DE4140139A1 - Aircraft which can be converted from biplane to monoplane - has short take-off and landing capability but high cruising speed - Google Patents

Aircraft which can be converted from biplane to monoplane - has short take-off and landing capability but high cruising speed

Info

Publication number
DE4140139A1
DE4140139A1 DE19914140139 DE4140139A DE4140139A1 DE 4140139 A1 DE4140139 A1 DE 4140139A1 DE 19914140139 DE19914140139 DE 19914140139 DE 4140139 A DE4140139 A DE 4140139A DE 4140139 A1 DE4140139 A1 DE 4140139A1
Authority
DE
Germany
Prior art keywords
wing
aircraft
decker
reversible
double
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Withdrawn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
DE19914140139
Other languages
German (de)
Inventor
Klaus Dipl.-Werkmeister 6600 Saarbruecken De Lellig
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
Application filed by Individual filed Critical Individual
Priority to DE19914140139 priority Critical patent/DE4140139A1/en
Publication of DE4140139A1 publication Critical patent/DE4140139A1/en
Withdrawn legal-status Critical Current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
    • B64C39/08—Aircraft not otherwise provided for having multiple wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/385—Variable incidence wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/34—Adjustable control surfaces or members, e.g. rudders collapsing or retracting against or within other surfaces or other members

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

The bi-plane aircraft has a fixed lower wing (1) and a movable upper wing (2). The upper wing is supported by pivoted links so that it can be swung down and lie on the lower wing. The upper surface of the lower wing matches the under surface of the upper wing so that when the upper wing is swung downwards the two wings form a single aerofoil section and thus convert the aircraft to a monoplane with a high cruising speed. USE/ADVANTAGE - Convertible aircraft with short take-off and landing in biplane form and with a high cruising speed.

Description

Die Erfindung bezieht sich auf ein Flugzeug mit einem feststehenden unteren Tragflügel und einem beweglich zu diesem einstellbaren oberen Tragflügel, welche so zueinander eingestellt werden können, daß die Flugeigenschaften eines Eindeckers oder eines Zweideckers genutzt werden können und zusätzlich durch einstellbare Zwischen­ stellungen durch Änderung des Anstellwinkels des oberen Tragflügels ein Bremsvorgang nach dem Aufsitzen am Boden und eine verbesserte Flugeigenschaft über laminare Luftströmung zwischen den Tragflügeln, welche zur Verkleinerung des Luftwiderstandes und zur besseren Stabilität beiträgt, erzielt wird.The invention relates to an aircraft with a fixed lower wing and a movable to this adjustable upper wings, which can be adjusted to each other, that the flight characteristics of a monoplane or a two-decker can be used and additionally by adjustable intermediate positions by changing the angle of attack of the upper wing a braking action after sitting on the ground and an improved Flight characteristics via laminar air flow between the wings, which to reduce air resistance and for better Stability contributes, is achieved.

Bei den bisher bekannten Eindecker und Zweideckerflugzeugen waren die vorbeschriebenen Vorteile nicht zusammengefaßt möglich. Um große Geschwindigkeiten zu erreichen wurde der Eindecker, wegen seinem geringen Luftwiderstand und der Doppeldecker wegen seiner schnelleren Start-und Landemöglichkeiten auf kürzerem Weg verwendet.In the previously known monoplanes and two-decker aircraft the advantages described above cannot be summarized. To reach high speeds, the monoplane was due to its low air resistance and the biplane because of its faster takeoff and landing options used on a shorter route.

Zur Lösung der genannten Aufgabe eines umsteuerbaren Flugzeuges vom Ein- zum Doppeldecker wird nachfolgenden Beschreibung eines Ausführungsbei­ spieles angeführt:To solve the aforementioned task of a reversible aircraft from entering the following description of an embodiment becomes a biplane game cited:

Hierbei wird die Beschreibung auf die beigefügten Zeichnungen von Fig. 1-Fig. 5 auf Blatt 4 und 5 bezogen: Here, the description to the accompanying drawings of Figure 1 Figure 5 is based on leaf 4 and 5..:

Es zeigt im Schnitt gezeichnet:It shows in section:

Die Fig. 1 ein Tragflügel eines Eindeckers in der bisher bekannten Form. Fig. 1 shows a wing of a monoplane in the previously known form.

Die Fig. 2 einen aus zwei Teile zusammengesetzten Tragflügel, den am Rumpf befestigten unteren Tragflügel 1 und den an diesem angelenk­ tem oberen einstellbaren Tragflügel 2. Fig. 2 is a composite of two parts of wings, the fuselage attached to the lower wing 1 and is directing at this tem adjustable upper wing 2.

Hierbei entsprechen die äußeren Umrisse der beiden Tragflügel dem Umriß und Form eines Eindeckertragflügels.The outer contours of the two wings correspond to the contours and shape of a monoplane wing.

Die Fig. 3 den unteren am Rumpf befestigten und unbeweglichen Tragflügel 1 den oberen einstellbaren Tragflügel 2 in ausgefahrener Stellung, wobei die Umrisse und die Raumanordnung denen eines Doppeldeckers entsprechen. Die Anlenkung des oberen an den unteren Tragflügel erfolgt über die paar­ weise angeordneten vorderen Stellhebel 3 und über die hinteren etwas kür­ zer gehaltenen Stellhebel 4 in den Gelenkpunkten 5. Fig. 3 the lower fixed to the fuselage and immovable wing 1, the upper adjustable wing 2 in the extended position, the outline and the spatial arrangement correspond to those of a biplane. The articulation of the upper to the lower wing takes place via the pair of wise arranged front control levers 3 and the rear control levers 4 held somewhat shorter in the articulation points 5 .

Die Fig. 4 zeigt dem oberen Tragflügel 2 in einer Zwischenstellung, wobei zu ersehen ist, daß die Hinterkante zum unteren Tragflügel 1, enger als die Vorderkante steht. (siehe Abstandsmaß a) Durch die kürzer gehaltenen hinteren Stellhebel wurde über eine Relativ­ bewegung in einem bestimmten Radius diese Stellung bewirkt. Hierbei wird die entstehende Luftdrosselung nach der Landung am Boden­ auslauf ähnlich eines Fallbremsschirmes zur Bremsung genutzt. In einer weiteren ansteuerbaren Zwischenstellung kann der Anstellwinkel des oberen Tragflügels 1 zum unteren Tragflügel 2 so eingestellt werden, daß zur Verbesserung der Flugeigenschaft eine laminare Luftströmung zur Hinterkante der Tragflügel entsteht, welche wesentlich zur Flugstabili­ sierung und zur Verbesserung des Wirkungsgrades beiträgt. Fig. 4 shows the upper wing 2 in an intermediate position, it can be seen that the rear edge of the lower wing 1 is narrower than the front edge. (see distance dimension a) This position was achieved by means of the relatively short rear control levers via a relative movement within a certain radius. The resulting air throttling after landing on the ground outlet is used for braking, similar to a parachute parachute. In a further controllable intermediate position, the angle of attack of the upper wing 1 to the lower wing 2 can be set so that a laminar air flow to the trailing edge of the wing arises to improve the flight characteristic, which substantially contributes to flight stabilization and to improving the efficiency.

Die Fig. 5 auf Seite 5 zeigt eine Anbauform des unteren festen Tragflügel 1 mit dem oberen Tragflügel 2 am Flugzeug in ausgefahrener Stellung ent­ sprechend der Fig. 3 in der angesteuerten Stellung, mit der Wirkungsweise eines Doppeldeckers. Fig. 5 on page 5 shows an attachment of the lower fixed wing 1 with the upper wing 2 on the aircraft in the extended position accordingly Fig. 3 in the controlled position, with the operation of a biplane.

Die Ansteuerung zur Umschaltung vom Ein-zum Doppeldecker und zur Ver­ besserung der Flugeigenschaft, kann wie zeichnerisch nicht dargestellt, vom Pilotensitz aus, direkt mechanisch, oder Hydraulik- und Elektrotrieb erfolgen.The control for switching from single to double decker and to Ver improvement of flight characteristics, as shown in the drawing, from the pilot's seat, directly mechanically, or hydraulic and electric drive respectively.

Alle in der Beschreibung genannten Gegenstände und Einrichtungen können für sich allein oder in jeglicher Kombination von wesentlicher Bedeutung sein.All objects and facilities mentioned in the description can essential on its own or in any combination be.

Claims (5)

1. Umsteuerbares Flugzeug vom Ein- zum Doppeldecker, dadurch gekennzeichnet, daß am Rumpf ein zweiteiliger Tragflügel angeordnet ist, welcher aus einem feststehenden unteren Tragflügel (1) und einem einstell­ baren oberen Tragflügel (2), über Stellhebel (3) und (4) in der Grundstellung so zusammengefügt ist, daß die Umrisse mit einer Ein­ deckertragfläche gleich sind.1. Reversible aircraft from single to double decker, characterized in that a two-part wing is arranged on the fuselage, which consists of a fixed lower wing ( 1 ) and an adjustable upper wing ( 2 ), via control levers ( 3 ) and ( 4 ) is put together in the basic position so that the outlines are the same with a decker wing. 2. Umsteuerbares Flugzeug vom Ein- zum Doppeldecker, nach Anspruch 1, da­ durch gekennzeichnet, daß nach dem Ausfahren des oberen Tragflügels (2) in der oberen Endstellung die Flügelanordnung und die Umrisse denen eines Doppeldeckerflugzeuges entsprechen.2. Reversible aircraft from single to double decker, according to claim 1, characterized in that after the extension of the upper wing ( 2 ) in the upper end position, the wing arrangement and the outlines correspond to those of a double-decker aircraft. 3. Umsteuerbares Flugzeug vom Ein- zum Doppeldecker, nach Anspruch 1 und 2, dadurch gekennzeichnet, daß die zur Rückseite paarweise angelenkten Stell­ hebel (4) zu den an der Vorderseite paarweise angelenkten Stellhebel (3) kürzer gehalten sind um einen vorbestimmten Einstellwegeverlauf beim Ein­ stellen des oberen Tragflügels (2) zu ermöglichen.3. Reversible aircraft from single to double decker, according to claim 1 and 2, characterized in that the pair of articulated levers to the rear ( 4 ) to the pair of articulated levers ( 3 ) are kept shorter by a predetermined course of adjustment when one the upper wing ( 2 ). 4. Umsteuerbares Flugzeug vom Ein- zum Doppeldecker, nach Anspruch 1, 2 und 3, dadurch gekennzeichnet, daß der obere einstellbare Tragflügel (2) in einer Zwischenstellung die Luftaustrittsöffnung, an den Hinterkanten der Trag­ flügel sich so verkleinert läßt, daß die gleiche Wirkung eines Brems­ fallschirmes entsteht und der Auslaufweg nach der Landung verkürzt wird.4. reversible aircraft from single to double decker, according to claim 1, 2 and 3, characterized in that the upper adjustable wing ( 2 ) in an intermediate position, the air outlet opening, at the rear edges of the wing can be reduced so that the same effect A brake parachute is created and the run-out distance is shortened after landing. 5. Umsteuerbares Flugzeug vom Ein-zum Doppeldecker, nach Anspruch 1, 2, 3 und 4, dadurch gekennzeichnet, daß der einstellbare obere Tragflügel (2) in einer weiter anwählbaren Zwischenstellung, auch der Anstellwinkel ge­ geändert werden kann. Die Einstellmöglichkeit des Anstellwinkels wird wie unter Patentanspruch 3 beschrieben durch die verschieden lang ausgeführten Stellhebel (3) und (4) durch die Relativbewegung in einem bestimmten Radius bewirkt.5. reversible aircraft from single to double decker, according to claim 1, 2, 3 and 4, characterized in that the adjustable upper wing ( 2 ) in a further selectable intermediate position, the angle of attack can be changed ge. The setting of the angle of attack is effected as described in claim 3 by the differently long actuating levers ( 3 ) and ( 4 ) by the relative movement in a certain radius.
DE19914140139 1991-12-05 1991-12-05 Aircraft which can be converted from biplane to monoplane - has short take-off and landing capability but high cruising speed Withdrawn DE4140139A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19914140139 DE4140139A1 (en) 1991-12-05 1991-12-05 Aircraft which can be converted from biplane to monoplane - has short take-off and landing capability but high cruising speed

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19914140139 DE4140139A1 (en) 1991-12-05 1991-12-05 Aircraft which can be converted from biplane to monoplane - has short take-off and landing capability but high cruising speed

Publications (1)

Publication Number Publication Date
DE4140139A1 true DE4140139A1 (en) 1993-06-09

Family

ID=6446359

Family Applications (1)

Application Number Title Priority Date Filing Date
DE19914140139 Withdrawn DE4140139A1 (en) 1991-12-05 1991-12-05 Aircraft which can be converted from biplane to monoplane - has short take-off and landing capability but high cruising speed

Country Status (1)

Country Link
DE (1) DE4140139A1 (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6601795B1 (en) * 2002-08-23 2003-08-05 Zhuo Chen Air vehicle having scissors wings
WO2004092009A1 (en) * 2003-01-17 2004-10-28 Shangxiang Zhu A Wing ASSEMBLY CAPABLE OF INCREASIGN THE LIFT AND THE ANGLE OF STALL
CN102060102A (en) * 2010-12-17 2011-05-18 中国航天空气动力技术研究院 Deformable biplane configuration
CN105197230A (en) * 2015-10-30 2015-12-30 佛山市神风航空科技有限公司 Aircraft provided with double rotor wings
CN111634408A (en) * 2020-06-03 2020-09-08 西北工业大学 Supersonic double-wing and design method thereof
CN114987735A (en) * 2022-08-08 2022-09-02 中国空气动力研究与发展中心计算空气动力研究所 Method for determining wide-speed-range low-sonic-explosion low-resistance wing profile and state configuration
RU2812162C1 (en) * 2023-11-17 2024-01-24 Федеральное автономное учреждение "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФАУ "ЦАГИ") Aircraft for local airlines

Citations (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB111691A (en) * 1917-04-26 1917-12-13 Edward Victor Hammond Improvements in and relating to Variable Wing Surfaces for Aeroplanes.
FR497720A (en) * 1918-12-12 1919-12-16 Firme A S Norsk Aeroplanfabrik Chr Hellesen Improvements to aircraft
US1336406A (en) * 1918-04-05 1920-04-06 Curtiss Aeroplane Convertible multiplane
FR516119A (en) * 1920-05-28 1921-04-14 Felix Vitu Airplane wing system with variable surfaces
FR527205A (en) * 1920-11-13 1921-10-22 Adolphe Etienne Lachassagne Aircraft wing with variable hollow and backbone
FR605597A (en) * 1925-10-31 1926-05-28 Wing device allowing an airplane to be used as a monoplane and as a biplane at will
FR620747A (en) * 1925-08-21 1927-04-28 Airplane with variable wing surface and curvature
DE461404C (en) * 1925-12-29 1928-06-20 Fernan Oscar Conill Airplane with additional wings which can be moved essentially vertically with respect to the main wings to facilitate the ascent and landing
US1718892A (en) * 1926-07-28 1929-06-25 Brown Frank Airplane
FR665704A (en) * 1927-11-22 1929-09-23 Method and devices for simultaneous or independent double and triple decomposition of airplane wings, by means of cables and articulated uprights
US1748262A (en) * 1929-01-04 1930-02-25 Wertz La Verne Franklin Aeroplane construction
US1842637A (en) * 1930-06-20 1932-01-26 Wertz La Verne Franklin Aeroplane construction
DE552213C (en) * 1927-09-11 1932-06-11 Sven Lindequist Low wing aircraft
DE594025C (en) * 1927-07-29 1934-03-09 Aldo Tammeo Aircraft with additional wings which can be moved in the vertical direction with respect to the fixed main wings
FR799840A (en) * 1935-12-24 1936-06-20 Aircraft wing with retractable auxiliary airfoil
FR813358A (en) * 1936-02-07 1937-05-31 Variable profile and surface airfoil
DE655359C (en) * 1936-03-24 1938-01-14 Francesco Tammeo Monoplane with a wing that can be dismantled into two half wings in the vertical direction
FR842416A (en) * 1938-02-16 1939-06-12 Retractable fin allowing at any time to vary in particular the surface of the wings and horizontal fixed planes of airplanes and seaplanes
US2172370A (en) * 1938-01-10 1939-09-12 Delmer S Fahrney Slot foil aircraft wing
US2317267A (en) * 1940-02-08 1943-04-20 Gazda Antoine Aircraft wing system
US2402733A (en) * 1943-03-23 1946-06-25 Pemberton Cooley Jr Aircraft wing structure
GB605075A (en) * 1945-12-13 1948-07-15 Rene Benquet Wing system for aircraft with variable lifting surface
FR2114978A1 (en) * 1972-01-27 1972-07-07 Lefeuvre Jean Claude
DE2928764A1 (en) * 1979-07-17 1981-06-04 Gerd Dipl.-Ing. 8121 Wessobrunn Berchtold Extendable aircraft wing assembly - has elements separately providing lift when extended, forming conventional wing shape when folded
FR2575722A2 (en) * 1985-01-04 1986-07-11 Aubertin Henri Lift augmenting device for light aircraft
DE3917973A1 (en) * 1989-06-02 1990-12-06 Istvan Horvath Double decker wing for aircraft - has upper and lower surfaces connected by vertical ribs

Patent Citations (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB111691A (en) * 1917-04-26 1917-12-13 Edward Victor Hammond Improvements in and relating to Variable Wing Surfaces for Aeroplanes.
US1336406A (en) * 1918-04-05 1920-04-06 Curtiss Aeroplane Convertible multiplane
FR497720A (en) * 1918-12-12 1919-12-16 Firme A S Norsk Aeroplanfabrik Chr Hellesen Improvements to aircraft
FR516119A (en) * 1920-05-28 1921-04-14 Felix Vitu Airplane wing system with variable surfaces
FR527205A (en) * 1920-11-13 1921-10-22 Adolphe Etienne Lachassagne Aircraft wing with variable hollow and backbone
FR620747A (en) * 1925-08-21 1927-04-28 Airplane with variable wing surface and curvature
FR605597A (en) * 1925-10-31 1926-05-28 Wing device allowing an airplane to be used as a monoplane and as a biplane at will
DE461404C (en) * 1925-12-29 1928-06-20 Fernan Oscar Conill Airplane with additional wings which can be moved essentially vertically with respect to the main wings to facilitate the ascent and landing
US1718892A (en) * 1926-07-28 1929-06-25 Brown Frank Airplane
DE594025C (en) * 1927-07-29 1934-03-09 Aldo Tammeo Aircraft with additional wings which can be moved in the vertical direction with respect to the fixed main wings
DE552213C (en) * 1927-09-11 1932-06-11 Sven Lindequist Low wing aircraft
FR665704A (en) * 1927-11-22 1929-09-23 Method and devices for simultaneous or independent double and triple decomposition of airplane wings, by means of cables and articulated uprights
US1748262A (en) * 1929-01-04 1930-02-25 Wertz La Verne Franklin Aeroplane construction
US1842637A (en) * 1930-06-20 1932-01-26 Wertz La Verne Franklin Aeroplane construction
FR799840A (en) * 1935-12-24 1936-06-20 Aircraft wing with retractable auxiliary airfoil
FR813358A (en) * 1936-02-07 1937-05-31 Variable profile and surface airfoil
DE655359C (en) * 1936-03-24 1938-01-14 Francesco Tammeo Monoplane with a wing that can be dismantled into two half wings in the vertical direction
US2172370A (en) * 1938-01-10 1939-09-12 Delmer S Fahrney Slot foil aircraft wing
FR842416A (en) * 1938-02-16 1939-06-12 Retractable fin allowing at any time to vary in particular the surface of the wings and horizontal fixed planes of airplanes and seaplanes
US2317267A (en) * 1940-02-08 1943-04-20 Gazda Antoine Aircraft wing system
US2402733A (en) * 1943-03-23 1946-06-25 Pemberton Cooley Jr Aircraft wing structure
GB605075A (en) * 1945-12-13 1948-07-15 Rene Benquet Wing system for aircraft with variable lifting surface
FR2114978A1 (en) * 1972-01-27 1972-07-07 Lefeuvre Jean Claude
DE2928764A1 (en) * 1979-07-17 1981-06-04 Gerd Dipl.-Ing. 8121 Wessobrunn Berchtold Extendable aircraft wing assembly - has elements separately providing lift when extended, forming conventional wing shape when folded
FR2575722A2 (en) * 1985-01-04 1986-07-11 Aubertin Henri Lift augmenting device for light aircraft
DE3917973A1 (en) * 1989-06-02 1990-12-06 Istvan Horvath Double decker wing for aircraft - has upper and lower surfaces connected by vertical ribs

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6601795B1 (en) * 2002-08-23 2003-08-05 Zhuo Chen Air vehicle having scissors wings
WO2004092009A1 (en) * 2003-01-17 2004-10-28 Shangxiang Zhu A Wing ASSEMBLY CAPABLE OF INCREASIGN THE LIFT AND THE ANGLE OF STALL
CN102060102A (en) * 2010-12-17 2011-05-18 中国航天空气动力技术研究院 Deformable biplane configuration
CN102060102B (en) * 2010-12-17 2013-12-18 中国航天空气动力技术研究院 Deformable biplane configuration
CN105197230A (en) * 2015-10-30 2015-12-30 佛山市神风航空科技有限公司 Aircraft provided with double rotor wings
CN111634408A (en) * 2020-06-03 2020-09-08 西北工业大学 Supersonic double-wing and design method thereof
CN114987735A (en) * 2022-08-08 2022-09-02 中国空气动力研究与发展中心计算空气动力研究所 Method for determining wide-speed-range low-sonic-explosion low-resistance wing profile and state configuration
RU2812162C1 (en) * 2023-11-17 2024-01-24 Федеральное автономное учреждение "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФАУ "ЦАГИ") Aircraft for local airlines

Similar Documents

Publication Publication Date Title
DE1531460C3 (en) Aircraft wing
DE2149956A1 (en) HIGH-FLOATING WINGS
DE4140139A1 (en) Aircraft which can be converted from biplane to monoplane - has short take-off and landing capability but high cruising speed
DE102022124533A1 (en) Wing or tailplane for a flying object
DE2236415A1 (en) HELICOPTER
DE723035C (en) Lag screw drive
DE1956173C3 (en) Jet-controlled aircraft with control flaps arranged in the area of the pilot's room
DE2529441C3 (en) Airfoils for aircraft, in particular for gliders
DE641119C (en) Airplane with several propellers arranged in front of the wings
DE411258C (en) plane
DE711216C (en) Airplane with jointly swiveling wing and horizontal stabilizer
DE665316C (en) Travel brake for aircraft
DE593495C (en) Brushless, multi-wing aircraft
DE396621C (en) Aircraft structure
DE541965C (en) Airplane with freely rotating wings driven by the airstream and fixed wings below
DE556008C (en) Equipment on aircraft to shorten the take-off and landing distance
DE674663C (en) Tail unit for aircraft
DE552565C (en) Spring-loaded fuselage joint for aircraft
DE668363C (en) Airplane wing with one or more flaps on the rear wing part
DE686586C (en) Aircraft tail unit with moveable elevator fin
DE681923C (en) Aircraft wing
DE673299C (en) Glide angle control device for aircraft
DE526343C (en) Multi-part aileron for aircraft that takes up the entire depth of the wing tip
DE1456070A1 (en) Deflection device for the propeller wake of an aircraft
DE632158C (en) Tail unit for gyroplane

Legal Events

Date Code Title Description
OM8 Search report available as to paragraph 43 lit. 1 sentence 1 patent law
8139 Disposal/non-payment of the annual fee