GB2196922A - Airship gondola construction - Google Patents
Airship gondola construction Download PDFInfo
- Publication number
- GB2196922A GB2196922A GB08623253A GB8623253A GB2196922A GB 2196922 A GB2196922 A GB 2196922A GB 08623253 A GB08623253 A GB 08623253A GB 8623253 A GB8623253 A GB 8623253A GB 2196922 A GB2196922 A GB 2196922A
- Authority
- GB
- United Kingdom
- Prior art keywords
- shell
- module
- hoop
- fuselage
- hoops
- 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.)
- Withdrawn
Links
- 238000010276 construction Methods 0.000 title abstract description 9
- 239000000463 material Substances 0.000 claims abstract description 13
- 238000000034 method Methods 0.000 claims description 23
- 230000005855 radiation Effects 0.000 claims description 5
- 239000011358 absorbing material Substances 0.000 claims description 4
- 239000002131 composite material Substances 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 239000011152 fibreglass Substances 0.000 description 3
- 239000002990 reinforced plastic Substances 0.000 description 3
- 239000004411 aluminium Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 150000001768 cations Chemical class 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000005670 electromagnetic radiation Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/22—Arrangement of cabins or gondolas
-
- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/064—Stringers; Longerons
-
- 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
- B64C2001/0018—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like comprising two decks adapted for carrying passengers only
- B64C2001/0027—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like comprising two decks adapted for carrying passengers only arranged one above the other
-
- 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
Abstract
Tubular shells 5 of relatively flexible material are connected together by hoops 1 of relatively rigid material to form modules 8 of a gondola fuselage. A set of modules is assembled together with nose and tail portions (33 and 34) to form a complete gondola fuselage in which each shell 5 is supported at each end by a rigid hoop 1. Each module is fitted with equipment and services prior to assembly. The construction method is suited to mass production of gondola fuselages of composite materials. Longerons 21 connect the hoops 1, and floors 22, 23 are supported on cross-members 24 which span the modules 8. External straps 20 cover the joints between modules. <IMAGE>
Description
SPECIFICATION
Airship gondola construction
This invention relates to a method of constructing a fuselage of an airship gondola or the like and to apparatus for use in such construction.
It is known to construct an airship gondola from lightweight composite materials such as fibreglass reinforced plastic. Known methods for forming large scale composite material structures have been used in which the composite material is wet laid onto a former or mould. Traditional methods of assembling a fuselage of an airframe on the other hand have made use of a skeletal frame of the complete fuselage which is supported by a surrounding jig prior to assembly of panels onto the frame to form the outer skin. Both of these methods suffer the disadvantage of expensive and complex tooling.
According to the present invention there is disclosed a method of constructing a fuselage of an airship gondola or the like comprising the steps of forming a set of tubular shells of relatively flexible sheet material and a set of complimentary hoops of relatively rigid material, mounting a first hoop at one end of a first shell so as to rigidly support an annular end portion of the shell, connecting a second shell to the first hoop on the opposite side thereof to rigidly support an annular edge portion of the second shell, connecting a further hoop to the unsupported end of the second shell in like manner and adding further shells and hoops to form a tubular module of the fuselage, forming one or more further modules in like manner, connecting the modules to form a tubular body of the fuselage and connecting the body with a nose and tail portion so as to close the open forward and rearward ends of the tubular body respectively and thereby to complete the fuselage such that in the completed fuselage each shell is supported at both ends by a hoop.
An advantage of such a method is that the need for complex tooling is of obviated and the use of a modular construction technique is more suited to mass production methods.
Preferably the method includes the further step of connecting hoops of the module with longitudinally extending struts, which struts and hoops constitute- a skeletal frame supporting the shells of the module in a predetermined shape.
Preferably the method further includes the step of installing equipment and services in each module prior to assembly with other modules and with the nose and tail portions
Individual modules may then be tested prior to transportation to an assembly site and modules may be interchangeable with spare modules so that faults may be corrected by changing any module thereby avoiding delay in assembly.
Conveniently adjacent modules are connected by mounting an annular edge portion of the end shell of one module in supporting engagement with an end hoop of the adjacent module.
Conveniently successive shells and hoops are assembled on a horizontal supporting surface by alternately adding hoops and shells in a vertical stack.
According to a further aspect of the present invention there is disclosed a hoop for use in a method as hereinbefore disclosed comprising an annular disc portion which extends radially with respect to the longitudinal axis of the module, an annular inner flange connected to the disc portion and projecting paraxially on each side thereof and an outer annular flange connected to the radially outer edge of the disc portion and extending paraxially on each side thereof, which disc portion and flanges define opposing annular channels such being adapted to receive a respective annular edge portion of a shell.
Preferably the disc portion is of a honeycomb reinforced sheet material.
According to a further aspect of the invention there is disclosed a shell for use in a method as hereinbefore disclosed and comprising inner and outer layers spaced apart by webs defining honeycomb cavities therebetween. Advantageously the honeycomb cavities may contain radiation absorbing material.
The term radiation absorbing material here refers to materials selected or formulated to be receptive to electromagnetic waves of a particular bandwith so as to absorb radiation with minimal reflection. The use of such material for example which is sensitive to radar frequencies will thereby reduce the radar cross section of the gondola to reduce the probability of detection by hostile active surveillance and guidance systems emiting electromagnetic radiation at radar frequencies.
Particular embodiments of the invention will now be described by way of example only and with reference to the accompanying drawings of which:
Figure 1 is a perspective view of a hoop,
Figure 2 is a sectional elevation of a shell to which a hoop has been mounted.
Figure 3 is a perspective view of the stack of shells and hoops,
Figure 4 is a sectional view of an alternative hoop showing the way in which edge portions of shells are bonded thereto,
Figure 5 is a perspective part cut away view of a module comprising a number of shells and hoops, and
Figure 6 is a view of a gondola constructed in accordance with the present invention prior to assembly of modules with a nose and tail portion.
A hoop 1 as shown in Fig. 1 comprises an annular disc portion 2 of a fibreglass rein forced plastics material having inner and outer flanges 3 and 4 respectively which extend at right angles to and on each side of the disc portion. The flanges 3 and 4 are similarly of fibreglass reinforced plastics material and are adhesively bonded to the disc portion 2. The hoop 1 is of relatively rigid construction by virtue of its I shaped cross section seen in section in Fig. 2.
A tubular shell 5 is shown in Fig. 2 positioned on a supporting surface 6 such that an annular end portion 7 is uppermost. The hoop 1 is adhesively bonded to the annular end portion 7 so as to be partially nested within the shell 5 such that one half of the hoop projects from the sheel in readiness for bonding to a further shell.
Fig. 3 shows a stack of shells 5 and hoops 1 which together constitute a module 8 comprising three shells and three hoops.
Fig. 4 shows an alternative hoop 9 in which the annular disc portion 2 carries an additional flange 4A extending parallel to and spaced from the flange 4 by a distance equal to the thickness of the shell 5 and which together with the flange defines opposing channels 10 and 11 in which annular end portions 7 of the shell are received in abutting reiationship.
The construction of the shell 5 is seen in
Fig. 4 to comprise an inner layer 12 and an outer layer 13 spaced apart by webs 14 defining honeycomb cavities 15 containing radiation absorbing material (not shown).
The module 8 is shown in Fig. 5 in a horizontally extending position in which the uppermost hoop 1 of the stack of Fig. 3 now lies in a vertical plane and provides rigid support to a first end 16 of the module whilst the opposing second end 17 of the module comprises an annular edge portion 18 of relatively flexible shell 5. The interface 19 between abutting shells 5 as seen in Fig. 3 is masked by butt straps 20 as seen in Fig. 5 which are adhesively bonded externally to the abutting shells 5 thereby providing increased cohesion therebetween.
Longitudinal struts 21 connect adjacent hoops 1 and upper and lower decks 22 and 23 respectively are supported on cross members 24 which horizontally span the module 8.
Eyes 25 are externally mounted on the module 8 for attachment to cables 26 by means of which the weight of the module may be supported, the eyes being connected through the shells 5 with one of the rigid hoops 1.
Fig. 6 shows a set of three modules 27, 28 and 29 supported on horizontal jigs 30, 31 and 32 respectively prior to assembly with one another to form a tubular body of a gondola fuselage. The jigs 30, 31, 32 comprise U shaped brackets and are of simple construction. They may be wheeled or supported on air bearings to facilitate alignment with other modules. Nose and tail portions 33 and 34 respectively are similarly mounted on jigs 35 and 36 respectively prior to assembly with the modules so as to close the open forward and rearward ends 37 and 38 respectively of the tubular body to thereby complete a fuselage.
In assembling adjacent modules 27, 28 and 29 an edge portion 18 of a shell 5 of one such module is adhesively bonded to an end hoop 1 of the adjacent module such that the outer skin of the fuselage is continuous and each shell is supported at both ends. Further longitudinal struts 21 are then added to reinforce the join. The hoops 1 and struts 21 together comprise a skeletal frame on which the fuselage skin is supported.
A fuselage of an airship gondola may therefore be constructed by forming a set of tubular shells 5 and a complimentary set of hoops
1 of relatively rigid material compared with that of the shells, mounting a first hoop at one end of a first shell as seen in Fig. 2 so as to rigidly support an annular end portion 7 of the shell, connecting a second shell to the first hoop on the opposite side thereof to rigidly support an annular edge portion of the second shell as seen in Fig. 3, connecting a further hoop to the unsupported end of the second shell in like manner and adding further shells and hoops to form a tubular module of the fuselage. Any number of shells may be included in the module as required. One or more further modules are formed in like manner and the modules connected to form a tubular body of the fuselage.The nose and tail portions of the fuselage are then added to the tubular body to complete the fuselage.
In the completed fuselage each shell 5 is supported at both ends by a hoop 1 and the connection between adjacent modules is carried out by leaving an unsupported shell at the end of a first module to be bonded to in supporting engagement with an end hoop of a second module. Modules may therefore be constructed in a series in which each module has one supported end and one unsupported end. Alternative arrangements are possible in which some modules have hoops at both ends whilst others are unsupported at both ends, the essential feature of the method being that in the completed fuselage each shell is supported at both ends to form a dimensionally stable and relatively rigid unit.
Alternative forms of hoop are possible in which the flanges 3 and 4 are connected to the disc portion 2 by means of metal channel inserts to provide additional strength. Such inserts may comprise a U shaped aluminium extrusion into which an end of the annular disc portion 2 is received with a flange and being adhesively bonded to the proposing side of the insert.
Whilst the above disclosure relates primarily to the construction of an airship gondola the method may also be used for the fuselage of a non dirigible aerostat or to any other lightweight structure for use in aeronautical appli cations.
Claims (12)
1. A method of constructing a fuselage of an airship gondola or the like comprising the steps of forming a set of tubular shells of relatively flexible sheet material and a set of complimentary hoops of relatively rigid material, mounting a first hoop at one end of a first shell so as to rigidly support an annular end portion of the shell, connecting a second shell to the first hoop on the opposite side thereof to rigidly support an annular edge portion of the second shell, connecting a further hoop to the unsupported end of the second shell in like manner and adding further shells and hoops to form a tubular module of the fuselage, forming one or more further modules in like manner, connecting the modules to form a tubular body of the fuselage and connecting the body with a nose and tail portion so as to close the open forward and rearward ends of the tubular body respectively and thereby to complete the fuselage such that in the completed fuselage each shell is supported at both ends by a hoop.
2. A method as claimed in claim 1 including the further step of connecting the hoops of the module with longitudinally extending struts, which struts and hoops constitute a skeletal frame supporting the shells of the module in a predetermined shape.
3. A method as claimed in either of claims 1 and 2 inciuding the further step of installing equipment and services in each module prior to assembly with other modules and with the nose and tail portions.
4. A method as claimed in any preceding claim wherein adjacent modules are connected by mounting an annular edge portion of the end shell of one module in supporting engagement with an end hoop of the adjacent module.
5. A method of constructing a module for use in a method as claimed in any of the preceding claims in which successive shells and hoops are assembled on a horizontal supporting surface by alternately adding hoops and shells in a vertical stack.
6. A hoop for use in a method as claimed in any preceding claim comprising an annular disc portion which extends radially with respect to the longitudinal axis of the module, an annular inner flange connected to the disc portion and projecting paraxially on each side thereof and an outer annular flange connected to the radially outer edge of the disc- portion and extending paraxially on each side thereof, which disc portion and flanges define opposing annular channels each being adapted to receive a -respective annular edge portion of a shell.
7. A hoop as claimed in claim 6 wherein the disc portion is of a honeycomb reinforced sheet material.
8. A shell for use in a method as claimed in any of claims 1 to 5 and comprising inner and outer layers spaced apart by webs defining honeycomb cavities therebetween.
9. A shell as claimed in claim 8 wherein the honeycomb cavities contain radiation absorbing material as hereinbefore defined.
10. A module for a fuselage of an airship gondola or the like and comprising a hoop or shell as claimed in any of claims 6 to 9.
11. An airship gondola constructed by a method as claimed in any of claims 1 to 4.
12. A method of constructing an airship gondola substantially as hereinbefore described with reference to and as shown in the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB08623253A GB2196922A (en) | 1986-09-26 | 1986-09-26 | Airship gondola construction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB08623253A GB2196922A (en) | 1986-09-26 | 1986-09-26 | Airship gondola construction |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB8623253D0 GB8623253D0 (en) | 1986-10-29 |
| GB2196922A true GB2196922A (en) | 1988-05-11 |
Family
ID=10604878
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB08623253A Withdrawn GB2196922A (en) | 1986-09-26 | 1986-09-26 | Airship gondola construction |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2196922A (en) |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0346210A1 (en) * | 1988-06-08 | 1989-12-13 | AEROSPATIALE Société Nationale Industrielle | Composite frame, in particular for an aircraft fuselage, and its manufacturing process |
| FR2638707A1 (en) * | 1988-11-10 | 1990-05-11 | Commissariat Energie Atomique | Balloon gondola made of composite materials, configured for transporting heavy loads |
| GB2295999A (en) * | 1994-12-16 | 1996-06-19 | British Aerospace | Aircraft fuselage manufacture |
| US5562264A (en) * | 1992-07-22 | 1996-10-08 | Eurocopter France | Fuselage structure for helicopter |
| EP1251066A2 (en) * | 2001-03-13 | 2002-10-23 | Astrium Gmbh | Ring for the connection of two structural elements with rotational symmetry |
| WO2004014726A1 (en) * | 2002-08-13 | 2004-02-19 | Sikorsky Aircraft Corporation | Composite tail cone assembly for a helicopter |
| WO2007065649A2 (en) * | 2005-12-06 | 2007-06-14 | Delcon Deutsche Luftfahrt Consult Gmbh | Aerial transporter |
| DE102006026169A1 (en) * | 2006-06-06 | 2007-12-27 | Airbus Deutschland Gmbh | Aircraft fuselage structure and method for its manufacture |
| EP2128018A1 (en) * | 2007-01-29 | 2009-12-02 | Airbus Operations S.L. | Aircraft loading frame of composite material |
| FR2933065A1 (en) * | 2008-06-30 | 2010-01-01 | Airbus France | METHOD FOR ASSEMBLING A FLOOR IN A HULL STRUCTURE PREFALLABLY CONSISTING OF AN AIRCRAFT FUSELAGE TRUNK |
| FR2933066A1 (en) * | 2008-06-26 | 2010-01-01 | Airbus France | AIRCRAFT FUSELAGE ELEMENT |
| WO2010003818A2 (en) * | 2008-07-07 | 2010-01-14 | Airbus Operations Gmbh | Method for installing a dome-shaped pressure bulkhead in a rear section of an aircraft, and device for carrying out the method |
| US8256713B2 (en) | 2008-12-09 | 2012-09-04 | Airbus Operations Sas | Aircraft fuselage section |
| US8366041B2 (en) * | 2006-04-20 | 2013-02-05 | Airbus Operations Sas | Aircraft floor, use of said floor and aircraft section fitted with said floor |
| US8567150B2 (en) | 2006-05-23 | 2013-10-29 | Airbus Operations Sas | Aircraft pressurized floor |
| US8651421B2 (en) | 2006-06-06 | 2014-02-18 | Airbus Operations Gmbh | Aircraft fuselage structure and method for its production |
| US8672265B2 (en) | 2007-03-05 | 2014-03-18 | Airbus Operations Sas | Container for air freight transport and fuselage of an aircraft for freight transport |
| US8695922B2 (en) | 2006-06-06 | 2014-04-15 | Airbus Operations Gmbh | Aircraft fuselage structure and method for its production |
| WO2016195520A1 (en) * | 2015-06-05 | 2016-12-08 | Instituto Superior Técnico | Multifunctional air transport system |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112373670A (en) * | 2020-10-22 | 2021-02-19 | 中国科学院空天信息创新研究院 | Pod for offshore recovery of aerostat |
| CN114313205B (en) * | 2021-12-30 | 2024-04-09 | 中国特种飞行器研究所 | Manned airship nacelle made of composite material and free of mechanical connection and having single-layer wallboard structure |
-
1986
- 1986-09-26 GB GB08623253A patent/GB2196922A/en not_active Withdrawn
Cited By (34)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0346210A1 (en) * | 1988-06-08 | 1989-12-13 | AEROSPATIALE Société Nationale Industrielle | Composite frame, in particular for an aircraft fuselage, and its manufacturing process |
| FR2632604A1 (en) * | 1988-06-08 | 1989-12-15 | Aerospatiale | FRAME OF COMPOSITE MATERIAL IN PARTICULAR FOR AIRCRAFT FUSELAGE, AND METHOD FOR MANUFACTURING SAME |
| US5024399A (en) * | 1988-06-08 | 1991-06-18 | Societe Nationale Industrielle Et Aetospatiale | Frame made of a composite material, especially for the fuselage of an aircraft, and its method of production |
| FR2638707A1 (en) * | 1988-11-10 | 1990-05-11 | Commissariat Energie Atomique | Balloon gondola made of composite materials, configured for transporting heavy loads |
| US5562264A (en) * | 1992-07-22 | 1996-10-08 | Eurocopter France | Fuselage structure for helicopter |
| GB2295999A (en) * | 1994-12-16 | 1996-06-19 | British Aerospace | Aircraft fuselage manufacture |
| EP1251066A2 (en) * | 2001-03-13 | 2002-10-23 | Astrium Gmbh | Ring for the connection of two structural elements with rotational symmetry |
| EP1251066A3 (en) * | 2001-03-13 | 2003-11-12 | Astrium Gmbh | Ring for the connection of two structural elements with rotational symmetry |
| US6729792B2 (en) | 2001-03-13 | 2004-05-04 | Astrium Gmbh | Ring for connecting two rotationally symmetrical structural parts and method of making same |
| WO2004014726A1 (en) * | 2002-08-13 | 2004-02-19 | Sikorsky Aircraft Corporation | Composite tail cone assembly for a helicopter |
| WO2007065649A2 (en) * | 2005-12-06 | 2007-06-14 | Delcon Deutsche Luftfahrt Consult Gmbh | Aerial transporter |
| WO2007065649A3 (en) * | 2005-12-06 | 2007-09-27 | Delcon Deutsche Luftfahrt Cons | Aerial transporter |
| US8152092B2 (en) | 2005-12-06 | 2012-04-10 | Delcon Deutsche Luftfahrt Consult Gmbh | Aerial transporter |
| US8366041B2 (en) * | 2006-04-20 | 2013-02-05 | Airbus Operations Sas | Aircraft floor, use of said floor and aircraft section fitted with said floor |
| US8567150B2 (en) | 2006-05-23 | 2013-10-29 | Airbus Operations Sas | Aircraft pressurized floor |
| DE102006026169A1 (en) * | 2006-06-06 | 2007-12-27 | Airbus Deutschland Gmbh | Aircraft fuselage structure and method for its manufacture |
| US8695922B2 (en) | 2006-06-06 | 2014-04-15 | Airbus Operations Gmbh | Aircraft fuselage structure and method for its production |
| US8651421B2 (en) | 2006-06-06 | 2014-02-18 | Airbus Operations Gmbh | Aircraft fuselage structure and method for its production |
| US8534605B2 (en) | 2006-06-06 | 2013-09-17 | Airbus Operations Gmbh | Aircraft fuselage structure and method for producing it |
| JP2009539673A (en) * | 2006-06-06 | 2009-11-19 | エアバス ドイッチュラント ゲゼルシャフト ミット ベシュレンクテル ハフツング | Aircraft fuselage structure and manufacturing method thereof |
| DE102006026169B4 (en) * | 2006-06-06 | 2012-06-21 | Airbus Operations Gmbh | Aircraft fuselage structure and method for its manufacture |
| EP2128018A1 (en) * | 2007-01-29 | 2009-12-02 | Airbus Operations S.L. | Aircraft loading frame of composite material |
| EP2128018A4 (en) * | 2007-01-29 | 2013-09-18 | Airbus Operations Sl | Aircraft loading frame of composite material |
| US8672265B2 (en) | 2007-03-05 | 2014-03-18 | Airbus Operations Sas | Container for air freight transport and fuselage of an aircraft for freight transport |
| WO2010004157A3 (en) * | 2008-06-26 | 2010-03-04 | AIRBUS OPERATIONS (Société par actions simplifiée) | Aircraft fuselage element |
| WO2010004157A2 (en) * | 2008-06-26 | 2010-01-14 | AIRBUS OPERATIONS (Société par actions simplifiée) | Aircraft fuselage element |
| FR2933066A1 (en) * | 2008-06-26 | 2010-01-01 | Airbus France | AIRCRAFT FUSELAGE ELEMENT |
| US8939405B2 (en) | 2008-06-26 | 2015-01-27 | Airbus Operations S.A.S. | Aircraft fuselage element |
| FR2933065A1 (en) * | 2008-06-30 | 2010-01-01 | Airbus France | METHOD FOR ASSEMBLING A FLOOR IN A HULL STRUCTURE PREFALLABLY CONSISTING OF AN AIRCRAFT FUSELAGE TRUNK |
| WO2010003818A3 (en) * | 2008-07-07 | 2010-05-14 | Airbus Operations Gmbh | Method for installing a dome-shaped pressure bulkhead in a rear section of an aircraft, and device for carrying out the method |
| WO2010003818A2 (en) * | 2008-07-07 | 2010-01-14 | Airbus Operations Gmbh | Method for installing a dome-shaped pressure bulkhead in a rear section of an aircraft, and device for carrying out the method |
| US9180957B2 (en) | 2008-07-07 | 2015-11-10 | Airbus Operations Gmbh | Method for installing a dome-shaped pressure bulkhead in a rear section of an aircraft, and device for carrying out the method |
| US8256713B2 (en) | 2008-12-09 | 2012-09-04 | Airbus Operations Sas | Aircraft fuselage section |
| WO2016195520A1 (en) * | 2015-06-05 | 2016-12-08 | Instituto Superior Técnico | Multifunctional air transport system |
Also Published As
| Publication number | Publication date |
|---|---|
| GB8623253D0 (en) | 1986-10-29 |
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