WO2013076633A1 - Method for obtaining supports for aircraft - Google Patents

Method for obtaining supports for aircraft Download PDF

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Publication number
WO2013076633A1
WO2013076633A1 PCT/IB2012/056486 IB2012056486W WO2013076633A1 WO 2013076633 A1 WO2013076633 A1 WO 2013076633A1 IB 2012056486 W IB2012056486 W IB 2012056486W WO 2013076633 A1 WO2013076633 A1 WO 2013076633A1
Authority
WO
WIPO (PCT)
Prior art keywords
pylon
support
elements
positioning
avionics
Prior art date
Application number
PCT/IB2012/056486
Other languages
French (fr)
Inventor
Cristiano Bordignon
Original Assignee
Aeronautical Service S.R.L.
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Aeronautical Service S.R.L. filed Critical Aeronautical Service S.R.L.
Publication of WO2013076633A1 publication Critical patent/WO2013076633A1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
    • B64D1/02—Dropping, ejecting, or releasing articles
    • B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
    • 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
    • B29C70/34—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 and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/342—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 and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
    • 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

Definitions

  • the present patent application is directed towards the avionics sector and in particular regards the coupling and sealing systems, commonly known as pylons, adapted to support the accessories with which both civilian and military aircraft can be externally and internally equipped.
  • the present invention refers to an innovative pylon, obtained entirely in composite material and to the relative molding techniques for manufacturing the pylon in series. Said techniques are expressly aimed for the use of only the molding technique defined supported processing, with the use of the "male mold”.
  • ylon in avionics, one intends the means for supporting innumerable different accessories such as: common tanks, additional fuel tanks, reserve tanks, armament of various types and advanced avionics equipment for spying and monitoring which normally equip or can equip aircraft, as a function of the mission that the aircraft can or must undertake.
  • the pylon with the relative suitable coupling systems with which it is provided allows a quick and completely safe installation of said accessories, independent of the critical nature of the operation and the speed at which the installation must be carried out.
  • this innovative molding technique allows handling all the significant stresses deriving from normal flight activity and the particular stresses that some missions can cause.
  • the innovative technique in the obtainment of the aforesaid pylons for avionics, object of the present invention allows the production of the primary structure as well as of the secondary structures and the internal bulkheads of each single pylon, by carrying out a single treatment or processing cycle. This innovative result was attained by carrying out the compaction in every aspect and geometry of the pylon itself.
  • Said compaction is ensured and obtained by a sequence of repetitive pre-compactions carried out with the aid of high pressure, together with the very strict control of the temperature at which processing occurs.
  • the very strict control of the temperature and the pressure in treatment step allows modulating the viscosity of the resin during processing in order to obtain a perfect adhesion of the single laminate layers.
  • the structure of the pylon, object of the present invention is subjected to strong, extreme stress during its use and it is consequently characterized by considerable thickness as well as by sudden, significant changes of the thickness itself as a function of the loads applied in its various parts.
  • Extensive research on shrinkage and thermal deformations has allowed improving the size constraints of each part of the pylon itself, offering the possibility to obtain the desired geometries with the required reduced tolerances. The required reduced tolerances were made possible due to the selection of the pre-flexion of the laminates themselves.
  • the pylon that is the object of the present invention is substantially constituted by a single- structure load-bearing structure, obtained by means of the careful stratification of single panels of unidirectional carbon fibers and fabrics pre-impregnated with epoxy resin. Said lamination has a characteristic section with an overturned U-shaped conformation where the molding equipment is positioned, according to the male mold technique.
  • the upper part i.e. the overturned U-shaped curved profile
  • the upper part is shaped and perforated in a manner such to allow the stable and secure coupling and connection to the aircraft on which it must be installed; in this manner, the pylon itself and the relative control and functioning equipment housed therein can correctly carry out their functions.
  • the two lateral flanks of said pylon can have shaped openings and the windows suitably embedded, in order to allow the installation of the aforesaid additional components.
  • the front part and the rear part remanufactured afterward can provide for the application of inlet and outlet corners, prefabricated in metal or composite material.
  • the innovation pertaining to the production techniques lies in creating single pre-laminated and pre-compacted blocks to be subsequently assembled together, making the structure uniform by means of the application of additional complete skins which cover the entire pylon body.
  • the rigidly sequenced laminations allow creating a continuous lamination without troughs and bulges, alternating reliefs and recesses of the fabrics.
  • the slots present on the support base Z allow the sliding of the single movable components which by translating along the longitudinal axis of the support base Z create the bulkheads, placing the laminations of the single blocks in contact with each other, creating a uniform lamination with well-determined thickness.
  • the fixed reference element is only block Bl .
  • the slots allow a limited longitudinal sliding, centering, relative alignment and relative tightening of the single blocks in position.
  • the thicknesses of the single bulkheads are predefined and designed in order to provide the desired structural rigidity and consistency, as a function of the loads to be supported.
  • Figure 1 is a side view of the support pylon according to the present invention in which the four single elements A, Bl, B2, C that compose it are observed, arranged on the support base Z.
  • Figure 2 is a side rear view of the support pylon according to the present invention in which the molding elements A, B2 and C are observed together with the central fixed element Bl arranged on the support base Z but not yet arranged in positioned and in contact with each other.
  • Figure 3 is a front side view of the pylon at the end of rolling/lamination.
  • the upper shaping and initiating of the front and rear outlets with the relative tapering can be inferred.
  • Figure 4 shows the separation/breaking apart of the elements inside block A, in which one observes the shaped molding surface obtained from the assembly of the single components of the internal structure of the element A of the pylon, constituting part of the object of the present invention. Such separation/breaking apart is necessary for removing the molding equipment from the pylon interior.
  • Figure 5 shows a detail of the single elements Bl and B2 in which one observes a wedge with parallelepiped form, with shape and thickness suitable for producing an underlying semi-bulkhead, present between the abovementioned blocks.
  • Figure 6 shows a slot according to the present invention. Preferred embodiment of the invention
  • the separation/breaking apart of the support pylon obtained according to the present invention into single, separate base elements - the elements A, C, Bl and B2 - speeds up and facilitates both the unmolding and extraction of the single preformed elements from their initial molding seat.
  • Said joined elements constitute the molding equipment, defined "male mold” processing.
  • the single elements, formed by the relative sub-elements, constitute the shaped central core, on which the various pre-impregnated carbon layers (the so-called pre- preg layers) are rolled/laminated.
  • the four elements, once laminated with fabrics that are still fresh, untreated, are arranged on the support base in the following order:
  • the element A is fixed on the front part. Except for the element Bl, which is the first to be stably constrained to the support base by means of fixing with bolt means, all the subsequent elements are fixed to said base by means of bolts, through the slide slots which allow, by translating, pressing said element A and B2 against the element Bl, and the element C afterward against the element B2. Then, the three elements A, B2 and C, after having been positioned on the support base Z, are made to slide along the longitudinal axis of said support base Z, coming to be compressed in a calibrated and guided manner against the central block called Bl . The spaces and voids created between each single element are filled with additional pre-impregnated carbon. Then, one proceeds to once again drape all the pre-compacted elements constrained on the position of the base in respect of the bulkhead thicknesses, ensuring the correct final geometry.
  • the continuity of the laminations between the single elements is therefore ensured by the latter draping and by the weld material filling, constituted by unidirectional carbon fibers precompacted at high pressure and inserted in the recesses between one block and the next.
  • the uniformity of the materials allows perfect compatibility and continuity of the fabrics.
  • the final further laying of pre-impregnated carbon laminates on the joined elements A, Bl , B2 and C allows the correct distribution of the stresses and the integrity of the structure.
  • the entire manufactured item thus obtained is then heat processed, in a single passage in the furnace, considerably improving the qualitative output and the polymerization process and at the same time optimizing the processing times and thus the output.
  • the use of said elements A, Bl, B2, C allows the obtainment of a single shaped block, complete with internal separators, with only one furnace treatment process.
  • the internal configuration of the manufactured item will be a reversed image, as represented in Figure 1.
  • the upper edge is constituted by further pre-compacted and preformed weld material by means of a preforming and pre-shaped mold applied on site at high pressure.
  • the total covering with several final fabrics allows the adhesion of the preformed edges to the rest of the component.
  • the initiation of the aerodynamic external surfaces is obtained by means of the application of a plate with reduced thickness, shaped to perfectly adhere to the profile and to the upper part of the pylon, covered by the preformed mold of the edges.
  • the method for processing the support pylon according to the present invention provides for the following processing steps:
  • the support pylon obtained according to the technique described in the present patent application can be covered with one or more anti-radar layers or anti-reflection layers in order to be invisible or hard to find by radar or any other detection system.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Reinforced Plastic Materials (AREA)
  • Laminated Bodies (AREA)

Abstract

Method for manufacturing a support pylon for avionics made of composite materials, adapted to allow the transport of external loads that cannot be directly supported at the primary or secondary structure of the aircraft. Said loads are represented by external tanks, armament of various types and/or avionics equipment.

Description

METHOD FOR OBTAINING SUPPORTS FOR AIRCRAFT
Description Field of the invention
The present patent application is directed towards the avionics sector and in particular regards the coupling and sealing systems, commonly known as pylons, adapted to support the accessories with which both civilian and military aircraft can be externally and internally equipped.
Description of the invention
The present invention refers to an innovative pylon, obtained entirely in composite material and to the relative molding techniques for manufacturing the pylon in series. Said techniques are expressly aimed for the use of only the molding technique defined supported processing, with the use of the "male mold".
With "pylon" in avionics, one intends the means for supporting innumerable different accessories such as: common tanks, additional fuel tanks, reserve tanks, armament of various types and advanced avionics equipment for spying and monitoring which normally equip or can equip aircraft, as a function of the mission that the aircraft can or must undertake.
The pylon with the relative suitable coupling systems with which it is provided allows a quick and completely safe installation of said accessories, independent of the critical nature of the operation and the speed at which the installation must be carried out.
Due to the technique of molding by means of male mold, it is possible to respect the reduced tolerances required for the installation of the most sophisticated and complex equipment, such as the ERU (as a non-limiting example). In addition, this innovative molding technique allows handling all the significant stresses deriving from normal flight activity and the particular stresses that some missions can cause. The innovative technique in the obtainment of the aforesaid pylons for avionics, object of the present invention, allows the production of the primary structure as well as of the secondary structures and the internal bulkheads of each single pylon, by carrying out a single treatment or processing cycle. This innovative result was attained by carrying out the compaction in every aspect and geometry of the pylon itself. Said compaction is ensured and obtained by a sequence of repetitive pre-compactions carried out with the aid of high pressure, together with the very strict control of the temperature at which processing occurs. The very strict control of the temperature and the pressure in treatment step allows modulating the viscosity of the resin during processing in order to obtain a perfect adhesion of the single laminate layers.
The structure of the pylon, object of the present invention, is subjected to strong, extreme stress during its use and it is consequently characterized by considerable thickness as well as by sudden, significant changes of the thickness itself as a function of the loads applied in its various parts. Thus, we have a component with high structural performance, with a considerable saving of weight with respect to an analogous structure made of metal material. Extensive research on shrinkage and thermal deformations has allowed improving the size constraints of each part of the pylon itself, offering the possibility to obtain the desired geometries with the required reduced tolerances. The required reduced tolerances were made possible due to the selection of the pre-flexion of the laminates themselves.
The pylon that is the object of the present invention is substantially constituted by a single- structure load-bearing structure, obtained by means of the careful stratification of single panels of unidirectional carbon fibers and fabrics pre-impregnated with epoxy resin. Said lamination has a characteristic section with an overturned U-shaped conformation where the molding equipment is positioned, according to the male mold technique.
The upper part, i.e. the overturned U-shaped curved profile, is shaped and perforated in a manner such to allow the stable and secure coupling and connection to the aircraft on which it must be installed; in this manner, the pylon itself and the relative control and functioning equipment housed therein can correctly carry out their functions. The two lateral flanks of said pylon can have shaped openings and the windows suitably embedded, in order to allow the installation of the aforesaid additional components. The front part and the rear part remanufactured afterward can provide for the application of inlet and outlet corners, prefabricated in metal or composite material. The innovation pertaining to the production techniques lies in creating single pre-laminated and pre-compacted blocks to be subsequently assembled together, making the structure uniform by means of the application of additional complete skins which cover the entire pylon body. On the single blocks, the rigidly sequenced laminations allow creating a continuous lamination without troughs and bulges, alternating reliefs and recesses of the fabrics. The slots present on the support base Z allow the sliding of the single movable components which by translating along the longitudinal axis of the support base Z create the bulkheads, placing the laminations of the single blocks in contact with each other, creating a uniform lamination with well-determined thickness. The fixed reference element is only block Bl . The slots allow a limited longitudinal sliding, centering, relative alignment and relative tightening of the single blocks in position. The thicknesses of the single bulkheads are predefined and designed in order to provide the desired structural rigidity and consistency, as a function of the loads to be supported.
Brief description of the drawings
Figure 1 : is a side view of the support pylon according to the present invention in which the four single elements A, Bl, B2, C that compose it are observed, arranged on the support base Z.
Figure 2: is a side rear view of the support pylon according to the present invention in which the molding elements A, B2 and C are observed together with the central fixed element Bl arranged on the support base Z but not yet arranged in positioned and in contact with each other.
Figure 3: is a front side view of the pylon at the end of rolling/lamination. The upper shaping and initiating of the front and rear outlets with the relative tapering can be inferred.
Figure 4: shows the separation/breaking apart of the elements inside block A, in which one observes the shaped molding surface obtained from the assembly of the single components of the internal structure of the element A of the pylon, constituting part of the object of the present invention. Such separation/breaking apart is necessary for removing the molding equipment from the pylon interior. Figure 5: shows a detail of the single elements Bl and B2 in which one observes a wedge with parallelepiped form, with shape and thickness suitable for producing an underlying semi-bulkhead, present between the abovementioned blocks.
Figure 6: shows a slot according to the present invention. Preferred embodiment of the invention
The separation/breaking apart of the support pylon obtained according to the present invention into single, separate base elements - the elements A, C, Bl and B2 - speeds up and facilitates both the unmolding and extraction of the single preformed elements from their initial molding seat. Said joined elements constitute the molding equipment, defined "male mold" processing. The single elements, formed by the relative sub-elements, constitute the shaped central core, on which the various pre-impregnated carbon layers (the so-called pre- preg layers) are rolled/laminated. The four elements, once laminated with fabrics that are still fresh, untreated, are arranged on the support base in the following order:
1) First, the element Bl is fixed;
2) Then, the element B2 is fixed on the rear part;
3) Afterwards, the element C is fixed;
4) The element A is fixed on the front part. Except for the element Bl, which is the first to be stably constrained to the support base by means of fixing with bolt means, all the subsequent elements are fixed to said base by means of bolts, through the slide slots which allow, by translating, pressing said element A and B2 against the element Bl, and the element C afterward against the element B2. Then, the three elements A, B2 and C, after having been positioned on the support base Z, are made to slide along the longitudinal axis of said support base Z, coming to be compressed in a calibrated and guided manner against the central block called Bl . The spaces and voids created between each single element are filled with additional pre-impregnated carbon. Then, one proceeds to once again drape all the pre-compacted elements constrained on the position of the base in respect of the bulkhead thicknesses, ensuring the correct final geometry.
The continuity of the laminations between the single elements is therefore ensured by the latter draping and by the weld material filling, constituted by unidirectional carbon fibers precompacted at high pressure and inserted in the recesses between one block and the next. The uniformity of the materials allows perfect compatibility and continuity of the fabrics. The final further laying of pre-impregnated carbon laminates on the joined elements A, Bl , B2 and C allows the correct distribution of the stresses and the integrity of the structure. The entire manufactured item thus obtained is then heat processed, in a single passage in the furnace, considerably improving the qualitative output and the polymerization process and at the same time optimizing the processing times and thus the output.
The use of said elements A, Bl, B2, C allows the obtainment of a single shaped block, complete with internal separators, with only one furnace treatment process. The internal configuration of the manufactured item will be a reversed image, as represented in Figure 1. The upper edge is constituted by further pre-compacted and preformed weld material by means of a preforming and pre-shaped mold applied on site at high pressure.
The total covering with several final fabrics allows the adhesion of the preformed edges to the rest of the component. The initiation of the aerodynamic external surfaces is obtained by means of the application of a plate with reduced thickness, shaped to perfectly adhere to the profile and to the upper part of the pylon, covered by the preformed mold of the edges.
Therefore, the method for processing the support pylon according to the present invention provides for the following processing steps:
1) Obtainment of the male mold constituted by the elements A, Bl, B2 and by the element C.
2) Cold rolling/lamination of each single element according to the technique of rolling/lamination with male mold with application of the vacuum technique, and repetitive pre-compaction in autoclave.
3) Positioning of the element Bl in a stable and central manner on the support base.
4) Positioning of the element B2 by means of bolts through the slots present on the base and following translation, it is constrained to the base in a position against the element Bl .
5) Positioning of the element A on the corresponding slot and subsequent compression of the element A against the element Bl .
6) Positioning of the element C on the respective slot and its compression against the element B2 in turn compressed against the element Bl .
7) Filling of the slits present between the single elements A, Bl, B2, C with portions of pre-impregnated and precompressed carbon.
8) Application of a further layer of pre-impregnated carbon laminate along all of the joined elements placed on the support base in a manner so as to form a single pylon.
9) Application of fabrics on the edges and preforms by means of a shaped mold.
10) Treatment in autoclave.
11) Gradual cooling up to ambient temperature and subsequent extraction of the pylon from the autoclave.
12) Separation of the treated pylon from the support base and extraction of the single blocks with the relative sub-elements from the pylon interior. The support pylon obtained according to the technique described in the present patent application can be covered with one or more anti-radar layers or anti-reflection layers in order to be invisible or hard to find by radar or any other detection system.

Claims

1. Method for obtaining and assembling at least four elements A, Bl, B2 and C adapted to constitute a support pylon for aircraft in their entirety, said pylon made of pre-impregnated carbon fiber, characterized by the presence of at least three internal separators and obtained according to the following processing steps:
a) Obtainment of the male mold constituted by the elements A, Bl, B2 and by the element C.
b) Cold rolling/lamination of each single element according to the technique of rolling/lamination with male mold with application of the vacuum technique, and cold pre-compaction in autoclave.
c) Positioning of the element Bl in a stable, fixed and central manner on the support base Z.
d) Positioning of the element B2 on the corresponding slot placed on said support base Z.
e) Positioning of the element A on the corresponding slot and subsequent compression of the element A against the element Bl .
f) Positioning of the element C on the respective slot and its compression against the element B2 in turn compressed against the element Bl .
g) Filling of the slits present between the single elements A, Bl, B2, C with portions of pre-impregnated and precompressed carbon.
h) Application of a further layer of pre-impregnated carbon laminate along the exposed faces of the joined elements A, Bl, B2 and C placed on the support base as described above, in a manner so as to form a single-structure pylon.
i) Treatment in autoclave of the entire obtained manufactured item.
2. Method according to the preceding claim, wherein the support slots of the elements A, B2 and C are movable slots, capable of sliding along a predefined direction, so as to press the elements A and B2 against the element Bl and the element C against the element B2 after this has been positioned.
3. Method according to the preceding claims, wherein the support pylon thus obtained is adapted to be used for the stable and reversible support of various accessories used in avionics: weapons systems, weapons, tanks, supplementary tanks, telecameras, video cameras, detection systems and monitoring equipment.
4. Support pylon for avionics, characterized in that it is obtained according to the technique of the preceding claims.
5. Support pylon for avionics, characterized in that it is treated or covered with anti-radar or anti-reflection surfaces.
6. Support pylon according to all the preceding claims, made of any natural or synthetic polymer adapted to be shaped on a male mold.
7. Support pylon according to the preceding claims, whose internal structure is characterized by the presence of at least three carbon separators with predefined thickness.
8. Support pylon according to the preceding claims, wherein the final treatment in a furnace occurs in a single step.
PCT/IB2012/056486 2011-11-25 2012-11-16 Method for obtaining supports for aircraft WO2013076633A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITRM2011A000626 2011-11-25
IT000626A ITRM20110626A1 (en) 2011-11-25 2011-11-25 METHOD FOR THE REALIZATION OF SUPPORT SUPPORTS FOR AVIONICS.

Publications (1)

Publication Number Publication Date
WO2013076633A1 true WO2013076633A1 (en) 2013-05-30

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WO (1) WO2013076633A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9566224B2 (en) 2013-03-13 2017-02-14 Avon Products, Inc. Tyrosinase inhibitors

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4565595A (en) * 1981-09-30 1986-01-21 The Boeing Company Method of making composite aircraft wing
US6190484B1 (en) * 1999-02-19 2001-02-20 Kari Appa Monolithic composite wing manufacturing process
EP1375345A1 (en) * 2002-06-20 2004-01-02 MBDA France Weapon provided with a missile and which is mounted on a stealth aircraft, and a weapon system comprising a stealth aircraft and such a weapon
US20060169835A1 (en) * 2004-12-16 2006-08-03 Laurence Maille Method and apparatus for manufacturing a helicopter rotor fairing, and a fairing obtained thereby
WO2008117174A1 (en) * 2007-03-28 2008-10-02 Alenia Aermacchi S.P.A. Under-wing pylon made of composite material

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4565595A (en) * 1981-09-30 1986-01-21 The Boeing Company Method of making composite aircraft wing
US6190484B1 (en) * 1999-02-19 2001-02-20 Kari Appa Monolithic composite wing manufacturing process
EP1375345A1 (en) * 2002-06-20 2004-01-02 MBDA France Weapon provided with a missile and which is mounted on a stealth aircraft, and a weapon system comprising a stealth aircraft and such a weapon
US20060169835A1 (en) * 2004-12-16 2006-08-03 Laurence Maille Method and apparatus for manufacturing a helicopter rotor fairing, and a fairing obtained thereby
WO2008117174A1 (en) * 2007-03-28 2008-10-02 Alenia Aermacchi S.P.A. Under-wing pylon made of composite material

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9566224B2 (en) 2013-03-13 2017-02-14 Avon Products, Inc. Tyrosinase inhibitors

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