BR102013007792A2 - Sistema de posicionamento de setores de dispositivos de produção de fuselagem de aeronaves - Google Patents

Sistema de posicionamento de setores de dispositivos de produção de fuselagem de aeronaves Download PDF

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Publication number
BR102013007792A2
BR102013007792A2 BRBR102013007792-5A BR102013007792A BR102013007792A2 BR 102013007792 A2 BR102013007792 A2 BR 102013007792A2 BR 102013007792 A BR102013007792 A BR 102013007792A BR 102013007792 A2 BR102013007792 A2 BR 102013007792A2
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BR
Brazil
Prior art keywords
axis
sector
sectors
support structure
supported
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BRBR102013007792-5A
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English (en)
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BR102013007792B1 (pt
Inventor
Guido Sibona
Ettore Mostarda
Giuseppe Iovine
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Alenia Aermacchi Spa
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Publication of BR102013007792A2 publication Critical patent/BR102013007792A2/pt
Publication of BR102013007792B1 publication Critical patent/BR102013007792B1/pt

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C33/00—Moulds or cores; Details thereof or accessories therefor
    • B29C33/44—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
    • B29C33/48—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C51/00—Shaping by thermoforming, i.e. shaping sheets or sheet like preforms after heating, e.g. shaping sheets in matched moulds or by deep-drawing; Apparatus therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
    • B29C53/80—Component parts, details or accessories; Auxiliary operations
    • B29C53/82—Cores or mandrels
    • B29C53/821—Mandrels especially adapted for winding and joining
    • B29C53/824—Mandrels especially adapted for winding and joining collapsible, e.g. elastic or inflatable; with removable parts, e.g. for regular shaped, straight tubular articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/32—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
    • 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
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • 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
    • Y02T50/40—Weight reduction

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Architecture (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Robotics (AREA)
  • Moulding By Coating Moulds (AREA)
  • Toys (AREA)

Abstract

Sistema de posicionamento de setores de dispositivos de produção de fuselagem de aeronaves sistema de posicionamento de setores de um dispositivo de produção de fuselagens de aeronaves em que um mandril de laminação (4) é adaptado para receber e sustentar uma faixa de material sintético impregnado que é depositada e enrolada sobre a superfície externa (5), formando uma série de camadas sobrepostas que são submetidas a um processo de polimerização a vácuo sob alta temperatura para formar uma seção estrutural da aeronave. O mandril de laminação (4) compreende uma série de setores (12) sustentados por uma estrutura de suporte e móveis ao longo de guias (17) sustentadas pela estrutura de suporte (10) entre: uma posição de laminação expandida e uma posição de desmontagem contraída. Cada guia (17) compreende uma parte fixa (17g) sustentada pela estrutura de suporte (10) e uma parte móvel (18) que desliza ao longo/com relação à parte fixa (17g) em direção retilinea h. Entre uma parte de cada parte móvel (18) frontal ao setor correspondente (12) e uma estrutura de reforço (21), é fornecido um dispositivo de posicionamento (p) que permite o ajuste da posição do setor (12) com relação á guia em duas direções (x, y) que repousam em um plano rp perpendicular ao eixo h da guia (17).

Description

Sistema de posicionamento de setores de dispositivos de produção de fuselagem de aeronaves. A presente invenção refere-se a um sistema de posicionamento de setores de dispositivos de produção de fuselagem de aeronaves. O Pedido de Patente PCT WO 2007/148301 descreve um dispositivo de produção de fuselagens de aeronaves em que um mandril de laminação é delimitado por uma superfície externa que define um sólido em rotação (particularmente um cilindro) com relação a um eixo de simetria. O mandril de laminação é adaptado para receber e sustentar uma faixa de material sintético impregnado que é enrolado e depositado sobre a superfície externa do mandril em uma fase de laminação que forma uma série de camadas sobrepostas. As mencionadas camadas sobrepostas são submetidas a um processo subsequente de polimerização a vácuo em um autoclave em alta temperatura para formar uma seção estrutural do aeroplano (tipicamente uma parte tubular da fuselagem). O mandril de laminação compreende uma série de setores espaçados em ângulo em volta do eixo e suspensos por guias que se estendem radialmente a partir de uma estrutura de suporte de grade. Os setores são móveis entre: uma posição de laminação expandida na qual os setores possuem extremidades retilíneas maiores paralelas ao eixo dispostas lado a lado e as superfícies externas dos setores opostos ao eixo definem a superfície externa; e uma posição de desmontagem contraída na qual os setores aproximam-se do eixo que se move para longe do traço da superfície para permitir a extração do mandril de laminação da^seção estrutural da aeronave ao final do processo de polimerização a vácuo.
Nos sistemas de tipo conhecido, cada setor é equipado com uma estrutura de sustentação que é conectada rigidamente a uma série de lâminas móveis que se movem ao longo das partes fixas correspondentes das guias sustentadas pela estrutura de sustentação.
Os mencionados sistemas não permitem nenhum posicionamento relativo do setor com relação às guias; a mencionada operação seria extremamente útil . para o propósito de recuperação de quaisquer tolerâncias de dimensões/erros de posicionamento do setor e/ou das guias.
The need is therefore felt to produce a positioning system of sectors which solves the technical problem highlighted above.
The preceding object is achieved by the present invention which relates to a positioning system of sectors of a device for producing an airplane fuselage in which a lamination mandrel is delimited by an externai surface which defines a rotation solid with respect to a symmetry axis; said lamination mandrel is adapted to receive and support a band of impregnated synthetic material which is deposited and wound on the externai surface forming a plurality of overlapping layers which are subjected to a polymerisation process under vacuum at high temperatura for forming a structural section of the airplane; the lamination mandrel comprises a plurality of sectors bome by a supporting structure elongated along said axis, angularly spaced about the axis and mobile along guides borne by the supporting structure under the thrust of an actuator between: - an expanded lamination position in which the sectors have greater rectilinear edges parallel to the axis arranged side by side and the externai surfaces of the sectors opposite the axis define together said externai surface; and - a contracted disassembling position in which at least part of said sectors approaches the axis moving away from the trace of the surface to reduce the radial dimensions of the mandrel and allow extraction of the mandrel from the structural section of the airplane; each guide comprises a fixed part borne by said supporting structure and a mobile part which runs along/with respect to the fixed part in a rectilinear direction H, characterised in that between a portion of each mobile part facing towards the respective sector, the stiffening structure is provided with a positioning device (P) which allows adjustment of the position of the sector with respect to the guide in two directions (x,y) which lie in a plane RP perpendicular to the axis H of the guide.
The invention will now be illustrated with reference to the accompanying figures which show a preferred embodiment example in which: - figure 1 illustrates - in a perspective view - a device for producing an airplane fuselage which uses an actuation system according to the invention; - figure 2 illustrates - in a perspective view - the internai structure of the device illustrated in figure 1; - figure 3 illustrates in lateral view and on an enlarged scale a cross section of the device illustrated in figures 1 and 2; - figure 4 illustrates in a perspective view the positioning device according to the present invention; - figure 5 illustrates in longitudinal section the operative positioning device of figure 4; and - figure 6 illustrates, in an overhead view, the positioning device according to the present invention.
In figures 4, 5 and 6 the reference number 1, as a whole, indicates a positioning system of sectors of a device 2 (figure 1) for producing an airplane fuselage.
In particular the device 2 (figure 1) comprises a lamination mandrel 4 delimited by an externai surface 5 which defines a rotation solid with respect to a symmetry axis 7. The lamination mandrel 4 is adapted to receive and support a band of impregnated synthetic material which is deposited and wound on the externai surface 5 forming a plurality of overlapped layers which completely and uniformly cover the surface 5.
The band of synthetic material (for example carbon fibre) is deposited by a lamination head (of known type - not illustrated) on the lamination mandrel 4.
For example, the band can be deposited by causing rotation of the mandrel 4 about the axis 7 and translation in a coordinated manner of the lamination head (not illustrated) along the axis 7. For example, the patent application US2005/0039843 illustrates a lamination head. At the end of lamination of the band, the band of impregnated composite material is subjected to a polymerisation process under a vacuum for producing a tubular structural section of the airplane. Said process is performed by placing the lamination mandrel 4 in an autoclave (not illustrated) and running a thermal heating cycle of known type.
In the example shown, the externai surface 5 is cylindrical and the lamination mandrel 4 is used for forming a cylindrical tubular portion of the airplane fuselage.
The lamination mandrel 4 comprises a plurality of sectors 12 angularly spaced about the axis 7 and borne by a supporting structure 10 (figure 2) which extends linearly along the axis 7.
The sectors 12 are mobile between: - an expanded lamination position (figure 1 and 3) in which the sectors 12 have greater rectilinear edges 13 parallel to the axis 7 arranged side by side and the externai surfaces of the sectors 12 opposite the axis 7 are contiguous and define - as a whole - the cylindrical surface 5; and - a contracted disassemblina position (not illustrated) in which the sectors 12 approach the axis 7 moving away from the trace of the surface 5 to reduce the radial dimensions of the mandrel 4 and allow extraction of the mandrel 4 from the structural section of the airplane at the end of the process.
The (figure 2) supporting structure 10 is produced by means of known techniques adapted to prevent the deflection thereof along the axis 7.
The supporting structure 10 extends between a first and a second annular end portion 16a, 16b (figure 1) each of which is provided with a respective portion of frustoconical shape 17a, 17b which extends axially.
The frustoconical end portions 17a, 17b are made of metallic material and each delimit a central opening 18 coaxial with the axis 7.
The patent application WO 20077148301 provides an example of embodiment and use of a supporting structure 10 of the type mentioned above and end portions 17a, 17b.
Each sector 12 comprises a curved metallic wall 20 (figure 3) which in cross section has the profile of an arc of a circle with aperture of 60° and centre in the axis 7 and a stiffening structure 21 formed of a plurality of ribs 21 spaced axially from one another and facing towards the inside of the mandrel 4 to prevent deflections/deformations of the wall 20 ensuring that the surface 5 remains perfectly cylindricai and coaxial with the axis 7.
The adjacent edges 13 of two contiguous sectors 12 are adapted to position themselves one above the other in a peripheral overlapping region 13s (figure 3).
Between the stiffening structure 21 of each sector 12 and the supporting structure 10, a pair of rectilinear guides 17 (of known type and therefore not further illustrated) is provided, adapted to support the sector 12 and aliow a linear translation movement, in a radial direction with respect to the axis 7 and in opposite directions, of each curved wall 20 between the expanded and contracted lamination positions.
In particular each sector 12 is supported by two pairs of rectilinear guides 17 (see figure 2) arranged at the annular end portions 16a, 16b of the supporting structure 10.
The guides 17 - of known type - are not further detailed and each comprise a fixed part 17g borne by the supporting structure and a mobile part 18 (slide - see figures 3 and 4) running along/with respect to the fixed part 17g in a rectilinear direction H.
According to the present invention, between an end portion of each mobile part 18 facing towards the stiffening structure 21 of the sector 12 a positioning device P is provided which allows adjustment of the position of the sector 12 with respect to the guide in a plane RP (outlined in figure 3) perpendicular to the axis H of the guide 17.
In further detail (figure 4), the slide 18 comprises a metallic body 45 of parallelepípedal shape provided, on the side facing towards the sector 12, with a flange 40 shaped in the form of a flat square frame delimiting a square internai opening 41 communicating with a seat42 provided in the slide 18.
The seat 42 has a parallelepípedal shape and is delimited by four flat rectangular lateral walls 43 and by a bottom wall 44 (figure 5) also flat and rectangular.
The seat 42 houses a metallic body 45 shaped as a frustum of pyramid delimited by a longer base wall 46 resting on the bottom wall 44, four peripheral walls 47 shaped in the form of an isosceles trapezium each facing a respective lateral wall 43 and a shorter base wall 48. The metallic body 45 bears a cylindricai metallic pin 50 which extends from the shorter base wall 48 towards the supporting structure 21 along an axis 51 perpendicular to the walls 46 and 48. The axis 51 is perpendicular to the plane RP.
The pin 50 is adapted for insertion in a hole 52 (figure 3) provided in the supporting structure 21 of the sector 12.
The position of the body 45 inside the seat 42 can be adjusted by means of four catch bodies 53 housed inside the seat 42; in particular each catch body 53 is shaped in the form of a wedge with rectangular trapezium section and has a flat watl 54 inclined with respect to the axis 51 and abutting on a respective peripheral wall 47 of the metallic body 45. The position along the axis 51 of each catch body 53 can be adjusted by means of a screw 55 having a threaded stem screwed inside a cylindrical seat provided in the catch body 53 and a head abutting on the bottom wall 44 on the side opposite the one defining the seat 42.
The heads of the screws 55 (provided with a hexagonal seat) are accessible by means of a window 54 obtained in a wall of the slide 18.
An operator (not illustrated) 55 can adjust the position of each catch body 53 within the seat 42 and along the axis 51 by means of the screws; in this way, thanks to the coupling between the walls 54 and 47, the movement of the pin 50 is obtained in two directions x and y (figure 4) which pass through the plane RP perpendicular to the axis 51 and parallel to the plane of the flange 40. In this way, by means of pairs of positioning devices P (or all four positioning devices) it is possible to adjust the position of the sector 12 with respect to the four guides 17 that support it. Once an optimal position has been reached, the supporting structure 12 is securely fixed to the slide 18 by means of bolts 55 (figure 6) borne by the flange 40.
The movement of each sector is obtained by an actuator 60 (figure 3) positioned between the pair of guides 17 and provided with an electric motor 61 (figure 3, shown schematically) configured to produce the above-mentioned translation movement.
For example, the actuator 60 is of the screw - nut screw type and comprises a nut screw 62 borne by the supporting structure 10 and rotated by the motor 61 (for the sake of simplicity of illustration, in figure 3 the transmission is not illustrated) and a rectilinear threaded element 63 coupled with the nut screw 62 and having one end hinged to the stiffening structure 21 of a sector 12. The rectilinear threaded element 63 extends in a radial direction along an axis 64 parallel to the axes H.
Alternatively the nut screw 62 could be arranged on the stiffening structure 21 of a sector 12 and the threaded element 63 could be borne by the supporting structure 10.
The shaft 60 has a first end portion from which a rectangular plate 66 extends which in turn is hinged to a triangular bracket 67 extending radially from the stiffening structure 21 towards the axis 7.

Claims (6)

1. Sistema de posicionamento configurado para operar com setores de um dispositivo (2) de produção de fuselagens de aeronaves em que um mandril de laminação (4) é definido por uma superfície externa (5) que define um sólido em rotação com relação a um eixo de simetria (7); em que o mencionado mandril de laminação (4) é adaptado para receber e sustentar uma faixa de material sintético impregnado que é depositada e enrolada sobre a superfície externa (5), formando uma série de camadas sobrepostas que são submetidas a um processo de polimerização a vácuo sob alta temperatura para formar uma seção estrutural da aeronave; o mandril de laminação (4) compreende uma série de setores (12) sustentados por uma estrutura de suporte que é alongada ao longo do mencionado eixo (7), espaçada em ângulo em volta do eixo (7) e móvel ao longo de guias (17) sustentadas pela estrutura de suporte (10) sob o impulso de um acionador (60) entre: uma posição de laminação expandida na qual os setores (12) possuem extremidades retilíneas maiores (13) paralelas ao eixo (7) e dispostas lado a lado e as superfícies externas dos setores (12) opostos ao eixo (7) definem juntas a mencionada superfície externa (5); e uma posição de desmontagem contraída na qual pelo menos uma parte dos mencionados setores (12) aproxima-se do eixo (7) que se move para longe do traço da superfície (5) para reduzir as dimensões radiais do mandril e permitir a extração do próprio mandril (4) da seção estrutural da aeronave; cada guia (17) compreende uma parte fixa (17g) sustentada pela mencionada estrutura de suporte (10) e uma parte móvel (18) que desliza ao longo/com relação à parte fixa (17g) ao longo de uma direção retilínea H; caracterizado pelo fato de que compreende um dispositivo de posicionamento (P) disposto entre uma parte de cada parte móvel (18) frontal ao setor correspondente (12) e uma estrutura de reforço (21) de um setor (12); em que o mencionado dispositivo de posicionamento (P) permite o ajuste da posição do setor (12) com relação à guia ao longo de duas direções (x, y) que repousam em um plano RP perpendicular ao eixo H da própria guia (17); o mencionado dispositivo de posicionamento compreende um corpo central (45) disposto em um assento (42) obtido na mencionada parte móvel (18) e equipado com uma parte (51) que se acopla (52) com a estrutura de suporte (21) do mencionado setor (12); e a posição do mencionado corpo central (45) no mencionado assento (42) é ajustável por meio de posicionamento no mencionado assento (42) de uma série de corpos de captura (53) que entram em contato com paredes laterais (47) do mencionado corpo central (45) para deslocá-lo.
2. Sistema de acordo com a reivindicação 1, caracterizado pelo fato de que cada setor (12) é sustentado por dois pares de guias retilíneas (17) dispostas em partes posteriores (16a, 16b) da estrutura de suporte.
3. Sistema de acordo com a reivindicação 1, caracterizado pelo fato de que o mencionado corpo central (45) é formado como tronco de pirâmide com bases quadradas e os mencionados corpos de captura (53) possuem forma de cunha.
4. Sistema de acordo com qualquer das reivindicações 1 ou 3, caracterizado pelo fato de que cada corpo de captura (53) pode ser posicionado no interior do mencionado assento (42) que age sobre um elemento rosqueado correspondente (55) que se estende, ao menos parcialmente, em uma cavidade obtida no próprio corpo de captura.
5. Sistema de acordo com a reivindicação 1, caracterizado pelo fato de que o mencionado acionador é do tipo rosca (31) - rosca de porca (29).
6. Sistema de acordo com a reivindicação 1, caracterizado pelo fato de que cada setor (12) compreende uma parede curva (20) que possui seção cruzada com o perfil de um arco de circunferência e uma estrutura de reforço (21) voltada para dentro do mandril (4) e adaptada para evitar deflexões/deformações da parede (20).
BR102013007792A 2012-03-30 2013-04-01 sistema de posicionamento de setores de um dispositivo de produção de fuselagem de aeronaves BR102013007792B1 (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
IT000287A ITTO20120287A1 (it) 2012-03-30 2012-03-30 Sistema posizionamento settori appartenenti ad un dispositivo per la realizzazione di una sezione di fusoliera di un aereo

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BR102013007792A2 true BR102013007792A2 (pt) 2015-07-07
BR102013007792B1 BR102013007792B1 (pt) 2020-05-19

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US (1) US9038686B2 (pt)
EP (1) EP2644360B1 (pt)
JP (1) JP6157176B2 (pt)
KR (1) KR102053102B1 (pt)
CN (1) CN103358561B (pt)
BR (1) BR102013007792B1 (pt)
CA (1) CA2810982C (pt)
ES (1) ES2553778T3 (pt)
IT (1) ITTO20120287A1 (pt)
RU (1) RU2622121C2 (pt)

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FR3100232B1 (fr) 2019-08-30 2022-01-14 Airbus Ensemble comportant une tour support et au moins deux systemes de support pour des panneaux d’un troncon de fuselage d’un aeronef

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CA2810982A1 (en) 2013-09-30
RU2013114259A (ru) 2014-10-10
ES2553778T3 (es) 2015-12-11
EP2644360B1 (en) 2015-09-02
JP6157176B2 (ja) 2017-07-05
KR20130111479A (ko) 2013-10-10
CN103358561A (zh) 2013-10-23
US20130292059A1 (en) 2013-11-07
RU2622121C2 (ru) 2017-06-13
CN103358561B (zh) 2016-12-07
KR102053102B1 (ko) 2020-01-08
CA2810982C (en) 2019-12-31
ITTO20120287A1 (it) 2013-10-01
JP2013212686A (ja) 2013-10-17
US9038686B2 (en) 2015-05-26
BR102013007792B1 (pt) 2020-05-19
EP2644360A1 (en) 2013-10-02

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