DE1283097B - Airplane with wings whose tips can be pivoted - Google Patents
Airplane with wings whose tips can be pivotedInfo
- 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
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)
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)
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)
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 |
-
1966
- 1966-06-24 DE DEV31347A patent/DE1283097B/en active Pending
Patent Citations (2)
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)
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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