DE1283097B - Airplane with wings whose tips can be pivoted - Google Patents

Airplane with wings whose tips can be pivoted

Info

Publication number
DE1283097B
DE1283097B DEV31347A DEV0031347A DE1283097B DE 1283097 B DE1283097 B DE 1283097B DE V31347 A DEV31347 A DE V31347A DE V0031347 A DEV0031347 A DE V0031347A DE 1283097 B DE1283097 B DE 1283097B
Authority
DE
Germany
Prior art keywords
wing
pivoted
airplane
tips
wings
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.)
Pending
Application number
DEV31347A
Other languages
German (de)
Inventor
Dr Wolfgang Herbst
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.)
Vereinigte Flugtechnische Werke Fokker GmbH
Original Assignee
Vereinigte Flugtechnische Werke Fokker 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 Vereinigte Flugtechnische Werke Fokker GmbH filed Critical Vereinigte Flugtechnische Werke Fokker GmbH
Priority to DEV31347A priority Critical patent/DE1283097B/en
Publication of DE1283097B publication Critical patent/DE1283097B/en
Pending legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/08—Stabilising surfaces mounted on, or supported by, wings

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Description

Flugzeug mit Tragflügeln, deren Spitzen schwenkbar sind Es sind Flugzeuge mit Tragflügeln bekannt, deren Spitzen im Fluge nach oben oder unten in eine senkrechte Lage schwenkbar sind, um die Tragflächenbelastung erhöhen und damit den Luftwiderstand und die Böenempfindlichkeit des Flugzeugs herabsetzen zu können.Airplane with wings, the tips of which can be swiveled They are airplanes known with hydrofoils, the tips of which in flight up or down in a vertical The position can be pivoted in order to increase the wing loading and thus the air resistance and to be able to reduce the sensitivity of the aircraft to gusts.

Das Schwenken der Flügelspitzen nach oben hat jedoch den Nachteil, daß die Tragflügel eine starke effektive positive V-Stellung annehmen, wodurch das Flugzeug für Bewegungen um seine Längsachse träge wird. Das Schwenken der Flügelspitzen nach unten führt dagegen zu einer unerwünscht großen effektiven el negativen V-Stellung der Tragflügel, die das Flugzeug um seine Längsachse instabil macht.However, pivoting the wing tips upwards has the disadvantage that that the wings assume a strong effective positive V-position, whereby the Aircraft becomes sluggish to move about its longitudinal axis. The pivoting of the wing tips downwards, on the other hand, leads to an undesirably large effective el negative V-position the wing, which makes the aircraft unstable about its longitudinal axis.

Beide Nachteile sollen durch die Erfindung behoben werden.Both disadvantages are intended to be remedied by the invention.

Diese Aufgabe ist bei einem Flugzeug mit Tragflügeln, deren Spitzen um Achsen in Tiefenrichtung in eine senkrechte Lage schwenkbar sind, erfindungsgemäß dadurch gelöst, daß jede schwenkbare Flügelspitze einen von ihrer Schwenkachse sich in Gegenrichtung erstreckenden Flügelteil aufweist, der bei nicht verschwenkter Flügelspitze eine Aussparung des festen Tragflügels ausfüllt.This task is in an aircraft with wings, their tips are pivotable about axes in the depth direction in a vertical position, according to the invention solved in that each pivotable wing tip one of its pivot axis having wing part extending in the opposite direction, which when not pivoted Wing tip fills a recess in the fixed wing.

Die Ausbildung nach der Erfindung hat die Wirkung, daß das Flugzeug schneller, wendiger und weniger böenempfindlich wird, ohne an Stabilität um die Längsachse zu verlieren.The training according to the invention has the effect that the aircraft becomes faster, more agile and less sensitive to gusts without compromising stability Lose the longitudinal axis.

Die Erfindung ist in den Zeichnungen in einem Ausführungsbeispiel dargestellt. Es zeigt F i g. 1 ein Flugzeug nach der Erfindung im Aufriß mit nicht verschwenkten Flügelspitzen, F i g. 2 das Flugzeug nach F i g. 1 in Ansicht von vorn, F i g. 3 die Ansicht nach F i g. 2 mit senkrecht stehenden Flügelspitzen.The invention is shown in the drawings in one embodiment. It shows F i g. 1 shows an aircraft according to the invention in elevation with wing tips not pivoted, FIG. 2 the aircraft according to FIG. 1 in front view, FIG. 3 the view according to FIG. 2 with vertical wing tips.

Das dargestellte Flugzeug besitzt einen Rumpf 1 und zwei Tragflügel 2. Am äußeren Rand des Hauptteils 3 jedes Tragflügels 2 ist mittels eines Scharniers 5 eine Flügelspitze 4 angelenkt. Die Achse des Scharniers 5 ist parallel zur Flugzeuglängsachse dargestellt, könnte aber mit dieser auch einen geringen Winkel bilden. Die Flügelspitze 4 ist um die Achse des Scharniers 5 schwenkbar und erstreckt sich von diesem gleich weit in entgegengesetzten Richtungen. In senkrechter Lage bildet sie eine nach oben und unten gerichtete Flügelendscheibe. In waagerechter Lage füllt eine ihrer beiden Hälften eine Ausnehmung auf der Unterseite des festen Hauptteils 3 des Tragflügels aus.The aircraft shown has a fuselage 1 and two wings 2. A wing tip 4 is articulated by means of a hinge 5 on the outer edge of the main part 3 of each wing 2. The axis of the hinge 5 is shown parallel to the longitudinal axis of the aircraft, but could also form a small angle with it. The wing tip 4 is pivotable about the axis of the hinge 5 and extends from this equally far in opposite directions. In a vertical position, it forms a winglet disk directed upwards and downwards. In the horizontal position, one of its two halves fills a recess on the underside of the fixed main part 3 of the wing.

Das zum Verschwenken der Flügelspitze dienende Gestänge ist nicht dargestellt. Es kann beliebig ausgeführt sein, z. B. kann ein hydraulischer Zylinder, auch mit Drehkolben, Verwendung finden.The linkage used to pivot the wing tip is not shown. It can be designed in any way, e.g. B. can a hydraulic cylinder, also find use with rotary lobes.

Claims (1)

Patentanspruch: Flugzeug mit Tragflügeln, deren Spitzen um Achsen in Tiefenrichtung in eine senkrechte Lage schwenkbarsind, dadurch gekennzeichnet, daß jede schwenkbare Flügelspitze(4) einen von ihrer Schwenkachse sich in Gegenrichtung erstreckenden Flügelteil aufweist, der bei nicht verschwenkter Flügelspitze eine Aussparung des festen Tragflügels ausfüllt. In Betracht gezogene Druckschriften: Britische Patentschrift Nr. 934 286; französische Patentschrift Nr. 1029 256. Claim: Airplane with wings, the tips of which can be pivoted about axes in the depth direction into a vertical position, characterized in that each pivotable wing tip (4) has a wing part which extends in the opposite direction from its pivot axis and which fills a recess in the fixed wing when the wing tip is not pivoted . References considered: British Patent No. 934,286; French patent specification No. 1029 256.
DEV31347A 1966-06-24 1966-06-24 Airplane with wings whose tips can be pivoted Pending DE1283097B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DEV31347A DE1283097B (en) 1966-06-24 1966-06-24 Airplane with wings whose tips can be pivoted

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEV31347A DE1283097B (en) 1966-06-24 1966-06-24 Airplane with wings whose tips can be pivoted

Publications (1)

Publication Number Publication Date
DE1283097B true DE1283097B (en) 1968-11-14

Family

ID=7586359

Family Applications (1)

Application Number Title Priority Date Filing Date
DEV31347A Pending DE1283097B (en) 1966-06-24 1966-06-24 Airplane with wings whose tips can be pivoted

Country Status (1)

Country Link
DE (1) DE1283097B (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4538779A (en) * 1982-09-30 1985-09-03 The Boeing Company Caster type empennage assembly for aircraft
US5078338A (en) * 1990-01-19 1992-01-07 Neill Terrence O Means for maintaining a desired relationship between roll and yaw stability in a swept-wing aircraft by varying dihedral as a function of lift coefficient
DE4215577A1 (en) * 1992-05-12 1993-11-18 Schubert Werner Aircraft or airship with improved stability in flight - has angled wings formed with wide downturned tips to create increased aerodynamic support
FR2962971A1 (en) * 2010-07-20 2012-01-27 Airbus Operations Sas DEVICE AND METHOD FOR LATERAL STABILIZATION OF AN AIRCRAFT
CN105035304A (en) * 2015-08-13 2015-11-11 中国航空工业集团公司西安飞机设计研究所 Tailless flying wing layout plane with split type wing tip

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1029256A (en) * 1950-12-07 1953-06-01 Advanced flying machine
GB934286A (en) * 1961-06-16 1963-08-14 English Electric Co Ltd Improvements in and relating to wing tip folding mechanisms

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1029256A (en) * 1950-12-07 1953-06-01 Advanced flying machine
GB934286A (en) * 1961-06-16 1963-08-14 English Electric Co Ltd Improvements in and relating to wing tip folding mechanisms

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4538779A (en) * 1982-09-30 1985-09-03 The Boeing Company Caster type empennage assembly for aircraft
US5078338A (en) * 1990-01-19 1992-01-07 Neill Terrence O Means for maintaining a desired relationship between roll and yaw stability in a swept-wing aircraft by varying dihedral as a function of lift coefficient
DE4215577A1 (en) * 1992-05-12 1993-11-18 Schubert Werner Aircraft or airship with improved stability in flight - has angled wings formed with wide downturned tips to create increased aerodynamic support
FR2962971A1 (en) * 2010-07-20 2012-01-27 Airbus Operations Sas DEVICE AND METHOD FOR LATERAL STABILIZATION OF AN AIRCRAFT
WO2012017152A1 (en) * 2010-07-20 2012-02-09 Airbus Operations (Sas) Method and device for the lateral stabilization of an aircraft
US8888039B2 (en) 2010-07-20 2014-11-18 Airbus Operations Sas Method and device for the lateral stabilization of an aircraft
CN105035304A (en) * 2015-08-13 2015-11-11 中国航空工业集团公司西安飞机设计研究所 Tailless flying wing layout plane with split type wing tip

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