FR2827029A1 - Aircraft with ventral streamlining joint located in slit between wing extrados and ventral streamlining has boss on free end of joint lip holding lip away from extrados - Google Patents

Aircraft with ventral streamlining joint located in slit between wing extrados and ventral streamlining has boss on free end of joint lip holding lip away from extrados Download PDF

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Publication number
FR2827029A1
FR2827029A1 FR0112829A FR0112829A FR2827029A1 FR 2827029 A1 FR2827029 A1 FR 2827029A1 FR 0112829 A FR0112829 A FR 0112829A FR 0112829 A FR0112829 A FR 0112829A FR 2827029 A1 FR2827029 A1 FR 2827029A1
Authority
FR
France
Prior art keywords
fuselage
joint
wing
lip
seal
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.)
Granted
Application number
FR0112829A
Other languages
French (fr)
Other versions
FR2827029B1 (en
Inventor
Jean Pierre Maury
Alain Milhau
Bernard Pauly
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Holding SAS
Original Assignee
Airbus Operations SAS
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
Priority to FR0108982A priority Critical patent/FR2827028B1/en
Application filed by Airbus Operations SAS filed Critical Airbus Operations SAS
Priority to FR0112829A priority patent/FR2827029B1/en
Priority claimed from EP20020291941 external-priority patent/EP1300335B1/en
Publication of FR2827029A1 publication Critical patent/FR2827029A1/en
Application granted granted Critical
Publication of FR2827029B1 publication Critical patent/FR2827029B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16JPISTONS; CYLINDERS; SEALINGS
    • F16J15/00Sealings
    • F16J15/02Sealings between relatively-stationary surfaces
    • F16J15/021Sealings between relatively-stationary surfaces with elastic packing
    • F16J15/022Sealings between relatively-stationary surfaces with elastic packing characterised by structure or material
    • F16J15/024Sealings between relatively-stationary surfaces with elastic packing characterised by structure or material the packing being locally weakened in order to increase elasticity
    • F16J15/027Sealings between relatively-stationary surfaces with elastic packing characterised by structure or material the packing being locally weakened in order to increase elasticity and with a hollow profile
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C7/00Structures or fairings not otherwise provided for

Abstract

The joint (22) is located in the slit (20) between the extrados (32) of a wing (6) and the ventral streamlining (10). The internal surface (26) of the free end (28) of the joint lip (24) comprises a boss (30) able to hold the lip locally away from the extrados in order to make a controlled escape of air passing through the slit.

Description

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 The present invention relates to an aircraft with a ventral fairing, as well as a joint for such an aircraft.

 It is known that certain aircraft, provided with a fuselage and a fixed wing comprising two wings opposite with respect to said fuselage, have a ventral fairing, generally projecting, in the form of a cradle, which is fixed to the lower part of said fuselage at the crossing of the latter with said wing to close the landing gear box, possibly increasing the volume downward, and which has two longitudinal edges rising laterally along said fuselage, said edges being each provided with an opening for the passage of the corresponding wing. Such a fairing completes the aerodynamic profile of the crossing zone and its shape is adapted to minimize the aerodynamic drag it generates.

 In certain known aircraft, the method of fixing this ventral fairing to the fuselage results in the formation of a first peripheral slot around the ventral fairing, between the latter and the fuselage, and of a second peripheral slot around each wing, between the latter and the periphery of the corresponding opening of said fairing. In order to close off said slots, an elongated seal is then provided, fixed at the periphery of said ventral fairing and at the periphery of each opening of the latter.

 It will be noted that, in addition to its sealing function, said seal must ensure the continuity of the surfaces to avoid the appearance of significant drag and absorb the relative movements between said fairing, on the one hand, and the airfoil and the fuselage, on the other hand.

 To do this, the seals currently used have two longitudinal elastic lifts capable of being applied, by the internal face of their

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 free end, respectively against the fuselage or the wing, one of these lips - hereinafter referred to as end lip - forming the free end edge of said joint, while the other - designated below after by internal lip - is carried by the internal face of this seal and is set back relative to said end lip.

 Such a known joint has many drawbacks. First of all, during its assembly, the internal lip - which is hidden by the joint itself and / or by the fairing - can turn over, its external face coming to bear on the fuselage or the wing at the place of its internal face. In this case, the seal can no longer fulfill its function and it wears out very quickly.

 Furthermore, in flight, because of the pressure difference between the lower surface (overpressure) and the upper surface (depression) of the wing, there is established, between the lower surface and the upper surface of each wing, air circulation inside the fairing through said first and second slots, which causes, in particular on the extrados side, the separation of the free end of said elastic lips of said joint, relative to the fuselage or to the wing. As a result, said elastic lips of the seal begin to vibrate, and this in a range of frequencies perfectly audible from inside the cabin, which is troublesome for passengers. These vibrations are transmitted to the fuselage and to the elements which it comprises (floor, support, etc.) and cause a structural stress in fatigue of said elements. In addition, the vibrations, associated with the aerodynamic forces applied to said lips, cause premature fatigue of the latter, which results in rapid wear which can go as far as tearing them apart. Finally, it results from these vibrations the appearance of a parasitic aerodynamic drag.

 The object of the present invention is to remedy these drawbacks.

 To this end, according to the invention, an aircraft comprising:

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 - a fuselage and a fixed wing comprising two wings opposite to said fuselage; a ventral fairing in the form of a cradle, fixed with clearance to the lower part of said fuselage, at the crossing of the latter with said wing and provided with two longitudinal edges rising laterally along said fuselage, said longitudinal edges being each provided, an opening for the passage with clearance of the corresponding wing, so that are formed:. a first peripheral slot around said ventral fairing, between the latter and said fuselage; and. a second peripheral slot around each wing, between the latter and the periphery of the corresponding opening; and - an elongated seal, fixed to the periphery of said ventral fairing and to the periphery of each opening, for closing said first and second slots, respectively, said seal comprising: a longitudinal elastic lifter end capable of being applied, by the internal face of its free end, respectively against said fuselage or said wing; and. an additional longitudinal sealing member, carried by the internal face of said seal recessed with respect to said end lip and also capable of being applied against said fuselage or said wing, respectively, is remarkable in that said member Additional longitudinal sealing is a radially elastic bead.

 Thus, thanks to the present invention, many advantages are obtained: - said radially elastic bead, carried by the internal face of the joint, always presents itself correctly in relation to the fuselage or to the

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 wings, during installation, which cannot turn over, as the internal lip did, which it replaces; and - said radially elastic bead, when applied against the fuselage or the airfoil of the aircraft, deforms and flattens forming a large bearing surface, incapable of vibrating as did said internal lip. In addition, this large bearing surface ensures excellent sealing, so that the detachment and the vibration entry of the free end of the end lip are if not completely eliminated, at least greatly reduced.

 To further reduce, and even completely eliminate the vibrations of said end lip, it is advantageous, in accordance with another feature of the present invention, made possible due to the excellent seal provided by said radially elastic bead, that said internal face of the free end of said end lip comprises, at least on a part of said seal, at least one abutment boss, capable of holding said end lip locally spaced from said fuselage or said wing, respectively, for provide a controlled air leak of air likely to pass through said first and second slots, in the event of a possible leak, occasional and / or momentary, of said bead.

 Of course, the height of each boss and the number of said bosses, as well as the distribution of these, are determined, by calculation or by experience, so that the flow of leakage air between said bosses generates little parasitic drag, while ensuring a low level of vibration of said end lip of the seal.

 Depending on the geometry of the fuselage, the wing and the ventral fairing of the aircraft, the pressure coefficient on the side of certain parts of the upper surface of the wings can be very negative, which is representative of a strong depression, so that any vibrations of the li-

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 bre of the elastic end lip could, at these locations, have a large amplitude. It is therefore advantageous to apply the seal in accordance with the present invention at least with respect to said upper surface portions to which the value of the pressure coefficient is strongly negative.

 Of course, the present invention also relates to such an elongated seal for aircraft, the additional longitudinal sealing member of which is a radially elastic bead.

 In addition, the internal face of the free end of said end lip may comprise, at least on a part of said seal, at least one abutment boss, capable of holding said end lip locally spaced from the fuselage or from the airfoil, respectively, to provide a controlled leakage of air capable of passing through said first and second slots.

 To both ensure a good presentation of said radially elastic bead when installing the seal and a good seal of said bead after installation, it is preferable that the stiffness of said radially elastic bead is greater on the side of the internal face of said seal that on the side of the free part of said bead capable of being applied, against said fuselage or the wing.

 To this end, in particular, it is advantageous for said radially elastic bead to be tubular. In this case, in order to ensure correct support of said bead against the fuselage or the wing, it may be advantageous for the two lateral parts of said tubular bead, respectively joining the internal face of said joint to the free part of said bead capable of apply against said fuselage or the wing, have different stiffnesses.

 Such variations in stiffness can be obtained by variations in the constituent material or by variations in thickness of the wall of said tubular bead, these variations in thickness being able themselves

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 result from the mutual eccentricity and / or ovalization of the internal passage of the tubular bead relative to the wall thereof.

 In a first embodiment, the seal according to the present invention comprises a flat longitudinal part intended for fixing said seal to said ventral fairing and this flat longitudinal fixing part is arranged at the end of said seal opposite to said longitudinal elastic lip d end, said radially elastic bead being in an intermediate position between said longitudinal elastic end lip and said flat longitudinal fixing part. Such a seal is particularly suitable for closing said second slot between said ventral fairing and the airfoil.

 As a variant, according to a second embodiment, the seal according to the present invention also comprises a flat longitudinal part intended for fixing said seal to said ventral fairing, but this flat longitudinal fixing part is disposed in an intermediate position between said lip. longitudinal elastic end and said radially elastic bead. The seal according to the invention is then particularly suitable for closing said first slot between the ventral fairing and the fuselage.

 Whatever its embodiment, it is advantageous that the seal according to the present invention comprises a longitudinal recess in the form of a blade, formed in the external face of said flat longitudinal fixing part and serving as a housing at the corresponding peripheral edge of said fairing. ventral.

 Preferably, the joint of the invention is produced, by extrusion or by molding, in the form of a profile or of a closed monolithic loop, for example in an elastomer reinforced with fibers.

 The figures of the appended drawing will make it clear how the invention can be implemented. In these figures, identical references

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 denote similar elements.

 Figure 1 is a schematic perspective view from below of an aircraft provided with a ventral fairing.

 Figure 2 is a schematic perspective view from above of said ventral fairing, separated from said aircraft and purified from the internal elements that compose it.

 Figure 3 is a schematic side view, on a larger scale, of the ventral fairing mounted on the aircraft and crossed by a wing, before fitting the seal according to the present invention.

 Figure 4 is an enlarged partial schematic sectional view along the line IV-IV of Figure 3, before fitting the seal according to the present invention.

 Figures 5 to 9 illustrate, in enlarged schematic cross section, five embodiments of the seal according to the present invention.

 FIG. 10 shows, in enlarged schematic cross-section, the seal of FIG. 6, installed on the ventral fairing to close the slot between the latter and a wing of the aircraft.

 FIG. 11 represents, in enlarged schematic cross-section, the joint of FIG. 7, installed on the ventral fairing to close the slot between the latter and the fuselage of the aircraft.

 Figure 1 2 shows in perspective from above the seal according to the invention shown in Figures 6 and 10, but not yet attached to the ventral fairing.

 FIG. 13 corresponds to a front view according to arrow XIII in FIG. 10.

 The aircraft 1 shown schematically in FIG. 1 comprises, in a known manner, a fuselage 2, a fixed wing 3 comprising two wings 4 and 5 opposite with respect to said fuselage 2, a ventral fairing 6 in

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 form of cradle which is fixed to the lower part of said fuselage 2, at the crossing of the latter with said wing 3, and which projects downward relative to the belly of said aircraft. Such a cradle has two longitudinal edges 7 and 8 rising laterally along said fuselage 2 (see also Figure 2), said edges 7 and 8 being each provided with an opening 9 or 1 0 for the passage of the wing. 4 or 5 corresponding.

 After fixing the ventral fairing 6 on the fuselage 2, there is: - a peripheral slot 11 around each wing 4 or 5 between the latter and the periphery 12 or 13 of the opening 9 or 10, as illustrated in the Figure 3; and a peripheral slot 14 around said ventral fairing 6 between the periphery 1 5 of the latter and the fuselage 2, as illustrated in FIG. 4.

 The object of the present invention is an elongated seal 16, possibly forming a closed loop, for example made of reinforced elastomer and intended to be fixed to the periphery 1 2, 1 3 of each opening 9, 10 and to the periphery 15 of the ventral fairing 6, for closing said peripheral slots 11 and 14.

 In FIGS. 5 to 9, there are illustrated in section five exemplary embodiments 16. 1 to 16. 5 of the seal 16. As can be seen in these figures, whatever the embodiment 16.1 to 16.5, the seal 16 comprises: - a longitudinal elastic end lip 17, forming one of the longitudinal edges of said seal, said lip 17 being able, as illustrated by FIGS. 10 and 11, to be applied by the internal face 18 of its free end against the wing 3,4, 5 or against the fuselage 2; a radially elastic bead 19, carried by the internal face 20 of the seal 16 recessed with respect to the end lip 17 and also capable of being applied against the fuselage 2 or the airfoil 3 by flattening out and

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 by offering a large bearing surface (see Figures 10 and 11) and therefore excellent sealing; and - a flat longitudinal part 21 intended for fixing the seal 16 to the ventral fairing 6.

 It will be noted that, in the exemplary embodiments 16. 1 and 16.2, said fixing part 21 forms the edge of said seal opposite the lip 17, the bead 19 then being in an intermediate position between the latter and said fixing part 21. On the other hand, in the exemplary embodiments 16. 3, 16.4 and 16.5, said fixing part 21 is arranged in an intermediate position between the lip 17 and the bead 19.

 Furthermore, on its external face, said fixing part 21 has a longitudinal recess in the form of a blade 22, capable of serving as a housing at the corresponding peripheral edge 12, 13 or 15 of the ventral fairing 6.

The fixing of the seal 1 6 on the ventral fairing 6 is obtained by screws or the like 23 passing through said peripheral edge 12, 13, 1 5 and said fixing part 21 (see FIGS. 10 and 11).

 In the embodiments 16.2 and 16.5 shown in FIGS. 6 and 9, the internal face 18 of the lip 17 has spaced-apart abutment bosses 24, intended to be positioned facing at least part of the fuselage 2 or of the airfoil 3. Such bosses 24 keep the end edge 25 of the lip 17 locally spaced from the fuselage 2 or from the airfoil 3 in order to provide spaces 26, organizing a controlled and calibrated leakage of the air passing through the slots 11 or 14, in the event of possible leakage of the bead 19 (see FIG. 13).

 Since the pressure coefficient on certain parts of the upper surface of the wing 3 can take strongly negative values, it is on the side of these parts that it is advantageous to apply such a seal.

Thus, when the air pressure between the lower surface and the upper surface of the airfoil 3 reaches a value high enough to take off the bead 19,

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 the air passes between it and the fuselage and / or the wing, respectively, and this results in a leak which is calibrated and controlled by the spaces 26. The height of the abutment bosses 24, their number and their distribution along of the free end 25 are determined so that the flow rate of the air leakage through the spaces 26 generates little parasitic drag, while ensuring a low level of vibrations for the lip 17.

 To ensure a good presentation of the bead 1 9 facing the fuselage 2 or of the airfoil 3 during the installation of said bead in said slots 11 and 14, it is advantageous that said bead has a relatively high stiffness in the vicinity of the internal face 20 of the seal 16. On the other hand, to ensure good sealing, the free part 27 of said bead intended to come to bear against the fuselage 2 or the wing 3 is relatively flexible.

 In order to be able to adjust these stiffness difference requirements, it is preferable for the bead 19, which however could be full, to be tubular with an internal passage 28.

 Thus, by playing on the shape and / or the eccentricity of said internal passage 28, it is easy to locally vary the thickness of the wall of the tubular bead 19, and therefore the stiffness of the latter, as illustrated in the Figures 5 to 9.

 For example, to further improve the presentation of the bead 19 during installation and the seal provided by the latter, the two lateral parts 29 and 30 of said bead 19, respectively joining the internal face 20 of the seal 16 to the free part 27 of the bead, have different stiffnesses.

 It will easily be understood that the seal 16 according to the present invention can have either the shape of a strip (profile) or that of a closed loop.

Claims (12)

1. Aircraft (1) comprising: - a fuselage (2) and a fixed wing (3) comprising two wings (4,5) opposite with respect to said fuselage (2); - a ventral fairing (6) in the form of a cradle, fixed with clearance to the lower part of said fuselage (2), at the crossing of the latter with said wing (3) and provided with two longitudinal edges (7,8) going up the literally along said fuselage (2), said longitudinal edges being each provided with an opening (9,10) for the passage with clearance of the corresponding wing (4,5), so that are formed:. a first peripheral slot (14) around said ventral fairing (6), between the latter and said fuselage (2); and. a second peripheral slot (11) around each wing (4,5), between the latter and the periphery (12, 13) of the corresponding opening (9,10); and - an elongated seal (16), fixed at the periphery of said ventral fairing and at the periphery of each opening, for closing said first and second slots (14, 11), respectively, said seal comprising:. a longitudinal elastic end lip (17) adapted to be applied, by the internal face (18) of its free end, respectively against said fuselage (2) or said wing (3); and. an additional longitudinal sealing member, carried by the internal face (20) of said seal (16) set back relative to said end lip (17) and also capable of being applied against said fuselage (2) or said wing (3), respectively, characterized in that said additional longitudinal sealing member is a radially elastic bead (19).
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 2. Aircraft according to claim 1, characterized in that said internal face (18) of the free end of said end lip (17) comprises, at least on a part of said seal, at least one stop boss, suitable maintaining said end lip (17) locally spaced from the fuselage (2) or from the airfoil (3), respectively, to provide a controlled leakage of air capable of passing through said first and second slots (14,11 ), in the event of a possible leak in said bead (19).
 3. Aircraft according to claim 2, characterized in that said seal (16) is applied at least on the side of the parts of the upper surface, to which the value of the pressure coefficient is strongly negative.
 4. Joint (16) for an aircraft (1) comprising: - a fuselage (2) and a fixed wing (3) comprising two wings (4,5) opposite with respect to said fuselage (2); and - a ventral fairing (6) in the form of a cradle, fixed with clearance to the lower part of said fuselage (2), at the crossing of the latter with said wing (3) and provided with two longitudinal edges (7,8) going up the - In general along said fuselage (2), said longitudinal edges being each provided with an opening (9,10) for the passage with clearance of the corresponding wing (4,5), so that are formed:. a first peripheral slot (14) around said ventral fairing (6), between the latter and said fuselage (2); and. a second peripheral slot (11) around each wing (4,5), between the latter and the periphery (12,13) of the corresponding opening (9,10), said seal (16) being elongated and being fixed to the periphery of said ventral fairing and to the periphery of each opening, for closing said pre-
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 first and second slots (14, 11), respectively, said seal (16) comprising: - a longitudinal elastic end lip (17) capable of being applied, by the internal face (18) of its free end, respectively against said fuselage (2) or said wing (3); and - an additional longitudinal sealing member, carried by the internal face (20) of said seal (16) set back relative to said end lip (17) and also capable of being applied against said fuselage (2 ) or said wing (3), respectively, characterized in that said additional longitudinal sealing member is a radially elastic bead (19).
 5. Joint for aircraft according to claim 4, characterized in that said internal face (18) of the free end of said end lip (17) comprises, at least on a part of said joint, at least one stop boss (24), capable of holding said end lip (17) locally spaced from the fuselage (2) or from the airfoil (3), respectively, to provide a controlled leak (26) of air capable of passing through said first and second slots (14, 11), in the event of a possible leak in said bead (19).
 6. Joint for aircraft according to one of claims 4 or 5, characterized in that said bead (19) is tubular.
 7. Seal for aircraft according to one of claims 4 to 6, characterized in that the stiffness of said radially elastic bead (19) is greater on the side of the internal face (20) of said seal (16) than on the side of the free part (27) of said bead (19) capable of being applied against said fuselage (2) or the airfoil (3).
 8. Joint for aircraft according to claim 6, characterized in that the two lateral parts (29,30) of said tubular bead (19), respectively joining the internal face (20) of said joint (16)
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 at the free part (27) of said bead adapted to be applied against said fuselage (2) or the airfoil (3), have different stiffnesses.
 9. Joint for aircraft according to one of claims 7 or 8, characterized in that the variations in stiffness of said radially elastic bead (1 9) are obtained by variations in thickness of the wall of said bead.
 10. Joint for aircraft according to one of claims 4 to 9, characterized in that it comprises a flat longitudinal part (21) intended for fixing said joint (16) to said ventral fairing (6) and in that said part longitudinal fixing plate (21) is disposed at the end of said seal (16) opposite said longitudinal elastic end lip (17), said radially elastic bead (19) being in intermediate position between said longitudinal elastic lip of end and said flat longitudinal fixing part.
 11. Joint for aircraft according to one of claims 4 to 9, characterized in that it comprises a flat longitudinal part (21) intended for fixing said joint (16) to said ventral fairing (6) and in that said part longitudinal fixing plate (21) is arranged in an intermediate position between said elastic longitudinal end lip (17) and said radially elastic bead (19).
 12. Joint for aircraft according to one of claims 10 or 11, characterized in that it comprises a longitudinal recess in the form of a blade (22) formed in the external face of said flat longitudinal fixing part (21) and serving as housing at the corresponding peripheral edge (13, 15) of said ventral fairing (6).
FR0112829A 2001-07-06 2001-10-05 Aircraft with ventral fairing and joint for such an aircraft Expired - Fee Related FR2827029B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR0108982A FR2827028B1 (en) 2001-07-06 2001-07-06 Aircraft with ventral carenage and joint for such an aircraft
FR0112829A FR2827029B1 (en) 2001-07-06 2001-10-05 Aircraft with ventral fairing and joint for such an aircraft

Applications Claiming Priority (7)

Application Number Priority Date Filing Date Title
FR0112829A FR2827029B1 (en) 2001-07-06 2001-10-05 Aircraft with ventral fairing and joint for such an aircraft
EP20020291941 EP1300335B1 (en) 2001-10-05 2002-08-01 Aircraft with belly fairing seal
DE2002603078 DE60203078T2 (en) 2001-10-05 2002-08-01 Airplane with wing hull siding gasket
ES02291941T ES2237655T3 (en) 2001-10-05 2002-08-01 Aircraft with ventral carenado.
US10/212,065 US6655635B2 (en) 2001-10-05 2002-08-06 Aircraft with ventral fairing and seal for such an aircraft
CA 2397190 CA2397190C (en) 2001-10-05 2002-08-08 Aircraft having a belly fairing, and seal joint for such aircraft
BR0203556A BR0203556B1 (en) 2001-10-05 2002-08-30 aircraft with ventral fairing and joint to it.

Publications (2)

Publication Number Publication Date
FR2827029A1 true FR2827029A1 (en) 2003-01-10
FR2827029B1 FR2827029B1 (en) 2003-10-17

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Family Applications (1)

Application Number Title Priority Date Filing Date
FR0112829A Expired - Fee Related FR2827029B1 (en) 2001-07-06 2001-10-05 Aircraft with ventral fairing and joint for such an aircraft

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FR (1) FR2827029B1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1593594A1 (en) * 2004-05-04 2005-11-09 Airbus France Transition shim between a means for fastening a wing to a fuselage of an aircraft and the wing, and aircraft comprising such a shim
FR2892999A1 (en) * 2005-11-08 2007-05-11 Airbus France Sas Aircraft comprising a central carriage pressure adjuster vessel by local geometric deformations
FR2906853A1 (en) * 2006-10-10 2008-04-11 Airbus France Sas Peripheral seal fixation unit protecting device for e.g. during manufacturing of airplane, has chock intercalated between fixation unit end and aircraft fuselage, where chock has friction face with fuselage, and mounting face on nut
WO2011144836A2 (en) 2010-05-19 2011-11-24 Aircelle Aerodynamic element for an aircraft nacelle

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE694021C (en) * 1939-07-02 1940-07-24 Messerschmitt Ag Gap fairing for aircraft
US3756529A (en) * 1972-05-01 1973-09-04 Mc Donnell Douglas Corp Fuselage seal
US4034939A (en) * 1975-11-05 1977-07-12 The Boeing Company Assembly for sealing the mounting opening for a flying horizontal stabilizer on a vertical stabilizer
FR2569455A1 (en) * 1984-08-21 1986-02-28 Sueddeutsche Kuehler Behr Sealing profile for parallel housing part edges
US5114162A (en) * 1986-11-13 1992-05-19 A-Lok Products, Inc. Gasket for use in manhole bases and the like
DE4443525C1 (en) * 1994-12-07 1996-02-15 Daimler Benz Ag Roof arrangement to cover cut=out in motor vehicle roof
DE29713153U1 (en) * 1997-07-24 1997-09-18 Lehnen Hans Guenter Dipl Ing Pressure and joint seals for wall module construction systems
FR2789144A1 (en) * 1999-02-03 2000-08-04 Joint Francais Aircraft panel seal has internal reinforcing member with projections for joining to panel by fixings
FR2793538A1 (en) * 1999-05-11 2000-11-17 Joint Francais Joint seal for the sealing of closures for retractable undercarriage on aircraft has flexible hollow section sealing strip

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE694021C (en) * 1939-07-02 1940-07-24 Messerschmitt Ag Gap fairing for aircraft
US3756529A (en) * 1972-05-01 1973-09-04 Mc Donnell Douglas Corp Fuselage seal
US4034939A (en) * 1975-11-05 1977-07-12 The Boeing Company Assembly for sealing the mounting opening for a flying horizontal stabilizer on a vertical stabilizer
FR2569455A1 (en) * 1984-08-21 1986-02-28 Sueddeutsche Kuehler Behr Sealing profile for parallel housing part edges
US5114162A (en) * 1986-11-13 1992-05-19 A-Lok Products, Inc. Gasket for use in manhole bases and the like
DE4443525C1 (en) * 1994-12-07 1996-02-15 Daimler Benz Ag Roof arrangement to cover cut=out in motor vehicle roof
DE29713153U1 (en) * 1997-07-24 1997-09-18 Lehnen Hans Guenter Dipl Ing Pressure and joint seals for wall module construction systems
FR2789144A1 (en) * 1999-02-03 2000-08-04 Joint Francais Aircraft panel seal has internal reinforcing member with projections for joining to panel by fixings
FR2793538A1 (en) * 1999-05-11 2000-11-17 Joint Francais Joint seal for the sealing of closures for retractable undercarriage on aircraft has flexible hollow section sealing strip

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1593594A1 (en) * 2004-05-04 2005-11-09 Airbus France Transition shim between a means for fastening a wing to a fuselage of an aircraft and the wing, and aircraft comprising such a shim
FR2869872A1 (en) * 2004-05-04 2005-11-11 Airbus France Sas A transitional shing between a means for fixing a wing on a fuselage of an aircraft and said wing, and an aircraft having such a shim.
US7607614B2 (en) 2004-05-04 2009-10-27 Airbus France Transition shim between structure for fastening a wing to a fuselage of an aircraft, and aircraft having such a shim
FR2892999A1 (en) * 2005-11-08 2007-05-11 Airbus France Sas Aircraft comprising a central carriage pressure adjuster vessel by local geometric deformations
WO2007054635A1 (en) * 2005-11-08 2007-05-18 Airbus France Aircraft comprising a central fairing that adjusts the pressure on the wing structures by means of local geometric deformations
US8177170B2 (en) 2005-11-08 2012-05-15 Airbus Operations Sas Aircraft comprising a central fairing that adjusts the pressure on the wing structures by means of local geometric deformations
FR2906853A1 (en) * 2006-10-10 2008-04-11 Airbus France Sas Peripheral seal fixation unit protecting device for e.g. during manufacturing of airplane, has chock intercalated between fixation unit end and aircraft fuselage, where chock has friction face with fuselage, and mounting face on nut
WO2011144836A2 (en) 2010-05-19 2011-11-24 Aircelle Aerodynamic element for an aircraft nacelle
FR2960216A1 (en) * 2010-05-19 2011-11-25 Aircelle Sa Aerodynamic element for an aircraft nacelle
WO2011144836A3 (en) * 2010-05-19 2012-01-05 Aircelle Aerodynamic element for an aircraft nacelle
US8939713B2 (en) 2010-05-19 2015-01-27 Aircelle Aerodynamic element for an aircraft nacelle
RU2571981C2 (en) * 2010-05-19 2015-12-27 Эрсель Aerodynamic element for aircraft nacelle

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