• 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:
    A method of arranging a plurality of spacecraft (SAT) comprising the steps of: arranging a first layer of spacecraft (SAT1 - SAT4) around a dispatcher; attaching the spacecraft of said first layer to said dispenser by means of mechanical interfaces extending in a radial direction; arranging a second layer of spacecraft (SAT5-SAT12) around said first layer and said dispenser, the spacecraft of said second layer being arranged to protrude, in a longitudinal direction of said cap, spacecraft from the first layer who interpose themselves between them and dispense it; securing the spacecraft of said second layer to said dispenser by means of mechanical interfaces extending in a radial direction a distance greater than that of the mechanical interfaces of the first layer; and arranging the assembly thus obtained, under the cap (CL) of a launcher. Assembly of spacecraft that can be obtained by such a method and dispense suitable for such an assembly.
    公开号:FR3035076A1
    申请号:FR1500801
    申请日:2015-04-17
    公开日:2016-10-21
    发明作者:Gilles Fernandez；Jean Claude Sost
    申请人:Thales SA；
    IPC主号:
    专利说明:

    [0001] The invention relates to the field of astronautics, and more particularly to the launching of the invention, the invention relates to the field of astronautics, and more particularly to the launching of a helicopter. spacecraft such as artificial satellites. More particularly, it relates to a method of arranging a plurality of spaceships under the cap of a launcher, on an assembly that may result from such a method and on a spacecraft dispenser adapted to the realization of such a assembly. The invention applies in particular to the simultaneous launching of a plurality of artificial satellites intended to form a constellation. In order to make constellations comprising a large number of identical artificial satellites of small dimensions (mass typically less than 500 kg, or even 200 kg), it is known to proceed with group launches. Several satellites, or even several tens in some cases, must then be arranged under the cover of the same launcher to be put into orbit simultaneously. These satellites are attached to a "dispenser", which is a tubular element placed along the axis of the launcher cap, equipped with mechanical interfaces for securing satellites; thus obtaining a rigid assembly which can be considered as constituting the launcher payload. In space, after release of this assembly, pyrotechnic charges disassociate the satellites of the dispenser. In addition spring "ejecting fingers" integrated in the mechanical interfaces, impart to the satellites a thrust in a radial direction, so as to disperse the cluster of satellites that has just been released. FIG. 1 shows an assembly of SAT satellites under the cap CL of a launcher according to the prior art. The dispenser D has a cylindrical shape, with an axis z coinciding with the longitudinal axis of the cap. The satellites are arranged on the surface of the dispenser, where they form a plurality of stages E1, E2, E3, E4 aligned in the axial direction, or longitudinal. Each stage is constituted by a ring of satellites - 18 in the example 3035076 2 considered - surrounding the dispense. The satellites of the different stages are aligned in the longitudinal direction, although this is not essential. In the example of Figure 1, radial partitions are provided to separate the satellites of each floor, but this is optional.
    [0002] The arrangement of FIG. 1 allows the grouped launching of 72 satellites, provided that their volume is sufficiently small to meet the congestion requirements of the cap. In the case of a Falcon 9 launcher, this presupposes that the dimensions of each satellite do not exceed 1000x500x500mm. If the satellites are larger in size, it is necessary to reduce the number and therefore, for a given constellation, to increase the number of launches, which leads to a very significant extra cost. The object of the invention is to allow a more efficient use of the volume available under the cover, and therefore to increase the number of satellites that can be launched simultaneously or - in an equivalent manner - to relax the constraints on their dimensions. According to the invention this object is achieved by arranging the satellites in two layers around the dispenser, and using a modified dispenser having mechanical interfaces of at least two different types, distinguished by their radial extension. Thus, an object of the invention is a method of arranging a plurality of spacecraft beneath a launcher cap, comprising the steps of: arranging a first layer of spacecraft around a dispenser having a longitudinal axis; attaching the spacecraft of said first layer to said dispenser by means of mechanical interfaces extending in a radial direction; arranging a second layer of spacecraft 30 around said first layer and said dispenser, the spacecraft of said second layer being arranged to protrude, in a longitudinal direction of said cap, space vessels from the first layer; interpose themselves between them and dispense it; fixing the spacecraft of said second layer to said dispenser by means of mechanical interfaces extending in a radial direction over a distance greater than that of the mechanical interfaces of the first layer; and arranging the assembly thus obtained, comprising the dispenser and the spacecraft, under the cap of a launcher with the longitudinal axis of the dispenser aligned with that of the cap.
    [0003] According to particular embodiments of such a method: both said first layer and said second layer may comprise a plurality of longitudinally spaced stages of the dispenser, each said stage consisting of a plurality of arranged spacecraft in a ring around said dispenser, each stage 15 of said second layer surrounding a corresponding stage of said first layer. Said spacecraft may be substantially identical to each other, the spacecraft of the second layer being rotated relative to those of the first layer about respective radially oriented axes. More particularly, said spacecraft can have an elongate shape along a so-called main axis and the spacecraft of the first layer can be arranged with their main axis oriented in a longitudinal direction of the dispenser and those of the second layer be arranged with their main axis. oriented perpendicular to the longitudinal direction of the dispenser. Another object of the invention is an assembly of spacecraft comprising a first set of spacecraft arranged around a dispenser having a so-called longitudinal axis to form a first layer of spacecraft, said spacecraft being fixed to said dispenser by means of mechanical interfaces extending in a radial direction from said dispenser; characterized in that it also comprises a second set of spacecraft arranged around said first layer and said dispenser to form a first layer of spacecraft, the spacecraft of said second layer being arranged to protrude, in the direction of said longitudinal axis, spaceships of the first layer interposed between them and dispensed and being fixed to said dispenser by means of mechanical interfaces extending in said radial direction over a distance greater than that of the mechanical interfaces of the first layer. According to particular embodiments of such an assembly: Both said first layer and said second layer of spacecraft may comprise a plurality of stages spaced in the direction of said longitudinal axis of the dispenser, each said stage consisting of a plurality of spacecraft arranged in a ring around said dispenser, each stage of said second layer surrounding a corresponding stage of said first layer. Said spacecraft may be substantially identical to each other, the spacecraft of the second layer being rotated relative to those of the first layer about respective radially oriented axes. More particularly, said spacecraft 20 may have an elongated shape along a principal axis and the spacecraft of the first layer may be arranged with their main axis oriented in a longitudinal direction of the dispenser and those of the second layer may be arranged with their axis. principal oriented perpendicular to the longitudinal direction of the dispenser.
    [0004] Yet another object of the invention is a spacecraft dispenser comprising an elongated central body along a so-called longitudinal axis and a plurality of mechanical interfaces for securing spacecraft extending radially from said central body. , said mechanical interfaces being arranged in longitudinally spaced stages, characterized in that it has an alternation of sets of mechanical interface stages extending radially over a first distance and 3035076 sets of interface stages. mechanical devices extending radially over at least a second distance, greater than said first distance. Other characteristics, details and advantages of the invention will emerge on reading the description given with reference to the appended drawings given by way of example and which represent, respectively: FIG. 1, described above, an assembly of spacecraft under cuff according to the prior art; FIGS. 2A and 2B, a stage of an assembly of spacecraft according to one embodiment of the invention; FIGS. 3A and 3B, a space ship dispenser according to an embodiment of the invention; and FIGS. 4A and 4B, two spacecraft assemblies according to respective embodiments of the invention. In the following, "longitudinal direction" (or "longitudinal axis") will be understood to mean a direction (respectively, an axis) parallel to the axis of the dispenser (and of the cap), and therefore to the direction of advancement of the launcher. The term "radial direction" means the direction of a line starting from the axis of the dispenser and extending perpendicular to the longitudinal direction. The term "spacecraft" may refer to an artificial satellite or any other spacecraft, such as an interplanetary probe. In the following, the terms "satellite" and "spaceship" will be used interchangeably. Figs. 2A and 2B are, respectively, a plan and elevation view of a stage comprising a spacecraft assembly according to one embodiment of the invention. This stage comprises 12 identical spacecraft - typically satellites - designated by the references SAT1 to SAT12. These satellites have an elongate shape, approximately in right pavement. The dispenser is not represented so as not to overload the figures. It can be seen that the satellites are arranged to form two concentric rings: an inner ring, formed by satellites SAT1 to SAT4, which are arranged with their main dimension (i.e., their longest side) oriented in a tangential direction, which is perpendicular to both the z axis of the cap and a radial direction of the x, y plane; and an outer ring, formed by satellites SAT5 to SAT12, which are arranged with their main dimension oriented in a longitudinal direction, i.e. parallel to the z axis. In other words, the satellites of the outer ring are rotated 90 ° about an axis oriented radially with respect to those of the inner ring. This rotation allows the satellites of the outer ring to be attached to the dispenser by mechanical interfaces IM - shown only partially in Figures 2A, 2B and more fully in Figures 3A, 3B. Indeed, since their main dimension extends in a longitudinal direction, their mechanical interfaces can pass "above" and "below" satellites of the inner ring whose longitudinal direction extends in a plane xy perpendicular to this longitudinal direction. As in the case of FIG. 1, a spacecraft arrangement according to the invention may comprise a plurality of stages - generally, but not necessarily, identical - spaced along the longitudinal direction (z-axis); in some cases, however, the arrangement may comprise a single stage. Thus, a satellite layer is generally formed by a plurality of rings of the same rank spaced along the z-axis, but may sometimes consist of a single ring of a single stage. FIGS. 3A and 3B are views, respectively in elevation and front view, of a dispenser D suitable for implementing the invention. This dispenser comprises a tubular body CT, whose axis z is intended to be aligned with that of the launcher cap, on the surface of which are fixed mechanical interfaces extending in a radial direction. These interfaces are of three types: the IM1 interfaces extend in the radial direction over a relatively small distance - typically a few centimeters: they are indeed intended for fixing the satellites 30 of the first layer (SAT1 to SAT4 in the embodiment of Figures 2A, 2B); the interfaces IM2 extend in the radial direction over a greater distance, typically several decimetres: they are in effect intended for fixing the satellites of the second layer (SAT5 to SAT12 in the embodiment of FIGS. 2A, 2B). It will be understood from FIGS. 3A and 2B that the radial extension of the interfaces IM2 is at least equal to that of the interfaces IM1 to which is added the length of the side of the satellites extending in the radial direction (the most small side in the embodiment of Figures 2A and 2B). Thus, the IM2 interfaces have a rod shape. Apart from this, they can be quite conventional and include, in particular, a pyrotechnic satellite release device and an ejection finger. It is important to note that the IM2 interfaces need not all be the same length, even if it simplifies the manufacture of the dispenser. For example, in the embodiment of FIGS. 2A and 2B, the mechanical interfaces IM2 associated with the satellites SAT5, SAT7, SAT9 and SAT 11 may be slightly longer than those associated with the satellites SATE, SATE, SAT10 and SAT 12. The interfaces IM3, which may be similar or identical to the IM1 interfaces, serve for the realization of the highest stages of the assembly, which will be described with reference to FIGS. 4A and 4B. The structure in stages of the assembly has repercussions on the arrangement of the mechanical interfaces IM1 and IM2. Thus it is possible to identify on FIG. 3A and 3B an alternation of sets of mechanical interface stages IM1 and IM2. More particularly, in the embodiment considered (see FIGS. 2A and 2B), each satellite is fixed by means of four mechanical interfaces corresponding to the corners of its rectangular face oriented towards the dispenser. Thus, the dispenser D has, except at the ends, an alternation of two IM1 interface stages - twice as many as the satellites of each stage of the inner layer - and two IM2 interface stages - twice as many. than the satellites on each floor of the inner layers. FIG. 4A illustrates an assembly according to a first embodiment of the invention, which can be housed under the cap of a Falcon launcher 9. This assembly comprises six stages (reference E) of 12 satellites having the structure illustrated in FIGS. 2A and 2B, plus a conventional single-layer stage comprising 4 satellites fixed by the IM3 interfaces and housed in the narrower upper part of the cap. It is therefore possible to simultaneously launch up to 76 satellites whose dimensions can reach 1300x980x545mm - that is to say a volume more than double 5 with respect to the satellites of the assembly of FIG. 1. FIG. 4B illustrates an assembly according to a second embodiment of the invention, which can also be housed under the cap of a Falcon launcher 9. This assembly comprises four stages (reference E) of 12 satellites having the structure illustrated in FIGS. 2A and 2B, plus one stage at 10 a layer of 6 satellites, fixed by the interfaces IM3, housed in the upper, narrower part of the cap. We can launch simultaneously up to 54 satellites, and their dimensions can reach 1700x780x600mm - that is to say a volume more than triple compared to the satellites of the assembly of Figure 1.
    [0005] The release of the satellites can be done as in the prior art; it will be necessary just to ensure that the pyrotechnic devices breaking the mechanical interfaces IM2 of the outer layer are triggered before those of the mechanical interfaces IM1 of the inner layer. The invention has been described with reference to particular embodiments, but its scope is more general. In particular: - The invention is generally suitable for the arrangement under cover, for their simultaneous launch, a plurality of spacecraft - typically but not necessarily satellites. It is not essential that these spacecraft be identical to each other, nor be intended to form a constellation. They may have different shapes from those of the embodiments described, and it is not always necessary for the spacecraft of the second layer to be rotated 90 ° with respect to those of the first layer: this depends on the shape of said spaceships. For example, if the spacecraft has a squared, square-based square shape with a square face oriented to dispense it, a rotation of 90 ° would be unnecessary while a rotation of 45 ° would be appropriate. This notion of rotation loses its interest if the spacecraft 3035076 9 of the second layer have a shape or dimensions different from those of the first layer. Moreover, the different stages may have an angular offset; in other words, each stage, or only some of them, can be rotated by a non-zero angle around the z-axis with respect to the adjacent stages. Coaxial layers of spacecraft may have structures different from those described. In particular, the number of spacecraft in each stage and in the entire assembly may be different from that of the examples described with reference to Figures 2A / 2B and 4A / 4B. The dispenser may have a structure different from that described with reference to FIGS. 3A and 3B. In the embodiments described, the spaceships are arranged on exactly two layers; the invention, however, has a more general scope and includes all arrangements comprising at least two layers. Indeed, in some cases it may be possible and appropriate to use an arrangement on three or more coaxial layers. In this case, the spacecraft of the different layers will be fixed to dispense with mechanical interfaces extending over increasing radial distances with the order of the layer.
    权利要求:
    Claims (9)
    [0001]
    REVENDICATIONS1. A method of arranging a plurality of spacecraft (SAT) under a launcher cap (CL), comprising the steps of: - arranging a first layer of spacecraft (SAT1 - SAT4) around a dispenser ( D) having a longitudinal axis (z); fixing the spacecraft of said first layer to dispense it by means of mechanical interfaces (IM1) extending in a radial direction; arranging a second layer of spacecraft (SAT5-SAT12) around said first layer and said dispenser, the spacecraft of said second layer being arranged to protrude, in a longitudinal direction of said cap, space vessels from the first layer that interpose between them and dispense it; fixing the spacecraft of said second layer to said dispenser by means of mechanical interfaces (IM2) extending in a radial direction over a distance greater than that of the mechanical interfaces of the first layer; and arranging the assembly thus obtained, including the dispenser and the spacecraft, under the launcher cap with the longitudinal axis of the dispenser aligned with that of the cap.
    [0002]
    The method of claim 1 wherein both said first layer and said second layer comprise a plurality of longitudinally spaced apart stages (E) of the dispenser, each said stage being comprised of a plurality of spacecraft arranged in a ring around said dispenser, each stage of said second layer surrounding a corresponding stage of said first layer. 30
    [0003]
    3. Method according to one of the preceding claims wherein said spacecraft are substantially identical to each other, the spacecraft of the second layer being rotated relative to those of the first layer about respective radially oriented axes.
    [0004]
    4. The method of claim 3 wherein said spacecraft have an elongated shape along a principal axis and wherein the spacecraft of the first layer are arranged with their main axis oriented in a longitudinal direction of the dispenser and those of the second layer. are arranged with their main axis oriented perpendicular to the longitudinal direction of the dispenser.
    [0005]
    5. A spacecraft assembly comprising a first set of spacecraft (SAT1 - SAT4) arranged around a dispenser (D) having a longitudinal axis (z) to form a first layer of spacecraft, said spacecraft being attached to said spacecraft dispensing by means of mechanical interfaces (IM1) extending in a radial direction from said dispenser; characterized in that it also comprises a second set of spacecraft (SAT5 - SAT12) arranged around said first layer and said dispenser to form a first layer of spacecraft, the spacecraft of said second layer being arranged to exceed in the direction of said longitudinal axis, space vessels of the first layer interposed therebetween and dispensing it and being secured to said dispenser by means of mechanical interfaces (IM2) extending in said radial direction for a distance greater than that of the mechanical interfaces of the first layer.
    [0006]
    The spacecraft assembly of claim 5 wherein both said first layer and said second layer of spacecraft comprise a plurality of stages (E) spaced apart in the direction of said longitudinal axis of the dispenser, each said stage being comprised of a plurality of spacecraft arranged in a ring around said dispenser, each stage of said second layer surrounding a corresponding stage of said first layer. 3035076 12
    [0007]
    7. A spacecraft assembly according to one of claims 5 or 6 wherein said spacecraft are substantially identical to each other, the spacecraft of the second layer being rotated relative to those of the first layer about respective axes oriented radially.
    [0008]
    The spacecraft assembly of claim 7 wherein said spacecraft has an elongated shape along a principal axis and wherein the spacecraft of the first layer are arranged with their main axis oriented in a longitudinal direction of the dispenser and those of the second layer are arranged with their main axis oriented perpendicular to the longitudinal direction of the dispenser. 15
    [0009]
    9. Dispenser (D) spacecraft comprising a central body (CT) of elongate shape along a longitudinal axis (z) and a plurality of mechanical interfaces (1M, IM1, IM2) for the docking of spacecraft s' extending radially from said central body, said mechanical interfaces being arranged in longitudinally spaced stages, characterized in that it has an alternation of sets of mechanical interface stages (IM1) extending radially over a first distance and sets of mechanical interface stages (IM2) extending radially over at least a second distance, greater than said first distance.
    类似技术:
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    同族专利:
    公开号 | 公开日
    EP3081496B1|2017-11-08|
    FR3035076B1|2018-04-20|
    US20160304222A1|2016-10-20|
    US10407190B2|2019-09-10|
    EP3081496A1|2016-10-19|
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    法律状态:
    2016-03-23| PLFP| Fee payment|Year of fee payment: 2 |
    2016-10-21| PLSC| Search report ready|Effective date: 20161021 |
    2017-03-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-03-27| PLFP| Fee payment|Year of fee payment: 4 |
    2020-01-10| ST| Notification of lapse|Effective date: 20191206 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1500801|2015-04-17|
    FR1500801A|FR3035076B1|2015-04-17|2015-04-17|METHOD FOR PROVIDING A PLURALITY OF SPATIAL VESSELS UNDER THE CAP OF A LAUNCHER, ASSEMBLY RESULTING FROM SUCH A METHOD AND DISPENSING SUITABLE FOR SUCH ASSEMBLY|FR1500801A| FR3035076B1|2015-04-17|2015-04-17|METHOD FOR PROVIDING A PLURALITY OF SPATIAL VESSELS UNDER THE CAP OF A LAUNCHER, ASSEMBLY RESULTING FROM SUCH A METHOD AND DISPENSING SUITABLE FOR SUCH ASSEMBLY|
    US15/097,943| US10407190B2|2015-04-17|2016-04-13|Method for arranging a plurality of spacecraft under the fairing of a launcher, assembly resulting from such a method and dispenser suited to such an assembly|
    EP16165409.0A| EP3081496B1|2015-04-17|2016-04-14|Method for providing a plurality of spacecraft under the fairing of a launcher, assembly resulting from such a method and dispenser adapted to such an assembly|
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