WO2009046555A1 - Wing for a fixed-wing aircraft - Google Patents
Wing for a fixed-wing aircraft Download PDFInfo
- Publication number
- WO2009046555A1 WO2009046555A1 PCT/CH2008/000413 CH2008000413W WO2009046555A1 WO 2009046555 A1 WO2009046555 A1 WO 2009046555A1 CH 2008000413 W CH2008000413 W CH 2008000413W WO 2009046555 A1 WO2009046555 A1 WO 2009046555A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- wing
- lid
- shell
- webs
- rigid
- Prior art date
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
- B64C3/46—Varying camber by inflatable elements
Definitions
- the present invention relates to wings of fixed wing aircraft according to the preamble of claim 1.
- the object of the present invention is to provide wings, which in the non-operating state have a low overall height and a smooth underside and, where appropriate, can be pivoted to the aircraft equipped therewith.
- the solution of the problem is reflected in the characterizing part of claim 1 in terms of their essential features in the following claims with respect to further advantageous embodiments.
- the solution is characterized by an aerodynamically smooth lower part of the wing, which, viewed statically, comprises both its tension zone and also essentially the pressure zone and an upper part of the wing, which is constructed by pneumatic elements, to supplement the wing profile.
- Such wings according to the invention can be used both for aircraft with main wing and elevation unit, as well as for those with a slat (so-called canards) or for aircraft with three pairs of wings, as known from the prior art.
- slat so-called canards
- canards for aircraft with three pairs of wings, as known from the prior art.
- Wing, Fig. 2 is a longitudinal section through the wing.
- FIG. 1 shows a cross section through a wing 1
- FIG. 2 shows a longitudinal section through the greatest height of the wing 1.
- the lower part of the wing 1 is formed from a lightweight and high-strength material such as CFRP, which is designed here as a shell 5.
- This shell 5 encloses a leading edge 6 and a trailing edge 7 and is in the Ab- _
- the space between shell 5 and lid 8 is filled with, for example, a honeycomb structure 9, which is formed of aluminum, CFRP or another rigid material.
- Shell 5, honeycomb structure 9 and cover 8 are glued together, as known from the prior art.
- this has also made of CFK and glued example or integrally with the shell 5 webs 2.
- Resulting cavities 2a can be acted upon with compressed air, the pressure for this purpose is preferably> lBar. Thus, the lower part of the wing can be biased.
- a web 11 is visible, for example made of a textile and low-stretch fabric, such as aramid crafted.
- This pneumatic part 10 of the wing 2 is closed at the top by means of an airtight and flexible outer skin 12 also made of a little stretchy fabric, in turn, for example, aramid, which is coated for the purpose of tightness with a UV-resistant plastic.
- the longitudinal section according to FIG. 3 the structure of the pneumatic part 10 in the direction of the longitudinal axis of the wing is visible.
- the webs 11 are glued to the lid 8, as is known in the art.
- the connection with the outer skin is also made by gluing or welding.
- the air pressure in the pneumatic part 10 of the wing 1 is chosen so that it remains smooth under the aerodynamic stress in any case. For this purpose, barometric pressures ⁇ 1 bar have proven sufficient. Since the lower, rigid part of the wing can absorb substantially all of the bending load of the wing, the neutral fiber of the wing is displaced by the pneumatic part 10 only slightly downwards.
- the cross sections of Canard wings 3 and the vertical stabilizer 4 differ only slightly from the extension of the wings 1, but otherwise are of similar construction: From shell 5, cover 8, rigid webs 2 honeycomb structure 9 and pneumatic part 10th
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The wing (1) according to the invention has a lower, rigid part and an upper, pneumatic part (10) of the wing. The lower part is made of a tray (5), for example composed made of CFRP, comprising a leading edge (6) and a trailing edge (7). Said tray (5) is closed from above by a lid (8). The space between the tray (5) and the lid (8) is completely filled with a honeycomb structure (9), which is glued to the tray (5) and the lid (8). The honeycomb structure is made, for example, of CFRP or aluminum, or another rigid material. Perpendicular to the lid (8) and substantially parallel to the axis of the wing, textile ribs (11) are glued onto the lid (8). An airtight outer skin (12) is connected to said textile ribs (11) by gluing or welding. The textile material of the ribs (11) and outer skin (12) is made of a woven fabric having little elasticity, for example aramid fibers.
Description
_ _ _ _
Flügel für ein StarrflügelflugzeugWing for a fixed-wing aircraft
Die vorliegende Erfindung bezieht sich auf Flügel von Starrflügelflugzeugen nach dem Oberbegriff des Patentanspruches 1. Die Aufgabe der vorliegenden Erfindung ist es, Flügel zu schaffen, welche im Nichbetriebszustande eine geringe Bauhöhe und eine glatte Unterseite aufweisen und gegebenenfalls an das damit ausgerüstete Flugzeug herangeschwenkt werden können. Die Lösung der gestellten Aufgabe ist wiedergegeben im kennzeichnenden Teil des Patentanspruches 1 hinsichtlich ihrer wesentlichen Merkmale, in den folgenden Ansprüchen hinsichtlich weiterer vorteilhafter Ausbildungen. Die Lösung zeichnet sich aus durch einen aerodynamisch glat- ten unteren Teil des Flügels, welcher statisch gesehen sowohl seine Zugzone und auch im Wesentlichen die Druckzone umfasst und einen durch pneumatische Elemente ausgeführten oberen Teil des Flügels zur Ergänzung des Flügelprofils. Solche erfindungsgemässen Flügel sind sowohl für Flugzeuge mit Hauptflügel und Höhenietwerk, als auch für solche mit einem Vorflügel (sog. Canards) oder auch für Flugzeuge mit drei Flügelpaaren, wie aus dem Stande der Technik bekannt, einsetzbar. Anhand der beigefügten Zeichnung wird der Erfindungsgedanke näher erläutert. Es zeigenThe present invention relates to wings of fixed wing aircraft according to the preamble of claim 1. The object of the present invention is to provide wings, which in the non-operating state have a low overall height and a smooth underside and, where appropriate, can be pivoted to the aircraft equipped therewith. The solution of the problem is reflected in the characterizing part of claim 1 in terms of their essential features in the following claims with respect to further advantageous embodiments. The solution is characterized by an aerodynamically smooth lower part of the wing, which, viewed statically, comprises both its tension zone and also essentially the pressure zone and an upper part of the wing, which is constructed by pneumatic elements, to supplement the wing profile. Such wings according to the invention can be used both for aircraft with main wing and elevation unit, as well as for those with a slat (so-called canards) or for aircraft with three pairs of wings, as known from the prior art. Reference to the accompanying drawings, the inventive concept is explained in detail. Show it
Fig. 1 einen Querschnitt durch einen erfindungsgemässen1 shows a cross section through an inventive
Flügel, Fig. 2 einen Längsschnitt durch den Flügel.Wing, Fig. 2 is a longitudinal section through the wing.
Fig. 1 zeigt einen Querschnitt durch einen Flügel 1, Fig. 2 einen Längsschnitt durch die grösste Höhe des Flügels 1. Der untere Teil des Flügels 1 ist gebildet aus einem leichten und hochfesten Werkstoff wie beispielsweise CFK, welcher hier als Schale 5 ausgebildet ist. Diese Schale 5 schliesst eine Anströmkante 6 und eine Abströmkante 7 ein und ist bei der Ab-
_1 shows a cross section through a wing 1, FIG. 2 shows a longitudinal section through the greatest height of the wing 1. The lower part of the wing 1 is formed from a lightweight and high-strength material such as CFRP, which is designed here as a shell 5. This shell 5 encloses a leading edge 6 and a trailing edge 7 and is in the Ab- _
strömkante 7 soweit in die Flügeloberseite hinaufgezogen, dass sie Steuerklappen Ia einschliessen kann.strömkante 7 pulled up into the wing top so far that they can include control flaps Ia.
Ein beispielsweise flacher Deckel 8, ebenfalls aus CFK hergestellt, schliesst die Schale 5 nach oben ab. Der Zwischenraum zwischen Schale 5 und Deckel 8 ist gefüllt mit beispielsweise einer Wabenstruktur 9, die aus Aluminium, CFK oder einem anderen steifen Werkstoff gebildet ist. Schale 5, Wabenstruktur 9 und Deckel 8 sind miteinander verklebt, wie aus dem Stand der Technik bekannt. In einem zweiten Ausführungsbeispiel der Schale 5 gemäss Fig. 2 weist diese, ebenfalls aus CFK gefertigte und beispielsweise eingeklebte oder einstückig mit der Schale 5 erzeugte Stege 2 auf. Dadurch entstehende Hohlräume 2a können mit Druckluft beaufschlagt werden, deren Druck für diesen Zweck vor- zugsweise >lBar ist. Damit kann der Untere Teil des Flügels vorgespannt werden.An example flat cover 8, also made of CFK, closes the shell 5 from above. The space between shell 5 and lid 8 is filled with, for example, a honeycomb structure 9, which is formed of aluminum, CFRP or another rigid material. Shell 5, honeycomb structure 9 and cover 8 are glued together, as known from the prior art. In a second embodiment of the shell 5 according to FIG. 2, this has also made of CFK and glued example or integrally with the shell 5 webs 2. Resulting cavities 2a can be acted upon with compressed air, the pressure for this purpose is preferably> lBar. Thus, the lower part of the wing can be biased.
Über dem Deckel 8 ist der pneumatische Teil 10 des Flügels 2 aufgebaut. In Fig. 2 ist ein Steg 11 sichtbar, beispielsweise aus einem textilen und wenig dehnbaren Gewebe, wie Aramid ge- fertigt. Dieser pneumatische Teil 10 des Flügels 2 ist nach oben abgeschlossen mittels einer luftdichten und flexiblen Aussenhaut 12 aus ebenfalls einem wenig dehnbaren Gewebe, wiederum beispielsweise aus Aramid, welches zum Zwecke der Dichtheit mit einem UV-beständigen Kunststoff beschichtet ist. Im Längsschnitt gemäss Fig. 3 ist der Aufbau des pneumatischen Teiles 10 in der Richtung der Längsachse des Flügels sichtbar. In beispielsweise regelmässigen Abständen sind die Stege 11 mit dem Deckel 8 verklebt, wie aus dem Stande der Technik bekannt ist. Die Verbindung mit der Aussenhaut er- folgt ebenfalls durch Kleben oder Schweissen.Over the cover 8 of the pneumatic part 10 of the wing 2 is constructed. In Fig. 2, a web 11 is visible, for example made of a textile and low-stretch fabric, such as aramid crafted. This pneumatic part 10 of the wing 2 is closed at the top by means of an airtight and flexible outer skin 12 also made of a little stretchy fabric, in turn, for example, aramid, which is coated for the purpose of tightness with a UV-resistant plastic. In the longitudinal section according to FIG. 3, the structure of the pneumatic part 10 in the direction of the longitudinal axis of the wing is visible. In, for example, regular intervals, the webs 11 are glued to the lid 8, as is known in the art. The connection with the outer skin is also made by gluing or welding.
Der Luftdruck im pneumatischen Teil 10 des Flügels 1 wird so gewählt, dass dieser bei der aerodynamischen Beanspruchung auf jeden Fall glatt bleibt. Dazu haben sich Luftdrucke <lBar als genügend erwiesen. Da der untere, rigide Teil des Flügels im Wesentlichen die ganze Biegelast des Flügels aufnehmen kann, wird die neutrale Faser des Flügels durch den pneumatischen Teil 10 nur wenig nach unten verschoben.
Die Querschnitte von Canard-Flügeln 3 und des Seitenleitwerkes 4 unterscheiden sich nur wenig von der Streckung der Flügel 1, sind aber sonst gleichartig aufgebaut: Aus Schale 5, Deckel 8, rigiden Stegen 2 Wabenstruktur 9 und pneumatischem Teil 10.
The air pressure in the pneumatic part 10 of the wing 1 is chosen so that it remains smooth under the aerodynamic stress in any case. For this purpose, barometric pressures <1 bar have proven sufficient. Since the lower, rigid part of the wing can absorb substantially all of the bending load of the wing, the neutral fiber of the wing is displaced by the pneumatic part 10 only slightly downwards. The cross sections of Canard wings 3 and the vertical stabilizer 4 differ only slightly from the extension of the wings 1, but otherwise are of similar construction: From shell 5, cover 8, rigid webs 2 honeycomb structure 9 and pneumatic part 10th
Claims
1. Flügel (1) für ein Starrflügelflugzeug gekennzeichnet durch folgenden Aufbau - ein unterer rigider Teil im Wesentlichen zur Aufnahme der Biegelast des Flügels (1) ein oberer pneumatischer Teil (10) zur aerodynamischen Ergänzung des Flügelprofils.1. wings (1) for a fixed wing aircraft characterized by the following structure - a lower rigid part substantially for receiving the bending load of the wing (1) an upper pneumatic part (10) for aerodynamic supplementation of the wing profile.
2. Flügel (1) nach Patentanspruch 1 dadurch gekennzeichnet, dass der untere rigide Teil aufgebaut ist aus einer Schale (5) , welche seine ganze Unterseite eine Anströmkante (6) und eine Abströmkante (7) des Flügels (1) ein- schliesst, ein flacher Deckel (8) vorhanden ist, welcher die Schale (5) nach oben abschliesst, eine Wabenstruktur (9) vorhanden ist und den Hohlraum zwischen der Schale (5) und dem Deckel ganz ausfüllt und mit der Schale (5) und dem Deckel verklebt ist, die Schale (5) und der Deckel aus einem leichten und hochfesten Werkstoff gebildet sind, die Wabenstruktur (9) aus einem steifen Werkstoff hergestellt ist.2. wing (1) according to claim 1, characterized in that the lower rigid part is constructed of a shell (5), which encloses its entire underside a leading edge (6) and a trailing edge (7) of the wing (1), a flat lid (8) is provided, which closes the shell (5) upwards, a honeycomb structure (9) is present and completely fills the cavity between the shell (5) and the lid and with the shell (5) and the lid is glued, the shell (5) and the lid are formed of a light and high-strength material, the honeycomb structure (9) is made of a rigid material.
3. Flügel (1) nach Patentanspruch 1 dadurch gekennzeichnet, dass der untere rigide Teil aufgebaut ist aus einer Schale (5), welche seine ganze Unterseite eine Anströmkante (6) und eine Abströmkante (7) des Flügels (1) ein- schliesst, ein flacher Deckel (8) vorhanden ist, welcher die Schale (5) nach oben abschliesst, eine Vielzahl von rigiden Stegen (2) vorhanden ist, welche sich in der Richtung der Flügelachse erstrecken mit zwischen den Stegen (2) liegenden Hohlräumen (2a), und den Raum zwischen der Schale (5) und _3. wing (1) according to claim 1, characterized in that the lower rigid part is constructed of a shell (5), which encloses its entire underside a leading edge (6) and a trailing edge (7) of the wing (1), a flat cover (8) is provided, which closes the shell (5) upwards, a plurality of rigid webs (2) is present, which extend in the direction of the wing axis with interposed between the webs (2) cavities (2a) , and the space between the shell (5) and _
dem Deckel ganz ausfüllen und mit der Schale (5) und dem Deckel verklebt sind, die Schale (5), die rigiden Stege (2) und der Deckel (8) aus einem leichten und hochfesten Werkstoff ge- bildet sind.completely fill the lid and are glued to the shell (5) and the lid, the shell (5), the rigid webs (2) and the lid (8) are made of a lightweight and high-strength material.
4. Flügel (1) nach Patentanspruch 3 dadurch gekennzeichnet, dass die Hohlräume (2a) zwischen den rigiden Stegen (2) mit Druckluft von >lBar beaufschlagt sind.4. wing (1) according to claim 3, characterized in that the cavities (2 a) between the rigid webs (2) are acted upon by compressed air of> lBar.
5. Flügel (1) nach Patentanspruch 3 dadurch gekennzeichnet, dass der leichte und hochfeste Werkstoff für die Schale (5), die rigiden Stege (2) und den Deckel (8) ein CFK ist .5. wing (1) according to claim 3, characterized in that the lightweight and high-strength material for the shell (5), the rigid webs (2) and the lid (8) is a CFRP.
6. Flügel (1) nach Patentanspruch 1 dadurch gekennzeichnet, dass der obere pneumatische Teil (1) des Flügels (1) aufgebaut ist aus einer Vielzahl von parallel zur Längs- achse des Flügels (1) und senkrecht auf dem Deckel (8) befestigten textilen Stegen (11) aus wenig dehnbarem Gewebe besteht, die textilen Stege (11) an einer Aussenhaut (12) befestigt sind, welche luftdicht ist, - die Aussenhaut (12) luftdicht am unteren rigiden Teil des Flügels (1) befestigt ist. die Aussenhaut (12) aus einem wenig dehnbaren textilen Gewebe besteht.6. wing (1) according to claim 1, characterized in that the upper pneumatic part (1) of the wing (1) is constructed of a plurality of parallel to the longitudinal axis of the wing (1) and perpendicular to the lid (8) textile webs (11) consists of low-stretch fabric, the textile webs (11) are attached to an outer skin (12) which is airtight, - the outer skin (12) airtight to the lower rigid part of the wing (1) is attached. the outer skin (12) consists of a little stretchy textile fabric.
7. Flügel (1) nach Patentanspruch 6 dadurch gekennzeichnet, dass das wenig dehnbare textile Gewebe von textilen Stegen (11) und Aussenhaut (12) aus Aramidfasern gewoben ist.7. wing (1) according to claim 6, characterized in that the low-stretch textile fabric of textile webs (11) and outer skin (12) is woven from aramid fibers.
8. Flügel (1) nach Patentanspruch 1 dadurch gekennzeichnet, dass sowohl Canard-Flügel (3) als auch Seitenleitwerk (4) aufgebaut sind, wie die Flügel (1). 8. wing (1) according to claim 1, characterized in that both Canard-wing (3) and vertical stabilizer (4) are constructed, as the wings (1).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH1582/07 | 2007-10-10 | ||
| CH15822007 | 2007-10-10 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2009046555A1 true WO2009046555A1 (en) | 2009-04-16 |
Family
ID=39539669
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/CH2008/000413 WO2009046555A1 (en) | 2007-10-10 | 2008-10-06 | Wing for a fixed-wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| WO (1) | WO2009046555A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102009060611A1 (en) * | 2009-12-28 | 2011-06-30 | Käser, Uwe, 69427 | Vehicle i.e. inflatable flight, for transportation on public road, has inflatable and/or telescopic profile segments swiveling out bearing surface and forming fully span width and profile geometry |
| CN102642611A (en) * | 2012-04-24 | 2012-08-22 | 哈尔滨工业大学 | Actively deformed stressed-skin structure based on pneumatic muscles |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2969207A (en) * | 1958-10-16 | 1961-01-24 | Doyle F Fain | Variable camber airfoil |
| FR2246444A1 (en) * | 1973-10-05 | 1975-05-02 | Morin Bernard | Aircraft with slow landing speed - wing section is variable between thin and thick in flight |
| US4582278A (en) * | 1985-02-15 | 1986-04-15 | Northrop Corporation | Air foil having adjustable shape |
| GB2165513A (en) * | 1984-10-15 | 1986-04-16 | Barry John Jacobson | Inflatable aeroplane wing structure |
| GB2311978A (en) * | 1996-04-10 | 1997-10-15 | Robert Pyatt | Adjustable wing |
| DE19836629C1 (en) * | 1998-08-13 | 1999-10-14 | Deutsch Zentr Luft & Raumfahrt | Aerodynamic wing for aircraft |
| US6199796B1 (en) * | 1996-07-18 | 2001-03-13 | Prospective Concepts Ag | Adaptive pneumatic wing for fixed wing aircraft |
| US6622974B1 (en) * | 2002-08-14 | 2003-09-23 | The Boeing Company | Geometric morphing wing with expandable spars |
| EP1442976A1 (en) * | 2003-02-03 | 2004-08-04 | The Boeing Company | Airfoil member comprising an inflatable geometric morphing device with embedded fiber matrix |
-
2008
- 2008-10-06 WO PCT/CH2008/000413 patent/WO2009046555A1/en active Application Filing
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2969207A (en) * | 1958-10-16 | 1961-01-24 | Doyle F Fain | Variable camber airfoil |
| FR2246444A1 (en) * | 1973-10-05 | 1975-05-02 | Morin Bernard | Aircraft with slow landing speed - wing section is variable between thin and thick in flight |
| GB2165513A (en) * | 1984-10-15 | 1986-04-16 | Barry John Jacobson | Inflatable aeroplane wing structure |
| US4582278A (en) * | 1985-02-15 | 1986-04-15 | Northrop Corporation | Air foil having adjustable shape |
| GB2311978A (en) * | 1996-04-10 | 1997-10-15 | Robert Pyatt | Adjustable wing |
| US6199796B1 (en) * | 1996-07-18 | 2001-03-13 | Prospective Concepts Ag | Adaptive pneumatic wing for fixed wing aircraft |
| DE19836629C1 (en) * | 1998-08-13 | 1999-10-14 | Deutsch Zentr Luft & Raumfahrt | Aerodynamic wing for aircraft |
| US6622974B1 (en) * | 2002-08-14 | 2003-09-23 | The Boeing Company | Geometric morphing wing with expandable spars |
| EP1442976A1 (en) * | 2003-02-03 | 2004-08-04 | The Boeing Company | Airfoil member comprising an inflatable geometric morphing device with embedded fiber matrix |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102009060611A1 (en) * | 2009-12-28 | 2011-06-30 | Käser, Uwe, 69427 | Vehicle i.e. inflatable flight, for transportation on public road, has inflatable and/or telescopic profile segments swiveling out bearing surface and forming fully span width and profile geometry |
| CN102642611A (en) * | 2012-04-24 | 2012-08-22 | 哈尔滨工业大学 | Actively deformed stressed-skin structure based on pneumatic muscles |
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