• 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:
    locking device / mechanical separator by rotation, comprising a main body (1), integral with a first system, provided with an actuator (2) for actuating in rotation a rotating rod (3) inserted in the main body; and having a receptacle (4) secured to a second system to be temporarily attached to the first system; for which the rotary rod is movable in translation under the action of a return spring (6) in the main body and is provided with a locking head (31) provided with a first locking recess (32). rotation, complementary to a second footprint (41) of said receptacle.
    公开号:FR3056967A1
    申请号:FR1659526
    申请日:2016-10-03
    公开日:2018-04-06
    发明作者:Pierre Courregelongue
    申请人:Airbus Safran Launchers SAS；
    IPC主号:
    专利说明:

    (57) mechanical locking / separating device by rotation, comprising a main body (1), integral with a first system, provided with an actuator (2) for actuating in rotation a rotary rod (3) inserted in the main body; and comprising a receptacle (4), integral with a second system to be temporarily fixed to the first system; for which the rotary rod is movable in translation under the action of a return spring (6) in the main body and is provided with a locking head (31) provided with a first recess (32) locking by rotation, complementary to a second imprint (41) of said receptacle.
    PROVISIONAL PUNCTUAL LINK DEVICE
    Field of the invention
    The present invention relates to a device for the temporary connection and separation of two systems, of the locker / separator type. Such a device can in particular be used in the aeronautical and space industry, for temporarily connecting two structural assemblies and for controlling their separation in a very short time. In the space sector, such devices are mounted, for example on the upper stages of launchers to fix the payloads or satellites, or can be used for the separation of two stages of a launcher or, for the cutting of the load-bearing structures of satellites. On the one hand, these devices are intended to ensure a connection between two elements so as to make them integral, on the other hand, they are intended to ensure a reliable separation of the two systems by limiting nuisances, such as solid pollution, gas, and induced shocks to system equipment. In addition, in the case of launchers, the locking / separating devices are able to withstand the longitudinal tensile and compressive forces between the two assembled elements.
    Technological background
    From a purely mechanical point of view, the separation of two space systems, such as a launcher and its payload, generally has two aspects:
    - A separation aspect proper, where it is first to break the mechanical connection between the payload and the launcher, we speak of unlocking;
    - An ejection aspect, because after a simple unlocking, if the payload is no longer linked to the launcher, it nonetheless remains attached to the launcher if no other action is taken. In principle, the payload must be given an impetus to move it away from the launcher, or even put it in its final orbit.
    The context in which the separation technology is situated is illustrated for example by the documents FR 2 876 985 Al, FR 2 902 472 Al and FR 2 947 808 Al. The first two documents relate to devices for releasing objects, the third concerns the separation of stages of launchers, and introduces the concept of soft separation.
    Separation can also be done in two ways:
    - By rupture or fusion of a part, for example as in documents FR 2 947 808 Al or Fr 2 661 464 Al
    - By dismantling a temporary link.
    The present invention is in this second scenario.
    The provisional connection systems with separation function used on a launcher generally require a high pre-tension in the assembly, in particular of several tens of thousands of Newton to ensure the correct maintenance of a payload during the various flight phases of a rocket.
    In addition, these systems are generally multipoint, generally 3 or 4 attachment points between the payload such as a satellite and the launcher. The operating time and above all the dispersions over this period must therefore be very low, of the order of a few ms, to guarantee the release and the correct placement of the payload.
    For these two reasons, significant unlocking effort due to the high pre-tension and reduced operating time, as well as for weight and space constraints, the existing devices are very often powered by a pyrotechnic charge and more rarely by capacity under pressure, pneumatic solution, or by an electric actuator.
    Many types of device exist and in particular the document US Pat. No. 4,671,715 A describes a temporary connection comprising a bolt with a head provided with an annular part which can be torn off under the action of a punch piston to achieve a shock-free break.
    Document FR 2 959 787 A1 relates for its part to a device for rapidly separating two sub-assemblies, under the action of a pyrotechnic gas generator. The device comprises a segmented nut comprising two half nuts held radially tight and separable by a movable release sleeve under the action of the gas generator.
    For the reasons mentioned above (significant pre-tension, short operating time, use of pyrotechnic charge), a problem to consider is to avoid a violent shock, detrimental to the payload, the launcher structures and the quality of the launch. post, when unlocking.
    These shocks are of 3 kinds:
    - Pyrotechnic shock due to the initiation of the pyrotechnic charge.
    - Mechanical end-of-travel shock for parts set in motion during device operation.
    - Mechanical shock due to the almost instantaneous release of the elastic energy of the pre-tension in the assembly during unlocking.
    The problem is to reduce the level of shocks existing within the provisional link mechanisms while maintaining pre-tensioning and unlocking time levels allowing use on multi-point satellite station system or systems requiring time. very short operation.
    Knowing that the existing technologies do not make it possible to reconcile strong pre-tension, low unlocking time and limitation of the shock levels in the payload separation mechanisms for launcher, the invention aims at a new unlocking device satisfying in terms cost, size and mass to limit separation shocks on the payload; this for rapid, punctual separation, that is to say according to localized attachment points; and low shock of payloads mounted on civilian or military launchers.
    In addition, a separation mechanism must preferably guarantee mounting without access to the second face of the payload, limit as much as possible the residual elements on the payload after separation, be as light as possible and compact in the sense that the stroke of the 'retracting element is substantially equal to its height and that the diameter of the body of the device is substantially that of the attachment to the payload.
    Another objective is to achieve a reduced operating time if possible less than 10 ms with an associated dispersion of the order of a millisecond, to have a reduced shock level and to have mechanical strength and pre-tension in the important assembly and stabilized over time.
    Brief description of the invention
    In this context, the present invention provides a mechanical locking / separating device by rotation, comprising a main body, integral with a first system, provided with an actuator for actuating in rotation a rotary rod inserted in the main body; and comprising a receptacle, integral with a second system to be temporarily fixed to the first system; for which the rotary rod is movable in translation under the action of a return spring in the main body and is provided with a locking head provided with a first rotation locking impression, complementary to a second impression locking said receptacle.
    According to a particular embodiment, the actuator is a pyrotechnic actuator of the pyro-piston type coupled to the rod by means for transforming a linear movement of the pyro-piston into a rotary movement of the rod.
    The actuator is advantageously coupled to the rod by means of a rotary unlocking ring.
    The rotary ring is advantageously provided with an actuating finger, the actuator comprising a fork for operating the finger.
    The ring and the rod preferably include engagement stops at the end of an angular zone of free travel.
    The rod is advantageously movable in translation in the main body between a retracted position for relaxing the spring and releasing the receptacle and an advanced position for compressing the spring and engaging with the receptacle.
    According to a first embodiment of the first and second locking imprints, the head of the rod comprises at least one quarter-turn imprint, the receptacle comprising at least one lug complementary to the imprint.
    According to a second embodiment, the head of the rod has a conical helical termination, the receptacle comprising a conical helical thread complementary to said termination.
    According to a third embodiment, the head of the rod comprises at least one lug, the receptacle comprising an opening for passage of the lug and a housing for retaining the lug angularly spaced.
    According to a fourth embodiment, the head of the rod and the receptacle each comprise an interrupted thread making toothed angular sectors and smooth angular sectors, the facing of the toothed sectors of the head and of the receptacle locking the head in the receptacle , the facing of the toothed sectors and of the smooth sectors freeing the head of the receptacle.
    According to a particular embodiment, the locking / separating device comprises an intermediate structure interposed between the receptacle and the main body.
    According to a preferred embodiment, the rod comprises at its end opposite the head means for tensioning the assembly of the main body and the receptacle.
    The invention further provides a launcher satellite comprising at least one device according to any one of the preceding claims for which the launcher is the first system and the satellite is the second system.
    The invention provides a method of assembling a satellite on a launcher equipped with devices according to the invention comprising the steps of:
    placing the rod in the retracted position;
    positioning a tensioning means at a threaded end of the rod opposite the head;
    installation of the satellite on the launcher structure by aligning the receptacles with the rods of the lockers / separators.
    pushing the rods manually or with a tool in the receptacle until the rod head is fully inserted in the receptacle;
    rotation of the rod by an angle necessary to engage the complementary locking imprints of the rod and of the receptacle;
    tensioning of the rod by tightening the means of tensioning the rod.
    Brief description of the drawings
    Other characteristics and advantages of the invention will become apparent on reading the following description of a nonlimiting example of embodiment of the invention with reference to the drawings which represent:
    In Figure 1: a view in perspective of a device according to the invention; in figure 2: a view in perspective bursts of device of Figure 1; in figure 3 a detail in perspective of the mechanism of
    locking / unlocking of the device of Figure 1;
    in Figure 4 a perspective view of unlocking means of the device of Figure 1;
    in FIGS. 5A to 5C: top views in section of elements of the unlocking device of FIG. 4;
    in Figures 6A and 6B: side sectional views of the device of Figure 1 respectively in the locked position and after separation;
    in FIGS. 7A, 7B: a perspective view of a first embodiment of locking means respectively in the locked position and in the unlocked position;
    in Figures 8A, 8B: a perspective view of a second embodiment of locking means respectively in the locked position and in the unlocked position;
    in Figures 9A, 9B: a perspective view of a third embodiment of locking means respectively in the locked position and in the unlocked position;
    Figures 10A, 10B: a perspective view of a fourth embodiment of locking means respectively in the locked position and in the unlocked position.
    Detailed description of embodiments of the invention
    The device of the invention finds particular use in the temporary assembly of a payload such as a satellite and a launcher.
    The device as shown by way of nonlimiting example in the drawings comprises, as shown in particular in FIG. 1, a first male part, the locker / separator comprising a main body 1 fixed on a first system such as the structure of a launcher, and a second female part comprising a receptacle 4 secured to a second system such as a payload and in particular a satellite.
    The device of the invention locks and unlocks to separate the systems by rotation.
    To do this, the receptacle is fixed to the payload while respecting a precise angular orientation relative to the orientation of the main body of the device.
    According to FIG. 2, the mechanical locking / separating device by rotation, comprising the main body 1, is provided with an actuator 2 for actuating in rotation a rotary rod 3 inserted in the main body.
    The rod 3 is used for fixation and at locking of receptacle on the body main and fits into the receptacle 4. According to Figure 3, the rod is fitted with a head 31 of locking provided with a first footprint 32 of
    locking by rotation, complementary to a second cavity 41 of said receptacle.
    According to this example shown in FIGS. 7A in the locked position and 7B in the unlocked position, the locking imprints are of the quarter-turn bayonet type with on the rod an imprint 321 comprising an entry groove 321a along the axis of the rod and a housing 321b at 90 ° to the axis of the rod laterally extending the groove receiving a pin 411 forming the locking impression of the receptacle.
    Returning to FIG. 3 and with reference to FIG. 4, a device unlocking mechanism comprises a rotary ring 26 which is adapted to drive the rod in rotation in the unlocking direction by means of engagement stops 27, 33 under the action of an actuator 2.
    According to the example, the ring carries two first opposite stops 27 arranged in a central cylindrical housing of the ring. The housing receives the rod and its engagement stops 33.
    The stops of the ring are arranged 180 degrees from each other and separated by two angular zones of free travel of the stops 33 of the rod.
    When the ring is in the rod locking position, the latter can be positioned in an angular position of introduction into the receptacle 4 for which the pins 41 are received in the entry groove of the impression 32 of the rod then be turned to lock the pins in the housings at the end of grooves and lock the receptacle on the main body.
    In this position the stops 33 of the rod come into contact with the stops 27 of the ring.
    FIG. 4 shows the ring 26 provided with a finger 25 which is operated by the actuator 2 by means of a drawer 23 provided with forks 24 between which the finger is positioned.
    Returning to FIG. 2, the actuator 2 of the example is of the pyro-piston type comprising a gas generator body 2a carrying a pyrotechnic charge, a cylinder 2b in which a piston 21 is capable of sliding during the explosion of the pyrotechnic charge. The piston also shown in Figure 5A has a termination adapted to push the drawer 23 carrying the fork 24 which moves the ring from the locking position shown in Figure 5B to the unlocking position shown in Figure 5C and rotates the rod releasing the pins of the receptacle from the housings of the bayonet locking device as in the position in FIG. 7B.
    The rotary rod is movable in translation under the action of a return spring 6 in the main body as shown in Figures 6A and 6B.
    In FIG. 6A which corresponds to the angular position of the rod of FIGS. 5B and 7B, the device is locked and the spring is compressed. When the device is unlocked by rotating the ring and the rod towards the positions of FIGS. 5C and 7A, the rod is no longer retained in the receptacle 4 and retracts into the body under the action of the spring 6 which relaxes as shown in Figure 6B. The receptacle 4 is then released.
    According to the example shown, the device comprises an intermediate structure 7 interposed between the receptacle 4 and the main body of the locker / separator for the needs of the placing of the payload, for example when there is an ejector plate in the probes requiring roll.
    According to FIGS. 6A, 6B in particular, the locker / separator comprises a bottom 8 secured to the main body 1 by a nut 9 and comprises a compression cell 10 provided with a force sensor.
    In the locked position, the receptacle is pressed against the main body possibly via the intermediate structure 7 by means of clamping means constituted here by a nut 34a, a lock nut 34b and a thread 35 on the rod.
    Once the head of the rod is locked in the receptacle 4, the nut 34a is tightened which compresses the bottom assembly 8, main body 1, possible intermediate structure 7 and receptacle 4 and puts the device under tension.
    The assembly of a satellite on the launcher equipped with devices of the invention is carried out as follows:
    Firstly, the rod 3 of the locker / separator is in the retracted position under the action of the spring 6.
    The tensioning nut 34a is loosened and positioned at the lower end of the thread 35 of the rod so that it does not interfere with the assembly phase.
    The satellite is placed on the launcher structure by aligning the receptacles 4 with the rods 3 of the lockers / separators.
    The locker / separator rod is pushed in manually or with a tool, if there is a recoil spring or a rod braking system, in the receptacle until the quarter-turn stops 41 are in contact at the bottom of grooves or grooves 321a of the rod.
    The locker / separator rod is turned by the angle necessary to position the quarter-turn stops below the shoulder of the rod in the housings 321b. The unlocking ring 26 which is provided with the lights 28 in line with the stops 33 for unlocking the rod is not rotated by the rod during this phase and remains in the locked position.
    The rod is then tensioned by tightening the nut 34a until the target pre-tension is obtained. The nut is then made integral with the rod by means of a lock nut 34b or any other anti-rotation device.
    For unlocking, in the example shown, the initiation of a pyrotechnic charge generates an increase in pressure inside the chamber 2b of the pyro-piston 21 which causes the displacement of the piston 21 and the displacement of the tie rod or drawer 23.
    The linear support of the fork 24 of the tie rod on the unlocking finger 25 causes the rotation of the ring 26 in pivot around the body of the locker / separator.
    The rotation of the unlocking ring causes that of the rod, the stops 27 of the ring pushing on the stops or keys 33 of the rod. The rotation of the ring and of the rod, by 90 ° in the example shown, stops after the various mobile elements have been brought into abutment.
    The pins 41 of the quarter-turn imprints are then released from the housings 321b of the rod, which allows the latter to retreat. The retraction of the rod can be carried out in several ways:
    By the residual pre-tension in the rod when the quarter-turn stops are released, the rod then behaves like a spring which recedes by itself.
    By a compression spring 6 installed inside the locker / separator or outside the locker / separator at the rear nut.
    By using the compressed gases still available inside the pyropiston chamber to generate thrust on the locker / separator rod. This solution requires sealing the internal volume of the locker / separator body, adding a gas passage between the pyro-piston and a rod pushing chamber in the main body and associating a piston device with the rod. .
    It should be noted that the pyrotechnic device producing the actuator 2 shown can be replaced by other sources of energy such as electrical, mechanical, pneumatic or hydraulic energy.
    As seen above, the locking device between the head and the receptacle of FIGS. 7A, 7B is a bayonet device; the head of the rod comprising at least one impression with a quarter-turn locking groove 321, the receptacle comprising at least one lug 411 complementary to the impression.
    The locking part between the rod and the receptacle can however be produced by other means than a bayonet device and in particular in FIGS. 8A, 8B is shown a second embodiment of locking means for which the head of the rod and the receptacle each comprise an interrupted thread producing toothed angular sectors 322a, 412a and smooth angular sectors 322b, 412b. According to FIG. 8A for which a part of the receptacle is cut, the facing of the toothed sectors of the head and of the receptacle lock the head in the receptacle by engagement of the teeth. According to FIG. 8B, the facing of the toothed sectors and of the smooth sectors release the head of the receptacle.
    According to this example, the head and the receptacle each comprise two smooth sectors and two toothed sectors interposed at 90 °.
    A third embodiment is shown in Figures 9A, 9B. According to this embodiment, the head of the rod comprises at least one lug 323 while the receptacle comprises a lumen 413a for passage of the lug and a housing 413b for retaining the lug angularly spaced.
    In FIG. 9A, the lug is positioned on its retaining housing 413b and the head is locked in the receptacle 4, in FIG. 9B, the lug is placed facing the light 413a and the head can be released from the receptacle.
    According to this example, two lugs are arranged at 180 ° on the rod and the receptacle comprises two 180 ° housings and two 180 ° lights interposed to allow locking unlocking under a rotation angle of the rod of 90 °.
    A fourth embodiment is shown in FIGS. 10A, 10B, the head of the rod comprises a conical helical termination 324 and the receptacle comprises a conical helical thread 414 complementary to said termination.
    In the latter case, the rotation is no longer of the order of 90 ° but of several turns, for example between 3 and 6 depending on the pitch of the screw and the angle of the cone to allow the rod to be released. relative to the receptacle.
    In such a case, the movement transformation means which allow the actuator to turn the rod may possibly be produced in the form of a rack on tie rod or drawer 23 acting on a toothed pinion around the rod.
    Thus, for locking / unlocking the head in the receptacle, the rotation can vary from a few tens of degrees to several times 360 ° depending on the positioning of the locking means.
    The principle of unlocking by rotation simplifies the implementation of the device. The mechanism is tensioned by a screw-nut system 34a, 35 at the rear of the rod which allows fine control of the preload in the assembly, by torque tightening, angle tightening, measurement of the force in the rod by ultrasonic measurement or by cell with strain gauge 10. If the precision sought on the pre-tension is not too high for certain applications, it is possible to control the quality of the assembly by adjusting and controlling the geometric dispersions of the parts to be assembled, locker / separator, payload and possibly intermediate structure. The device will then behave like a simple bayonet connector which it suffices to push into the payload and rotate 90 ° or the optimum angle value to ensure the elements are held together.
    The mechanism of the invention, while remaining in short operating times, makes it possible to significantly reduce shocks by using the following principles:
    - Unlocking by rotation of the parts, instead of translation by spacing or recoil of elements, which removes the end of stroke shocks. In addition, the mechanism is designed so that the rod retracts towards the launching structure and no mobile element is projected inside the satellite or the probe.
    - A rotation of the ring and a displacement of the piston parallel to the positioning plane of the satellite, which avoids generating detachments from the launcher / satellite contact area as on existing lockers / separators, such detachments being detrimental for the quality the payload station.
    In addition, the contact plane of the rotation stops can be tilted a few degrees, which gradually reduces the pre-tension in the assembly during the rotation of the system so as to gradually release the elastic energy present in the rod.
    Advantageously, the system is optimized in terms of stiffness of the assembly, unlocking angle and inclination of the contact plane of the stops so that there is no more pre-tension in the rod at the end of rotation.
    One can however, alternatively, keep part of the initial pre-tension at the end of rotation when the male part of the female part of the rotation device is released. In this case, this residual energy is used to generate the recoil of the rod without requiring any additional recoil device such as a spring, gases from the pyro-piston or the like.
    Finally, the inclination of the abutment support plane can be sufficiently small, for example of the order of the pitch of an aeronautical screw, so as not to risk loosening the rod under a dynamic atmosphere and in particular in the event of vibrations and shocks. An additional means of braking the rod, leaf spring, shear pin, seal stressing the rod on the body of the locker / separator can however be installed in the mechanism if necessary.
    The mechanism is designed with a reduction gear as a function of the displacement distance of the piston and the length of the finger of the ring, which reduces the energy required to initiate and maintain the unlocking. This makes it possible to limit the amount of pyrotechnic charge necessary for triggering the device and therefore the associated pyrotechnic shock.
    It should be noted that the fork 24 and finger 25 system can be modified for example by using a pin on the drawer which moves in a groove in the finger or as seen above by a rack system.
    According to an alternative embodiment, the pyro-piston is replaced by a mechanical motorization of the compression spring, torsion bar or other hydraulic, electric or pneumatic device type.
    This rotation solution also has other advantages. It makes it possible to produce a device composed of fewer parts than existing systems and thereby reduce the cost of the mechanism while increasing its intrinsic reliability since the effort chain between the launcher structure and the payload is composed of a minimum of parts.
    The system, also thanks to unlocking by rotation rather than by translation, also makes it possible to be very competitive in terms of mass and size, in particular longitudinally or in diameter at the level of the payload interface, whether on the launcher side or on the side. payload. It may even be envisaged to merge the body of the locker / separator with the carrier structure of the launcher to further gain in compactness and mass, which most of the existing mechanisms do not allow, by virtue of their implementation and their complexity.
    Finally, still on the aspect implemented, this system does not generate damage to the adjacent structures and the mechanism itself during unlocking. It is therefore resettable, reusable and can be a source of
    It can also have 10 cost saving lockers / separators in the context of spacecraft separation systems or reusable launcher stages.
    Excluding space applications, the device of the invention can be envisaged on applications requiring rapid unlocking, low shock, high pre-tension and high level of reliability, for example on fasteners between military or civil aircraft and a load. useful to release, missile or space plane for example.
    be considered to convert this into a device combining the functions of separation and ejection using the setting in motion of the rod for the ejection of the payload to be stationed.
    权利要求:
    Claims (13)
    [1" id="c-fr-0001]
    1 - Locking device / mechanical separator by rotation, comprising a main body (1), integral with a first system, provided with an actuator (2) for actuating in rotation a rotary rod (3) inserted in the body main; and comprising a receptacle (4), integral with a second system to be temporarily fixed to the first system; characterized in that the rotary rod is movable in translation under the action of a return spring (6) in the main body and is provided with a locking head (31) provided with a first indentation (32) of locking by rotation, complementary to a second cavity (41) of said receptacle.
    [2" id="c-fr-0002]
    2 - Locking device / mechanical separator according to claim 1 for which the actuator (2) is a pyrotechnic actuator of pyro-piston type coupled to the rod by means (23, 24, 25, 26) for transforming a movement linear movement of the pyro-piston in a rotary movement of the rod.
    [3" id="c-fr-0003]
    3 - Locking device / mechanical separator according to claim 1 or 2 for which the actuator (2) is coupled to the rod by means of a rotary unlocking ring (26) provided with an actuating finger (25 ), The actuator comprising a fork (24) for operating the finger.
    [4" id="c-fr-0004]
    4 - Locking device / mechanical separator according to claim 3 for which the ring (26) and the rod (3) have engagement stops (27, 33) at the end of an angular zone of free travel.
    [5" id="c-fr-0005]
    5 - Locking device / mechanical separator according to any one of claims 1 to 4 for which the rod (3) is movable in translation in the main body between a retracted position of relaxation of the spring (6) and release of the receptacle (4 ) and an advanced position for compression of the spring and engagement with the receptacle.
    [6" id="c-fr-0006]
    6 - Locking device / mechanical separator according to any one of the preceding claims, in which the head of the rod comprises at least one quarter-turn impression (321), the receptacle comprising at least one lug (411) complementary to the impression.
    [7" id="c-fr-0007]
    7 - Locking device / mechanical separator according to any one of claims 1 to 5 for which the head of the rod and the receptacle each comprise an interrupted thread producing toothed angular sectors (322a, 412a) and smooth angular sectors (322b, 412b), the facing of the toothed sectors of the head and of the receptacle locking the head in the receptacle, the facing of the toothed sectors and of the smooth sectors releasing the head of the receptacle.
    [8" id="c-fr-0008]
    8 - Locking device / mechanical separator according to any one of claims 1 to 5 for which the head of the rod comprises at least one lug (323, the receptacle comprising a lumen (413a) for passage of the lug and a housing ( 413b) retaining the angularly spaced lug.
    [9" id="c-fr-0009]
    9 - Locking device / mechanical separator according to any one of claims 1 to 5 for which the head of the rod has a conical helical termination (324), the receptacle comprising a conical helical thread (414) complementary to said termination.
    [10" id="c-fr-0010]
    10 - Locking device / mechanical separator according to any one of the preceding claims comprising an intermediate structure (7) interposed between the receptacle (4) and the main body (1).
    [11" id="c-fr-0011]
    11 - Locking device / mechanical separator according to any one of the preceding claims for which the rod (3) comprises at its end opposite to the head means (34a, 34b, 35) for tensioning the assembly of the main body and the receptacle.
    [12" id="c-fr-0012]
    12 - Satellite assembly on launcher comprising at least one device according to any one of the preceding claims for which the launcher is the first system and the satellite is the second system.
    [13" id="c-fr-0013]
    13 - Method of assembling a satellite on a launcher equipped with devices according to any one of claims 1 to 10 comprising the steps of:
    placing the rod (3) in the retracted position; positioning a tensioning means (34a) at a threaded end (35) of the rod opposite the head (31);
    installation of the satellite on the launcher structure by aligning the receptacles (4) with the rods (3) of the lockers / separators.
    insertion of the rods manually or with a tool in the receptacle until complete insertion of the rod head (31) in the receptacle (4);
    rotation of the rod by an angle necessary to engage the complementary locking imprints (32, 41) of the rod and of the receptacle;
    tensioning the rod by tightening the means (34a) for tensioning the rod.
    1/9
    Fig. 1
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3519300B1|2021-12-22|Coupling device for provisional punctual connection
    EP0454564B1|1994-03-09|Quick-release locking mechanism for use in spacecraft
    EP0441669A1|1991-08-14|System for retaining a number of articulated elements on a spacecraft
    EP3563075A1|2019-11-06|Actuator with passive locking
    FR2902472A1|2007-12-21|Compact temporary mechanical joining device, e.g. for joining satellite to spacecraft, includes segmented annular device with gripping heads, bolting ring and fixed and movable supports
    EP1234983B1|2009-04-22|Compensated actuator with optimised power
    EP0296936A1|1988-12-28|Drive mechanism for fast and controlled separation of two coupled elements
    FR2943330A1|2010-09-24|VARIABLE MECHANICAL GAIN COUPLING SYSTEM
    EP0516519B1|1995-04-26|Selflocking, reversible mechanism for the deployment of a rocket nozzle cone
    EP0836001B1|2003-04-16|Rocket nozzle with ejectable inserts
    EP3043966B1|2021-08-18|Mechanism for locking/unlocking a torque wrench
    CA2063700A1|1992-09-29|Device for deploying a payload from a spacecraft
    FR2577885A1|1986-08-29|AIRCRAFT EJECTOR TRIGGERING DEVICE
    EP3575224A1|2019-12-04|Punctual electromechanical separating system
    EP3344547A1|2018-07-11|Method for the linear separation and connection of two elements
    FR2876985A1|2006-04-28|Object e.g. satellite, connection device for e.g. launch vehicle`s structure, has connection unit and locking unit that are moved to respectively lead to electrical disjunction and mechanical unlocking between object and structure
    FR2973778A1|2012-10-12|Resettable locking and unlocking device for e.g. locking antenna mast in folded state during launching phase of artificial satellite, has support lip whose spherical cup shaped recesses receive balls in extended position of moving element
    EP0354088B1|1992-07-15|Device for opening projectile fins
    EP0275766B1|1990-08-29|Brake mechanism for a deployable wing and guided missile therewith
    WO2018065703A1|2018-04-12|Device for attaching a booster
    FR3109928A1|2021-11-12|Improved deployment device for nano-satellite
    EP0628478A1|1994-12-14|Device for ejecting removable object attached to a structure
    FR3061527A1|2018-07-06|PASSIVE BALL BEARING ACTUATOR
    WO2021209724A1|2021-10-21|Low-shock and reusable retention and release device
    EP0633446A1|1995-01-11|Pyrotechnic device for ejecting articles
    同族专利:
    公开号 | 公开日
    WO2018065704A1|2018-04-12|
    EP3519300A1|2019-08-07|
    EP3519300B1|2021-12-22|
    FR3056967B1|2019-06-14|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP0699581A1|1994-08-30|1996-03-06|AEROSPATIALE Société Nationale Industrielle|Device for the releasable connection of two objects, especially in the field of space technology|
    FR2876985A1|2004-10-21|2006-04-28|Eads Space Transp Sa Sa|Object e.g. satellite, connection device for e.g. launch vehicle`s structure, has connection unit and locking unit that are moved to respectively lead to electrical disjunction and mechanical unlocking between object and structure|
    US4671715A|1986-04-03|1987-06-09|Hi-Shear Corporation|Lesser shock separation fastener|
    FR2661464B1|1990-04-27|1992-08-14|Aerospatiale Ste Nat Indle|DEVICE FOR TEMPORARILY SUBJECTING AN OBJECT TO A SUPPORT WITH A TRACTION CALIBRATED BREAK AREA.|
    FR2902472B1|2006-06-14|2008-12-05|Eads Space Transp Sas Soc Par|TEMPORARY MECHANICAL JUNCTION DEVICE OF AN OBJECT ON A STRUCTURE|
    FR2947808B1|2009-07-09|2011-12-09|Astrium Sas|SOFT LINEAR SEPARATION DEVICE OF A FIRST PART AND A SECOND PART|
    FR2959787B1|2010-05-07|2012-06-08|Pyroalliance|UNLOCKING DEVICE TRIGGERED, CONNECTING TWO DETACHABLE SUB-ASSEMBLIES|US10562646B2|2016-04-21|2020-02-18|Lockheed Martin Corporation|Single-point release mechanism for spacecraft|
    US10697519B2|2017-04-20|2020-06-30|Lockheed Martin Corporation|Solar array positioning actuator for spacecraft|
    CN112343900A|2020-10-28|2021-02-09|北京特种机械研究所|Locking device of butt joint transfer trolley|
    CN112660428A|2020-12-30|2021-04-16|中国航天科工集团八五一一研究所|Space low-impact separation unlocking mechanism|
    法律状态:
    2017-10-27| PLFP| Fee payment|Year of fee payment: 2 |
    2018-04-06| PLSC| Publication of the preliminary search report|Effective date: 20180406 |
    2018-10-31| PLFP| Fee payment|Year of fee payment: 3 |
    2019-10-28| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 5 |
    2021-10-21| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1659526A|FR3056967B1|2016-10-03|2016-10-03|PROVISIONAL PITCH LINK DEVICE|
    FR1659526|2016-10-03|FR1659526A| FR3056967B1|2016-10-03|2016-10-03|PROVISIONAL PITCH LINK DEVICE|
    EP17786973.2A| EP3519300B1|2016-10-03|2017-09-29|Coupling device for provisional punctual connection|
    PCT/FR2017/052674| WO2018065704A1|2016-10-03|2017-09-29|Temporary connection device|
    [返回顶部]