ES2226510B1 - PROCESS OF UNION OF A REAR FUSELAGE AND A VERTICAL STABILIZER. - Google Patents
PROCESS OF UNION OF A REAR FUSELAGE AND A VERTICAL STABILIZER.Info
- Publication number
- ES2226510B1 ES2226510B1 ES200102357A ES200102357A ES2226510B1 ES 2226510 B1 ES2226510 B1 ES 2226510B1 ES 200102357 A ES200102357 A ES 200102357A ES 200102357 A ES200102357 A ES 200102357A ES 2226510 B1 ES2226510 B1 ES 2226510B1
- Authority
- ES
- Spain
- Prior art keywords
- fuselage
- zone
- joining
- vertical stabilizer
- holes
- 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 - Fee Related
Links
- 239000003381 stabilizer Substances 0.000 title claims abstract description 31
- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000005304 joining Methods 0.000 claims abstract description 22
- 238000002360 preparation method Methods 0.000 claims abstract description 13
- 238000007743 anodising Methods 0.000 claims abstract description 8
- 238000004140 cleaning Methods 0.000 claims abstract description 3
- 238000005553 drilling Methods 0.000 claims abstract description 3
- 238000003801 milling Methods 0.000 claims abstract description 3
- 210000001503 joint Anatomy 0.000 claims description 9
- 238000009826 distribution Methods 0.000 claims description 2
- 230000003247 decreasing effect Effects 0.000 claims 1
- 238000003754 machining Methods 0.000 abstract 1
- 238000010276 construction Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 210000005036 nerve Anatomy 0.000 description 1
- 238000010422 painting Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
Classifications
-
- A—HUMAN NECESSITIES
- A47—FURNITURE; DOMESTIC ARTICLES OR APPLIANCES; COFFEE MILLS; SPICE MILLS; SUCTION CLEANERS IN GENERAL
- A47J—KITCHEN EQUIPMENT; COFFEE MILLS; SPICE MILLS; APPARATUS FOR MAKING BEVERAGES
- A47J27/00—Cooking-vessels
- A47J27/08—Pressure-cookers; Lids or locking devices specially adapted therefor
- A47J27/09—Safety devices
-
- 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
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K17/00—Safety valves; Equalising valves, e.g. pressure relief valves
- F16K17/02—Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side
- F16K17/04—Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side spring-loaded
- F16K17/06—Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side spring-loaded with special arrangements for adjusting the opening pressure
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Food Science & Technology (AREA)
- Lining Or Joining Of Plastics Or The Like (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
El procedimiento de unión entre un fuselaje posterior y un estabilizador vertical.The joining procedure between a fuselage rear and a vertical stabilizer.
El procedimiento de unión entre un fuselaje posterior y un estabilizador vertical se realiza según una unión a tope formada por varios elementos de fijación que atraviesan conjuntamente los largueros del estabilizador vertical y las superficies de unión (5) del fuselaje posterior. La preparación superficial de las zonas a unir es la siguiente:The joining procedure between a fuselage posterior and a vertical stabilizer is performed according to a joint to stop formed by several fasteners that pass through together the struts of the vertical stabilizer and the joining surfaces (5) of the rear fuselage. The preparation The surface of the areas to be joined is as follows:
- con el fuselaje ya montado, primeramente se mecaniza la superficie mediante un fresado superficial,- with the fuselage already assembled, first of all Machines the surface by surface milling,
- seguidamente se procede al taladrado de los agujeros existentes en la superficie y se realiza un afeitado para retirar la rebaba producida durante el mecanizado,- then the drilling of the existing holes in the surface and a shave is performed to remove the burr produced during machining,
- se protegen los agujeros, se enmascaran los elementos coincidentes con las superficies de unión (5) y se realiza una preparación superficial previa al anodizado realizando un lijado y una limpieza posterior, y- holes are protected, masks are masked elements coinciding with the joining surfaces (5) and performs a surface preparation prior to anodizing by performing sanding and subsequent cleaning, and
- por último se anodiza toda la superficie de contacto y posteriormente se pinta.- finally the entire surface of anodizing is anodized contact and later it is painted.
Description
Procedimiento de unión de un fuselaje posterior y un estabilizador vertical.Procedure for joining a posterior fuselage and a vertical stabilizer
La presente invención se refiere, como su propio título indica, a un procedimiento que comprende una serie de etapas durante las cuales se realiza un tratamiento superficial al fuselaje posterior para que la unión con el estabilizador vertical se lleve a cabo sin ningún tipo de inconveniente según una unión a tope y sin la inclusión de largueros que se extiendan a partir del estabilizador vertical.The present invention is referred to as its own title indicates, to a procedure comprising a series of stages during which a superficial treatment is performed at rear fuselage so that the union with the vertical stabilizer is carried out without any inconvenience according to a union to top and without the inclusion of stringers that extend from the Vertical stabilizer.
El objetivo principal es desarrollar un método que permita realizar las uniones estructurales, de mayor complejidad en cuanto a la preparación superficial de las zonas a unir, mediante el establecimiento de una serie de etapas que otorgan a las citadas superficies de una rugosidad mínima y de unas óptimas cualidades frente al futuro deterioro de las mismas.The main objective is to develop a method that allows to realize the structural unions, of greater complexity in terms of surface preparation of areas to unite, by establishing a series of stages that give the aforementioned surfaces a minimum roughness and some optimal qualities against their future deterioration.
El estabilizador vertical se monta sobre el fuselaje posterior según varios tipos de uniones que se analizarán en detalle un poco más adelante. En cuanto al fuselaje posterior, normalmente está constituido por una estructura que debido a su ubicación en la parte posterior de la aeronave corresponde a una zona no presurizada, formada por cuadernas semicirculares y limitada en su parte frontal por un mamparo de forma lenticular. Durante la fabricación de la aeronave se constituyen ambos elementos por separado y posteriormente se ensamblan entre sí de dos formas, bien mediante una unión a tope o bien mediante uno o varios largueros que se prolongan desde el estabilizador vertical y se introducen en el fuselaje atravesándolo. Ambos métodos de ensamblaje se presentan como conocidos en el estado de la técnica y están publicados en "Airframe Structural Design" de Michael Chun-Yung Niu (ISBN 962-7128-04-X). De los dos métodos existentes, tiene mayor complejidad en la preparación de las superficies a unir el formado mediante la unión a tope. Ahora bien, una vez conseguida una perfecta planitud en las superficies de unión, el ensamblaje se realiza de forma más rápida y cómoda que en el método que introduce los largueros prolongación del estabilizador vertical en el interior del fuselaje.The vertical stabilizer is mounted on the posterior fuselage according to several types of joints that will be analyzed in detail a little later. As for the subsequent fuselage, normally it is constituted by a structure that due to its location on the back of the aircraft corresponds to a non-pressurized area, consisting of semicircular and limited frames in its frontal part by a bulkhead of lenticular form. During the Aircraft manufacturing are both elements constituted by separated and then assembled together in two ways, either by a butt joint or by one or several stringers that extend from the vertical stabilizer and are introduced into the fuselage through it. Both assembly methods are presented as known in the state of the art and are published in "Airframe Structural Design" by Michael Chun-Yung Niu (ISBN 962-7128-04-X). From The two existing methods have more complexity in the preparation of the surfaces to join the formed by joining stop, top, maximum as a noun, top as an adverb. Now, once achieved a perfect flatness in the bonding surfaces, the assembly is done faster and comfortable than in the method that introduces the extension stringers of the vertical stabilizer inside the fuselage.
En línea con el tipo de montaje mencionado en último lugar se encuentran las patentes siguientes: La US 3.66.211 de McDonnell Douglas donde se presenta una unión realizada por mediación de unos largueros que bordean el motor y sujetan el estabilizador vertical sobre el fuselaje, la US 4.448.372 de Boeing presenta un sistema de integración estructural entre el fuselaje y el estabilizador vertical formado por varios largueros que se extienden desde el estabilizador y se encastran en el mamparo de presión, la EP 737.616 de Daimler-Benz Aerospace Airbus muestra un cuerpo de estabilizador vertical donde se acorta el fuselaje de cola y se sujeta el empenaje mediante soportes que unen los largueros del estabilizador vertical y las costillas del fuselaje. Por último la patente DE 19719915 de Daimler-Benz Aerospace Airbus propugna una unión a tope mediante un componente horquillado para la sujeción del estabilizador al fuselaje, estando la unión realizada mediante un tornillo excéntrico y su correspondiente casquillo, y asegurándose todo ello con una unión dentada que trabaja a cortadura.In line with the type of mounting mentioned in Last place are the following patents: US 3.66.211 of McDonnell Douglas where a union made by mediation of stringers that line the engine and hold the vertical stabilizer on the fuselage, US 4,448,372 to Boeing presents a system of structural integration between the fuselage and the vertical stabilizer formed by several stringers that extend from the stabilizer and are embedded in the bulkhead of pressure, EP 737.616 from Daimler-Benz Aerospace Airbus shows a vertical stabilizer body where it is shortened the tail fuselage and the instep is held by brackets that join the struts of the vertical stabilizer and the ribs of the fuselage. Finally, patent DE 19719915 of Daimler-Benz Aerospace Airbus advocates a union to stop using a bracketed component to hold the stabilizer to the fuselage, the union being made by means of a eccentric screw and its corresponding bushing, and making sure all this with a toothed union that works to cut.
De las anteriores patentes mencionadas se desprende que la unión entre elementos se realiza principalmente mediante la inserción de largueros que se extienden desde el estabilizador vertical introduciéndose en el fuselaje, y todo ello debido a que la otra unión, la unión a tope, requiere de una mayor complejidad en la preparación de las superficies a unir. Con el objeto de subsanar eficazmente las carencias que presentan este tipo de uniones en cuanto a conseguir una perfecta planitud en las superficies de unión, se ha desarrollado el procedimiento de unión entre un fuselaje posterior y un estabilizador vertical, objeto de la presente invención.Of the above mentioned patents are it follows that the union between elements is mainly done by inserting stringers that extend from the vertical stabilizer entering the fuselage, and all this because the other union, the butt joint, requires a greater complexity in the preparation of the surfaces to be joined. With the in order to effectively remedy the deficiencies presented by this type of unions in terms of achieving a perfect flatness in the bonding surfaces, the bonding procedure has been developed between a rear fuselage and a vertical stabilizer, object of The present invention.
El primer paso en la unión a tope realizada entre el estabilizador vertical y el fuselaje trasero es la preparación de la superficie de ensamblaje correspondiente al fuselaje trasero y para ello se toma como referencia de montaje el plano de intersección entre el estabilizador vertical y el fuselaje. En la preparación de dicha superficie se realizan los siguientes pasos, primeramente se afeita la superficie buscando la planitud de los soportes, seguidamente se procede al taladrado de los agujeros existentes en la superficie y a través de los cuales se realiza la unión, mediante la correspondiente plantilla, se realiza el trabajo en frío para el endurecimiento de la superficie correspondiente a las paredes interiores de los orificios, se protegen los agujeros, se enmascaran y se preparan para el tercer y último paso. La última operación a realizar en el procedimiento objeto de la invención es el anodizado de toda la superficie de contacto y el pintado de la misma para conseguir un acabado que tenga buenas garantías de futuro y cuente con una buena protección para la corrosión.The first step in the butt joint made between the vertical stabilizer and the rear fuselage is the preparation of the assembly surface corresponding to the rear fuselage and for this purpose the assembly plan is taken as a reference intersection between the vertical stabilizer and the fuselage. In the preparation of said surface the following steps are carried out, first the surface is shaved looking for the flatness of the supports, then the holes are drilled existing on the surface and through which the union, through the corresponding template, the work is done cold for surface hardening corresponding to the inner walls of the holes, the holes are protected, they mask themselves and prepare for the third and last step. The last operation to be performed in the process object of the invention is the anodizing of the entire contact surface and the painting of the same to get a finish that has good guarantees of future and have good corrosion protection.
Una vez finalizado el procedimiento de preparación del fuselaje posterior se procede al ensamblaje del mismo con el estabilizador vertical. La base correspondiente a unos refuerzos nervados y dispuestos lateralmente a los largueros del estabilizador, son atornillados a las superficies previamente preparadas, disponiendo dos pares de elementos de fijación por cada una de las seis zonas del fuselaje tratadas y anodizadas.Once the procedure of preparation of the subsequent fuselage is assembled Same with vertical stabilizer. The base corresponding to some ribbed and laterally arranged reinforcements to the stringers of the stabilizer, are screwed to the surfaces previously prepared, having two pairs of fasteners for each one of the six areas of the fuselage treated and anodized.
\newpage\ newpage
De todo lo descrito anteriormente se deducen las
siguientes ventajas. Mediante el presente procedimiento se puede
optar por una unión a tope a pesar de las carencias y complejidades
que presentan este tipo de uniones. Esta unión garantiza una
rugosidad mínima entre superficies y una fijación fiable gracias al
gran número de tornillos, trabajando a tracción, utilizados en la
unión. La preparación de estas superficies debe llevarse a cabo de
forma muy rigurosa, teniendo en cuenta que la planitud practicada
en el fuselaje posterior debe ser milimétrica, para que al
ensamblarse con el estabilizador vertical este último quede exento
de cualquier tipo de desviación. Otra importante ventaja es el
ahorro de peso, factor muy importante en la construcción
aeronáutica, conseguido mediante este tipo de unión y por último,
la rapidez de montaje, minimizando tiempos y costes, frente a otros
tipos de unión como el presentado mediante la inserción de
largueros que se extienden desde el estabilizador vertical
introduciéndose en el
fuselaje.The following advantages are deduced from everything described above. Through this procedure you can opt for a butt joint despite the shortcomings and complexities of this type of joint. This union guarantees a minimum roughness between surfaces and a reliable fixation thanks to the large number of screws, working under tension, used in the union. The preparation of these surfaces must be carried out in a very rigorous manner, taking into account that the flatness practiced in the posterior fuselage must be millimetric, so that when assembled with the vertical stabilizer the latter is exempt from any type of deviation. Another important advantage is the saving of weight, a very important factor in aeronautical construction, achieved through this type of connection and finally, the speed of assembly, minimizing time and costs, compared to other types of connection such as the one presented by the insertion of stringers that extend from the vertical stabilizer into the
fuselage.
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, accompanies a sheet of drawings in which a case has been represented practical embodiment of the scope of the present invention.
La figura 1 es una vista en perspectiva de la parte superior del fuselaje posterior, donde se muestra desde el mamparo de presión hasta el final de la zona unión con el estabilizador vertical.Figure 1 is a perspective view of the upper part of the rear fuselage, where it is shown from the pressure bulkhead until the end of the junction zone with the Vertical stabilizer.
La figura 2 es una vista en planta de la zona correspondiente al fuselaje donde se muestra con mayor detalle las distintas zonas donde se establecen las superficies de unión, su tamaño, disposición, número de agujeros pasantes, etc.Figure 2 is a plan view of the area corresponding to the fuselage where the different areas where bonding surfaces are established, their size, layout, number of through holes, etc.
La figura 3 es una vista en perspectiva que muestra en detalle el extremo inferior de un larguero y la parte superior de una cuaderna donde se realiza la unión a tope entre el fuselaje y el estabilizador vertical.Figure 3 is a perspective view that shows in detail the lower end of a crossbar and the part top of a frame where the butt joint is made between the fuselage and vertical stabilizer.
Tal y como se representa en la figura 1, el fuselaje trasero de una aeronave es un espacio no presurizado en forma de cono, debido a ello una de las partes corresponde a la zona cerrada del cono (1) y la parte contraria se corresponde con la zona de unión al fuselaje (2), lugar en el que se sitúa el mamparo de presión (3) que aísla la zona presurizada del fuselaje de la zona no presurizada de la parte trasera (4). La unión a tope propugnada en la presente invención obliga a un tratamiento superficial de las piezas a unir. En el caso del fuselaje trasero, la superficie de unión (5) está formada por varios miembros sobresalientes de forma cuadrangular y con varias curvas de resalte o zapatas (6) que se extienden en forma decreciente desde las citadas superficies hasta la piel superior (7) que cubre el fuselaje.As shown in Figure 1, the rear fuselage of an aircraft is an unpressurized space in cone shape, because of this one of the parts corresponds to the closed zone of the cone (1) and the opposite part corresponds to the fuselage junction zone (2), the place where the pressure bulkhead (3) that isolates the pressurized area of the fuselage from the non-pressurized area of the rear (4). The butt joint advocated in the present invention obliges a treatment surface of the pieces to join. In the case of the rear fuselage, the joining surface (5) is formed by several members outstanding quadrangular shape and with several protrusion curves or shoes (6) that extend decreasingly from the said surfaces to the upper skin (7) covering the fuselage.
En la figura 2 se detalla la distribución por zonas de las superficies de unión (5), así en la Zona 1 correspondiente a la parte abierta (2) del fuselaje sedisponen las superficies de unión A y B, en la Zona 2 o zona intermedia se ubican las superficies de unión C y D, y por último, en la Zona 3 o parte correspondiente a la zona cerrada del fuselaje es donde se sitúan las superficies de unión E y F. Todas estas superficies de unión (5) son simétricas respecto a un eje longitudinal del avión que atraviesa el fuselaje desde la punta hasta el mamparo de presión (3) y todas ellas incorporan agujeros pasantes (8) uniformemente distribuidos junto a los vértices de la zona cuadrangular.Figure 2 shows the distribution by areas of the joining surfaces (5), as well as in Zone 1 corresponding to the open part (2) of the fuselage the joining surfaces A and B, in Zone 2 or intermediate zone locate the joining surfaces C and D, and finally, in Zone 3 or part corresponding to the closed area of the fuselage is where locate the joining surfaces E and F. All these surfaces of junction (5) are symmetrical with respect to a longitudinal axis of the plane that crosses the fuselage from the tip to the bulkhead of pressure (3) and all of them incorporate through holes (8) evenly distributed along the vertices of the area quadrangular.
Los pasos realizados en la preparación de la superficie se detallan a continuación:The steps taken in the preparation of the Surface are detailed below:
- primeramente se mecaniza la superficie mediante un fresado superficial buscando la planitud de los soportes,- the surface is first mechanized by a superficial milling looking for the flatness of the supports,
- seguidamente se procede al taladrado de los agujeros existentes en la superficie mediante la correspondiente plantilla, se realiza el trabajo en frío para el endurecimiento de la superficie correspondiente a las paredes interiores de los orificios y se realiza un rebarbado para retirar la rebaba producida durante el trabajo en frío,- then the drilling of the holes in the surface through the corresponding template, cold work is done to harden the surface corresponding to the interior walls of the holes and an overburden is made to remove the burr produced during cold work,
- se protegen los agujeros, se enmascaran las superficies de unión (5) y se realiza una preparación superficial previa al anodizado realizando un lijado y posterior limpieza.- holes are protected, masks are masked bonding surfaces (5) and a surface preparation is performed prior to anodizing by sanding and subsequent cleaning.
La última operación es el anodizado de toda la superficie de contacto, realizado mediante el cátodo de la herramienta, mientras que el ánodo se conecta a un un punto de toma de tierra (9) dispuesto entre la Zona 2 y la Zona 3. Tras el anodizado se midió la rugosidad y el espesor en las seis superficies de unión (5) A, B, C, D, E y F.The last operation is the anodizing of all the contact surface, made by means of the cathode of the tool, while the anode is connected to a socket of land (9) arranged between Zone 2 and Zone 3. After the anodized roughness and thickness were measured on all six surfaces of union (5) A, B, C, D, E and F.
Rugosidad, R_{a}Roughness, R_ {a}
Espesor del anodizadoThickness anodized
Una vez finalizados los pasos anteriormente detallados se pinta la superficie y se deja la pieza preparada para su ensamblaje.After completing the steps above detailed the surface is painted and the piece is left ready for its assembly
Tal y como se muestra en la figura 3, la unión a tope también se realiza por zonas, coincidiendo cada una de ellas (Zona 1), (Zona 2) y (Zona 3) con una cuaderna (10) dispuesta inferiormente a las superficies de unión (5) tomadas dos a dos. Así pues, las superficies de unión (5) contactan inferiormente con una cuaderna (10) y superiormente con un larguero (11), el cual está reforzado con unas piezas (12) en cuya base se insertan los elementos de fijación que componen la unión a tope. Dichas piezas (12) son de - forma rectangular, se acoplan a la base del larguero (11) y disponen de varios nervios (13) que se prolongan desde la base hasta la zona superior formando un par de acanaladuras. El grado de inclinación de los largueros (11) se corresponde con la disposición de los mismos, teniendo mayor inclinación el primero correspondiente a la Zona 1 y menor el último correspondiente a la Zona 3.As shown in Figure 3, the binding to top is also done by zones, each of them coinciding (Zone 1), (Zone 2) and (Zone 3) with a frame (10) arranged inferiorly to the joining surfaces (5) taken two by two. So therefore, the joining surfaces (5) contact inferiorly with a frame (10) and superiorly with a crossbar (11), which is reinforced with pieces (12) at whose base the fasteners that make up the butt joint. These pieces (12) are rectangular in shape, attached to the base of the crossbar (11) and have several nerves (13) that extend from the base to the upper area forming a pair of grooves. He degree of inclination of the stringers (11) corresponds to the their disposition, the first one having a greater inclination corresponding to Zone 1 and less the last corresponding to the Zone 3
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ES200102357A ES2226510B1 (en) | 2001-10-24 | 2001-10-24 | PROCESS OF UNION OF A REAR FUSELAGE AND A VERTICAL STABILIZER. |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ES200102357A ES2226510B1 (en) | 2001-10-24 | 2001-10-24 | PROCESS OF UNION OF A REAR FUSELAGE AND A VERTICAL STABILIZER. |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| ES2226510A1 ES2226510A1 (en) | 2005-03-16 |
| ES2226510B1 true ES2226510B1 (en) | 2005-12-16 |
Family
ID=8499278
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| ES200102357A Expired - Fee Related ES2226510B1 (en) | 2001-10-24 | 2001-10-24 | PROCESS OF UNION OF A REAR FUSELAGE AND A VERTICAL STABILIZER. |
Country Status (1)
| Country | Link |
|---|---|
| ES (1) | ES2226510B1 (en) |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2392788A (en) * | 1941-03-26 | 1946-01-08 | Budd Edward G Mfg Co | Aircraft structure |
| FR916967A (en) * | 1945-07-03 | 1946-12-20 | Const Aeronautiques Du Ct Soc | Device for connecting a sealed shell and components carried externally by the latter, in particular in an airplane |
| GB2167443B (en) * | 1984-11-05 | 1989-05-17 | Bl Tech Ltd | A method of fabricating structures from aluminium sheet and structures comprising aluminium components |
| US5692704A (en) * | 1995-06-07 | 1997-12-02 | Buttgereit; Volker | Body tail unit for a commercial aircraft |
-
2001
- 2001-10-24 ES ES200102357A patent/ES2226510B1/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| ES2226510A1 (en) | 2005-03-16 |
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