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
  • B64D29/00—Power-plant nacelles, fairings, or cowlings
  • B64D29/06—Attaching of nacelles, fairings or cowlings
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/04—Mounting of an exhaust cone in the jet pipe
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
  • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
  • F16B2200/00—Constructional details of connections not covered for in other groups of this subclass
  • F16B2200/50—Flanged connections
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
  • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
  • F16B2200/00—Constructional details of connections not covered for in other groups of this subclass
  • F16B2200/50—Flanged connections
  • F16B2200/509—Flanged connections clamped
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
  • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
  • F16L23/00—Flanged joints

Definitions

• the present invention relates to an assembly for maintaining the interface of a turbojet casing and the structure of an inverter of a nacelle surrounding said turbojet engine.
• the present invention also relates to a propulsion assembly comprising such a holding assembly.
• An aircraft is generally driven by a propulsion unit comprising a turbojet engine surrounded by a nacelle.
• the turbojet engine has upstream fan blades driven by a motor. Blower blades are surrounded by a housing for mounting said turbojet engine in the nacelle.
• the blower of the turbojet engine essentially consists of a rotary shaft carrying a plurality of blades. At their radial end, the blades are surrounded circumferentially by a housing.
• Blower housings are generally machined metal elements.
• the turbojet may be a turbofan engine capable of generating a hot air flow (also called primary flow) from the turbojet engine combustion chamber, and a cold air flow (secondary flow) from the circulating fan.
• a hot air flow also called primary flow
• secondary flow cold air flow from the circulating fan.
• an nu the ire also called "vein”
• fo rm é be a ca re n ag turbojet engine and an inner wall of the nacelle.
• the two primary and secondary streams mix.
• This nacelle is generally equipped with a thrust reverser.
• the thrust reverser during the landing of an aircraft improves the braking capacity of the aircraft by redirecting forward at least a portion of the thrust generated by the turbojet engine.
• the inverter obstructs the gas ejection nozzle and directs the ejection flow of the engine towards the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the engine. the plane.
• a nacelle generally has a structure comprising an air inlet upstream of the engine, a median structure intended to surround the turbojet engine housing, and a downstream structure comprising a fixed internal structure (“IFS”) and a fixed external structure (“OFS”) intended to surround the combustion chamber of the turbojet and housing thrust reversal means.
• IFS fixed internal structure
• OFS fixed external structure
• the thrust reverser means are varied and may be in the form of at least one movable cowl, its "thrust reversing cowls", moving in translation thanks to actuators in a direction substantially parallel to an axis longitudinal of the nacelle.
• the upstream part of the downstream structure in particular the fixed external structure, is connected at the downstream end of the fan casing of the turbojet engine.
• the structure of the inverter is generally made in two half parts articulated in the upper part on the pylon, called "D-duct" structure.
• D-duct structure
• the maintenance between the casing and the fixed external structure is achieved by a male part, generally carried by the fixed external structure, cooperating in a female part, generally carried by the casing.
• the downstream structure may also be in the form of a single-piece external assembly without a break in structural continuity, called an "O-duct" structure.
• This external assembly is dissociated from the internal structure surrounding the motor and is actuated to give access to the body of the engine by a rectilinear displacement towards the rear of the nacelle beyond the setback value necessary for the thrust reversal .
• the maintenance of the fixed external structure and the casing can not be done in the same way as the maintenance of the "D-duct" structures.
• An object of the present invention is therefore to provide a holding assembly for uniformly distributed maintenance on the circumference of the housing interface and the fixed external structure, to reduce the maintenance time, to facilitate it and to limit the number of parts needed and the cost.
• the invention relates to an assembly for maintaining the interface of a fixed external structure of a nacelle and a turbojet casing, comprising:
• said first and second relief elements being configured to be brought into contact with each other;
• two half-rings formed by a wall defining a housing, configured to receive the first and second elements in relief when the housing and the external fixed structure are mounted edge to edge, and stop means configured to maintain the first and second relief elements in the dwelling.
• the holding assembly of the invention thus makes it possible to connect, by the half-rings, the downstream end of the casing and the upstream end of the fixed external structure of the downstream structure housing the thrust reversal means.
• the holding assembly of the invention thus makes it possible to lock and unlock the interface of the housing and the fixed external structure in a simple, efficient, fast manner involving few parts. Maintenance time and cost are reduced and controlled.
• the support is uniformly distributed over the circumference of the interface.
• the holding assembly of the invention comprises one or more of the following optional features considered alone or according to all the possible combinations:
• the wall forms a housing of substantially U-shaped or V-shaped cross section
• At least one raised element has a ramp configured to cooperate with at least one side edge of the wall which has an inclined surface complementary to the ramp when said raised element is inserted into the housing which allows a slight misalignment of the two elements in relief before closing the half-ring;
• At least one raised element comprises a sealing means so as to ensure the seal between the first element in relief and the second element in relief when they are received in the housing which makes it possible to avoid any leakage of the flow cold air and hot air flow so as not to generate a disturbance on the performance of the propulsion system of the invention;
• the element or elements in relief comprise a transverse centering means relative to the longitudinal axis of the nacelle which makes it possible to facilitate the closure of the casing and of the fixed external structure without making the holding assembly of the invention heavier;
• To the e ns und em i-ring comprises a lever means for facilitating the passage of the locking position in which the two raised elements are received in the housing in the unlocked position in which the relief elements are out of the housing;
• the lever means is an outgrowth configured to be attached to the end of a half-ring and to bear on at least one fixed surface;
• the two half-rings are fixed to one another by fastening means, which makes it possible to ensure the effort of clamping and holding the elements in relief;
• the fastening means comprise at least one bolt or at least one three-point hook latch
• At least one half-ring comprises a polarizer in order to avoid locking said half-ring without the elements in relief;
• At least one half-ring is formed of a multitude of parts in order to adapt the flexibility or the rigidity of the half-ring;
• the part comprising the housing is made of several sectors fixed to each other by fixing means, which advantageously makes it possible to lift the half-ring on parts with a small clearance; at least one sector is mounted articulately on the next;
• the articulation of the sector is associated with one or two levers mounted on either side of said sector to facilitate the unlocking of the sector;
• At least one half-ring comprises holding means configured to support said half-ring in the unlocking position
• the holding means is in the form of a connecting rod fixed on said half-ring and on a support fixed on the casing or on the fixed external structure;
• each half-ring is mounted articulated at substantially 12 o'clock of the external fixed structure.
• the subject of the invention is a propulsion unit comprising a turbojet engine housed in a nacelle adapted to be connected to the aircraft by an attachment pylon, the turbojet engine comprising fan blades surrounded by a crankcase mounted on board. on board with a fixed external structure of the downstream structure of the nacelle which houses thrust reversal means, said propulsion unit comprising a holding assembly of the invention.
• the propulsion unit of the invention comprises one or more of the following optional features considered alone or according to all the possible combinations:
• At least one half-ring is mounted at substantially 12 o'clock of the nacelle, which makes it possible to have the largest possible clearance and to facilitate access to the turbojet engine;
• At least one half-ring is articulated on the attachment pylon or on the casing by means of a fixed pivot;
• a connecting rod connecting the pivot points arranged on each side of the attachment pylon ensures the fixing of the half-rings between them in order to ensure continuity of peripheral loading
• At least one half-ring is mounted on the upstream cover to the fixed external structure
• the half-rings are carried by the upstream cover with play which helps the proper operation and avoids interfacing problems due to the hyperstaticity between the fixed outer structure and the housing;
• At least one half-ring is connected to the cover by means of a partition or a fitting configured to receive a half-ring.
• FIG. 1 is a longitudinal section of a propulsion system of the invention
• FIG. 2 is a perspective view of said propulsion assembly of FIG. 1;
• FIG. 3 is a perspective view of an embodiment of a holding assembly of the invention.
• FIGS. 4 to 7 are cross sections of variants of the embodiment of FIG. 3;
• FIG. 8 is a perspective view of an embodiment of the attachment of the half-rings of the assembly of the invention.
• Figures 9 to 14 are side views of variants of the embodiment of Figure 8;
• FIGS. 15 and 16 are side views of two half-ring attachment embodiments of the holding assembly of the invention to each other;
• FIG. 17 is a cross-section of an embodiment of the holding assembly of the invention.
• FIGS. 18 to 21 are perspective side views of embodiments of a semiconductor of the invention.
• FIGS. 22 and 23 are side perspective views of a variant of the holding assembly of the invention.
• FIG. 24 is a front perspective view of a variant of the holding assembly of the invention mounted on the propulsion unit;
• FIG. 25 is an enlargement of zone XXV of FIG.
• FIGS. 26 to 28 are cross sections of a half ring of the holding assembly of the invention mounted on the hood of the fixed outer structure of the propulsion system of the invention;
• Fig. 29 is an enlargement of the XXIX area of the embodiment of Fig. 28;
• FIGS. 30 to 31 are perspective views of variants of attachment of a half-ring of the holding assembly of the invention.
• the propulsion unit 1 of the invention comprises a nacelle 3 surrounding a turbojet engine 5 which both have an axis of revolution or main longitudinal axis 6.
• the nacelle 3 typically comprises a structure 7, a median structure 9 surrounding the blades of a fan 1 1 of the turbojet engine 5, and a downstream structure 13.
• the downstream structure 13 comprises, in a manner known per se, a structure external re 15, OFS dice, housing thrust reversal means 17, and an internal structure 19, called IFS.
• the thrust reversal means are here in the form of a movable cowl 21 in longitudinal translation downstream of the nacelle 3 and a fixed grid 23 through which the flow of cold air is deflected.
• the nacelle 3 is attached downstream via any appropriate means, including connecting rods, to a suspension mast, not shown in Figure 1, for the attachment of the nacelle 3 under an aircraft wing.
• the fixed outer structure 15 and the fixed inner structure 19 also define an annular flow channel 25 through which the cold air flow is intended to flow.
• the fixed internal structure 19 is intended to cover a downstream portion of the turbojet engine extending downstream of the blades of the fan 1 1.
• the fan blades 1 1 of the turbojet engine are circumferentially surmounted by a casing 27.
• the casing 27 is intended to be attached to the fixed external structure 1 5 of the struc ture ava l. More particularly, the upstream end of the casing 27 is configured to be connected to the downstream end of the fixed outer structure 15. In this case, the casing 27 and the fixed outer structure 15 are said to be "edge-to-edge".
• a holding assembly 101 maintains and locks the outer structure 15 and the housing 27.
• the assembly of the invention 101 comprises:
• said first 105 and second 107 relievable elements being configured to be brought into contact with each other;
• two half-rings 109 formed by a wall defining a housing 1 January 1, configured to receive the first 105 and the second 107 elements in rel ief when the housing 27 and the external fixed structure 1 5 are mounted edge to edge, and stop means 1 13 configured to maintain the first 105 and second 107 elements in the housing 1 1 1.
• the holding assembly of the invention 101 makes it possible to connect the interface of the downstream end of the casing 27 and the upstream end of the fixed external structure 15 by the half-rings 109.
• the support is uniformly distributed over the circumference of the interface.
• the holding assembly of the invention 101 also allows to lock and unlock this interface in a simple, effective, fast and involving few parts.
• the maintenance time, the costs and the mass are reduced and controlled compared to the prior art.
• to lock or unlock the holding assembly it is sufficient to translate the casing 27 and the fixed external structure 1 5 long itud inally relative to the longitudinal axis and then rotate each half-ring 109 on the raised elements 105 and 107 placed opposite or respectively to disengage by pivoting said half-ring 109 out of the raised elements 105 and 107. Therefore, it is useless to disjoin a male part of a female part or to remove point means for disengaging the casing 27 and the fixed external structure 15.
• the abutment means 1 13 advantageously allow to maintain in the housing 1 1 1 the two raised elements 105 and 107.
• the "locking position” is defined as the position of the holding assembly of the invention 101 in which the two raised elements 105 and 107 belonging to the casing 27 and to the fixed external structure 15 are received in the housing 1 1 1 at least one half-ring 109.
• the "unlocking position” or “maintenance position” is defined as the position of the holding assembly of the invention 101 in which the two raised elements 105 and 107 belonging to the casing 27 and to the fixed external structure 15 are out of the housing 1 1 1 of at least one half-ring 109.
• each half-ring 109 thus defines the housing 1 1 1 and abutment means 1 1 3.
• the abutment means 1 13 are for example formed by the lateral extension of the wall defining the housing 1 1 1.
• At least one, or both, half-ring 1 09 may be a double knife, namely the wall forms a housing 1 January 1 of cup-shaped cross section, in particular of substantially V-shaped cross section or U.
• the relief elements 105 and 107 are in the form of flange normal or transverse to the longitudinal axis 6 of the nacelle 3.
• the raised elements 105 and 107 may be of continuous structure to ensure a uniform load distribution on said relief elements 105 and 107.
• the wall forming the housing 111 and the abutment means 113 of the half-ring 109 are not in contact with the opposite surface, namely not facing each other, of said elements 105 and 107 which defines a clearance 115 and 117.
• the clearance 115 and / or 117 makes it possible to limit the transverse and / or longitudinal displacement of the raised elements 105 and 107.
• the clearance 115 may therefore be longitudinal, namely along the principal longitudinal axis 6 of the nacelle or transverse 117, namely along an axis perpendicular to the main axis 6.
• At least one raised element 105 or 107 may have a ramp 121 configured to cooperate with at least one side edge of the wall which has an inclined surface 123 complementary to the ramp 121 when said raised element 105 or 107 is inserted into the housing 111 which allows a slight misalignment of the two relief elements 105 and 107 before the closure of the half-ring 109.
• the two elements 105 and 107 have their non-facing walls having such a ramp 121.
• the side edges of the wall 113 comprises each an inclined surface 123 on which a ramp 121 is able to slide.
• the ramp 121 slides on the inclined surface 123 until the relief elements 105 and 107 are introduced into the housing 1 1 1.
• the ramp 121 may have an angle less than or equal to about 30 °.
• At least one releive element 105 may comprise a sealing means 131 so as to seal between the first raised element 105 and the second raised element 107 when they are housed in the housing 1 1 1 which prevents any leakage of the cold air flow and hot air flow so as not to generate a disturbance on the performance of the propulsion unit 1 of the invention.
• the sealing means 131 may be in the form of a seal housed in the housing 133 formed in one of the raised elements 105.
• the element or elements in rel ief 105 and 107 may include a centering means transverse to the longitudinal axis 6 of the nacelle 3 which facilitates the closure of the housing 27 and the fixed external structure 15 without weighing down the holding assembly of the invention 101.
• a centering means makes it possible to limit the forces generated by the bursting of a light fan 11 which tends to desalign and separate the casing 27 and the fixed external structure 15.
• the centering means may be in the form of a protrusion 151 belonging to the housing 27 configured to fit into a recess 153 formed in the fixed external structure 15 (see FIG. 7).
• any rotational force caused by the rotation of the unbalanced blower can be absorbed.
• each half-ring 1 09 only supports the axial forces.
• At least one, or both, half-ring 109 may comprise a lever means 161 for facilitating the locking and unlocking of said half-ring 109 on the relief elements 105 and 107 (see Figures 8 to 14).
• the lever means makes it possible to reduce the angular displacement of said half-ring 109.
• a half-ring 1 09 is articulated by virtue of a pivot at 12 o'clock of the nacel 1, namely close to or on when the latter is seen by the entrance of the platform 3, it is sometimes impossible to open a half-ring 1 09 in a manner sufficient to disengage the casing 27 and the fixed external structure 15.
• the lever system 1 61 makes it possible to provide clearance for the housing 27 and the ladle fixed external structure 1 5 with a low pivot angle, ie less than 15 °.
• the lever system 1 61 can be mounted upstream of the pivot point of the half-rings 109.
• the lever means may be a protuberance 161 configured to be attached to the half-ring 1 09, in particular at one end, and to bear on at least one inner surface 165 of the support 163 of each half-ring 109.
• the lever means 161 in position locking means, is not in contact with the housing 27, the fixed external structure 1 5 or the support 163 of said ring 109 so as not to generate stray force.
• the half-ring 1 09 is displaced by a small angle, less than 15 °, so as to disengage said elements 1 05 and 107.
• the protrusion 161 comes into contact with the surface 1 65 of the support, which has the effect of effecting an oblique effect of this emi-annle ledger 1 09 to completely disengage said raised elements 105 and 107.
• the support 165 on which the lever means 1 61 is based is disposed on the "lower" surface, namely the closest to the housing interface 27 and the fixed external structure 15.
• the support 167 on which the lever means 1 61 is based is located on the "upper" surface, namely the most distant from the housing interface 27 and the fixed external structure 15. This configuration allows assistance in the embedment of the half-ring 109 on the relief elements 105 and 107.
• the lever means may comprise two protuberances 61 a and 61 b connected to each other and each configured to bear on the lower surface and on the upper surface.
• the two half-rings 109 can be fastened to each other by fastening means, which makes it possible to ensure the clamping and holding force of the raised elements 105 and 107.
• a centering element radial can be added either by adding a centering pin or by integrating complementary shapes in one and the other ends of the half-rings.
• the two half-rings 109 can advantageously meet in position 6h relative to the platform 3 in front view.
• the fastening means of said half-rings 109 are located in this position 6h.
• the locking of the two half-rings 109 can be realized under tension, in particular not mechanical and manual fixing means.
• the fastening means may comprise at least one bolt 171 (see FIG. 15) which makes it possible to lock the two half-rings 109 in a simple and inexpensive manner.
• the free end of a half-a nn ea u 1 09 may comprise two walls 173 substantially perpendicular to the remainder of the half-rings, in other words going in the radial direction transverse to the longitudinal axis 3 of the nacelle 3. Said two walls are then vis-à-vis when the two demi-rings 1 09 are in the locking position.
• the bolt 171 may be associated with a nut passing through the two walls 733 in order to maintain the locking.
• the interface of the two walls 173 can be made with a clearance 175 after tightening the bolt 171 which is made so as to ensure the holding force of the two rings 1 09 between them.
• the fastening means comprise at least one three-point hook latch 181 which makes it possible to have a permanent lock on the half-ring 109.
• one of the half-rings 109 supports the part of the latch comprising the hook 183 and the other half-ring 109 supports the part comprising the retaining member 1 85 dud it c roc h and 1 87.
• the retainer 185 may be adjustable so as to allow adjustment of the locking voltage generated by the cooperation of the hook 1 87 and the retaining member 1 85 when the two half-rings 109 are in the locking position.
• the contact of the half-rings 109 in the locking position is made in a plane substantially close to the alignment of the three-point latch 181.
• the abutment of the half-rings may be identical to that of the previous configuration.
• a three-point latch 181 may have some of its components doubled in order to improve the reliability of said latch 181.
• the pivot of the hook 187 can be doubled by the presence of two concentric pivots of the same axis placed one inside the other.
• the fixing means may be supported by a monobloc and damage-tolerant encircling structure which can also support the half-ring 109.
• a first sideband may overlap on one side of the housing receiving a first relief element 105 and a second sideband overlapping the other relief element 107.
• the strips laterals can come together in a position substantially 12h of the nacelle 3.
• At least one half-ring 1 09 may comprise a polarizer 191 in order to avoid closing and locking led dem i-ring 109 without the relief elements 1 05 and 1 07, namely without the two elements in relief 1 05 and 1 07 are received in the housing 1 1 1.
• the polarizer 191 may be in the form of a longitudinal extension 191 of one of the walls of the abutment means 1 13 (see Figure 1 7). In this way, this extension 191 abuts against the raised element 1 05 of the fixed external structure or housing. According to a va ri a nte, the polarizer 191 can be s usla fo rm ededeux longitudinal extensions of the walls of the abutment means 1 13. In addition, such a polarizer is seen by the operator who then finds that one of the elements in relief 105 and 107 is not received in the housing 1 1 1 of the half-ring 109.
• the polarizer 191 may be local, multiple or continuous. In other words, the polarizer 191 may extend over all or part of the periphery of the half-ring 109 in one or more sectors.
• At least one, or both, half-ring 1 09 can be realisé form monobloc or formed of a multitude of parts to adapt the flexibility or rigidity of the half-ring 1 09.
• a half -anneau 1 09 is made of several parts, it is possible to add a substantially annular reinforcement means, in particular on the outer wall dud it dem i-ring 109.
• a half-ring 1 09 can be composed of two parts.
• the first part may comprise the articulation and the locking and the second part may comprise the housing 1 January 1 configured to receive the first 105 and second 107 elements in relief.
• the second part may be made in one piece or in several sectors, and / or in several materials, such as aluminum or titanium. In the case where the second part is made of several sectors, the sectors may be interconnected for example by rivets. It is preferable to lift the half-ring 1 09 on parts with a small deflection, in particular less than 10 °.
• each sector 201a, 201b can be hingedly mounted to the next, as shown in FIGS. 18-21.
• a sector 201a is connected to an adjacent sector 201b by an axis 203 enabling the sector 201a to pivot.
• the positioning configuration of the pivot is according to Figures 1 8 and 19 according to the position of the tensile force to bring the point of articulation in the appropriate plane.
• the sector 201a may contain a stop at the joint 205 to assist in opening the next sector.
• the articulation of the sector 201 is associated with one or two levers 21 1 mounted on either side of said sector 201 has to facilitate the unlocking and lifting the sector 201 a.
• the lever or levers 21 1 can bear on the casing 27 and / or on the fixed outer structure 15.
• the rotation of the first sector 201 has the contact of the lever 21 1 on the fixed surface of the housing 27 or the fixed external structure 1 5. With this contact, the second sector 201 b can also be raised to reach the unlocking position.
• At least one, or both, half-ring 109 may comprise a holding means configured to support said half-ring 109 in the unlocked position.
• the holding means may be in the form of a connecting rod 221 fastened to said half-ring 1 09 and to a support 223a and 223b fastened to the casing 27 or to the fixed external structure 15 , especially on one of the relief elements 105 or 107.
• the half-ring 109 may comprise openings 225 and 227 so as not to interfere with the supports fixed on one of the raised elements 105 and 1 07 when the half-ring 109 is in the locking position, namely housing the two Embossed elements 105 and 1 07.
• the support 223a and 223b may be composed of a first bracket 223a and a second bracket 223b, the first bracket configured to receive the pivoting end of the connecting rod 221 and the second fitting 223b can receive the end of the connecting rod 221 connected to the half-ring 109.
• the first fitting 223a and the second fitting 223b are arranged on the same side of the half-ring 109.
• the holding means may comprise a fitting 231 mounted in the cover 233 fixed external structure which allows not to achieve the clearance at the half-ring 109 and reduce the mass of said holding means.
• the cover 233 may be formed of two parts configured to be raised in the unlocking position and that i are fixed in the normal operating position in the 6 o'clock position of the platform 3.
• the fitting 231 is then placed downstream of the hood 233 and comprises a housing 235.
• On the half-year n water 1 09 is dpospose a su pport 237 having a rod 239 configured to cooperate with the housing 235.
• the assembly of the invention January 01 may comprise a means for detecting the position of the components of the assembly together, namely relief elements 1 05 and 1 07, half-rings 109.
• detection means can be used in the form of permanent electronic sensors, such as a proximity sensor.
• the assembly of the invention 101 may comprise means for detecting the locking voltage of the two half-rings 109.
• At least one half-ring 109 is connected to the hood of the fan 251, rigidly or otherwise, which is articulated substantially in part 12h of the pod 3.
• said fan cover 251 as a support for at least one or both half-rings 109.
• said half-ring 109 can be associated with the structure of the hood of the blower 251 rigidly, for example by means of a partition 253 (see Figure 26) or through fitting 255 in which the half-ring 109 is receivable (see Figures 27 and 28).
• said half-ring 1 09 is mounted in the fitting 255 so as to have a lateral play 257 which allows a better grip of the cover 251 during the release of the half-ring 109 .
• each half-ring 109 is mounted on the upper part of the external fixed structure 1 5 and therefore of the platform 3, which makes it possible to have the largest clearance possible and facilitate access to the turbojet engine 5.
• one or even both half-ring 1 09 can be articulatedly mounted substantially to 1 2h of the external fixed structure 1 5 and therefore of the nacelle 3.
• each half-ring 109 can be articulated on the attachment pylon 31 by means of a fixed pivot 261.
• a fitting (not shown) may be attached to the attachment mast 31.
• the axis of traction is defined here by an axis passing through a surface parallel to the surface to be clamped by which the circumferential locking forces transit.
• the half-ring (s) 109 can be fixed by means of a fitting on the casing 27, which makes it possible to contain the alignment of the half-rings 109 with respect to the interface of the casing 27 and the fixed external structure 15. It is possible to join the two fittings by a rigid internal structure to the latching mast 31 as close as possible to the axis of traction so as to avoid any effort of lever type generated by unlocking the dem i-ring 1 09 and secondly to ensure the integrity of peripheral charging.
• the fixed fittings of the preceding embodiments may be replaced by a connecting rod relying on the pivot points disposed on each side of the attachment pylon 31 in order to ensure continuity of peripheral loading.
• said connecting rod can be placed in a plane close to the traction axis.
• the connecting rod is "floating", ie mounted through the latching mast 31 so as not to generate additional force between the two half-rings 109 and to resume any differential movement between the fixed structure of the nacelle 3 and that of the turbojet engine 5.
• the floating link 301 can pass through a housing 302 formed in the support 303 of the half-ring 109 which is carried by the casing 27.
• the connecting rod 301 is not in contact with the walls of the housing 302.
• One end 309 of the connecting rod 171 can be configured to cooperate with the complementary part of the half-ring 109.
• the opposite end of the connecting rod 301 has two protuberances 31 1 and 313 configured to grip the free end 309 of the connecting rod 301.
• the two ends 309 and 31 1, 313 are fixed together for example by means of a rod or a bolt (not shown).
• the support 303 only undergoes the efforts of maintaining the half-ring in the maintenance position.
• the ends 31 1 and 31 3 may be in the form of hooks configured to grip a rod 321 of the end 309 of the rod 301.

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