DE102018123470B4 - aircraft - Google Patents
aircraft Download PDFInfo
- Publication number
- DE102018123470B4 DE102018123470B4 DE102018123470.8A DE102018123470A DE102018123470B4 DE 102018123470 B4 DE102018123470 B4 DE 102018123470B4 DE 102018123470 A DE102018123470 A DE 102018123470A DE 102018123470 B4 DE102018123470 B4 DE 102018123470B4
- Authority
- DE
- Germany
- Prior art keywords
- aircraft
- wings
- ducted propellers
- wing
- wing rig
- 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.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
Luftfahrzeug (10), das folgende Merkmale umfasst:- das Luftfahrzeug (10) umfasst Tragflächen (11), waagerechte Mantelpropeller (12) und ein Flügelrigg (13) mit flexiblen, segmentweise mit Segelstoff bespannten Kohlefaser-Rippen zum Öffnen der Tragflächen (11) auf ihrer Oberseite und Unterseite in einer Öffnungsrichtung quer zum Luftfahrzeug (10),- die waagerechten Mantelpropeller (12) und das Flügelrigg (13) sind derart in die Tragflächen (11) integriert, dass die waagerechten Mantelpropeller (12) freiliegen, wenn das Flügelrigg (13) gerefft ist, und die waagerechten Mantelpropeller (12) bedeckt sind, wenn das Flügelrigg (13) gesetzt ist und- das Luftfahrzeug (10) ist dazu eingerichtet, das Flügelrigg (13) bei Start und Landung selbsttätig zu reffen.Aircraft (10) comprising the following features:- the aircraft (10) comprises wings (11), horizontal ducted propellers (12) and a wing rig (13) with flexible carbon fiber ribs covered in segments with sail fabric for opening the wings (11) on its top and bottom in an opening direction transverse to the aircraft (10), - the horizontal ducted propellers (12) and the wing rig (13) are integrated into the wings (11) in such a way that the horizontal ducted propellers (12) are exposed when the wing rig (13) is reefed and the horizontal ducted propellers (12) are covered when the wing rig (13) is set and- the aircraft (10) is set up to reef the wing rig (13) automatically during take-off and landing.
Description
Die vorliegende Erfindung betrifft ein Luftfahrzeug, insbesondere ein vollelektrisches, senkrecht start- und landefähiges (vertical take-off and landing, VTOL) Luftfahrzeug.The present invention relates to an aircraft, in particular an all-electric, vertical take-off and landing (VTOL) aircraft.
Als VTOL wird in der Luft- und Raumfahrttechnik sprachübergreifend jedwede Art von Flugzeug, Drohne oder Rakete bezeichnet, welche die Fähigkeit besitzt, im Wesentlichen senkrecht und ohne Start- und Landebahn abzuheben und wieder aufzusetzen. Dieser Sammelbegriff wird nachfolgend in einem weiten Sinne verwendet, der nicht nur Starrflügelflugzeuge mit Tragflächen, sondern ebenso Drehflügler wie Hub-, Trag-, Flugschrauber und Hybride wie Verbundhub- oder Kombinationsschrauber sowie Wandelflugzeuge einschließt. Erfasst seien des Weiteren Luftfahrzeuge mit der Fähigkeit, auf besonders kurzen Strecken zu starten und zu landen (short take-off and landing, STOL), auf kurzen Strecken zu starten, aber senkrecht zu landen (short take-off and vertical landing, STOVL) oder senkrecht zu starten, aber horizontal zu landen (vertical take-off and horizontal landing, VTHL).In aerospace engineering, a VTOL is a cross-linguistic term for any type of aircraft, drone or rocket that has the ability to take off and touch down essentially vertically and without a runway. This collective term is used in the following in a broad sense, which includes not only fixed wing aircraft with wings, but also rotorcraft such as helicopters, autogyros, helicopters and hybrids such as compound helicopters or combination helicopters and convertible aircraft. Also included are aircraft with the ability to take off and land over particularly short distances (short take-off and landing, STOL), to take off over short distances but to land vertically (short take-off and vertical landing, STOVL) or vertical take-off and horizontal landing (VTHL).
Die Erfindung stellt ein Luftfahrzeug, insbesondere ein vollelektrisches, im obigen Sinne senkrecht start- und landefähiges Luftfahrzeug gemäß dem unabhängigen Anspruch 1 bereit.The invention provides an aircraft, in particular an all-electric aircraft capable of vertical take-off and landing in the above sense, according to independent claim 1.
Ein Vorzug dieser Lösung liegt in der eröffneten Möglichkeit, Ober- und Unterseite eines Flügels gemäß einem äußerst unkomplizierten Prinzip gleichzeitig zu öffnen und zu schließen, ohne die Geometrie der Flügelaußenseiten zu stören. Ein aus der Segelsporttechnik an die Luftfahrtanforderungen adaptiertes Rigg ersetzt hierbei die aus aerodynamischen Gründen im Horizontalflug herkömmlicherweise zur Abdeckung verwendeten Lamellen (louvers).An advantage of this solution lies in the possibility it opens up of simultaneously opening and closing the top and bottom of a wing according to an extremely uncomplicated principle, without disturbing the geometry of the outer sides of the wing. A rig adapted from sailing technology to aviation requirements replaces the slats (louvers) conventionally used for aerodynamic reasons in horizontal flight.
Weitere vorteilhafte Ausgestaltungen der Erfindung sind in den abhängigen Patentansprüchen angegeben. So kann das Luftfahrzeug etwa mit abgeknickten oder gar wahlweise abknickbaren Tragflächen ausgestattet sein. Eine entsprechende Variante vergrößert die im Horizontalflug wirksame Flügelfläche, ohne aber die Standfläche des Luftfahrzeuges auszudehnen.Further advantageous refinements of the invention are specified in the dependent patent claims. For example, the aircraft can be equipped with angled or even optionally foldable wings. A corresponding variant increases the effective wing area in level flight, but without expanding the footprint of the aircraft.
Ferner mag das Luftfahrzeug über ein schnell ladbares Batteriesystem verfügen, welches die Antriebsenergie für Senkrechtstart und -landung sowie Horizontalflug bereitstellt und eine kurzfristige Aufladung des Luftfahrzeuges im Stand ermöglicht.Furthermore, the aircraft may have a fast-charging battery system, which provides the drive energy for vertical take-off and landing as well as level flight and allows the aircraft to be charged for a short time while stationary.
Zum Antrieb des Luftfahrzeuges können hierbei anstelle freifahrender Rotoren mehrere Mantelpropeller (ducted fans) auch unterschiedlicher Größe zum Einsatz kommen, wie sie abseits der Luftfahrttechnik etwa von Luftkissenfahrzeugen oder Sumpfbooten bekannt sind. Das den Propeller umgebende zylindrische Gehäuse vermag in einer derartigen Ausführungsform die Schubverluste infolge von Verwirbelungen an den Blattspitzen beträchtlich zu reduzieren. Geeignete Mantelpropeller mögen horizontal oder vertikal ausgerichtet oder zwischen beiden Stellungen schwenkbar ausgeführt sein. Zudem ist eine reine Horizontalschuberzeugung mittels feststehender Mantelpropeller denkbar.Instead of free-running rotors, several ducted fans of different sizes can be used to drive the aircraft, such as are known outside of aviation technology, for example from hovercraft or sump boats. In such an embodiment, the cylindrical housing surrounding the propeller is capable of considerably reducing the thrust losses as a result of turbulence at the blade tips. Suitable ducted propellers may be aligned horizontally or vertically, or may be pivotable between the two positions. In addition, a purely horizontal thrust generation by means of fixed ducted propellers is conceivable.
Schließlich kommt - neben einem vorzugsweise vollautonomen Betrieb des Luftfahrzeuges - bei hinreichender Qualifikation auch die Einräumung einer manuellen Kontrolle an den menschlichen Piloten in Betracht, was der erfindungsgemäßen Vorrichtung eine größtmögliche Flexibilität in der Handhabung verleiht.Finally, in addition to a preferably fully autonomous operation of the aircraft, the granting of manual control to the human pilot with sufficient qualification also comes into consideration, which gives the device according to the invention the greatest possible flexibility in handling.
Ein Ausführungsbeispiel der Erfindung ist in den Zeichnungen dargestellt und wird im Folgenden näher beschrieben.
-
1 zeigt die teiltransparente Draufsicht eines Luftfahrzeuges. -
2 zeigt eine Tragfläche des Luftfahrzeuges in geschlossenem Zustand. -
3 zeigt einen perspektivischen Schnitt der geschlossenen Tragfläche in einer alternativen Ausführungsform. -
4 zeigt die Tragfläche gemäß2 in geöffnetem Zustand.
-
1 shows the partially transparent plan view of an aircraft. -
2 shows a wing of the aircraft in the closed state. -
3 shows a perspective section of the closed wing in an alternative embodiment. -
4 shows the wing according to2 in open condition.
Die
Erfindungsgemäß ist hierzu vielmehr ein vollautomatisch reffbares, stoffbespanntes Flügelelement in Gestalt eines sogenannten Wing-Riggs (13) in die Tragfläche (11) integriert, welches - insofern einem Vorhang vergleichbar - die Tragfläche (11) gleichzeitig auf ihrer Oberseite und Unterseite öffnet.According to the invention, a fully automatic reefable, fabric-covered wing element in the form of a so-called wing rig (13) is integrated into the wing (11), which - comparable to a curtain - opens the wing (11) on its upper side and underside at the same time.
Claims (7)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102018123470.8A DE102018123470B4 (en) | 2018-09-24 | 2018-09-24 | aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102018123470.8A DE102018123470B4 (en) | 2018-09-24 | 2018-09-24 | aircraft |
Publications (2)
Publication Number | Publication Date |
---|---|
DE102018123470A1 DE102018123470A1 (en) | 2020-03-26 |
DE102018123470B4 true DE102018123470B4 (en) | 2022-07-28 |
Family
ID=69725547
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE102018123470.8A Active DE102018123470B4 (en) | 2018-09-24 | 2018-09-24 | aircraft |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE102018123470B4 (en) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102020127034A1 (en) | 2020-10-14 | 2022-04-14 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Ducted propeller of an aircraft, aircraft and component thereof |
DE102020127041B3 (en) | 2020-10-14 | 2021-09-16 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Aircraft ducted propellers and aircraft |
DE102020127029B3 (en) | 2020-10-14 | 2021-09-30 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Aircraft ducted propellers and aircraft |
DE102020133449B3 (en) | 2020-12-15 | 2021-12-30 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Ducted propeller of an aircraft, aircraft and component thereof |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5620153A (en) | 1995-03-20 | 1997-04-15 | Ginsberg; Harold M. | Light aircraft with inflatable parachute wing propelled by a ducted propeller |
US7066426B2 (en) | 2001-12-07 | 2006-06-27 | Atair Aerospace, Inc. | Multimodal, deployable vehicle |
DE202010016892U1 (en) | 2010-12-21 | 2011-08-26 | Walter Pahling | Amphibious ultralight aircraft of recent design |
DE102011105880A1 (en) | 2011-06-14 | 2012-12-20 | Eads Deutschland Gmbh | Electric drive device for an aircraft |
DE112012003115T5 (en) | 2011-07-25 | 2014-08-14 | Lightening Energy | Fast charging electric vehicle and method and apparatus for fast charging |
DE202015003815U1 (en) | 2015-05-27 | 2015-07-22 | Maximilian Salbaum | Vertical launching and landing aircraft with electric ducted propellers |
DE202015007089U1 (en) | 2015-10-10 | 2015-11-12 | Maximilian Salbaum | Launching and landing vertically blended wing body aircraft with electric ducted propellers |
DE202018000856U1 (en) | 2018-02-19 | 2018-03-06 | Christian Danz | Protection system for flight systems |
GB2555440A (en) | 2016-10-27 | 2018-05-02 | Mono Aerospace Ip Ltd | Vertical take off and landing aircraft |
-
2018
- 2018-09-24 DE DE102018123470.8A patent/DE102018123470B4/en active Active
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5620153A (en) | 1995-03-20 | 1997-04-15 | Ginsberg; Harold M. | Light aircraft with inflatable parachute wing propelled by a ducted propeller |
US7066426B2 (en) | 2001-12-07 | 2006-06-27 | Atair Aerospace, Inc. | Multimodal, deployable vehicle |
DE202010016892U1 (en) | 2010-12-21 | 2011-08-26 | Walter Pahling | Amphibious ultralight aircraft of recent design |
DE102011105880A1 (en) | 2011-06-14 | 2012-12-20 | Eads Deutschland Gmbh | Electric drive device for an aircraft |
DE112012003115T5 (en) | 2011-07-25 | 2014-08-14 | Lightening Energy | Fast charging electric vehicle and method and apparatus for fast charging |
DE202015003815U1 (en) | 2015-05-27 | 2015-07-22 | Maximilian Salbaum | Vertical launching and landing aircraft with electric ducted propellers |
DE202015007089U1 (en) | 2015-10-10 | 2015-11-12 | Maximilian Salbaum | Launching and landing vertically blended wing body aircraft with electric ducted propellers |
GB2555440A (en) | 2016-10-27 | 2018-05-02 | Mono Aerospace Ip Ltd | Vertical take off and landing aircraft |
DE202018000856U1 (en) | 2018-02-19 | 2018-03-06 | Christian Danz | Protection system for flight systems |
Also Published As
Publication number | Publication date |
---|---|
DE102018123470A1 (en) | 2020-03-26 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
DE102018123470B4 (en) | aircraft | |
DE102018116147A1 (en) | aircraft | |
DE102019112132A1 (en) | Aircraft | |
DE102018116152A1 (en) | aircraft | |
DE102018116144B4 (en) | aircraft | |
DE102018116153B4 (en) | Aircraft | |
DE102015121744B4 (en) | Propulsion device for a missile | |
DE102018116161A1 (en) | aircraft | |
DE102019118023B3 (en) | Aircraft | |
DE102020113489B4 (en) | aircraft | |
WO2021233573A1 (en) | Aircraft having a ducted fan in the airfoil | |
CN204956905U (en) | Parachuting autogyro | |
DE102018116171B4 (en) | aircraft | |
DE102019101359B4 (en) | aircraft | |
DE102018116150B4 (en) | Aircraft | |
DE102019118024B4 (en) | aircraft | |
DE102018116158A1 (en) | aircraft | |
DE102018116154B4 (en) | aircraft | |
DE102018116160B4 (en) | aircraft | |
DE102020112654B3 (en) | Aircraft | |
DE102018116172A1 (en) | aircraft | |
DE102020120266B4 (en) | aircraft | |
DE102018116151A1 (en) | aircraft | |
CN108313264A (en) | Adjustable rotor engine body system for fixed-wing unmanned plane | |
DE102018116168A1 (en) | aircraft |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
R012 | Request for examination validly filed | ||
R016 | Response to examination communication | ||
R016 | Response to examination communication | ||
R018 | Grant decision by examination section/examining division | ||
R020 | Patent grant now final |