• 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:
    Satellite (1) comprising a main body (2) of cylindrical shape, the main body (2) having an inner wall (3) delimiting an inner space (9) and an outer wall (4) and extending along an axis (A) main between a lower end surface (5) and a top end surface (6) at least one of the lower end surface (5) and the top end surface (6) comprising an interface mechanism (7, 8) for cooperating with a complementary interface mechanism (7, 8) of another satellite or a launcher, the satellite (1) further comprising at least one device ( 15) externally fixed to the outer wall (4) of the main body, the outer equipment (15) extending in transverse projection on the outer wall (4) with respect to the main axis (A).
    公开号:FR3041940A1
    申请号:FR1559386
    申请日:2015-10-02
    公开日:2017-04-07
    发明作者:De Beaupre Rene Cheynet；Francis Palayret；Philippe Bertheux
    申请人:Airbus Defence and Space SAS；
    IPC主号:
    专利说明:

    The invention relates to the field of space vehicles, and more particularly the field of satellites intended to be placed in orbit.
    A satellite conventionally comprises a support body for the satellite equipment. The equipment can be divided into two categories. The first category is called the payload and includes the main instrument of the mission as well as the electronic devices necessary for its proper functioning. This is for example an optical instrument in the case of a mission to collect images and optical measurements, or one or more antennas in the case of telecommunication satellites. The second category includes equipment designated in this application as secondary, intended for the general operation of the satellite such as thrusters, receiving antennas, tanks or solar panels as well as electronic devices ensuring the control and control of these servitudes. .
    The launching of a satellite for orbiting is done in a conventional manner by means of a launcher in which the satellite is placed. The launcher includes propulsion means enabling it to reach the intended destination and to drop the satellite.
    In order to reduce costs, it is known to use a launcher to put into orbit several satellites, and this during a single launch. We then speak of multiple launching.
    The problems to be solved include the holding of the satellites in the launcher and their storage in the cap.
    Indeed, during the launch and then at the moment of release, the satellites are subjected to shocks and vibrations transmitted from the launcher to the satellites. The disposition of the satellites in the launcher must therefore prevent shocks and vibrations from propagating too much in the satellites and deteriorate the equipment while ensuring good mechanical strength of all the satellites in the launcher.
    A known solution for multiple launching is to connect the satellites to a central structure of the launcher, called the dispenser, which forms housings in which the satellites are placed. US 8,939,409 describes an example of a dispenser. A dispenser typically comprises on the one hand elements attached to the launcher and possibly on the other hand elements attached to the satellites, that is to say on the one hand interface elements intended to remain in the launcher after the release satellites and on the other hand interface elements intended to accompany the dropped satellites. The satellites are thus supported by the dispenser in the manner of a shelf, and do not support each other. Such a structure is however cumbersome and is only suitable for satellites of small dimensions, or limits the number of satellites that can be installed in the launcher by the size of the cap. In addition, it is an increase in the weight of the launcher, while it is useless to the mission.
    Another solution is then to stack the satellites on each other by providing, on the structure of each satellite, a dedicated interface for the stack.
    Document US Pat. No. 8,511,617 proposes an example of a satellite stack having a dedicated interface structure. In this document, the dedicated structure is in the form of an outer cylinder, the cylinders then serving as a path for the transmission of forces when the satellites are stacked. The diameter of the cylinder of a satellite is included in this document between 2 m and 5 m.
    A disadvantage of the structure is that it is large in diameter compared to the standard launching interface diameters in the spatial domain. Indeed, in order to mount a satellite in a launcher, the latter comprises a satellite interface ring on which the satellite is fixed. In order for the launcher to be compatible with several satellites, it is known that the satellite interface ring of the launcher is of a standard diameter, selected from 937 mm (millimeters), 1194 mm and 1666 mm. Therefore, the dedicated structure described in US Pat. No. 8,511,617 can not be mounted directly on the satellite interface ring of the launcher, but an intermediate support must be placed between the satellite and the launcher ring to make the connection between the two. diameters. In addition, the diameter of the dedicated structure is greater than the largest of the standard diameters, almost completely filling the undercap space of the launcher, so that all the equipment of the satellite is located inside the cylinder of the structure dedicated.
    Therefore, there is a need for a new satellite having a structure including overcoming the aforementioned drawbacks.
    Thus, a first object of the invention is to provide a satellite to be installed in a launcher with good mechanical strength.
    A second object of the invention is to provide a satellite that can be stacked with another satellite with satisfactory rigidity.
    A third object of the invention is to provide a satellite for arranging the equipment to optimize the space under the cover in a launcher.
    A fourth object of the invention is to provide a satellite in which the mounting of the equipment on the body of the satellite is simplified.
    A fifth object of the invention is to provide a satellite for which the installation in a launcher is simplified.
    A sixth object of the invention is to propose a satellite that can integrate an optical instrument.
    A seventh object of the invention is to provide a satellite for the stack of reduced mass.
    An eighth object of the invention is to provide a satellite for the easy manufacturing stack.
    According to a first aspect, the invention proposes a satellite comprising a main body, of cylindrical shape. The main body has an inner wall defining an interior space and an outer wall and extends along a major axis between a lower end surface and an upper end surface. At least one of the lower end surface and the upper end surface includes an interface mechanism for cooperating with a complementary interface mechanism of another satellite or launcher. The satellite further comprises at least one interior equipment, fixed on the inner wall of the main body and extending at least partially in the interior space and at least one external equipment fixed on the outer wall of the main body. The outer equipment extends in transverse projection on the outer wall relative to the main axis, the at least one external equipment may be an electronic, a propellant tank a gyroscopic actuator or a reaction wheel.
    The satellite thus designed allows in particular to optimize the space in the space under a launcher cover, using both the interior space and the surface of the outer wall of the body.
    According to one embodiment, the main body comprises a cylinder having an average diameter diameter corresponding to a standard diameter in the spatial range, selected from the following values: 937 mm, 1194 mm and 1666 mm.
    The main body can then directly rest on and directly attached to an interface ring of a launcher, without the intermediary of an adapter. The assembly thus formed then creates a transmission path of the forces between the interface ring and the body which is substantially parallel to the main axis of the main body, increasing the rigidity of the assembly.
    According to one embodiment, the outer wall of the main body comprises at least a flat surface portion forming a facet on which the outer equipment is fixed. The facet facilitates the assembly of outdoor equipment.
    According to one embodiment, the main body is made of monolithic aluminum parts. The interior equipment includes for example an optical instrument for shooting. The interior equipment includes for example the electronics associated with the optical instrument. The interior equipment may comprise an optical instrument comprising a line of sight oriented parallel to the main axis of the main body. The interior equipment may further include a mounting plate attached to the inner wall of the main body and extending at least partially out of the interior space beyond the upper end surface of the main body. The optical instrument is then fixed rigidly to the mounting plate. The line of sight of the optical instrument is preferably oriented toward the lower end surface of the main body, and the mounting plate extends at least partially beyond the upper end surface of the main body.
    According to one embodiment, the interface mechanism is linear. For example, the interface mechanism includes a webbing system.
    According to a second aspect, the invention proposes a stack of satellites comprising at least two satellites as presented above. The main axes of the main bodies of the two satellites are parallel to each other. An interface mechanism of the upper end surface of a first satellite is in contact along the main axes with an interface mechanism of the lower end surface of the body of the second satellite. The interface mechanisms then cooperate with each other to secure the two satellites.
    According to one embodiment, the inner equipment of the first satellite extends partially into the interior space of the second satellite.
    According to a third aspect, the invention proposes a launch assembly comprising a launcher and at least one satellite as presented above. The launcher then comprises a cap defining a housing for at least one satellite and an interface ring and the lower end surface of the main body of the satellite comprises an interface mechanism to be secured to the launcher interface ring. . Other features and advantages will become apparent in the light of the description of embodiments of the invention, accompanied by the figures in which:
    Figure 1 is a schematic representation of a sectional view of a satellite.
    FIG. 2 is a schematic representation of a side view of the body of the satellite of FIG.
    Fig. 3 is a side view of a satellite according to an embodiment in which the satellite comprises an optical instrument.
    FIG. 4 is a three-dimensional view from above of the satellite of FIG. 3.
    FIG. 5 is a three-dimensional bottom view of the satellite of FIG. 3.
    FIG. 6 is a schematic representation of a sectional view of a stack of satellites of FIG.
    Figure 7 is a schematic representation of a sectional view of a satellite of Figure 1 stacked with a satellite of another structure.
    Figure 8 is a schematic view of a sectional view of several satellite stacks of Figure 1 on the same satellite interface of a launcher.
    FIG. 9 is a three-dimensional bottom view of an exemplary embodiment of several stacks of satellites on the same satellite interface of a launcher.
    Figure 1 schematically shows a satellite 1, intended to be placed in orbit around the Earth by means of a launcher. The satellite 1 comprises a main body 2, of generally cylindrical shape extending along a main axis A.
    In what follows, the adjective "longitudinal" and its variants designate what is parallel to the main axis A; the adjective "transversal" and its variants designate what is included in a plane perpendicular to the main axis A. The adjective cylindrical here must be understood in its broad sense as defining a surface drawn by a generating line describing a guiding curve. The guide curve may be circular, the main body 2 then having a tubular shape, or polygonal, the main body 2 then having the shape of a prism.
    The main body 2 has an inner wall 3 and an outer wall 4, which define a thickness of the main body 2.
    In what follows, the adjective "interior" and its variants designate what is turned towards or close to the principal axis A, as opposed to the adjective "outside" and its variants, which designate what is turned to the opposite to or away from the main A axis.
    The main body 2 extends along the main axis A between a so-called lower end surface 5 and a so-called upper end surface 6. In order to allow the stacking of several satellites 1 with good mechanical strength, as will be explained later, the two end surfaces 5, 6 have identical transverse dimensions, making it possible to match the upper end surface 6. a satellite 1 with the lower end surface of another satellite.
    The diameter of the lower end surface is then compatible with the standard spatial diameters, which are those applied to the launchers satellite interface ring: 937 mm, 1194 mm and 1666 mm.
    More specifically, the diameter of the lower end here refers, for the sake of simplification, to the diameter of the middle circle at the main body 2 between the inner surface 3 and the outer surface 4 at the lower end. The diameter of the lower end is then substantially equal to one of the standard values stated above.
    Therefore, it is possible to define for the cylindrical body 2 an average cylinder CM whose guide curve is a circle of diameter substantially equal to one of the standard values stated above, the average cylinder CM extending over the entire longitudinal dimension of the cylindrical body 2, between the two surfaces 5, 6 end, and included, again over its entire longitudinal dimension, between the inner wall 3 and the outer wall 4.
    At least one of the lower end surface and the upper end surface 6 comprises an interface mechanism for cooperating with another complementary interface mechanism of a satellite interface of a launcher or from another satellite. According to a particular embodiment, the lower end surface comprises a lower interface mechanism and the upper end surface comprises an upper interface mechanism.
    The interface mechanisms 7, 8 thus allow the satellite 1 to be brought into contact with and to be secured to another satellite or to a satellite interface ring of a launcher. Advantageously, the lower interface mechanism 7 is complementary to the upper interface mechanism 8, making it possible for two satellites 1 as shown above to be stacked and to be secured by their interface mechanisms 7, 8. correspondence.
    The mechanisms, respectively 7, 8 of interface, are for example linear, that is to say that they extend continuously over the entire circumference of the ends, respectively 5, 6 of the main body 2 . According to an exemplary embodiment, the lower interface mechanism 7 of the satellite 1 comprises an interface ring and the upper interface mechanism 8 of the same satellite 1 also comprises a ring whose shape allows it to fit on the lower interface mechanism 7 ring of another satellite. As will be explained below, the upper interface mechanism 7 and / or the lower interface mechanism 8 comprises a releasable webbing system which makes it possible to grip and maintain two complementary interface mechanisms of two satellites stacked at the same time. by means of a strap. The diameter of the rings of the interface mechanisms 7, 8 correspond to the diameter of the average cylinder CM.
    The inner wall 3 defines an interior space 9, extending between the two surfaces 5, 6 of the main body 2 extreme. Inner equipment is in contact with and attached to the inner wall so as to extend at least partially into the inner space.
    Equipment means here any instrument, set of instruments or any electronics of the satellite. For example, the interior equipment comprises arms 11 extending transverse to the main axis A, one end of which is in contact with and fixed on the inner wall 3 and the other end is in contact with and fixed on the inside wall. 10 interior equipment.
    Preferably, the interior equipment comprises the payload of the satellite, i.e. the main equipment necessary for the mission of the satellite 1.
    According to an exemplary embodiment of the satellite, which is that illustrated in the figures, the payload comprises an optical instrument 13. The interior equipment 10 can then include a mounting plate 12 on which the instrument 13 is rigidly fixed. The arms 11 are advantageously fixed on the plate 12 also. The plate 12 may comprise one or more optical detectors which preferably have an unobstructed view on at least one face for good radiation cooling. This is why the plate 12 can emerge beyond one of the ends 5, 6 of the main body 2 of the satellite 1, outside the inner space 9. The optical instrument 13 is defined in particular by a viewing axis V, virtually defining the direction in which the optical instrument "sees", and by a field of view, defining the entry cone of the light rays in the instrument 13 optical.
    Preferably, the plate 12 emerges from the inner space 9 by the upper end surface 6. Thus, the V-axis of sight of the optical instrument 13 is directed towards the lower end surface 5 of the main body 2.
    The main body 2 may, in addition to its force transmission function in a satellite stack, provide other functions, including protection functions of the indoor equipment. For example, the main body 2 can serve as a cabinet. Preferably, the fragile elements of the optical instrument 13 are wholly within the interior space. Fragile elements are for example mirrors and their support. The main body 2 then forms a barrier preventing the sun's rays from reaching the fragile elements of the optical instrument.
    Alternatively or in combination, the main body 2 may be made of monolithic aluminum, as opposed to a composite material such as Aluminum and Nida Aluminum skin, so as to form a thermal distributor for the outdoor equipment. In addition the equipment can be attached directly to the structure, without the use of inserts, unlike composites commonly used in space.
    Preferably the main body 2 and the lower and upper interface mechanisms form a monolithic single piece, which can be obtained by machining an aluminum cylinder. In this case, the transmission capacity of the forces and the rigidity of the assembly are increased, especially if it is associated with a linear interface mechanism 7, 8, as indicated above such as a strap.
    It is also possible to directly machine secondary support structures for holding equipment or instrument.
    According to this example, the interior equipment furthermore comprises the electronics associated with the instrument 13. The electronics is then for example directly in contact with and fixed on the inside wall 3, in the inner medium 9, so as to It can be mounted in one piece with the instrument 13. In fact, the instrument 13 and its control electronics are generally delivered to the assembly site of the satellite 1 as a set whose connections are tested and certified. as functional. Any disconnection causes the need to re-test the connections. Thus, by keeping the assembly formed by the instrument 13 and its internal electronics to fix it on the inner wall 3 of the main body 2, the disconnections are avoided. The viewing axis V of the optical instrument 13 may be confused with the main axis A, in which case the control electronics may be distributed around the instrument 13 in the inner space 9. However, the sighting axis V is preferably parallel to the main axis A, but offset, so as to disengage a region in the inner space 9 to place the control electronics. In another variant, the sighting axis V can be inclined with respect to the main axis A.
    The satellite 1 further comprises at least one external equipment, in contact with and fixed on the outer wall of the body 2 of the satellite, and thus extending out of the inner space 9. The external equipment is selected from electronics such as satellite control electronics 16, propellant tank 18, a gyroscopic actuator 17 (also known as CMG for Control Momentum Gyroscope) or a reaction wheel. Other external secondary equipment can also be attached to the outer wall 4, for example, sensors, thrusters to rectify the trajectory of the satellite 1 if necessary or solar panels. The outer equipment thus forms a projection transverse to the main axis A on the outer wall 4 on a controlled dimension, corresponding to the place in the launcher. For example, the outside equipment defines a circle Cmax, circumscribed to the outside equipment, and whose diameter is greater than the diameter of the circle CCir circumscribing the outer wall 4 of the main body 2 by at least 20% (FIG. 6). It is possible to mount larger equipment with possibly additional external secondary structures connected to the main body. Flat solar panels can also be mounted. The diameter of the circle Cmax can then be 30% or even 40% or 50% greater than that of the circumscribed circle CCir. The practical limit is the diameter of the launcher's cap used.
    Thus, since the diameter of the average cylinder CM corresponds to a standard diameter, space is released around the main body 2 when the satellite 1 is placed under the cap of a launcher, making it possible to fix the equipment 15 on the outside wall. bulky outer surfaces. Congestion under the cap is optimized.
    According to one embodiment, the outer wall 4 of the body 2 of the satellite may comprise a flat portion, which may extend but not necessarily over the entire dimension along the main axis A so as to form a facet. For example, when the directional curve of the main body 2 is a polygon as illustrated in FIGS. 3 to 6, the outer wall 4 is formed of a succession of substantially flat facets 19, which are particularly suitable for fixing the external equipment. , and in particular to electronics.
    Thus, the main body 2 offers possibilities for mounting interior equipment and outdoor equipment 15 particularly suited to optimize the space available under the casing in the launcher.
    The satellite 1 thus described can be stacked with other satellites and be placed under the cap of a launcher.
    A first example of a stack is illustrated in FIG. 7. According to this example, four satellites 1 as described above and substantially identical are stacked one above the other by their main body 2. The satellites 1 are arranged along the same main axis A, and their interior equipment comprises an optical instrument 13 whose line of sight V is directed towards the lower end surface. The four satellites 1 have a main body 2 centered on an average CM cylinder of the same diameter.
    According to the example, a first satellite 1 is fixed to the launcher by its lower interface mechanism 7. More specifically, the launcher comprises a satellite interface mechanism, typically a ring 20, complementary to the ring of the lower interface mechanism 7 of a first satellite 1. The first satellite 1 is then placed so that its mechanism 7 lower interface is nested on the ring of the launcher interface mechanism. Since the ring of the lower satellite interface mechanism 7 of the first satellite is equal to the diameter of the average cylinder CM, which corresponds to the diameter of the ring 20 of the satellite interface mechanism of the launcher, it is not necessary to place a adapter between the launcher ring 20 and the first satellite 1. The launcher also includes a releasable lashing system, the strap of which surrounds the launcher interface mechanism ring 20 and the lower interface mechanism ring 7. of the first satellite. The first satellite 1 is thus secured to the launcher.
    A second satellite 1 is stacked on the first satellite 1, the ring of the lower interface mechanism 7 of the second satellite being fitted on the ring of the upper interface mechanism 8 of the first satellite. The upper interface mechanism 8 of the first satellite then comprises a releasable webbing system, the webbing of which engages the ring of the upper interface mechanism 8 of the first satellite 1 and the ring of the lower interface mechanism 7 of the second satellite .
    A third satellite is likewise stacked on the second satellite 1, and a fourth satellite 1 is stacked on the third satellite. The fourth, and last, satellite 1 does not include a webbing system. Here again, since all the satellites of the stack are centered on the same average CM cylinder, no adapter between the satellites 1 is necessary.
    The satellites 1 thus stacked have their main axes A confused. Likewise, the V-axis of sight of the optical instruments 13 are all substantially parallel.
    According to the example presented here, the optical instrument 13 of each satellite 1 being at a distance from the lower end surface of the body 2 of the corresponding satellite, the interior equipment can be astride within the interior space of two satellites 1 stacked. Indeed, the plate 12 emerging through the upper end surface 6 of a lower satellite can be housed in the interior space 9 of the upper satellite, between the optical instrument 13 and the lower end surface 5. from the upper satellite 1.
    The external equipment of the satellites 1, extending transversely from the outer wall 4 of the body 2 of each satellite 1 do not interfere with each other.
    In addition, since there is no change in diameter from the ring 20 of the launcher to the main body 2 of the fourth satellite 1, the mechanical strength of the stack is increased. The stacked satellites 1 have their average cylinder CM substantially in the continuity of each other and the satellite interface ring of the launcher, embodying the path through which the forces are transmitted between the satellites. The transmission path of the stresses thus extends almost exclusively longitudinally from the satellite interface ring 20 of the launcher to the fourth satellite 1 and passes only through the main bodies 2 of the satellites 1, which allows the stack of have a good mechanical strength. The equipment 10 inside each satellite 1 is protected from vibrations and shocks, the forces not being transmitted to them.
    The linear connection provided by the strapping systems also ensures a good distribution of forces over the entire circumference of the main bodies 2 satellites 1.
    As a result of the design of the satellites 1 and their stacking, the V-axis of sight of each of the optical instruments 13 is oriented towards the satellite interface ring of the launcher.
    This orientation of the V-axis of view allows the satellite to gain compactness. Indeed, especially in the case where the optical instrument 3 is a shooting instrument, by orienting the V-axis of sight towards the satellite interface ring of the launcher, the diameter of the mirrors of the optical instrument 3 can be increased while maintaining the optically necessary dimensional ratios within the instrument 3. However, the larger the diameter of the mirrors, the better the resolution of the optical instrument 3. Moreover, the forces passing through the main body 2, the mounting plate 12 can have its thickness reduced compared to the state of the art, making it possible to increase the dimension along the main axis A of the optical instrument 3 while maintaining a total dimension along the axis A of the satellite adapted to the space in the launcher. Thus, keeping the size of the satellite along the main axis A adapted to the space requirement in the launcher, the performance of the optical instrument 3 is increased.
    When the satellites 1 must be dropped into space, each strapping system is open, so as to release the interface mechanisms 7, 8, for example by means of a pyrotechnic device controlled remotely from the Earth, since the launcher or programmed to respect a specific drop sequence. The separation between the satellites 1 and the first satellite 1 and the satellite interface ring 20 can be facilitated by means of prestressed elements, of spring type, released when the straps are open.
    The strapping systems of the first, second and third satellites 1 preferably remain attached to their respective satellites once opened. For example, each strapping system comprises a point of attachment on the body of the corresponding satellite. When the first satellite 1 is dropped, the webbing system of the launcher remains attached to the launcher.
    According to a particular embodiment, each satellite 1 may have a system for capturing the webbing system once opened.
    According to a particular embodiment, each satellite 1 must ensure the transmission of the control of the opening of the webbing system to the next satellite 1, from the first satellite 1 to the fourth satellite 1. In so doing, the same order repeated n times allows to release n satellite one by one.
    In FIG. 8, there is shown a second example of a stack of a satellite 1 according to one embodiment of the invention and a different satellite 21. The different satellite 21 has, in particular, transverse dimensions that do not correspond to those of the surfaces 5, 6 of the ends of the satellite 1 according to the invention. The satellite 1 according to the invention is mounted as previously on a satellite interface ring 20 of a launcher, and the different satellite 21 is stacked on the upper end surface 6 of the satellite according to the invention, using an adapter 22 to fill the difference in transverse dimensions.
    In Figures 9 and 10, there is illustrated a third example of a stack of satellites 1, substantially identical and according to the invention. According to this third example, several columns 23 of satellites 1 can be mounted next to each other on the same satellite interface ring 20 of a launcher. The columns 23 may be transversely aligned or arranged in staggered rows on the ring 20. An adapter is then mounted between the first satellite of each column 23 and the satellite interface ring 20.
    The number of satellites 1 may be, but not necessarily, the same in each column 23. The column arrangement makes it possible, for example, to carry out space drop sequences by column 23, the satellites 1 of a column 23 being brought to a specific location from where they can then be separated from each other. Thus, only one trajectory control device per column 23 can be put in place. The column arrangement also makes it possible to carry out drop sequences in the space per slice. The satellites of the same slice slice are dropped at the same time. The next slice can be dropped into a different orbit if the launcher has the ability to re-ignite its propulsion.
    权利要求:
    Claims (14)
    [1" id="c-fr-0001]
    A satellite (1) comprising a main body (2) of cylindrical shape, the main body (2) having an inner wall (3) delimiting an inner space (9) and an outer wall (4) and extending according to a main axis (A) between a lower end surface (5) and an upper end surface (6) at least one of the lower end surface (5) and the lower end surface (6). upper end comprising an interface mechanism (7, 8) for cooperating with a complementary interface mechanism (7, 8, 20) of another satellite or a launcher, the satellite (1) further comprising minus an equipment (10) inside, fixed on the inner wall (3) of the main body (2) and extending at least partially in the internal space (9) and at least one external equipment (15) fixed on the wall (4) exterior of the main body, the equipment (15) extending outwardly transverse projection s on the outer wall (4) with respect to the main axis (A), the at least one external equipment (15) which may be an electronics, a propellant tank, a gyroscopic actuator or a reaction wheel.
    [2" id="c-fr-0002]
    The satellite according to claim 1, wherein the main body (2) comprises a cylinder having an average diameter (CM) of diameter corresponding to a standard diameter in the spatial range, selected from the following values: 937 mm, 1194 mm and 1666 mm.
    [3" id="c-fr-0003]
    The satellite (1) according to claim 1 or claim 2, wherein the outer wall (4) of the main body (2) comprises at least a flat facet surface portion (19) on which the equipment ( 15) outside is fixed.
    [4" id="c-fr-0004]
    4. Satellite (1) according to any one of the preceding claims, wherein the main body (2) is made of monolithic aluminum parts.
    [5" id="c-fr-0005]
    The satellite (1) according to any one of the preceding claims, wherein the interior equipment (10) comprises an optical imaging instrument.
    [6" id="c-fr-0006]
    6. Satellite (1) according to claim 5, wherein the equipment (10) inside comprises the electronics associated with the optical instrument (3).
    [7" id="c-fr-0007]
    7. Satellite (1) according to claim 5 or claim 6, wherein the equipment (10) inside comprises an optical instrument (13) comprising a sighting axis (V) oriented parallel to the main axis (A) of the main body (2).
    [8" id="c-fr-0008]
    8. Satellite (1) according to claim 7, wherein the equipment (10) inside comprises a mounting plate (12) attached to the wall (3) inside the main body (2) and extending at least partially in outside the inner space (9), beyond the upper end surface (6) of the main body (2), and wherein the optical instrument (13) is rigidly attached to the platen (12) of mounting.
    [9" id="c-fr-0009]
    9. Satellite (1) according to claim 8, wherein the aiming tax (V) of the optical instrument (13) is oriented towards the lower end surface (5) of the main body, the mounting plate (12). extending at least partially beyond the upper end surface (6) of the main body (2).
    [10" id="c-fr-0010]
    Satellite (1) according to any of the preceding claims, wherein the interface mechanism (7, 8) is linear.
    [11" id="c-fr-0011]
    11. Satellite (1) according to the preceding claim, wherein the interface mechanism (7, 8) comprises a webbing system.
    [12" id="c-fr-0012]
    12. Stacking satellites (1) comprising at least two satellites (1) according to any one of the preceding claims, the main axes (A) of the main body (2) of the two satellites (1) being parallel, a mechanism (8) ) of interface of the upper end surface (6) of a first satellite (1) in contact with the main axes (A) with an interface mechanism (7) of the end surface (5) lower body (2) of the second satellite (1), the interface mechanisms (7, 8) cooperating with each other to secure the two satellites (1).
    [13" id="c-fr-0013]
    13. Stack of satellites (1) according to claim 12, wherein the equipment (10) inside the first satellite (1) extends partially in the space (9) inside the second satellite (1).
    [14" id="c-fr-0014]
    14. Launching assembly comprising a launcher and at least one satellite (1) according to any one of claims 1 to 11, the launcher comprising a cap defining a housing for at least one satellite (1) and a ring (20) d interface, the lower end surface (5) of the main body (2) of the satellite (1) comprising an interface mechanism (7) to be secured to the launcher interface ring (20).
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    同族专利:
    公开号 | 公开日
    EP3313734A1|2018-05-02|
    US20180265227A1|2018-09-20|
    ES2690991T3|2018-11-23|
    WO2017055770A1|2017-04-06|
    PL3313734T3|2019-01-31|
    EP3313734B1|2018-09-26|
    FR3041940B1|2018-07-13|
    US10689133B2|2020-06-23|
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    JP2021510650A|2018-01-22|2021-04-30|ルアク・シュヴァイツ・アクチェンゲゼルシャフトＲｕａｇ Ｓｃｈｗｅｉｚ Ａｇ|Payload carrier assembly|
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    法律状态:
    2016-10-25| PLFP| Fee payment|Year of fee payment: 2 |
    2017-04-07| PLSC| Search report ready|Effective date: 20170407 |
    2017-10-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-10-26| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-16| ST| Notification of lapse|Effective date: 20200906 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1559386|2015-10-02|
    FR1559386A|FR3041940B1|2015-10-02|2015-10-02|CYLINDRICALLY MAIN BODY SATELLITE, STACK COMPRISING SUCH SATELLITE AND LAUNCH SET FOR SUCH A SATELLITE|FR1559386A| FR3041940B1|2015-10-02|2015-10-02|CYLINDRICALLY MAIN BODY SATELLITE, STACK COMPRISING SUCH SATELLITE AND LAUNCH SET FOR SUCH A SATELLITE|
    US15/764,678| US10689133B2|2015-10-02|2016-09-30|Satellite with cylindrical main body, stack comprising such a satellite and launch assembly for such a satellite|
    PL16788161T| PL3313734T3|2015-10-02|2016-09-30|Satellite with cylindrical main body, stack comprising such a satellite and launch assembly for such a satellite|
    EP16788161.4A| EP3313734B1|2015-10-02|2016-09-30|Satellite with cylindrical main body, stack comprising such a satellite and launch assembly for such a satellite|
    PCT/FR2016/052507| WO2017055770A1|2015-10-02|2016-09-30|Satellite with cylindrical main body, stack comprising such a satellite and launch assembly for such a satellite|
    ES16788161.4T| ES2690991T3|2015-10-02|2016-09-30|Cylindrical main body satellite, stacking comprising such satellite and launch set for such satellite|
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