• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The hatch (76) comprises: - an internal partition (70) sealing, intended to be mounted in a sealed manner on a structure of the aircraft; - a releasable locking assembly (76) of the inner partition (70) on the structure. The hatch (36) includes a pressure equalizing valve (88) between an inner surface of the inner partition (70) for placement in an interior volume of the aircraft and an outer surface of the inner partition (70). , intended to communicate with the outside of the aircraft. The valve (88) is movable by a user between a closed sealing position and an open pressure balancing position, the releasable locking assembly (76) being secured in a latching configuration when the valve (88) occupies its closed position of sealing.
    公开号:FR3046777A1
    申请号:FR1600069
    申请日:2016-01-14
    公开日:2017-07-21
    发明作者:Sandrine Viaud；Claude Fons
    申请人:Dassault Aviation SA；
    IPC主号:
    专利说明:

    Blanking hatch of an opening through the structure of an aircraft, structure, and associated method
    The present invention relates to a shutter opening of an opening through the structure of an aircraft, comprising: - an internal sealing wall, intended to be mounted in a sealed manner on a structure of the aircraft, - a releasable locking assembly of the inner partition on the structure, adapted to be operated between a locking configuration and a release configuration of the inner partition.
    Such a hatch is intended in particular to be used in a delivery system mounted in the fuselage of an aircraft to allow secure release packages from the aircraft, especially when the aircraft is a search and rescue aircraft in sea.
    The package is for example a rescue and recovery chain, designated by the English term "search and rescue" or "SAR". It contains an envelope containing life-saving equipment at sea, such as a self-inflating inflatable boat, a distress beacon, a VHF radio and elements essential for survival (water, food, medicine, first aid, etc.). ).
    To drop such packages, it is known to spare in the floor of the aircraft a lower opening closed by a trap system, provided with a deployable deflector. The release hatch has large dimensions, for example of the order of one meter by 60 cm. The hatch and the baffle are electrically slaved or / and hydraulically and are opened and deployed when approaching the work area.
    The pilot or an observer gives the green light to perform the drop to an observer / largess who manually ejects the package through the hatch. The opening of the hatch for the release therefore requires a complicated mechanism and the provision of bonded energy. This results in revisions and scheduled maintenance and increased risk of failure.
    Furthermore, it is necessary to provide safety systems preventing the opening of the hatch when the aircraft and below a safe altitude, and possibly allowing a balancing of internal and external pressures, before opening the hatch . This further complicates the structure of the hatch, and the necessary maintenance.
    An object of the invention is to provide a shutter door of an opening in the fuselage of an aircraft, which can be opened in a simple manner during flight, and which does not require frequent revisions and interviews , while guaranteeing safety during the flight before opening the hatch. To this end, the subject of the invention is a hatch of the aforementioned type, characterized in that the hatch comprises a pressure equalization valve between an inner surface of the inner partition intended to be placed in an interior volume of the aircraft. and an outer surface of the inner partition, for communicating with the outside of the aircraft, the valve being movable by a user between a closed sealing position and an open pressure balancing position, the locking assembly releasable being immobilized in its locking configuration when the valve is in its closed sealing position.
    The hatch according to the invention may comprise one or more of the following characteristics, taken in isolation or in any technically possible combination: the valve is mechanically linked to the releasable locking assembly in the closed sealing position, the valve being released from the releasable locking assembly in the open pressure balancing position, the valve comprises a movable rod projecting from the inner surface of the inner partition, the releasable locking assembly comprising an arm blocking device arranged on the side of the outer surface of the inner partition, the locking arm defining a receiving housing of the movable rod in the closed sealing position, - the releasable locking assembly comprises an actuating lever, arranged on the side of the inner surface of the inner partition, the lever being movable relative to the key Inner bird to pass the releasable locking assembly into the inner partition release configuration, - the operating lever is connected to the locking arm through the inner partition, - the releasable locking assembly comprises at least one pin closure device adapted to immobilize the inner partition on the structure, the closing pin being connected to the lever by a transmission mechanism, - the releasable locking assembly comprises a bistable member, connected to the lever to maintain it stably in the configuration. opening and in the closing configuration, - the flap comprises a resilient biasing member of the valve towards its closed position, - the inner partition defines at least one through-pressure-balancing light, the flap sealingly covering the light through in the closed position, the valve allowing the passage of gas between the interior surface and the outer surface of the inner wall through the through-light in the open position, - the door comprises a shut-off latch in the closed position, operable on the inner surface of the inner partition, - the flap comprises a manual gripping lug protruding inward away from the inner surface of the inner partition; the flap is adapted to be displaced by a manual pulling force applied to the lug to a maximum value of pressure difference between the inner surface and the outer surface of the intermediate partition, the maximum value being less than 10500 Pa, the lug being advantageously configured to allow the application of a maximum manual traction force of between 10 kgf and 15 kgf. kgf. - The hatch comprises an outer wall for closing the opening in the fuselage, and an intermediate frame connecting the inner wall to the outer wall. The invention also relates to a system for dropping a package from an aircraft, comprising: a panel intended to form a part of a skin of the aircraft, the panel delimiting a transverse opening opening at a distance of outside the aircraft, a trap as defined above, the system comprising a guide sleeve of the hatch through the panel, the guide sleeve opening into the through opening, the hatch being operable in the sleeve of guiding between a closure configuration of the opening and a configuration of passage of the package through the transverse opening.
    The system according to the invention may comprise one or more of the following characteristics, taken in isolation or in any technically possible combination: it comprises a removable hatch, a sleeve guiding the hatch through the panel, the guide sleeve defining the through opening, the hatch being operable in the guide sleeve between a closure configuration of the through opening and a configuration of passage of the package through the through opening, - the hatch comprises a set of releasable locking, adapted to be accessible from inside the aircraft when the hatch occupies its closed configuration, - the releasable locking assembly projects at least partly out of the guide sleeve in the closed configuration, - the system includes a package release guide, at least partially deployable outwardly around the through opening in the configuration of passage of the package, the hatch is able to be totally removed from the guide sleeve in the package-passing configuration, the release guide being adapted to be inserted into the guide sleeve, instead of the hatch. in the package delivery configuration, the guide sleeve comprises guide elements of the release guide and / or the trapdoor arranged in the through opening, the system comprises positioning stops of the release guide with respect to the guide sleeve in an outwardly extended position; - the delivery guide comprises a tubular casing having a notch at a free end deployable out of the panel; - the panel has an external wall intended to be placed in contact with a mass of d air in which the aircraft circulates, an internal wall intended to delimit a pressurized volume of the aircraft, and an intermediate wall connecting the with an outer wall to the inner wall, the guide sleeve passing through the panel between the outer wall and the inner wall, - the guide sleeve protrudes inwardly from the inner wall. The invention also relates to an aircraft, comprising: - a structure defining an interior volume, the structure comprising an outer skin defining an access passage to the interior volume, - a system as defined above, the panel being mounted in the access passage. The invention also relates to a method of releasing an opening formed through the structure of an aircraft, the opening being closed by a hatch as described above, comprising the following steps: immobilization of the assembly releasably locking in its latching configuration when the valve is in its closed sealing position, - moving the valve by a user between a closed sealing position and an open pressure balancing position; then - maneuvering the releasable lock assembly between the lock configuration and the release configuration.
    The method according to the invention may comprise one or more of the following characteristics, taken separately or in any technically possible combination: the valve being mechanically connected to the releasable locking assembly in the closed sealing position, the method comprises disengaging the valve away from the releasable locking assembly during the passage of the valve into the open pressure balancing position, - the method comprises providing a system as defined above, the removable hatch occupying its closed configuration; * maneuver the removable hatch in the guide sleeve to pass in the configuration of passage of a package; * insertion of a package in the guide sleeve; * drop the package through the through opening; - It includes after the maneuver of the removable hatch, the deployment of a parcel drop guide around the through opening at least partially outside the panel, the drop package comprising the passage of the package through the guide drop; - The maneuver of the removable hatch comprises the total withdrawal of the hatch out of the guide sleeve, the deployment of the release guide comprising the insertion of the release guide into the guide sleeve in place of the hatch. The invention will be better understood on reading the description which follows, given solely by way of example, and with reference to the appended drawings, in which: FIG. 1 is a side perspective view of a aircraft equipped with a release system according to the invention in a closed configuration; - Figure 2 is a view similar to Figure 1, in an opening configuration; FIG. 3 is a view from the outside of the panel intended to form a skin of the aircraft in the system of FIG. 1; FIG. 4 is an internal view of the panel of FIG. 3; Figure 5 is a perspective side view of a guide for insertion into the panel of Figure 3; FIG. 6 is a perspective view of a hatch intended to be inserted into the panel of FIG. 3; - Figure 7 is a front view of the release system, when the door is inserted into the panel; - Figure 8 is a view similar to Figure 7, when the guide is inserted into the panel; - Figure 9 is a bottom view of the internal partition of the hatch of Figure 6, before unlocking the valve; - Figure 10 is a view of the flap of the hatch of Figure 6, the latch of the valve being in the open position; - Figure 11 is a sectional view of the valve in position on the inner wall, when it provides a seal; - Figure 12 is a view similar to Figure 11, the valve has been moved to balance the pressures; - Figure 13 is a view similar to Figure 9, after release of the locking assembly; - Figure 14 is a view similar to Figure 7, after release of the locking assembly; and - Figure 15 is a view similar to Figure 1, the release system having been disassembled.
    An aircraft 10 equipped with a first release system 12 according to the invention is illustrated schematically in FIG. 1. The release system 12 is intended to allow the delivery of a package 13, visible in FIG. 2, from the aircraft 10, when the latter is in flight.
    The package is for example a rescue and recovery chain designated by the term "search and rescue" or "SAR". It contains an envelope containing life-saving equipment at sea, such as a self-inflating inflatable boat, a distress beacon, a VHF radio and elements essential for survival (water, food, medicine, first aid, etc.). ). In this example, the envelope of the package 13 is of elongated cylindrical shape.
    With reference to FIG. 15, the aircraft 10 comprises a structure 14 comprising an internal framework 16, and an outer skin 18, mounted on the frame 16. The internal frame 16 defines an interior volume 20 of the aircraft 10 which opens out through the frame 16 and through the skin 18 through an access passage 22.
    In this example, the access passage 22 is an access passage to a hold or cabin of the aircraft, provided in the structure 14. This access passage 22 is able to be closed by a door defining a part of the skin 18 of the aircraft 10.
    The access passage 22 is provided with interfaces 24 for mounting a door.
    The release system 12 according to the invention is mounted in the access passage 22 in place of a door, via the same mounting interfaces 24 as those used to mount the door. The release system 12 is advantageously removably mounted in the access passage 22 to be replaced if necessary by a door.
    When the delivery system 12 is mounted in the access passage 22, and is closed, as shown in Figure 1, the interior volume 20 of the aircraft is adapted to be pressurized.
    With reference to FIGS. 3 to 6, the delivery system 12 comprises a panel 30 intended to be mounted in the access passage 22 to selectively close it, the panel 30 having a through opening 32.
    The delivery system 12 further comprises a guide sleeve 34 delimiting the periphery of the through opening 32 of the panel 30, a removable hatch 36, visible in FIG. 6, intended to close the through opening 32, and a guide release opening 38, visible in FIG. 5, intended to be deployed from the through opening 32 in place of the removable door 36.
    Referring to Figures 3 and 4, the panel 30 has an inner wall 40 to be placed in the inner volume 20, and an outer wall 42, to form a portion of the outer skin 18 of the aircraft and to be placed in contact with an air mass in which the aircraft operates 10.
    The panel 30 further comprises a peripheral intermediate wall 44 connecting the inner wall 40 to the outer wall 42. It is advantageously equipped with covers 46 intended to cooperate with the interfaces 24 to fix the panel 30 on the internal framework 16.
    In this example, the inner wall 40 has a substantially vertical straight shape. The outer wall 42 has a curved shape for flush with the adjacent fuselage panels on the outer skin 18.
    The inner wall 40, the outer wall 42, and the peripheral wall 44 define between them an intermediate space (not visible) through which the guide sleeve 34 is inserted.
    The outer wall 42 advantageously has access doors 48 to the intermediate space to allow adjustment and locking of the panel 30 on the interfaces 24.
    The guide sleeve 34 here extends downwardly from the inside to the outside through the internal space of the panel 30. It comprises a passage tube 50, and an internal collar 52, extending along the inner edge of the tube 50. It is provided with elements 54 for locking the hatch 36, elements 55 for locking the guide 38, and guide elements 56 of the hatch 36 and / or the guide 38. in the through aperture 32.
    The tube 50 has an outer edge flush with the outer wall 42. It has an inner portion 60 projecting inwardly into the inner volume 20 from the inner wall 40.
    The collar 52 protrudes radially from the internal free edge of the tube 50. It carries the locking elements 54.
    The guide elements 56 are arranged in the tube 50, along generatrices of the tube 50. In this example, they are formed by guide rails. The through opening 32 extends through the tube 50 and opens out through the outer wall 42. It opens inwards at the collar 52.
    In this example, the through opening 32 has a constant circular cross section.
    The hatch 36 is adapted to be operated in the guide sleeve 34 between a closure configuration of the through opening 32 and a passage configuration of the package 13 through the through opening 32, in which it has been completely extracted from the sleeve. guide 34.
    With reference to FIG. 6, the hatch 36 comprises an internal partition 70 intended to close the guiding sleeve 34, an external partition 72 intended to be placed in the transverse opening 32 at the level of the outer skin 18, to close the transverse opening 32 and an intermediate frame 74 connecting the internal partition 70 to the external partition 72.
    The hatch 36 further comprises a handling assembly 75, a releasable locking assembly 76, and a pressure balancing assembly 78 on either side of the internal partition 70.
    The internal partition 70 has a contour corresponding to the outer contour of the guide sleeve 34. It is adapted to rest on an internal shoulder of the guide sleeve 34 defined at the flange 52, to flush with the flange 52 in the configuration of FIG. closing.
    With reference to FIGS. 11 and 12, the internal partition delimits a seat 82 for receiving the pressure balancing assembly 78. It defines at least one through-passing lumen 84 for balancing pressure between an internal surface of the internal partition 70 , intended to be placed facing the inner volume 20 and an outer surface of the inner partition 70, intended to be placed facing the through opening 32, being oriented outwardly.
    The seat 82 has a cylindrical skirt 86 for guiding the pressure-balancing assembly 78 projecting outwards.
    The outer wall 72 is flush with the outer wall 42 of the panel 30 in the closed configuration. It thus forms part of the outer skin 18 of the aircraft, in contact with an air mass in which the aircraft 10 evolves. The intermediate frame 74 rigidly connects the internal partition 70 to the outer partition 72. is provided with longitudinal guides 80 adapted to cooperate with the guide elements 56 arranged in the guide sleeve 34, to ensure a translational movement of the door 36 in the guide sleeve 34 along an axis A-A 'of the through opening 32, visible in Figures 3 and 4.
    With reference to FIGS. 10 to 12, the pressure balancing assembly 78 comprises a manually operable balancing valve 88 between a closed pressurization position and an open pressure balancing position and, advantageously, a latch 90 of FIG. maintaining the valve 88 in the closed position.
    The valve 88 has a shutter plate 92 intended to fit into the seat 82 to cover each lumen 84, a locking rod 94, inserted into the skirt 86, and provided at its free end with a retaining ring 96. , and an elastic biasing member 98 of the valve 88 to its closed position.
    The valve 88 further comprises a gripping pin 100 projecting inwards with respect to the plate 92.
    The plate 92 is able to seal the seat 82 and its lumens 84, advantageously with the interposition of a peripheral seal 102 in the closed position. It is adapted to disengage from the seat 82 to release an air flow passage between the plate 92 and the seat 82 to the lights 84 in the open position.
    The shape and size of the lug 100 limit the maximum manual pulling force on the valve 88 that can be exerted by a user along the longitudinal axis of the lug 100.
    This force F, expressed in kilograms-force by the formula F = m.g, with g = 9.81 m.sup.-2, is between 10 kgf and 15 kgf. Indeed, from 10 kgf, the handling of the valve 88 is made difficult and goes from difficult to impossible from 10 kgf to 15 kgf.
    In particular, the geometry of the lug 100 prevents its gripping by more than two fingers and thus limits the force developed manually by the user. The area A of the plate 92 is then calculated to prevent manual operation of the valve 88 using the lug 100 between the closed position and the open position when the pressure difference on either side of the partition. internal 70 is greater than a predetermined maximum value, this maximum value being, for example less than 10500 Pa, in particular 10335 Pa (1.5 psi) and preferably equal to 8268 Pa (1.2 psi).
    This area A is calculated by the equation
    where A is the area of plate 92, m. is the maximum applied mass, g is 9.81 ms "2 and p is the maximum pressure value The rod 94 is inserted into the skirt 86. It protrudes beyond the skirt 86 to engage mechanically with the locking assembly 76, as will be seen below.
    The ring 96 is fixedly mounted on the rod 94, in the vicinity of its free end. It is adapted to guide the rod 94 in translation in the skirt 86. The resilient biasing member 98 is interposed between the ring 96 and the seat 82. It is formed here by a helical spring. It requests by default the valve 88 to its closed position.
    The latch 90 is adapted to be operated manually between a locking configuration of the valve 88 in its closed position and a release configuration of the valve 88.
    It is for example formed by a rotary butterfly 106, one of whose branches is applied to the plate 92 in the locking configuration. The latch 90 further includes throttle lock jumpers 108 in each of the lock and release configurations.
    Referring to Figure 6, the handling assembly 75 comprises a peripheral 110 handling bar, fixed on an inner surface of the internal partition 70. The releasable locking assembly 76 has, facing the inner surface of the partition internal 70, at least one closing pin 112 for locking the inner partition 70 on the guide sleeve 34, a rotary lever 114 for actuating each closure pin 112, and a transmission mechanism 116 connecting the lever 114 to each closing pin 112. The assembly 76 also comprises, on the side of an outer surface of the internal partition 70, a locking arm 118 connected to the lever 114, able to cooperate with the valve 88 to prevent the unlocking of the assembly. locking 76 when the valve 88 is in its closed position.
    In the example shown in FIG. 7, the locking assembly 76 comprises a plurality of closure pins 112 distributed around the periphery of the internal partition 70. Each closure pin 112 is radially movable under the effect of the action lever 114 for insertion into the locking elements 54 on the guide sleeve 34.
    The lever 114 is rotatably mounted about an axis advantageously coaxial with the axis of the through opening 32 when the hatch 36 is inserted into the through opening 32. The lever 114 is adapted to be maneuvered manually by a user to make passing the lock assembly 76 from a lock configuration to a release configuration of the internal partition 70.
    The transmission mechanism 116 has on the inner surface side of the inner partition 70, an eccentric 120, rotatable in conjunction with the lever 114, and for each closure pin 112, a connecting rod 122 connecting the eccentric 120 to the spindle 112.
    The mechanism 116 further includes a bistable member 124, connecting the eccentric 120 to a fixed point 125 on the partition, to bias the lever 114 to maintain the latch assembly 76 in the latch configuration or in the release configuration. , resting.
    Referring to Figures 9 and 13, the locking arm 118 is connected to the lever 114 through the internal partition 70. It is movable jointly in rotation with the lever 114, between two adjustable stops 123 which limit its angular travel around the axis of rotation of the lever 114. It has a curved shape centered on the axis of rotation of the lever 114.
    The locking arm 118 defines a housing 126 for receiving the rod 94 of the valve 88. Thus, when the valve 88 is in its closed position, the end of the rod 94 is received in the housing 126 in order to lock the arm blocking 118, and consequently the lever 114, as visible in FIG. 11.
    On the other hand, when the valve 88 is in its open position, shown in FIG. 12, the end of the rod 94 has been disengaged from the housing 126, and the locking arm 118, as well as the lever 114, are free to rotate about of the axis of rotation of the lever 114.
    Referring to Figure 5, the release guide 38 comprises a tubular casing 130, open at its ends, a gripping flange 132, located on the inner edge of the tubular casing 130 and guide projections 134 adapted to cooperate with the guide elements 56 of the guide sleeve 34. The tubular envelope 130 has a cross section of contour substantially complementary to the internal contour of the through opening 32 in the guide sleeve 34. It has a length greater than that of the sleeve of guidance 34.
    The guide 38 comprises an end section 136 capable of protruding out of the guide sleeve 34. As can be seen in FIG. 5, the end section 136 advantageously defines an external indent 138 for guiding the release of the package 13 in a preferential direction.
    The gripping flange 132 is provided with handles 140 and radial stops 142 for fixing on the locking elements 54 of the guide sleeve 34.
    The release guide 38 is adapted to be inserted manually into the guide sleeve 34, instead of the removable door 36. Once inserted into the guide sleeve 34, the outer portion 136 protrudes beyond the outer skin 18 of the aircraft 10 to remove the package 13 of the aircraft 10 during its release. The guide 38 then occupies an extended position.
    The length of the outer portion 136 extracted from the transverse opening 32 is greater than 20% of the total length of the guide, taken along its axis, the notch 138 avoids the skew of the package 13. It also ensures reproducibility the ejection path of the package 13 out of the guide 38.
    Referring to Figure 8, the locking elements 55 of the guide 38 are formed by tongues rotatably mounted a quarter turn on the flange 52 between a position released from the gripping flange 132 and a position engaged on the flange of gripping 132.
    The operation of the delivery system 12 according to the invention will now be described.
    Initially, the release system 12 was mounted on the structure 14 of the aircraft 10, at an access passage 22 provided in this structure 14 to access the cabin or a cargo hold. This assembly is for example in replacement of a door placed in the access passage 22.
    The interfaces 24 present in the access passage 22 are used to fix the intermediate wall 44 of the panel 30 on the internal framework 16. In this configuration, as shown in FIG. 1, the external wall 42 of the release system 12 is flush with the outer skin 18 of the aircraft 10.
    Furthermore, the hatch 36 has previously been inserted into the through opening 32, through the guide sleeve 34. The outer partition 72 closes the through opening 32 to the outside. It is flush with the outer wall 42 of the panel 30, minimizing the aerodynamic disturbances on the aircraft 10.
    The internal partition 70 is pressed against the guide sleeve 34 and seals it tightly. The lock assembly 76 is maintained in its lock configuration. For this purpose, the closing pins 112 cooperate with the locking elements 54 on the guide sleeve 34. The bistable member 124 holds the lever 114 stably in this configuration.
    The valve 88 is in its closed position. The plate 92 is sealingly applied to the seat 82 defined in the internal partition 70. This prevents the passage of air from the interior volume 20 out through the through-holes 84. The resilient biasing member 98 maintains the plate 92 applied against the seat 82.
    The rod 94 of the valve 88 is received in a complementary manner in the housing 126, blocking in rotation the locking arm 118 and consequently the lever 114.
    The latch 90 is placed in abutment on the plate 92, preventing the displacement of the valve 88 to the open position.
    The pressurization of the internal volume 20 can thus be implemented without leakage towards the outside through the through opening 32.
    Given the dimensions of the plate 92, and the presence of the latch 90, it is impossible for a user to pull the valve 88 inadvertently. The latch 90 also makes it possible to keep the valve 88 closed in the event of an external pressure greater than the internal pressure, in particular during an external air discharge in the case of a rapid descent of the aircraft 10.
    In addition, even if the latch 90 is pivoted to release the valve 88, the latter remains closed if the difference between the internal pressure and the external pressure is too great, according to the predetermined threshold defined by the area of the plate 92 of the valve 88.
    The valve 88 being immobilized in position, it is also impossible for a user to maneuver the lever 114, which ensures that the hatch 36 can not be removed inadvertently.
    When the aircraft 10 reaches the drop zone, and it is low enough so that the difference between the internal pressure and the external pressure is less than the predetermined threshold, the user manually operates the latch 90 to release it from the valve 88 For this purpose, it grasps the handling pin 100 of the valve 88 accessible from the internal volume 20 and pulls inwards on the valve 88, against the biasing force generated by the elastic biasing member. 98.
    It compresses the biasing member 98 and moves the rod 94 inwardly. The plate 92 then moves away from the seat 82, as can be seen in FIG. 12, giving off an air passage to enable a pressure equalization between the internal volume 20 of the aircraft 10 and the outside of the aircraft 10, through the lights 84 and through aperture 32.
    In addition, the rod 94 is withdrawn from the housing 126 and releases the locking arm 118. The user then manually manipulates the lever 114 to pass the locking assembly 76 from its locking configuration to its unlocked configuration.
    The rotation of the lever 114 about its axis jointly displaces in rotation the eccentric 120 and the locking arm 118. Under the effect of the displacement of the connecting rods 122, the closing pins 112 are disengaged from the locking elements 54 by moving towards the axis of rotation of the lever 114.
    When the locking assembly 76 is in its unlocked configuration, the lever 114 is held in position by the bistable member 124. The internal partition 70 is then free to move relative to the guide sleeve 34. The user then grasps the hatch 36 by means of the handling arch 110 and completely extracts the hatch 36 from the guide sleeve 34 to clear the through opening 32.
    The hatch 36 is guided in translation along the axis of the through opening 32 by the cooperation between the guides 80 and the guide elements 56 present in the sleeve 34.
    Then, the user grasps the release guide 38 and introduces it into the guide sleeve 34 via its outer portion 136 through the through opening 32. The insertion of the release guide 38 into the sleeve 34 is guided by the cooperation between the guide projections 134 present on the tubular casing 130 and the guide elements 56.
    The release guide 38 is inserted until the inner flange 132 abuts against the flange 52.
    In this position, as illustrated in Figure 2, the outer portion 136 projects out of the transverse opening 32 from the outer wall 42. The notch 138 is then directed downwardly and rearwardly.
    The locking elements 55 are moved in their engaged position on the gripping flange 132.
    The package 13 is then introduced into the release guide 38 in the inner volume 20. The package 13 is then pushed outward for its release to the desired position.
    The presence of the release guide 38 makes it possible to control the direction of the release and to re-route the trajectory each time a package is released 13. In addition, a sufficient safety distance between the package 13 released and the fuselage of the aircraft 10 is guaranteed by the presence of the drop guide 38.
    Once the release is made, the release guide 38 is released from the guide sleeve 34 by performing the reverse operations previously described.
    Then, the hatch 36 is reintroduced into the guide sleeve 34 in place of the release guide 38. The lever 114 is operated to deploy the closing pins 112 in the locking elements 54 on the sleeve 34 to the configuration of FIG. locking.
    The rod 94 then enters the housing 126 to lock in rotation the locking arm 118 and the lever 114, as previously described. The latch 90 is put in place on the valve 88.
    The delivery system 12 according to the invention has the advantage of not modifying the primary structure 14 of the aircraft 10, since it fits into access passages 22 provided in this structure 14 to access the cabin and / or at the bunkers of the aircraft. The interfaces 24 used to close the access passages 22 by means of doors can be used to mount the panel 30 of the delivery system, without substantial modifications.
    The replacement of a basic aircraft door 10 by the release system 12 is easy and reversible.
    Furthermore, the operation of the various components of the release system 12 is simple and can be done by hand by a user. It does not require energy of servitude, nor of particular utility. Maintenance is reduced to a minimum and the risk of failure is minimal.
    Thanks to the presence of a link between the valve 88 and the lever 114 for unlocking the hatch 36, the safety during the flight is ensured by allowing the balancing of internal and external pressures only at a sufficiently low altitude for the security. Unlocking the lever 114 is thus made impossible until the pressures are balanced between the interior volume 20 of the aircraft 10 and the outside.
    The unlocking of the hatch 36 is manual, and does not require service energy. As before, maintenance is reduced to a minimum and the risk of failure is minimized.
    In a variant, the delivery system 12 is implemented without providing a valve 88, as described above.
    In another variant, the removable hatch 36 is used to close a through opening 32 of the aircraft 10 which is not necessarily intended for the release of a package 13.
    权利要求:
    Claims (15)
    [1" id="c-fr-0001]
    1.-Trap (36) closing an opening (32) formed through the structure (14) of an aircraft (10), comprising: - an inner partition (70) sealing, intended to be mounted sealingly to a structure (14) of the aircraft (10); - a releasable locking assembly (76) of the inner partition (70) on the structure (14) adapted to be operated between a locking configuration and a release configuration of the inner partition (70); characterized in that the hatch (36) includes a pressure balancing valve (88) between an inner surface of the inner partition (70) for placement in an interior volume (20) of the aircraft (10) and an outer surface of the inner partition (70), intended to communicate with the outside of the aircraft (10), the valve (88) being movable by a user between a sealed sealing position and an open balancing position pressure, the releasable locking assembly (76) being immobilized in its locking configuration when the valve (88) is in its closed sealing position.
    [2" id="c-fr-0002]
    2. - hatch (36) according to claim 1, wherein the valve (88) is mechanically connected to the releasable locking assembly (76) in the closed sealing position, the valve (88) being released from the releasable locking assembly (76) in the open pressure balancing position.
    [3" id="c-fr-0003]
    3. - hatch (36) according to one of claims 1 or 2, wherein the valve (88) comprises a rod (94) movable projecting from the inner surface of the inner partition (70), all releasable locking device (76) comprising a locking arm (118) disposed on the outer surface side of the inner partition (70), the locking arm (118) defining a receiving housing (126) for receiving the stem (94) movable in the closed sealing position.
    [4" id="c-fr-0004]
    4. A hatch (36) as claimed in any one of the preceding claims, wherein the releasable locking assembly (76) comprises an actuating lever (114) disposed on the inner surface side of the inner partition (70). ), the lever (114) being movable relative to the inner partition (70) to pass the releasable locking assembly (76) into the release configuration of the inner partition (70).
    [5" id="c-fr-0005]
    5. - hatch (36) according to claim 4, taken in combination with claim 3 wherein the lever (114) of actuation is connected to the locking arm (118) through the inner wall (70).
    [6" id="c-fr-0006]
    6. - hatch (36) according to claim 5, wherein the releasable locking assembly (76) comprises at least one closing pin (112) adapted to immobilize the inner partition (70) on the structure (14), the closing pin (112) being connected to the lever (114) by a transmission mechanism (116).
    [7" id="c-fr-0007]
    7. - hatch (36) according to any one of the preceding claims, comprising a member (98) resilient biasing of the valve (88) to its closed position.
    [8" id="c-fr-0008]
    8. - hatch (36) according to any one of the preceding claims, wherein the inner partition (70) defines at least one through-light (84) for pressure equalization, the valve (88) sealingly covering the light through (84) in the closed position, the valve (88) allowing the passage of gas between the inner surface and the outer surface of the inner partition (70) through the through-light in the open position.
    [9" id="c-fr-0009]
    9. - hatch (36) according to any one of the preceding claims, comprising a latch (90) for immobilizing the valve (88) in the closed position, operable on the inner surface of the inner partition (70).
    [10" id="c-fr-0010]
    10. - hatch (36) according to any one of the preceding claims, wherein the valve (88) comprises a pin (100) for manual entry projecting inward away from the inner surface of the inner partition. (70).
    [11" id="c-fr-0011]
    11. - trapdoor according to claim 10, wherein the valve (88) is adapted to be displaced by a manual traction force applied on the pin (100) to a maximum pressure difference value between the inner surface and the outer surface of the intermediate partition (70), the maximum value being less than 10500 Pa, the lug (100) being advantageously configured to allow the application of a maximum manual traction force of between 10 kgf and 15 kgf.
    [12" id="c-fr-0012]
    12. - hatch (36) according to any one of the preceding claims, comprising an outer wall (72) for closing the opening (32) in the fuselage, and an intermediate frame (74) connecting the inner wall (70). to the external partition.
    [13" id="c-fr-0013]
    13. - System (12) for dropping a package (13) from an aircraft (10), comprising: - a panel (30) intended to form part of a skin (18) of the aircraft (10), the panel (30) defining a transverse opening (32) opening outwardly of the aircraft (10); - A hatch (36) according to any one of the preceding claims, the system (12) comprising a guide sleeve (34) of the hatch (36) through the panel, the guide sleeve (34) opening into the through opening (32), the hatch (36) being operable in the guide sleeve (34) between a closure configuration of the opening (32) and a configuration of passage of the package (13) through the transverse opening ( 32).
    [14" id="c-fr-0014]
    14. - Method of releasing an opening (32) formed through the structure (14) of an aircraft (10), the opening (32) being closed by a hatch (36) according to any one of the claims 1 to 12, comprising the steps of: immobilizing the releasable locking assembly (76) in its locking configuration when the valve (88) is in its closed sealing position; - Movement of the valve (88) by a user between a closed position of sealing and an open position of pressure equalization; then - maneuvering the releasable latch assembly (76) between the latch configuration and the release configuration.
    [15" id="c-fr-0015]
    The method of claim 14, the valve (88) being mechanically bonded to the releasable locking assembly (76) in the closed sealing position, the method comprising disengaging the valve (88) away from the releasable locking assembly (76) during passage of the valve (88) into the open pressure balancing position.
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    同族专利:
    公开号 | 公开日
    US10577071B2|2020-03-03|
    FR3046777B1|2018-02-16|
    US20170203828A1|2017-07-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2432640A|1946-02-25|1947-12-16|Boeing Aircraft Co|Flare releasing mechanism|
    EP0061398A1|1981-03-24|1982-09-29|François Boulard|Method and device for stocking and releasing a cylindrical object from a vehicle|
    US20110049299A1|2009-09-01|2011-03-03|Cessna Aircraft Company|Aircraft Cabin Door Pressure Vent System|
    FR3046779B1|2016-01-14|2018-02-16|Dassault Aviation|SYSTEM FOR PACKAGING A PACKAGE FROM AN AIRCRAFT, AIRCRAFT AND ASSOCIATED METHOD|
    USD905597S1|2018-04-26|2020-12-22|Standard Car Truck Company|Railroad car combined vented hatch cover protector and gasket|
    CN108583843B|2018-06-21|2021-04-20|西安飞机工业（集团）有限责任公司|Aircraft lifeboat hatch cover locking mechanism|
    CN109458084B|2018-09-25|2020-06-09|陕西飞机工业（集团）有限公司|Two fan type cargo hold gate control system of military aircraft|
    法律状态:
    2016-12-19| PLFP| Fee payment|Year of fee payment: 2 |
    2017-07-21| PLSC| Publication of the preliminary search report|Effective date: 20170721 |
    2017-12-22| PLFP| Fee payment|Year of fee payment: 3 |
    2019-12-12| PLFP| Fee payment|Year of fee payment: 5 |
    2020-12-30| PLFP| Fee payment|Year of fee payment: 6 |
    2021-12-10| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1600069|2016-01-14|
    FR1600069A|FR3046777B1|2016-01-14|2016-01-14|CLOSURE HATCH OF AN OPENING MADE THROUGH THE STRUCTURE OF AN AIRCRAFT, STRUCTURE, AND METHOD THEREOF|FR1600069A| FR3046777B1|2016-01-14|2016-01-14|CLOSURE HATCH OF AN OPENING MADE THROUGH THE STRUCTURE OF AN AIRCRAFT, STRUCTURE, AND METHOD THEREOF|
    US15/402,728| US10577071B2|2016-01-14|2017-01-10|Hatch for closing an opening provided through an aircraft structure, related structure and method|
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