭机翼飞行器概念的方法以及对应的飞行器构造

Family Cites Families (5)

* 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
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
GB8715073D0 (en) * 1987-06-26 1987-08-05 Skywardens Ltd Aircraft twin-wing configuration

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO8806551A1 *

Also Published As

Publication number Publication date
WO1988006551A1 (fr) 1988-09-07
GB2203714B (en) 1991-07-03
GB8804792D0 (en) 1988-03-30
GB2203714A (en) 1988-10-26

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Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

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17P Request for examination filed

Effective date: 19890508

AK Designated contracting states

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Effective date: 19900926

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18D Application deemed to be withdrawn

Effective date: 19910409