• 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 invention relates to the field of fueling devices, in particular for refueling rockets on the ground. A refueling device (4) according to the invention comprises at least two mutually complementary refueling connectors (5, 6), a breakable connecting member (15) connecting these two refueling connectors (5, 6) and presenting a breaking section (15c) between these two refueling connectors (5, 6), and a force transmitting member (16) connected to said breaking section (15c) so as to transmit to it a breaking load for unlock the connection between the two refueling connectors (5,6). Upon unlocking, a breaking load transmitted by the force transmission member (16) thus ensures the rupture of the breaking section (15c).
    公开号:FR3029173A1
    申请号:FR1461646
    申请日:2014-11-28
    公开日:2016-06-03
    发明作者:Olivier Yhuellou；Georges Verdier；Olivier Adam；William Barre
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The present invention relates to the field of fueling devices, in particular for refueling rockets on the ground.
    [0002] In this context, "rocket" is understood in a broad sense also extending to machines with at least one aerobic propulsion stage, and not only to those using only anaerobic rocket motors. Such a rocket may in particular be a launcher intended to put a payload on an orbital trajectory, extra-orbital or suborbital. On the ground, on the launch pad or launch pad, such a rocket is often connected to umbilical supply lines propellant, pressurization fluids, and / or electricity until the moment of its takeoff. These conduits may also provide other services, such as, for example, data transmission between the rocket and a control station. To ensure the connection between these umbilical ducts and the rocket, they have mutually complementary pairs of connectors often called "valve plates" because of the presence of valves to stop the flow of fluids during the separation of these connectors. On some current rockets, such as for example launchers of the Ariane 5 family, the separation of at least some of these pairs of mutually complementary refueling connectors is carried out before the ignition of the first stage propulsion engines. As a result, it is normally necessary to check their disconnection before the rocket takes off. Especially, in case of aborted takeoff after separation of the refueling connectors, and in particular when rocket tanks contain cryogenic liquids, including propellant, the emptying of these tanks through other connectors, and the replacement of refueling connectors, typically become necessary. However, this involves expensive means of intervention, as well as the immobilization of the rocket for a precious time. OBJECT AND SUMMARY OF THE INVENTION The present disclosure seeks to remedy these drawbacks. In particular, it aims at providing a refueling device comprising at least two mutually complementary refueling connectors, capable in particular of refueling a rocket on the ground, and which can be unlocked extremely reliably in response to a refueling device. relative displacement of two elements, such as that of a rocket relative to its firing point during its effective take-off. In at least one embodiment, this object is achieved by the fact that the refueling device also comprises a breakable connecting member connecting said two refueling connectors, and having a break section between these two refueling connectors. and a force transmission member connected to said breaking section of the breakable link member so as to transmit a breaking load to unlock the link between the two refueling connectors. Thanks to these provisions, the unlocking can therefore be carried out in a simple manner, by breaking the connecting member to its breaking section, caused by the load transmitted by the force transmission member. In particular, said force transmission member may be a lever substantially perpendicular to said main axis of the connecting member. By "substantially perpendicular" is meant, in the present context, that the orientation of this main axis does not differ from more than, for example, 5 or 100 of the orientation of an axis orthogonal to the plane of rotation of the lever. Thus, the breaking load can be transmitted in torsion to the breaking section of the connecting member, the length of the lever ensuring at least part of the reduction of this breaking force, so that a moderate force at the end of the arm of this lever may be sufficient to break the breaking section of the torsion connecting member. In addition, thanks to this configuration, the force transmission member can be actuated by a force orthogonal to the main axis of the connecting member, which simplifies the arrangement of the refueling device, especially for a rocket fueling device. Apart from the lever, other devices, such as pulleys or capstans, can also contribute to the reduction of the breaking force. In addition, said connecting member is hollow, forming a conduit between said two ends. Thus, the connecting member may also be used for the transfer of fluids, in particular a propellant or a pressurizing gas, from one side to the other of the refueling device. Said refueling connectors may be configured to substantially sealing the ducts of at least one fluid, in particular a liquid and more particularly a propellant. In addition, the refueling device may also include at least one resilient spring disposed to separate said two connectors 10 after rupture of the connecting member, which is a particularly simple and effective way to ensure the separation of the two connectors. However, other types of actuator, for example magnetic, electric or fluidic actuators, can also be envisaged alternately or in addition to the actuation by elastic spring. It is even conceivable to completely do without actuator, the separation of the connectors can be ensured by gravity alone and / or inertia. Finally, the refueling device may also comprise a traction line connected to the force transmission member. Thus, the unlocking of the refueling connector can be ensured simply, reliably and effectively by pulling the traction line on the force transmission member, traction being able to result in particular from the vertical movement of the rocket at takeoff. The disclosure also relates to a method of unlocking a refueling device in which a breaking load transmitted by a force transmission member breaks a breaking section of a breakable connecting member, thereby breaking a connection between two refueling connectors of said refueling device which are mutually complementary. In particular, said force transmission member may be a lever substantially perpendicular to a main axis of the connecting member connecting its two ends, this lever transmitting a torsional breaking load to the breakable connecting member. This method can in particular serve to unlock a fueling device of a rocket, initially connecting said rocket to ground refueling services. The invention will be better understood and its advantages will appear better, on reading the detailed description which follows, of an embodiment shown by way of non-limiting example. The description refers to the accompanying drawings, in which: FIG. 1 schematically illustrates a space launcher on its firing point before launch; - Figure 2 schematically illustrates the space launcher of Figure 1 in an initial takeoff phase; FIG. 3A is a front view of a pair of mutually complementary refueling connectors of a refueling device according to an embodiment of the invention, in the locked position; FIG. 3B is a longitudinal sectional view, along the line B-B, of the refueling connectors of FIG. 3A; FIG. 4 is a perspective view of the device for unlocking the refueling connectors of FIGS. 3A and 3B; FIG. 5A is a front view of the refueling connectors of FIGS. 3A and 3B, being unlocked; Figure 5B is a longitudinal sectional view of the refueling connectors of Figure 4A; and FIG. 6 is a longitudinal sectional view of the refueling connectors of FIGS. 3A to 4B, after unlocking. DETAILED DESCRIPTION OF THE INVENTION FIG. 1 illustrates a liquid propellant rocket 1 for launching satellites on its firing point 2 before its take-off. In this position, the rocket 1 is connected, for its refueling with propellants, as well as for example pressurizing gas and / or electricity, to umbilical ducts 3, through a refueling device 4 comprising mutually complementary connectors 5 6 are normally locked to each other and fixed respectively to the rocket 1 and to the umbilical ducts 3. These complementary connectors 5,6 are normally called "valve plates" because they are equipped with shut-off valves. the flow of fluid during their separation. line pulling line 7 connecting the connector 6 ground side - at the firing point 2 to trigger the unlocking and separation of the complementary connectors 5.6 during the takeoff of the rocket 1, comm9, igustré-in Figure 2. In addition , a remote device 8 of the -connector 6 can make it possible to facilitate the separation of the complementary connectors 5, 6 once unlocked during takeoff of the rocket 1. In the illustrated embodiment, this removal device 8 is formed by a single additional traction line, connecting the ground-side connector 6 to a higher point of the firing point 2 and offset laterally of the rocket 1, so that the fall of the connector 6 by simple gravity. after unlocking its connection to the complementary connector 5 will also cause a lateral movement away from the rocket 1. However, other alternative configurations, such as for example rigid arms swinging laterally, can also be envisaged. FIGS. 3A and 3B illustrate in detail the refueling device 4. In this refueling device 4, the refueling connector 5 is secured to an outer wall of the fuze 1 and, in the illustrated embodiment, connected by conduits to a first and a second propellant tank and to a pressurization gas tank (not shown) for refueling. This connector 5 is further equipped with valves 9 to isolate the propellant reservoirs when it separates from the complementary connector 6. Each valve 9 is equipped with a spring 10 exerting a constraint in the direction of closing the valve 9. In the illustrated embodiment, the ground-side fueling connector 6 comprises ducts 12 connected to propellant supply umbilical ducts 3a. A slider 13 is mounted around each of the propellant conduits 12, facing actuating surfaces of the valves 9. These sliders 13 are also equipped with springs 14, which exert a stress in the opposite direction to the springs 10 of the valves 9. Thus, the sliders 13, pushing on the actuating surfaces of the -9 valves 9, keep them in the open position as long as the connection between the connectors 5 and 6 is maintained. The ground side connector 6 can also be equipped with valves (not shown) to stop the flow of these fluids when separating the connectors 5,6. To ensure the connection between the connectors 5 and 6, the refueling device 4 comprises in particular a breakable connection member 15, with a first end 15a integral with the connector 5 on the rocket side, a second end 15b, integral with the refueling connector 6 ground side and a breaking section 15c located between said first and second ends 15a, 15b. The refueling device 4 further comprises a force transmission member 16, able to transmit a breaking load to said breaking section 15c of the connecting member. In the illustrated embodiment, the transmission member Stresses 16 take the form of a lever with a distal end 16a connected to the traction line 7 and a proximal end 16b integral with the connecting member 15 in rotation. This lever is arranged to rotate around its proximal end 16b in a plane substantially perpendicular to a main axis X of the connecting member 15. To transmit a tensile load in torsion to the breaking section 15c of the connecting member 15, the proximal end 16b of the force transmission member 16 is engaged on a segment 15d of the connecting member 15 having a prismatic section. As illustrated in FIG. 4, the rupture section 15c of the connecting member 15 is directly interposed between this segment 15d with a prismatic section and a segment of the first end 15a of the connecting member 15 which is also prismatic and received. in a cavity of the connector 5 of complementary section to ensure their solidarity in rotation relative to the connector 5. The rupture section 15c is thinner than the prismatic section of the segment 15d or the first end 15a of the connecting member 15, so as to ensure the rupture of the connecting member 15 at this location when a torsional failure load is transmitted by the force transmission member 16 to the connecting member 15. In addition, connecting member 15 also has a preload segment 15e between its prismatic section 15d and its second end 15b, which is fixed to the connector 6 on the ground side by a nut 17. This prestressing segment 15e allows t establish a voltage prestressing between the two ends 15a, 15b of the connecting member 15, thereby pushing the complementary connectors 5,6 against each other to seal their connection. In addition, this prestressing segment 15e also has a certain torsional elasticity allowing a limited rotation of the prismatic section 15d with respect to the second end 15b of the connector. The illustrated connecting member 15 is also hollow, being traversed from one end to the other by the conduit 15f, which can also be used for refueling fluid. Thus, in the illustrated embodiment, the conduit 15f is connected to a supply pipe 3b pressurized gas. However, it is not excluded that, in other embodiments, this conduit 15f through the connecting member 15 can be used for refueling propellant or other fluids or services. The unlocking of the refueling device can be explained with reference to FIGS. 5A, 5B and 6. In FIG. 5A, it can be seen how the lever forming the force transmission member 16 rotates about the main axis X of the connecting member 15 following traction on the pulling line 7, traction being able in particular to be caused by the take-off of the rocket 1 and its vertical displacement with respect to the firing point 2. As can be seen in FIG. 5B this rotation of the force transmission member 16, transmitted to the breaking section 15c of the connecting member 15 through its prismatic section 15d, causes the breaking of the connecting member 15 at this point, disengaging the two ends 15a, 15b of the connecting member 15 and thus unlocking the connection between the two connectors 5,6. Following this unlocking, the prestressing of the springs 10, 14 contribute to the separation of the two ends 15a, 15b of the connecting member 15, and therefore of the two connectors 15a, 15b, as illustrated in FIG. 6 and, in the 1, in FIG. 2. In this way, a simple and reliable unlocking of the refueling connectors 5,6 is obtained in response to the effective take-off of the rocket 1, thus making it possible to replace the rocket 1 devices. state of the art that required unlocking prior to ignition of the rocket 1, with the aforementioned disadvantages in case of aborted launch after unlocking.
    [0003] Although the present invention has been described with reference to a specific exemplary embodiment, it is obvious that various modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, it is conceivable to use, alternately or in addition to the torsion used in this embodiment, a breaking load in tension and / or bending to break the connecting member of the refueling device. In addition, individual features of the various embodiments mentioned can be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.
    权利要求:
    Claims (8)
    [0001]
    REVENDICATIONS1. A refueling device (4), comprising at least two mutually complementary refueling connectors (5, 6), a breakable connecting member (15) connecting said two refueling connectors (5, 6), and having a rupture section (15c), and a force transmission member (16) connected to said breaking section (15c) of the connecting member (15) so as to transmit to it a breaking load to unlock the link between the two refueling connectors (5,6).
    [0002]
    2. Fueling device (4) according to claim 1, wherein said force transmitting member (16) is a lever 15 substantially perpendicular to a main axis (X) of the connecting member (15).
    [0003]
    3. Fueling device (4) according to any one of the preceding claims, wherein said connecting member (15) is hollow, forming a duct (15f) between the two refueling connectors (5, 6).
    [0004]
    The refueling device (4) according to any of the preceding claims wherein said refueling connectors (5, 6) are configured to substantially seal fueling lines in at least one fluid. 25
    [0005]
    5. fueling device (4) according to any one of the preceding claims, further comprising at least one resilient spring disposed to separate said two fueling connectors (5,6) after rupture of the connecting member (15).
    [0006]
    6. Fueling device (4) according to any one of the preceding claims, further comprising a traction line (7) connected to the force transmission member (16).
    [0007]
    7. A method of unlocking a refueling device (4), wherein a breaking load transmitted by a force transmission member (16) breaks a breaking section (15c) of a brushable connecting member (15), thus breaking a connection between the two refueling connectors (5, 6) of said refueling device (4) which are mutually complementary.
    [0008]
    8. Unlocking method according to claim 6 wherein said force transmission member (16) is a lever substantially perpendicular to a main axis (X) of the connecting member connecting its two ends (15a, 15b), lever transmitting a torsional breaking load to the breakable connecting member (15).
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20170260929A1|2017-09-14|
    JP6847832B2|2021-03-24|
    FR3029173B1|2018-03-23|
    WO2016083713A1|2016-06-02|
    EP3224144B1|2018-09-12|
    EP3224144A1|2017-10-04|
    US10717552B2|2020-07-21|
    RU2017122444A3|2019-05-16|
    JP2017535481A|2017-11-30|
    RU2017122444A|2018-12-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP0371867A1|1988-11-29|1990-06-06|AEROSPATIALE Société Nationale Industrielle|Filling device for cryogenic rocket fuel, automatically separated at launching|
    FR2685903A1|1992-01-06|1993-07-09|Latecoere Sa|Breakable assembly used for transferring fluid between an umbilical supply assembly and the inlet leaving the side edge of a moving machine such as a launcher|
    FR2943627A1|2009-03-31|2010-10-01|Snecma|DEVICE FOR SEPARATING BOTH PARTS OF A LAUNCHER FEEDING MODULE|FR3061894A1|2017-01-17|2018-07-20|Latecoere Services|LAUNCHER RETRACTABLE FEEDING SYSTEM AND CORRESPONDING RETRIEVAL METHOD|US3183468A|1960-04-27|1965-05-11|Bendix Corp|Electrical connector|
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    JP2013202244A|2012-03-29|2013-10-07|Betekku:Kk|Control board storage box and game machine|FR3016865B1|2014-01-29|2016-02-19|Snecma|IMPROVED ERGOL POWER SUPPLY SYSTEM FOR A SPATIAL VEHICLE|
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    法律状态:
    2015-11-10| PLFP| Fee payment|Year of fee payment: 2 |
    2016-06-03| PLSC| Publication of the preliminary search report|Effective date: 20160603 |
    2016-11-10| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-23| PLFP| Fee payment|Year of fee payment: 4 |
    2018-11-22| PLFP| Fee payment|Year of fee payment: 5 |
    2020-10-16| ST| Notification of lapse|Effective date: 20200906 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1461646A|FR3029173B1|2014-11-28|2014-11-28|DEVICE AND METHOD FOR UNLOCKING A FEEDING DEVICE|
    FR1461646|2014-11-28|FR1461646A| FR3029173B1|2014-11-28|2014-11-28|DEVICE AND METHOD FOR UNLOCKING A FEEDING DEVICE|
    JP2017528495A| JP6847832B2|2014-11-28|2015-11-23|Fuel supply equipment locking and equipment|
    US15/529,836| US10717552B2|2014-11-28|2015-11-23|Device and locking of a fueling device|
    RU2017122444A| RU2017122444A3|2014-11-28|2015-11-23|
    PCT/FR2015/053168| WO2016083713A1|2014-11-28|2015-11-23|Device and locking of a fueling device|
    EP15817445.8A| EP3224144B1|2014-11-28|2015-11-23|Device and locking of a fueling device|
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