FR2646494A1 - LIGHT MATERIAL FOR AEROSPATIAL STRUCTURES - Google Patents
LIGHT MATERIAL FOR AEROSPATIAL STRUCTURES Download PDFInfo
- Publication number
- FR2646494A1 FR2646494A1 FR9005261A FR9005261A FR2646494A1 FR 2646494 A1 FR2646494 A1 FR 2646494A1 FR 9005261 A FR9005261 A FR 9005261A FR 9005261 A FR9005261 A FR 9005261A FR 2646494 A1 FR2646494 A1 FR 2646494A1
- Authority
- FR
- France
- Prior art keywords
- light material
- material according
- under
- structures
- elements
- 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.)
- Pending
Links
- 239000000463 material Substances 0.000 title claims abstract description 15
- 239000001307 helium Substances 0.000 claims abstract description 7
- 229910052734 helium Inorganic materials 0.000 claims abstract description 7
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims abstract description 7
- 239000003562 lightweight material Substances 0.000 claims abstract description 6
- 229910052751 metal Inorganic materials 0.000 claims abstract description 5
- 239000002184 metal Substances 0.000 claims abstract description 5
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 4
- 239000001257 hydrogen Substances 0.000 claims abstract description 4
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 4
- 230000003014 reinforcing effect Effects 0.000 claims description 5
- 230000002787 reinforcement Effects 0.000 abstract description 2
- 238000010276 construction Methods 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 230000006837 decompression Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 230000009897 systematic effect Effects 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
-
- 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
- B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Buildings Adapted To Withstand Abnormal External Influences (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
Matériau léger pour structures aérospatiales. Ce matériau comprend une enveloppe métallique 2, ayant une épaisseur de paroi inférieure à 1 mm, emplie d'hydrogène ou d'hélium sous une pression telle qu'en cas d'absence de charges mécaniques, la structure obtenue soit sous un état de tension mécanique. De tels éléments peuvent être accolés, sous des peaux externes, pour former des panneaux plats ou des éléments arrondis. Application : éléments de renforcement ou de support de charge pour structures aérospatiales.Lightweight material for aerospace structures. This material comprises a metal casing 2, having a wall thickness of less than 1 mm, filled with hydrogen or helium under a pressure such that in the absence of mechanical loads, the structure obtained is in a state of tension. mechanical. Such elements can be joined together, under external skins, to form flat panels or rounded elements. Application: elements of reinforcement or load support for aerospace structures.
Description
La présente invention concerne des matériaux légers, destinés à servir àThe present invention relates to lightweight materials for use in
la construction de structures aérospatiales. Un matériau couramment utilisé dans la construction des avions et aéronefs consiste en deux peaux métalliques entre lesquelles il y a, reliée et/ou collée à ces peaux,une the construction of aerospace structures. A material commonly used in the construction of aircraft and aircraft consists of two metal skins between which there is, connected and / or glued to these skins, a
couche en nid d'abeilles métallique. Ce matériau est large- layer of honeycomb metal. This material is wide-
ment utilisé dans les cas o les charges sont réparties ou distribuées par nature, comme dans le cas des sols de cabines ou certaines aires ou surfaces des ailes, des plans ou ailettes ou dérives de queue. On connaît également un matériau gonflable consistant en un sac flexible de forme convenable, dont des régions sont reliées par des éléments flexibles tendus. Ce matériau était spécifiquement destiné used in cases where the loads are distributed or distributed by nature, as in the case of cabin floors or certain areas or surfaces of wings, planes or fins or tail fins. Also known is an inflatable material consisting of a flexible bag of suitable shape, regions of which are connected by flexible elements tensioned. This material was specifically intended
à servir dans un contexte spatial pour permettre l'"atter- to be used in a spatial context to allow the "landing
rissage" des structures sous forme aplatie et leur dilata- "flattened structures and their dilat-
tion subséquente à leur forme finale quand les structures following their final form when the structures
ont atteint leur destination.have reached their destination.
Dans de nombreuses applications aérospatiales, la combinaison de la charge et de la longueur de transmission In many aerospace applications, the combination of load and transmission length
est telle que les structures résultantes sont en compres- is such that the resulting structures are compres-
sion et que leur comportement est régi par des critères de stabilité élastique. Les charges que les structures doivent supporter régissent le dimensionnement du matériau servant their behavior is governed by criteria of elastic stability. The loads that the structures must support govern the dimensioning of the material serving
à fabriquer les structures et en régissent donc les masses. to manufacture the structures and thus govern the masses.
Selon la présente invention, celle-ci propose un matériau léger destiné à servir de composant de support de According to the present invention, it proposes a light material intended to serve as a support component of
charges d'nne structure aérospatiale, le matériau compre- aerospace structure, the material includes
nant une enveloppe métallique ayant une épaisseur de paroi inférieure à 1 mm et qui est emplie d'hydrogène ou d'hélium à une pression telle que, lorsque la structure n'est pas soumise à des charges mécaniques, cette structure se trouve metal shell having a wall thickness of less than 1 mm and which is filled with hydrogen or helium at a pressure such that, when the structure is not subjected to mechanical loads, this structure is
en un état de tension mécanique.in a state of mechanical tension.
De préférence, le gaz est de l'hélium. Typiquement, l'épaisseur de la paroi de l'enveloppe est de 0,1 mm, et la Preferably, the gas is helium. Typically, the thickness of the wall of the envelope is 0.1 mm, and the
pression du gaz est de 10 bars.gas pressure is 10 bar.
L'invention sera maintenant décrite, à titre d'exemple illustratif et nullement limitatif, en référence aux dessins d'accompagnement sur lesquels: la figure 1 est une représentation d'un élément simple de renforcement comportant une mise en oeuvre de l'invention; la figure 2 est une représentation d'une structure de panneau comportant la mise en oeuvre de l'invention; la figure 3 est une représentation d'une autre forme de structure de panneau comportant la mise en oeuvre de l'invention; et la figure 4 montre une autre forme d'élément de The invention will now be described, by way of illustrative and non-limiting example, with reference to the accompanying drawings, in which: FIG. 1 is a representation of a simple reinforcing element comprising an implementation of the invention; FIG. 2 is a representation of a panel structure comprising the implementation of the invention; Figure 3 is a representation of another form of panel structure embodying the invention; and Figure 4 shows another form of element of
renforcement comportant la mise en oeuvre de l'invention. reinforcement comprising the implementation of the invention.
En se référant aux dessins, on voit que la figure 1 montre un élément simple de renforcement,qui consiste en une chambre 1 cylindrique dont la paroi 2 est en un alliage d'aluminium et a une épaisseur d'environ 0,1 mm. La chambre Referring to the drawings, it is seen that Figure 1 shows a simple reinforcing member, which consists of a cylindrical chamber 1 whose wall 2 is made of an aluminum alloy and has a thickness of about 0.1 mm. Bedroom
1 cylindrique est emplie d'hélium sous une pression d'envi- 1 cylindrical is filled with helium under a pressure of about
ron 10 bars.10 bars.
La figure 2 montre une façon de fabriquer une struc- Figure 2 shows a way of fabricating a structure
ture de panneau sensiblement plat. Comme dans le cas de l'élément de renforcement décrit en référence à la figure 1, la structure de panneau consiste en une chambre 21, qui a une paroi 22 en un alliage d'aluminium ayant environ 0,1 mm d'épaisseur et qui est emplie d'hélium sous une pression d'environ 10 bars. Dans ce cas, cependant, la chambre 21 est mise sous forme d'un panneau sensiblement plat, précontraint à l'aide d'éléments 23 de précontrainte qui relient des régions opposées de la paroi 22 de la chambre 21. Les éléments 23 de précontrainte peuvent avoir la forme de fils métalliques, de filés ou d'éléments substantially flat panel. As in the case of the reinforcing element described with reference to FIG. 1, the panel structure consists of a chamber 21, which has a wall 22 made of an aluminum alloy having a thickness of about 0.1 mm and which is filled with helium under a pressure of about 10 bar. In this case, however, the chamber 21 is in the form of a substantially flat panel, prestressed with prestressing elements 23 which connect opposite regions of the wall 22 of the chamber 21. The prestressing elements 23 may be in the form of wires, yarns or
filetés, ou bien prendre la forme de feuilles minces con- threads, or take the form of thin sheets
tinues. On peut réaliser des structures de panneaux ayant une forme autre qu'une forme sensiblement plane, par exemple un plan de sustentation ou une aile, ou une partie d'un tel plan ou d'une telle aile, en faisant varier de façon systématique convenable les longueurs des éléments 23 de précontrainte. On peut ainsi obtenir un ou des panneaux tinues. Panel structures having a shape other than a substantially planar shape, for example a lift plane or a wing, or part of such a plane or wing, can be made by varying in a suitable systematic manner. the lengths of the prestressing elements 23. It is thus possible to obtain one or more panels
de forme aérodynamique incurvée.curved aerodynamic shape.
Un inconvénient de la structure de panneau repré- A disadvantage of the panel structure
sentée sur la figure 2 est que, en raison de la minceur de la paroi 22 de la chambre 21, elle tend à se bosseler aux endroits o les éléments 23 de précontrainte sont reliés à la paroi 22 de la chambre 21. On peut surmonter cet effet grâce à l'agencement représenté sur la figure 3. Dans ce cas, plusieurs chambres 31, ayant la même structure que celle précédemment décrite, sont reliées ensemble sur la majeure partie de leurs périphéries. Non seulement le fait de relier ainsi ensemble les chambres 31 leur donne des sections allongées semblables à celles de la structure de panneau décrite à propos de la figure 2, mais cela permet d'y parvenir sans avoir besoin de recourir à des éléments internes quelconques de précontrainte. Des peaux externes 32 et 33 sont reliées et/ou collées aux extrémités 34 arrondies des chambres 31, pour donner des surfaces externes dépourvues de bosselures. Un avantage de cette forme de structure est qu'une perte d'intégrité suivie d'une décompression d'une ou plusieurs chambres 31 ne va 2 is that, because of the thinness of the wall 22 of the chamber 21, it tends to dent at the locations where the prestressing elements 23 are connected to the wall 22 of the chamber 21. This can be overcome. This is because of the arrangement shown in FIG. 3. In this case, several chambers 31, having the same structure as that previously described, are connected together over most of their peripheries. Not only does the fact of thus connecting the chambers 31 together give them elongated sections similar to those of the panel structure described with reference to FIG. 2, but this makes it possible to achieve this without the need to resort to any internal elements of prestressing. External skins 32 and 33 are connected and / or glued to the rounded ends 34 of the chambers 31, to provide external surfaces free of dents. An advantage of this form of structure is that a loss of integrity followed by decompression of one or more chambers 31 will not
pas nécessairement provoquer un affaissement du panneau. not necessarily cause a collapse of the panel.
Comme précédemment, on peut réaliser des panneaux ayant une épaisseur autre qu'une épaisseur uniforme, en faisant varier les longueurs d'une chambre 31 dans la direction As before, panels having a thickness other than a uniform thickness can be made by varying the lengths of a chamber 31 in the direction
perpendiculaire aux peaux externes 32 et 33 du panneau. perpendicular to the outer skins 32 and 33 of the panel.
Une construction multicellulaire semblable, pour protéger contre une perte de solidité mécanique, peut être appliquée à des éléments de renforcement, et une telle structure est représentée sur la figure 4. Plusieurs A similar multicellular construction, to protect against a loss of mechanical strength, can be applied to reinforcing elements, and such a structure is shown in FIG.
chambres 4 cylindriques et séparées sont étroitement acco- 4 cylindrical and separate rooms are closely
lées et reliées et/o collées ensemble le long de leurs lignes de contact, en formant ainsi un garnissage serré. Ces chambres sont entourées par un cylindre 42 externe auquel sont reliées et/ou collées les chambres 4' cylindriques and bonded and / or bonded together along their nips, thereby forming a tight packing. These chambers are surrounded by an outer cylinder 42 to which are connected and / or glued the cylindrical chambers 4 '
externes du garnissage intérieur.external lining.
Claims (6)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB898909490A GB8909490D0 (en) | 1989-04-26 | 1989-04-26 | Aerospace structures |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| FR2646494A1 true FR2646494A1 (en) | 1990-11-02 |
Family
ID=10655727
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| FR9005261A Pending FR2646494A1 (en) | 1989-04-26 | 1990-04-25 | LIGHT MATERIAL FOR AEROSPATIAL STRUCTURES |
Country Status (3)
| Country | Link |
|---|---|
| DE (1) | DE4013169A1 (en) |
| FR (1) | FR2646494A1 (en) |
| GB (2) | GB8909490D0 (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19549000A1 (en) * | 1995-01-04 | 1996-07-11 | Martin K Rzyttka | Helium chamber for aircraft or airship |
| DE102007009645B4 (en) * | 2007-02-26 | 2012-05-31 | Frank Wagner | Technical procedure for the reduction of transport costs and pollutant emissions during the transport of goods and living beings through the use of "carrying gases" to lift gain |
| DE102010025994A1 (en) | 2010-07-04 | 2012-08-16 | Frank Wagner | Technical procedure for the reduction of transport costs and pollutant emissions during the transport of goods and living beings through the use of carrying gases to gain lift in passenger cabins |
| DE102010034326A1 (en) | 2010-08-14 | 2013-05-23 | Frank Wagner | Technical procedure to reduce transport costs and pollutant emissions during transport of goods and living things by the use of inert gases to gain lift in the spaces between the loading area and outer wall / shell of aircraft |
| DE102011107915A1 (en) | 2011-07-02 | 2013-04-25 | Frank Wagner | Method for placing carrier gas envelope in wing of motor vehicle, involves counteracting force of gravity of aircraft by filling carrier gas in carrier gas envelope |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB946762A (en) * | 1960-01-25 | 1964-01-15 | Secr Aviation | Improvements in aircraft |
| GB1134752A (en) * | 1965-01-29 | 1968-11-27 | Marston Excelsior Ltd | Inflatable fairings |
| US3596622A (en) * | 1969-01-27 | 1971-08-03 | Moore Alvin E | Light-weight wreck-resistant vehicle |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB835221A (en) * | 1955-05-26 | 1960-05-18 | Mini Of Supply | Improvements in aircraft |
| GB837591A (en) * | 1956-03-24 | 1960-06-15 | Mini Of Supply | Improvements in or relating to aircraft having inflatable structural members |
-
1989
- 1989-04-26 GB GB898909490A patent/GB8909490D0/en active Pending
-
1990
- 1990-04-12 GB GB9008419A patent/GB2230751B/en not_active Expired - Fee Related
- 1990-04-25 DE DE4013169A patent/DE4013169A1/en not_active Withdrawn
- 1990-04-25 FR FR9005261A patent/FR2646494A1/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB946762A (en) * | 1960-01-25 | 1964-01-15 | Secr Aviation | Improvements in aircraft |
| GB1134752A (en) * | 1965-01-29 | 1968-11-27 | Marston Excelsior Ltd | Inflatable fairings |
| US3596622A (en) * | 1969-01-27 | 1971-08-03 | Moore Alvin E | Light-weight wreck-resistant vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| GB8909490D0 (en) | 1989-06-14 |
| DE4013169A1 (en) | 1990-10-31 |
| GB9008419D0 (en) | 1990-06-13 |
| GB2230751A (en) | 1990-10-31 |
| GB2230751B (en) | 1992-07-15 |
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