WO2005073082A1 - Reinforcing elements in the rear section of an aircraft - Google Patents
Reinforcing elements in the rear section of an aircraft Download PDFInfo
- Publication number
- WO2005073082A1 WO2005073082A1 PCT/ES2004/000040 ES2004000040W WO2005073082A1 WO 2005073082 A1 WO2005073082 A1 WO 2005073082A1 ES 2004000040 W ES2004000040 W ES 2004000040W WO 2005073082 A1 WO2005073082 A1 WO 2005073082A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- frame
- aircraft
- fittings
- rear section
- intercostals
- 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.)
- Ceased
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
Definitions
- the present invention refers to the reinforcements arranged on a certain structural part of an aircraft and more specifically to the reinforcements of a frame corresponding to the rear section of the fuselage.
- the empennages are especially sensitive to dynamic problems, being subjected to strong bending and torsional moments, especially pronounced in the last frame, of the set of frames used to join the horizontal stabilizer and the structure.
- SUBSTITUTE SHEET (RULE 26) They refer to the union between the stabilizer and the fuselage, the use of diagonal reinforcing braces for the union of the vertical stabilizers is verified.
- the patent ES 2,112,711 of M. Torres for "Structure for aircraft” incorporates carbon fiber frames that are reinforced by a cross tube that goes through all the frames of the aircraft at the bottom. In the case of the rear fuselage, the reinforcement is incorporated at the top and a side member is added at the bottom. This reinforcement could be equivalent to the intercostals that extend perpendicularly to the sides of the frame, but they are not reinforcements like those presented in the object of the present invention.
- Typical pawn configurations on commercial aircraft consist essentially of a vertical stabilizer and a horizontal stabilizer. As its name suggests, its function is to provide stability to the plane's flight. Similarly they provide control to the plane
- SUBSTITUTE SHEET (RULE 26) by means of control surfaces located at the rear: Depth rudders ('elevator') and direction rudders ('rudder').
- the horizontal stabilizer is mounted in the rear fuselage through the "cut-out", two lateral recesses made in the rear fuselage of the aircraft, through which the aforementioned horizontal stabilizer passes.
- a series of reinforcements are incorporated in the last frame that is next to the gap through which it passes. the stabilizer.
- One of the reinforcements is made up of elements such as braces or struts that brace the interior hollow of the frame crossing it diagonally from lugs that connect with the stabilizer to the corners of the frame that forms the central hollow of the frame (predominantly rectangular).
- Another of the reinforcements is achieved through reinforcing braces that start from the edges of the frame and are integrated into the lateral stringers of the structure, extending perpendicularly from the walls of said frame.
- Figure 1 is an overview of an aircraft.
- Figure 2 is a perspective view of the rear section of the aircraft and its horizontal stabilizer, for a better view of the reinforced frame object of the invention, the tail cone has been removed.
- Figure 3 represents a profile view of the final frame, the intercostals that extend perpendicular to it and the reinforcing elements that extend between the frame and the intercostals.
- Figure 4 shows an elevation view of the final frame and the reinforcing elements that extend into its intermediate gap.
- a general airplane model is made up of the fuselage and the supporting elements.
- the fuselage is broken down into the front fuselage (1), the intermediate fuselage (2) and the final fuselage (3).
- the support surfaces are made up of the wings (4), the vertical stabilizer (5) and the horizontal stabilizer (6).
- Stabilizers (5) and (6) are set in the rear section (8) of the aircraft.
- the horizontal stabilizer (6) is assembled in the housing (7) existing for this purpose in the rear section (8) of the aircraft.
- the interior structure is exposed and the final frame (10) is shown.
- the rear section (8) of the aircraft is made up of successive frames joined together by stringers, stringers and intercostals (not shown in the drawing) on which the skins are arranged: both the upper skin (11) and the lower skin ( 1?).
- the final frame (10) is subjected to great efforts since it must withstand the moments transmitted by the connection with the horizontal stabilizer (6). Being a piece subjected to. strong stresses are adequately reinforced with rigid elements anchored to two points, that is, cylindrical bars (13) with ball joints (14) at their ends. On the one hand, the union between the frame (10) and the intercostals (15) is reinforced so that the axial load is transmitted, and on the other hand, the internal gap (16) that is established between the upper arch (17) is reinforced, the lower arch (18) and the intermediate frame (19) of the frame itself (10).
- one or more reinforcing elements are arranged passing from side to side the interior gap (16) existing in the center of the final frame (10).
- One of the ends of the cylindrical bar (13) is anchored in the corner of the hole (16) and the other end can be anchored either in the opposite corner of said hole (16) or in the hardware (20) existing in the intermediate frame (19) of the frame (10). All this according to the practical embodiment used for the development of the invention.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
Description
ELEMENTOS DE REFUERZO EN LA SECCIÓN POSTERIOR DE UNA AERONAVE. REINFORCEMENT ELEMENTS IN THE REAR SECTION OF AN AIRCRAFT.
Objeto de la invención.Object of the invention.
La presente invención se refiere a los refuerzos dispuestos sobre una determinada parte estructural de una aeronave y más concretamente a los refuerzos de una cuaderna correspondiente a la sección posterior del fuselaje. En el proceso de desarrollo de los componentes estructurales es deseable optimizar costes, plazos de desarrollo y pesos (inherente este último requisito a la industria aeronáutica). Con estas premisas, se considera necesario el análisis en detalle de todos los parámetros para proceder al dimensionado de los distintos elementos estructurales del conjunto a fabricar. Así se realiza una derivación de cargas internas, las utilizadas en el diseño y en el dimensionado, a partir de las cargas reales externas que actúan sobre el avión. Con posterioridad se realiza un conjunto de ensayos sobre los prototipos de la aeronave y sobre los modelos aerodinámicos, donde pueden detectarse inestabilidades u otro tipo de fenómenos que implicarían un rediseño de la estructura y el reforzamiento de la misma.The present invention refers to the reinforcements arranged on a certain structural part of an aircraft and more specifically to the reinforcements of a frame corresponding to the rear section of the fuselage. In the development process of structural components it is desirable to optimize costs, development times and weights (this last requirement inherent in the aeronautical industry). With these premises, a detailed analysis of all the parameters is considered necessary to proceed to the dimensioning of the different structural elements of the assembly to be manufactured. Thus, a derivation of internal loads, those used in the design and dimensioning, is made from the actual external loads acting on the aircraft. Subsequently, a set of tests is carried out on the prototypes of the aircraft and on the aerodynamic models, where instabilities or other phenomena can be detected that would imply a redesign of the structure and its reinforcement.
Por otra parte, los empenajes son especialmente sensibles a problemas dinámicos, estando sometidos a fuertes momentos de flexión y de torsión especialmente acusados en la última cuaderna, del conjunto de cuadernas empleadas para la unión del estabilizador horizontal y la estructura.On the other hand, the empennages are especially sensitive to dynamic problems, being subjected to strong bending and torsional moments, especially pronounced in the last frame, of the set of frames used to join the horizontal stabilizer and the structure.
Antecedentes de la invención.Background of the invention.
Es amplia y extensa la bibliografía existente en referencia a la unión del estabilizador horizontal con el fuselaje trasero. En los distintos diseños de aeronaves mostrados en el "Airplane Design" de Jan Roskam se puede apreciar que las cuadernas pertenecientes al fuselaje trasero y que incluyen la inserción del estabilizador horizontal presentan refuerzos complementarios para absorber los momentos transmitidos por el estabilizador. De igual forma, en los ejemplos existentes en el "Airframe Structural Design" de NIU, ISBN: 962-7128-04-X, queThe existing bibliography regarding the union of the horizontal stabilizer with the rear fuselage is wide and extensive. In the different aircraft designs shown in Jan Roskam's "Airplane Design", it can be seen that the frames belonging to the rear fuselage and which include the insert of the horizontal stabilizer have complementary reinforcements to absorb the moments transmitted by the stabilizer. Similarly, in the existing examples in the NIU "Airframe Structural Design", ISBN: 962-7128-04-X, which
HOJA DE SUSTITUCIÓN (REGLA 26) hacen referencia a la unión entre el estabilizador y el fuselaje, se constata la utilización de tirantes diagonales de refuerzo para la unión de los estabilizadores verticales. La patente ES 2.112.711 de M. Torres por "Estructura para aviones" incorpora unas cuadernas de fibra de carbono que se refuerzan mediante un tubo transversal que atraviesa todas las cuadernas de la aeronave por su parte inferior. Para el caso del fuselaje trasero se incorpora el refuerzo en la parte superior y se añade un larguero en la parte inferior. Este refuerzo podría ser equivalente a las intercostales que se extienden perpendicularmente a los laterales de la cuaderna, pero no son refuerzos como los presentados en el objeto de la presente invención.SUBSTITUTE SHEET (RULE 26) They refer to the union between the stabilizer and the fuselage, the use of diagonal reinforcing braces for the union of the vertical stabilizers is verified. The patent ES 2,112,711 of M. Torres for "Structure for aircraft" incorporates carbon fiber frames that are reinforced by a cross tube that goes through all the frames of the aircraft at the bottom. In the case of the rear fuselage, the reinforcement is incorporated at the top and a side member is added at the bottom. This reinforcement could be equivalent to the intercostals that extend perpendicularly to the sides of the frame, but they are not reinforcements like those presented in the object of the present invention.
La patente US 4621780 de Societe Nationale IndustrielleAerospatiale por "Método para ampliar una "frame" estructural" donde se cuenta con unas barras conectadas entre "frame"s adyacentes que permiten una elongación temporal de una determinada área estructural de una aeronave. Son cuadernas relativas al comportamiento de carga. Todos los miembros de refuerzo que presentan son elementos longitudinales, no presentando ninguna barra transversal como en el caso que nos ocupa.US Patent 4621780 to Societe Nationale IndustrielleAerospatiale for "Method to enlarge a structural" frame "where there are bars connected between adjacent" frames "that allow a temporary elongation of a certain structural area of an aircraft. They are frames related to loading behavior. All the reinforcing members that they present are longitudinal elements, not presenting any crossbar as in the case at hand.
La patente US 6474600 de BAE Systems por "Fuselaje de una aeronave con abertura de carga" donde en el hueco de carga creado en la parte no presurizada del fuselaje, se aprecia que las cuadernas pertenecientes al compartimento de carga poseen refuerzos que se extienden desde los laterales de las cuadernas cruzándolas longitudinalmente. Los refuerzos son para cuadernas relativas al compartimento de carga y solo presentan elementos longitudinales y ninguna barra transversal.BAE Systems patent US 6474600 for "Aircraft fuselage with cargo opening" where in the cargo gap created in the non-pressurized part of the fuselage, it is appreciated that the frames belonging to the cargo compartment have reinforcements that extend from the sides of the frames crossing them longitudinally. The reinforcements are for frames relative to the load compartment and only have longitudinal elements and no crossbar.
Descripción de la invención.Description of the invention.
Las configuraciones típicas de empenajes en aviones comerciales constan fundamentalmente de un estabilizador vertical y un estabilizador horizontal. Como su propio nombre indica, su función es proporcionar estabilidad al vuelo del avión. Del mismo modo proporcionan control al aviónTypical pawn configurations on commercial aircraft consist essentially of a vertical stabilizer and a horizontal stabilizer. As its name suggests, its function is to provide stability to the plane's flight. Similarly they provide control to the plane
HOJA DE SUSTITUCIÓN (REGLA 26) mediante superficies de control situadas en su parte posterior: Timones de profundidad ('elevator') y de dirección ('rudder'). El estabilizador horizontal se monta en el fuselaje posterior a través del "cut-out", dos huecos laterales practicados en el fuselaje trasero de la aeronave, por donde atraviesa el citado estabilizador horizontal.SUBSTITUTE SHEET (RULE 26) by means of control surfaces located at the rear: Depth rudders ('elevator') and direction rudders ('rudder'). The horizontal stabilizer is mounted in the rear fuselage through the "cut-out", two lateral recesses made in the rear fuselage of the aircraft, through which the aforementioned horizontal stabilizer passes.
Siendo los estabilizadores piezas de gran envergadura y generan grandes momentos en la estructura del fuselaje, con la finalidad de tratar de absorber estos momentos de flexión y de torsión se incorporan una serie de refuerzos en la última cuaderna que se encuentra junto al hueco por donde atraviesa el estabilizador. Uno de los refuerzos está constituido por elementos como tirantes o puntales que arriostran el hueco interior de la cuaderna atravesándolo en diagonal desde unas orejetas de unión con el estabilizador hasta las propias esquinas del marco que forma el hueco central de la cuaderna (marco de forma predominantemente rectangular). Otro de los refuerzos se logra a través de unos tirantes de refuerzo que parten de los bordes de la cuaderna y se integran en los largueros laterales de la estructura, extendiéndose perpendicularmente desde las paredes de la citada cuaderna. De todo lo descrito anteriormente se desprende la importante ventaja aportada por los refuerzos en el aspecto de la absorción de los momentos de torsión y de flexión generados en este tipo de uniones.As the stabilizers are large parts and generate great moments in the structure of the fuselage, in order to try to absorb these moments of flexion and torsion, a series of reinforcements are incorporated in the last frame that is next to the gap through which it passes. the stabilizer. One of the reinforcements is made up of elements such as braces or struts that brace the interior hollow of the frame crossing it diagonally from lugs that connect with the stabilizer to the corners of the frame that forms the central hollow of the frame (predominantly rectangular). Another of the reinforcements is achieved through reinforcing braces that start from the edges of the frame and are integrated into the lateral stringers of the structure, extending perpendicularly from the walls of said frame. From everything described above, the important advantage provided by the reinforcements in the aspect of absorption of the torsional and bending moments generated in this type of joints can be deduced.
Con el fin de facilitar la explicación se acompaña una hoja de dibujos en la que se ha representado un caso práctico de realización del alcance de la presente invención.In order to facilitate the explanation, a sheet of drawings is attached in which a practical case of embodiment of the scope of the present invention has been represented.
Breve descripción de los dibujos. La figura 1 es una vista general de una aeronave.Brief description of the drawings. Figure 1 is an overview of an aircraft.
La figura 2 es una vista en perspectiva de la sección posterior de la aeronave y de su estabilizador horizontal, para una mejor visión de la cuaderna reforzada objeto de la invención, se ha eliminado el cono de cola.Figure 2 is a perspective view of the rear section of the aircraft and its horizontal stabilizer, for a better view of the reinforced frame object of the invention, the tail cone has been removed.
HOJA DE SUSTITUCIÓN (REGLA 26) La figura 3 representa una vista de perfil de la cuaderna final, las intercostales que se extienden perpendicularmente a la misma y los elementos de refuerzo que se extienden entre la cuaderna y las intercostales. La figura 4 muestra una vista en alzado de la cuaderna final y los elementos de refuerzo que se extienden en su hueco intermedio.SUBSTITUTE SHEET (RULE 26) Figure 3 represents a profile view of the final frame, the intercostals that extend perpendicular to it and the reinforcing elements that extend between the frame and the intercostals. Figure 4 shows an elevation view of the final frame and the reinforcing elements that extend into its intermediate gap.
Descripción de una realización preferencial. Tal y como se representa en la figura 1 , un modelo general de avión está compuesto por el fuselaje y los elementos sustentadores. El fuselaje se descompone en fuselaje delantero (1 ), fuselaje intermedio (2) y fuselaje final (3). Las superficies sustentadoras se componen de las alas (4), del estabilizador vertical (5) y del estabilizador horizontal (6). Los estabilizadores (5) y (6) se establecen en la sección posterior (8) de la aeronave.Description of a preferred embodiment. As shown in figure 1, a general airplane model is made up of the fuselage and the supporting elements. The fuselage is broken down into the front fuselage (1), the intermediate fuselage (2) and the final fuselage (3). The support surfaces are made up of the wings (4), the vertical stabilizer (5) and the horizontal stabilizer (6). Stabilizers (5) and (6) are set in the rear section (8) of the aircraft.
En la figura 2, el estabilizador horizontal (6) se ensambla en el alojamiento (7) existente a tal fin en la sección posterior (8) de la aeronave. Al retirar el cono de cola (9), representado en la figura anterior, queda al descubierto la estructura interior y se muestra la cuaderna final (10). La sección posterior (8) de la aeronave está formada por sucesivas cuadernas unidas entre si por largueros, larguerillos e intercostales (no mostrados en el dibujo) sobre los que se disponen las pieles: tanto la piel superior (11 ) como la piel inferior (1?).In figure 2, the horizontal stabilizer (6) is assembled in the housing (7) existing for this purpose in the rear section (8) of the aircraft. When removing the tail cone (9), represented in the previous figure, the interior structure is exposed and the final frame (10) is shown. The rear section (8) of the aircraft is made up of successive frames joined together by stringers, stringers and intercostals (not shown in the drawing) on which the skins are arranged: both the upper skin (11) and the lower skin ( 1?).
Tal y como se muestra en las figuras 3 y 4, la cuaderna final (10) está sometida a grandes esfuerzos ya que debe soportar los momentos que transmite la unión con el estabilizador horizontal (6). Siendo una pieza sometida a. fuertes solicitaciones se refuerza adecuadamente con elementos rígidos anclados a dos puntos, esto es barras cilindricas (13) con rótulas (14) en sus extremos. Por una parte se refuerza la unión entre la cuaderna (10) y las intercostales (15) de forma que se transmita la carga axial y por otra parte se refuerza el hueco interior (16) que se establece entre el arco superior (17), el arco inferior (18) y el marco intermedio (19) de la propia cuaderna (10).As shown in Figures 3 and 4, the final frame (10) is subjected to great efforts since it must withstand the moments transmitted by the connection with the horizontal stabilizer (6). Being a piece subjected to. strong stresses are adequately reinforced with rigid elements anchored to two points, that is, cylindrical bars (13) with ball joints (14) at their ends. On the one hand, the union between the frame (10) and the intercostals (15) is reinforced so that the axial load is transmitted, and on the other hand, the internal gap (16) that is established between the upper arch (17) is reinforced, the lower arch (18) and the intermediate frame (19) of the frame itself (10).
HOJA DE SUSTITUCIÓN (REGLA 26) De esta forma, varios elementos de refuerzo se extienden desde los herrajes (20) que se disponen en el marco intermedio (19) y entre los herrajes (21) de las intercostales (15), siendo las intercostales (15) prolongaciones que se extienden perpendicularmente desde el arco superior (17) y el arco inferior (18) de la cuaderna (10). Normalmente se utilizará un refuerzo por cada intercostal (15), existiendo dos intercostales (15) en el arco superior (17) y otras dos en el arco inferior (18).SUBSTITUTE SHEET (RULE 26) In this way, several reinforcing elements extend from the fittings (20) that are arranged in the intermediate frame (19) and between the fittings (21) of the intercostals (15), the intercostals (15) being extensions that extend perpendicularly from the upper arch (17) and the lower arch (18) of the frame (10). Normally a reinforcement will be used for each intercostal (15), with two intercostals (15) in the upper arch (17) and two in the lower arch (18).
Por otro lado, según la realización práctica que se considere, uno o varios elementos de refuerzo se disponen atravesando de lado a lado el hueco interior (16) existente en el centro de la cuaderna final (10). Uno de los extremos de la barra cilindrica (13) se ancla en la esquina del hueco (16) y el otro extremo se puede anclar bien en la esquina opuesta del citado hueco (16) o bien en los herrajes (20) existentes en el marco intermedio (19) de la cuaderna (10). Todo ello según la realización práctica utilizada para el desarrollo de la invención.On the other hand, according to the practical implementation that is considered, one or more reinforcing elements are arranged passing from side to side the interior gap (16) existing in the center of the final frame (10). One of the ends of the cylindrical bar (13) is anchored in the corner of the hole (16) and the other end can be anchored either in the opposite corner of said hole (16) or in the hardware (20) existing in the intermediate frame (19) of the frame (10). All this according to the practical embodiment used for the development of the invention.
HOJA DE SUSTITUCIÓN (REGLA 26) SUBSTITUTE SHEET (RULE 26)
Claims
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/ES2004/000040 WO2005073082A1 (en) | 2004-01-30 | 2004-01-30 | Reinforcing elements in the rear section of an aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/ES2004/000040 WO2005073082A1 (en) | 2004-01-30 | 2004-01-30 | Reinforcing elements in the rear section of an aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2005073082A1 true WO2005073082A1 (en) | 2005-08-11 |
Family
ID=34814531
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/ES2004/000040 Ceased WO2005073082A1 (en) | 2004-01-30 | 2004-01-30 | Reinforcing elements in the rear section of an aircraft |
Country Status (1)
| Country | Link |
|---|---|
| WO (1) | WO2005073082A1 (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE325695C (en) * | 1920-09-17 | Flugzeugwerke G M B H Deutsche | plane | |
| US1392278A (en) * | 1918-10-14 | 1921-09-27 | Curtiss Aeroplane & Motor Co | Fuselage |
| GB281659A (en) * | 1926-11-30 | 1928-05-03 | Fiat Spa | Improvements in aeroplane fuselages |
| GB281670A (en) * | 1926-11-30 | 1929-01-31 | Fiat Societa Anonima | |
| GB334405A (en) * | 1929-09-26 | 1930-09-04 | Barnes Neville Wallis | Improvements in or connected with frame structures particularly suitable in aircraft construction |
| US1840901A (en) * | 1931-03-16 | 1932-01-12 | Ford Motor Co | Airplane |
| US1946408A (en) * | 1930-08-21 | 1934-02-06 | Flavius E Loudy | Fuselage joint |
-
2004
- 2004-01-30 WO PCT/ES2004/000040 patent/WO2005073082A1/en not_active Ceased
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE325695C (en) * | 1920-09-17 | Flugzeugwerke G M B H Deutsche | plane | |
| US1392278A (en) * | 1918-10-14 | 1921-09-27 | Curtiss Aeroplane & Motor Co | Fuselage |
| GB281659A (en) * | 1926-11-30 | 1928-05-03 | Fiat Spa | Improvements in aeroplane fuselages |
| GB281670A (en) * | 1926-11-30 | 1929-01-31 | Fiat Societa Anonima | |
| GB334405A (en) * | 1929-09-26 | 1930-09-04 | Barnes Neville Wallis | Improvements in or connected with frame structures particularly suitable in aircraft construction |
| US1946408A (en) * | 1930-08-21 | 1934-02-06 | Flavius E Loudy | Fuselage joint |
| US1840901A (en) * | 1931-03-16 | 1932-01-12 | Ford Motor Co | Airplane |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102442433B (en) | For the propelling thrust absorption equipment being combined with the ball and cocket joint of three alignment with pipe link of aircraft engine attachment pylon | |
| ES2895276T3 (en) | modular aircraft | |
| US8177166B2 (en) | Tail structure for an aircraft or spacecraft | |
| RU2438922C2 (en) | Aircraft fuselage floor structural set | |
| CN100548804C (en) | System for fixing an engine strut to a wing | |
| ES2398287B1 (en) | FUSELAGE OF AIRCRAFT RESISTANT TO IMPACT AND TOLERANT TO DAMAGE. | |
| US10343768B2 (en) | Landing gear well roof | |
| ES2609598T3 (en) | Permanently curved beam and manufacturing method | |
| ES2364109A1 (en) | Front trimming fitting and related assembly | |
| US20090321575A1 (en) | Structure of an aircraft aerofoil | |
| EP3169576B1 (en) | Vehicle and chassis | |
| WO2011000987A1 (en) | Reinforcing frame for an aircraft fuselage | |
| ES2672528T3 (en) | Aircraft fuselage section | |
| ES2277774B2 (en) | AIRCRAFT WITH A REAR SECTION OF THE FUSELAGE FOR THE SETTING OF THE ELEVATION STABILIZER AND THE STEERING TIMON. | |
| JP4954283B2 (en) | Aircraft fuselage assembly structure | |
| ES2631302T3 (en) | Interchangeable connection concept for a cone of a rear fuselage of an airplane | |
| WO2013128054A2 (en) | Reinforcing structure incorporated into an internal structure of an aircraft, made from composite material | |
| ES2293809B1 (en) | REAR SECTION OF THE FUSELAGE OF AN AIRPLANE. | |
| WO2005073082A1 (en) | Reinforcing elements in the rear section of an aircraft | |
| WO2010049565A1 (en) | System for incorporating half-sections of aerofoils in aircraft | |
| CN101242991A (en) | Framed wing boxes for wings | |
| ES2315109A1 (en) | Fitting with torsion box, of plastic material reinforced with carbon fibre, for coupling a drive motor / spindle unit for trimming of a horizontal stabiliser of an aircraft | |
| CN111348170A (en) | Civil aircraft keel beam structure capable of improving structural comprehensive performance | |
| US1433657A (en) | Two-seater monoplane aeroplane | |
| US20140349540A1 (en) | Structural Reinforcement Design for Model Aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| AK | Designated states |
Kind code of ref document: A1 Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BW BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE EG ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NA NI NO NZ OM PG PH PL PT RO RU SC SD SE SG SK SL SY TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW |
|
| AL | Designated countries for regional patents |
Kind code of ref document: A1 Designated state(s): BW GH GM KE LS MW MZ SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LU MC NL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG |
|
| 121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
| NENP | Non-entry into the national phase |
Ref country code: DE |
|
| WWW | Wipo information: withdrawn in national office |
Country of ref document: DE |
|
| 122 | Ep: pct application non-entry in european phase |