DE748739C - Tail-less aircraft with tail unit or leading wing arranged in front of the wing, transverse to the flight direction on the nose of the fuselage - Google Patents
Tail-less aircraft with tail unit or leading wing arranged in front of the wing, transverse to the flight direction on the nose of the fuselageInfo
- Publication number
- DE748739C DE748739C DE1939748739D DE748739DD DE748739C DE 748739 C DE748739 C DE 748739C DE 1939748739 D DE1939748739 D DE 1939748739D DE 748739D D DE748739D D DE 748739DD DE 748739 C DE748739 C DE 748739C
- Authority
- DE
- Germany
- Prior art keywords
- tail
- wing
- aircraft
- fuselage
- nose
- 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.)
- Expired
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/10—Stabilising surfaces adjustable
- B64C5/18—Stabilising surfaces adjustable in area
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Description
Schwanzloses Flugzeug mit vor der Tragfläche, quer zur Flugrichtung am Rumpfbug angeordnetem Leitwerk oder Vorflügel Der Gegenstand der Erfindung verbessert ein schwanzloses Flugzeug mit vor der Tragfläche, quer zur Flugrichtung am Rumpfbug angeordnetem Leitwerk oder Vorflügel. Die Erfindung besteht darin, daß das Leitwerk oder der Vorflügel zur Längssymmetrieebene des Flugzeuges unsymmetrisch einziehbar ausgebildet ist.Tailless aircraft with in front of the wing, transverse to the direction of flight Tail unit or slat arranged on the nose of the fuselage. The object of the invention is improved a tailless aircraft with in front of the wing, at right angles to the direction of flight on the nose of the fuselage arranged tail unit or slat. The invention consists in that the tail unit or the slat can be retracted asymmetrically to the longitudinal plane of symmetry of the aircraft is trained.
Bekanntlich wird durch die schwanzlose .Ausbildung von Flugzeugen eine Verbesserung der aerodynamischen Eigenschaften und damit eine - Erhöhung der Fluggeschwindiglceit angestrebt. Für die Höhen- und Quersteuerung eines solchen Flugzeuges dienen an das Flügelende angelenkte Querruder und Klappen. Hierbei ist der Hebelärm von der nuerachse des Flugzeuges aus, an dem die §teuerflächen angreifen, verhältnismäßig klein und zwingt zur Verwendung großer Flächen, die bei Schnellflugzeugen jedoch unerwünscht sind. Auch ein schnelles und genaues Austrimmen des Flugzeuges bei verringerter Fluggeschwindigkeit ist mittels der am Flügel angelenlcten Klappen zufolge des kurzen Hebelarmes mit erheblichen Schwierigkeiten verbunden.As is well known, the tailless training of aircraft an improvement in the aerodynamic properties and thus an - increase in Airspeed aimed for. For the elevation and aileron control of such Ailerons and flaps hinged to the wing tip are used in the aircraft. Here is the lever noise from the center of the aircraft on which the control surfaces attack, relatively small and forces the use of large areas, which in high-speed aircraft however, are undesirable. Also quick and accurate trimming of the aircraft at reduced airspeed is by means of the flaps hinged on the wing associated with considerable difficulties due to the short lever arm.
Es ist bereits ein schwanzloses Flugzeug bekanntgeworden, bei dem das Leitwerk oder der Vorflügel vor der Tragfläche, quer zur Flugrichtung am Rumpfbug angeordnet ist. Es ist auch ferner bekannt, den zum Austrinniien vorgesehenen Vorflügel am Hauptflügel in Flugrichtung ein- und ausfahrbar anzuordnen.A tailless aircraft has already become known in which the tail unit or the slat in front of the wing, at right angles to the flight direction at the nose of the fuselage is arranged. It is also known, the slat intended for Austria to be arranged on the main wing so that it can be retracted and extended in the direction of flight.
Die Erfindung bezieht sich nun auf schwanzlose Flugzeuge mit vor dem Flügel angeordnetem Leitwerk oder Vorflügel, der zum Zwecke der Widerstandsverminderung im Sinne anderer bekannter einziehbarer Teile an Flugzeugen gleichfalls einziehbar ausgebildet ist. Das wesentliche Kennzeichen der Erfindung besteht darin, daß das Leitwerk oder der Vorflüge, zur Längssymmetrieebene des Flugzeuges unsymmetrisch einziehbar ausgebildet ist. Diese Einrichtung hat gegenüber dem Bekannten den Vorteil, daß das Leitwerk bz«-. der Vorflüge, bei Langsamflug neben seiner Wirkung zur Erzielung der Stabilität des Flugzeuges um die Querachse auch zur Unterstützung der Querruderwirkung mit herangezogen werden kann. Dadurch können die Ruderflächen am Flügel kleine, für den Schnellflug günstige Abmessungen erhalten, während bei Langsamflug die Querruderwirkung mit Hilfe des alsdann ausgefahrenen Vorflügels verstärkt wird. Ferner können auch um die Längsachse wirkende Momente durch unsymmetrisches Ausfahren des Vorflügels ausgeglichen werden.The invention now relates to tailless aircraft with before Wing arranged tail unit or slat, which is used for the purpose of reducing drag also retractable in the sense of other known retractable parts on aircraft is trained. The essential characteristic of the invention in that the tail unit or the preliminary flights, to the longitudinal plane of symmetry of the aircraft is designed to be retractable asymmetrically. This facility has towards the known the advantage that the tail unit bz «-. of the preliminary flights, in addition to its effect in slow flight to achieve the stability of the aircraft around the transverse axis also for support the aileron effect can also be used. This allows the rudder surfaces on the wing small dimensions that are favorable for high-speed flight are obtained, while with Slow flight the aileron effect with the help of the then extended slat is reinforced. Furthermore, moments acting around the longitudinal axis can also be caused by asymmetrical Extension of the slat can be compensated.
Das Leitwerk bzw. der Vorflüge, und die zugehörige Bedienungseinrichtung können derartig eingerichtet sein, daß entsprechend den Ausschlagwinkeln der Landeklappen bzw. den sonstigen Einflüssen auf die Verteilung der Auftriebskraft eine beliebig gewünschte Lage des ausgefahrenen Leitwerks eingestellt werden kann.The tail unit or the preliminary flights and the associated controls can be set up in such a way that according to the deflection angles of the landing flaps or any other influences on the distribution of the buoyancy force desired position of the extended tail can be adjusted.
Die Zeichnung gibt ein Beispiel des erfindungSgemäß ausgebildeten Flugzeuges wieder. Der Vorflüge, bzw. die Leitwerksflächen -, sind zu beiden Seiten des Rumpfbugs i angeordnet. Die ausgezogenen Linien in der Zeichnung stellen die eingefahrene Lage des Vorflügels dar, der dabei bis auf einen Reststummel 3 verkürzt ist. Die gestrichelten Linien zeigen die verschiebbaren Teile a des Vorflügels in der ausgefahrenen Stellung. Die Einrichtung zur Betätigung der Teile 2 des Vorflügels ist so getroffen, daß die Teile a der beiden Flugzeugseiten je für sich oder gemeinsam in jede beliebige Ausfahrstellung gebracht werden können.The drawing gives an example of what is constructed in accordance with the invention Plane again. The preliminary flights, or the tail surfaces - are on both sides of the bow of the fuselage i arranged. The solid lines in the drawing represent the represents the retracted position of the slat, which is shortened to a residual stub 3 is. The dashed lines show the movable parts a of the slat in the extended position. The device for actuating the parts 2 of the slat is made so that the parts a of the two sides of the aircraft each individually or together can be brought into any extended position.
Claims (1)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE748739T | 1939-09-15 |
Publications (1)
Publication Number | Publication Date |
---|---|
DE748739C true DE748739C (en) | 1944-11-08 |
Family
ID=6649042
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE1939748739D Expired DE748739C (en) | 1939-09-15 | 1939-09-15 | Tail-less aircraft with tail unit or leading wing arranged in front of the wing, transverse to the flight direction on the nose of the fuselage |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE748739C (en) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1049241B (en) * | 1953-12-31 | 1959-01-22 | United Aircraft Corp | plane |
DE1097285B (en) * | 1958-03-13 | 1961-01-12 | Ludwig Hoffmann Dipl Ing | End plate for propeller wing |
DE1134593B (en) * | 1960-11-14 | 1962-08-09 | Boelkow Entwicklungen Kg | Rotor for rotary wing aircraft |
DE1269498B (en) * | 1962-01-10 | 1968-05-30 | North American Aviation Inc | Control device for the longitudinal position of an aircraft |
BE1006009A3 (en) * | 1991-09-10 | 1994-04-19 | Deloge Philippe | Extendable tail unit with surface proportionate to the incidence angle |
WO2001069339A1 (en) * | 2000-03-16 | 2001-09-20 | Bae Systems Plc | Flight control system for an aircraft |
FR2962971A1 (en) * | 2010-07-20 | 2012-01-27 | Airbus Operations Sas | DEVICE AND METHOD FOR LATERAL STABILIZATION OF AN AIRCRAFT |
ES2758366A1 (en) * | 2018-11-02 | 2020-05-05 | Torres Martinez M | AIRCRAFT WITH ENERGY GENERATION AND ACCUMULATION (Machine-translation by Google Translate, not legally binding) |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1755540A (en) * | 1928-09-19 | 1930-04-22 | Charles H Gunn | Controllable auxiliary wing for airplanes |
US1891261A (en) * | 1931-10-05 | 1932-12-20 | Charles H Gunn | Safety wing for airplanes |
GB497967A (en) * | 1936-07-06 | 1939-01-02 | Bosch Robert | Improvements in means for automatically regulating the voltage and current output of variable speed dynamos |
-
1939
- 1939-09-15 DE DE1939748739D patent/DE748739C/en not_active Expired
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1755540A (en) * | 1928-09-19 | 1930-04-22 | Charles H Gunn | Controllable auxiliary wing for airplanes |
US1891261A (en) * | 1931-10-05 | 1932-12-20 | Charles H Gunn | Safety wing for airplanes |
GB497967A (en) * | 1936-07-06 | 1939-01-02 | Bosch Robert | Improvements in means for automatically regulating the voltage and current output of variable speed dynamos |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1049241B (en) * | 1953-12-31 | 1959-01-22 | United Aircraft Corp | plane |
DE1097285B (en) * | 1958-03-13 | 1961-01-12 | Ludwig Hoffmann Dipl Ing | End plate for propeller wing |
DE1134593B (en) * | 1960-11-14 | 1962-08-09 | Boelkow Entwicklungen Kg | Rotor for rotary wing aircraft |
DE1269498B (en) * | 1962-01-10 | 1968-05-30 | North American Aviation Inc | Control device for the longitudinal position of an aircraft |
BE1006009A3 (en) * | 1991-09-10 | 1994-04-19 | Deloge Philippe | Extendable tail unit with surface proportionate to the incidence angle |
WO2001069339A1 (en) * | 2000-03-16 | 2001-09-20 | Bae Systems Plc | Flight control system for an aircraft |
US6685137B2 (en) | 2000-03-16 | 2004-02-03 | Bae Systems Plc | Flight control system for an aircraft |
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 |
ES2758366A1 (en) * | 2018-11-02 | 2020-05-05 | Torres Martinez M | AIRCRAFT WITH ENERGY GENERATION AND ACCUMULATION (Machine-translation by Google Translate, not legally binding) |
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