• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
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    • 专利摘要:
    A space vehicle (1, 100), such as a satellite, the vehicle (1, 100) comprising: - at least one equipment carrier module (2) for supporting equipment of the vehicle (1); at least three posts extending at least partially in the same longitudinal direction and at the periphery of the equipment carrying module, each post being provided with at least one device ) releasable lock; - a reinforcing structure (16) rigidly connecting transversely each post (12) to at least two other posts (12).
    公开号:FR3040978A1
    申请号:FR1558695
    申请日:2015-09-16
    公开日:2017-03-17
    发明作者:Dominique Poncet；Hon Christophe Prud；Serge Guyot
    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 but not exclusively, the field of satellites intended to be placed in orbit around the Earth.
    Conventionally, a satellite is put into orbit by means of a launcher, which brings the vehicle into space to drop it according to the planned orbit.
    In order to reduce the costs associated with launching a satellite, it is known to place in one and the same launcher several satellites that will be dropped during the same launch. This is called launching a cluster of satellites. The more satellites launched, the greater the cost savings.
    A problem when several satellites are placed in the same launcher is the management of efforts at launch. Indeed, the launch phase generates vibrations and shocks, in addition to creating a thrust due to acceleration. Thus, a simple stack of satellites on each other produces especially on the satellites located under one or more satellites (with respect to the gravity and / or the direction of the acceleration) efforts likely to damage the equipment carried by this satellite.
    However, the current trend is to launch more and more powerful satellites, including multiple equipment and radiative walls of large surfaces to cool the equipment. Some satellites may have a weight of a few tons.
    It is then necessary to provide means for adequately placing the satellites in the same launcher to minimize the efforts on the satellites.
    One known means is to set up a structure in the launcher known as the "dispenser". US 8,939,409 describes an example of a dispenser. A dispenser typically comprises on the one hand elements fixed to the launcher and possibly on the other hand elements attached to the satellites, that is to say on the one hand elements intended to remain connected to the launcher after the dropping of the satellites and on the other hand 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.
    Providers, however, have the disadvantage of being specially adapted to the type of satellite to send. Thus, the design of the dispensers depends on their use. It may also happen that several satellites of different design must be dropped by the same launcher, complicating the structure of the dispenser in the launcher. In addition, the dispenser includes elements that are integral parts of the launcher. These elements add weight to the thrower and are, in the end, penalizing the mission. The weight distribution in the launcher must also be monitored, especially during the drop. Indeed, in order to maintain the balance of the launcher once launched, the satellite dropping sequence must comply at all times a distribution of the appropriate weight within the launcher. The dropping operations are complicated.
    Another disadvantage of a dispenser is that the shape and dimensions of the satellites are limited by the space offered by the dispenser.
    It is also known to directly stack the satellites on each other by providing, on the structure of each satellite, a dedicated interface for the stack, so that the bodies of the satellites are not themselves in contact with each other. with others, but through the dedicated interface.
    US 8,915,472 provides an example of a system for attaching two satellites together. For this purpose, each satellite comprises a central structure extending over an entire length of the satellite, on which load support panels are placed. The central structure of a first satellite is connected with the central structure of a second satellite by means of an alleged detachable strip. The transmission of forces between the two satellites then pass through their central structure.
    A disadvantage of this system is that it reduces the space available to mount the equipment on the satellites. In particular, the antennas of a telecommunication satellite are placed on the Earth face of the satellite body. In US 8,915,472, the central structure must be accessible by at least one face of the satellite body to allow contact between two central structures of two satellites without contact with other elements. These faces in question are then unavailable to put satellite equipment, including antennas.
    Another disadvantage is that, incidentally to the disadvantage mentioned above, the satellites can not be arranged in a manner optimizing the space inside the launcher, called the undercap space. Indeed, the presence of the central structure imposes an identical orientation for all the satellites stacked.
    Document US Pat. No. 8,511,617 also proposes to stack satellites having a dedicated interface structure. In this document, the dedicated structure is in the form of a cylinder outside the body of the satellite, the cylinders then serving as support when the satellites are stacked.
    A disadvantage of this solution is that the cylinder outside the satellite also limits the space available for the equipment carried by the satellite. In addition, again, the satellites can not be arranged in any direction because of the outer cylinder which imposes a placement of equipment in the space available between the body of the satellite and the cylinder. The undercap space is not optimized either.
    Finally, both the central structure described in US 8,915,472 and the outer cylinder disclosed in US 8,511,617 are relatively massive and imposing structures that increase the weight of the satellite.
    There is therefore a need for a solution for stacking in a launcher several satellites, or generally more space vehicles, overcoming in particular the aforementioned drawbacks.
    A first object of the invention is to provide a spacecraft to be placed in a launcher with at least one other vehicle without the transmission of efforts to damage the vehicles.
    A second object of the invention is to provide a space vehicle to be placed in a launcher with at least one other vehicle not increasing or little or the total weight of the satellite and the weight of the launcher.
    A third object of the invention is to provide a spacecraft to be placed in a launcher with at least one other vehicle offering flexibility in the orientation of vehicles placed in the launcher to optimize the space under the cap.
    A fourth object of the invention is to provide a space vehicle for being placed in a launcher with at least one other vehicle offering flexibility in the shape and dimensions of each stacked vehicle.
    A fifth object of the invention is to propose a space vehicle that can be placed in a launcher with at least one other vehicle in which the interface structure between the two vehicles can be adapted to the equipment that can be installed on satellites.
    A sixth object of the invention is to provide a space vehicle for being placed in a launcher with at least one other vehicle in which the vehicles can be dropped one by one or by group.
    Thus, according to a first aspect, the invention proposes a space vehicle, such as a satellite, intended to be placed in orbit around a planet, the vehicle comprising: at least one equipment carrier module, intended to support equipment of the vehicle ; at least three posts extending at least partially in the same longitudinal direction and at the periphery of the equipment carrier module, each post being provided with at least one releasable locking device intended to take two states: a locked state, in which the locking device is fixed on a complementary locking device, o an unlocked state, in which the locking device is released from any other locking device; a reinforcing structure rigidly connecting transversely each post to at least two other posts.
    The reinforcing structure may comprise reinforcement elements in the form of a branch whose number corresponds at least to the number of posts, each branch being fixed between two posts. The branches can then be confused with walls of the equipment carrier module, the support walls for vehicle equipment.
    The reinforcing structure may alternatively comprise reinforcement elements in the form of a branch whose number corresponds at least to the number of poles, each branch being fixed on the one hand to a pole and on the other hand to the same center of attachment.
    Advantageously, the reinforcing branches are connected in pairs by consolidation elements in shear.
    According to one embodiment, the posts are three in number and are distributed at the vertices of an equilateral triangle.
    According to another embodiment, the posts are four in number and are distributed at the vertices of a parallelogram.
    Each releasable locking device may comprise for example a magnetic element or a pyrotechnic element.
    Each post may advantageously be provided with two releasable locking devices for stacking the satellite on another satellite or on an interface structure and for stacking another satellite on the satellite.
    Preferably, but not necessarily, each post extends longitudinally between two ends, each end being provided with a locking device. The satellite stack is then made by the ends of the columns, following the longitudinal direction. The stresses supported by the columns are then mainly shear stresses, and the poles can be designed (shapes and dimensions) to support these constraints.
    According to a second aspect, the invention proposes a method of assembling at least two vehicles as presented above. The method comprises the following steps: positioning the at least two vehicles so that the posts of a first vehicle extend at least partially in the same longitudinal direction as the posts of the second vehicle; putting each locking device of the first vehicle in cooperation with a locking device of the second vehicle; transition to the locked state of the locking devices of the first vehicle on the locking devices of the second vehicle.
    According to a third aspect, the invention proposes a stack of vehicles as presented above, comprising at least two vehicles integral with each other, the at least one releasable locking device of each pole of a first vehicle. being in the locked state with a locking device on a post of the second vehicle, the posts (of each vehicle extending in the same longitudinal direction, the stack further comprising a device for controlling the state of the locking.
    The vehicles of the stack are in particular satellites comprising a face Earth and an anti-Earth face, the faces Earth and anti-Earth, which can be oriented in the longitudinal direction of the poles or in a direction transverse to the poles.
    According to a fourth aspect, the invention proposes a launcher of space vehicles, the launcher comprising a vehicle interface structure and at least a first stack of vehicles as presented above. At least the first vehicle of the stack is a vehicle comprising on each post two releasable locking devices, a first locking device of each post of the first vehicle being in the locked state on a locking device of the second vehicle, the second locking device of each pole of the first vehicle being in the locked state on the vehicle interface structure.
    According to a fifth aspect, the invention proposes a method of releasing vehicles by means of a launcher as presented above, comprising a step of separating a vehicle to be dumped and a vehicle intended to remain in the launcher by putting into the unlocked state of the locking devices between the two vehicles so as to drop a single vehicle. As a variant or in combination, the release method comprises a step of separating a group of vehicles to be dumped and a vehicle intended to remain in the launcher by putting the locking devices in the unlocked state between a vehicle of the group to be dumped and the vehicle intended to remain in the launcher, so as to drop the group of vehicles. Other features and advantages of the invention will emerge in the light of the following description of particular embodiments accompanied by the figures in which:
    FIG. 1 is a three-dimensional diagrammatic view of a first example of a satellite, comprising a body on which equipment is placed, solar panels being represented in the deployed position in full lines and in the folded position in broken lines;
    Figure 2 is a three-dimensional view of the satellite of Figure 1, the body being transparent;
    Figure 3 is a top view of the satellite of Figure 2;
    Figure 4 is a schematic top view of posts of the satellite of Figures 1 to 3 and a reinforcing structure according to a first embodiment;
    Figure 5 is a three-dimensional view of the posts and the reinforcing structure of Figure 4;
    Figure 6 is a schematic top view of poles of the satellite of Figures 1 to 3 and a reinforcing structure according to a second embodiment;
    Figure 7 is a three-dimensional view of the posts and the reinforcing structure of Figure 6;
    Figure 8 is a three-dimensional view of an exemplary embodiment of a satellite stack of Figures 1 to 3;
    Figure 9 is a side view of the stack of Figure 8;
    Figure 10 is a three-dimensional view of a satellite stack of Figures 1 to 3 placed in a launcher, the latter being shown in transparency;
    Figure 11 is a top view of the launcher of Figure 10;
    Figure 12 is a schematic representation of an embodiment of two releasable locking devices placed at the ends of two posts located opposite one another;
    FIG. 13 is a three-dimensional view of another exemplary embodiment of a stack of a second example of a satellite;
    FIG. 14 is a schematic representation in plan view of a satellite of the stack of FIG. 13;
    Figure 15 is a representation of the stack of Figure 13 placed in a launcher;
    Fig. 16 is a diagram illustrating an example of a method of stacking satellites in a launcher.
    In Figures 1 to 11, there is shown a first example of a spacecraft, and in particular an example of a telecommunications satellite 1, intended to orbit the Earth.
    The term "vehicle" here designates any element comprising an equipment carrier module capable of transporting equipment. It may be provided with propulsion means of its own, or be intended to be simply dropped at a point in space in the expectation of being subsequently recovered by other space means.
    The equipment carrier module of the satellite 1 is commonly called body 2 of satellite 1, and is of generally parallelepipedal shape, so as to have four faces called face 3 West, face 4 East, face 5 North, face 6 South, with reference to terrestrial cardinal points, and two faces called face 7 Earth and face 8 anti-Earth, with reference to the orientation of these faces with respect to the Earth. One or more antennas 9, shown schematically in the figures, are commonly placed on the face 7 Earth to be oriented towards the Earth. The satellite 1 is provided with various equipment according to its mission. Typically, the satellite 1 may include solar panels, mounted on the North and South faces to receive maximum sunlight. In Fig. 1, solar panels are shown in solid lines in deployed position. In broken lines, the solar panel 10 mounted on the North face 5 is illustrated in the folded position against this face. The satellite 1 can also embark propellers to correct the trajectory of the satellite 1 in orbit. Pointing the satellite in the desired direction generally uses optical sensors, such as star sensors.
    In FIGS. 2 and 3, the solar panel 10 mounted on the face 6 South is represented in folded position against this face 6, and the solar panel 10 and the face 6 South are represented in transparency in order to reveal the structure of the body 2 of the satellite, here represented schematically. It is then visible that the satellite 1 comprises posts 12, extending in the same longitudinal direction A, perpendicular to the North 5 and South faces 6 according to the example presented.
    In what follows, the terms "longitudinal", "longitudinally" and their variants designate what is parallel to the longitudinal direction A. The terms "transverse", "transversely" and their variants then designate what is perpendicular to the longitudinal direction A.
    The number of posts 12 is at least three, and is preferably equal to four in the case of the parallelepiped body 2. The posts 12 are not aligned, and are arranged for example at the vertices of a triangle in the case of three poles, or to the vertices of a quadrilateral in the case of four poles 12.
    The posts 12 are placed at the periphery of the body 2, that is to say that they are at a distance from a geometric center C of the body 2.
    The posts 12 may be placed at the inner periphery of the body 2, as illustrated in FIGS. 1 to 11, that is to say that the walls bearing the faces 3 to 8 of the body 2 of the satellite 1 envelop and extend between the posts 12. In other words, the posts 12 materialize the real contour of the body 2.
    Alternatively, the posts 12 may be placed at the outer periphery of the body 2, that is to say that the posts define a virtual contour of the body 2, the walls carrying the faces 3 to 8 of the body 2 of the satellite 1 s extending inside this virtual outline.
    The geometric center C of the body 2 is for example the center of gravity of the body 2. The four columns 12 are preferably arranged equidistant from the geometric center C, at the vertices of a rectangle or a square, depending on the dimensions of the faces 5 North and South 6.
    Thus, as shown in Figures 2 and 3, the walls of the body 2 embodying the faces 3, 4 West, East and 7, 8 Earth, anti-Earth of the satellite 1 are each fixed between two posts 12. The volume delimited by the body 2 of the satellite does not extend beyond the posts 12.
    Each post 12 comprises two ends, namely a so-called distal end 13 and a so-called proximal end 14, the adjectives "distal" and "proximal" being taken here with reference to the distance with a vehicle interface structure of a launcher, as will be explained later, a proximal end 14 being closer to the vehicle interface structure than a distal end 13. The distal ends 13 of the posts 12 of the satellite 1 are preferably in the same transverse plane. Similarly, the proximal ends 14 of the posts 12 are also located in the same transverse plane. However, nothing prevents that all the posts 12 of a satellite 1 have a different size to adapt to the configuration of the satellite 1. At least one of the ends 13, 14 is provided with a releasable locking device 15. In practice, each end 13, 14 of the posts 12 of the satellite 1 is provided with a releasable locking device 15.
    The posts 12 are intended to allow the stacking of at least two satellites 1 one on the other, so that the transmission of forces between the two stacked satellites 1 pass mainly, and preferably exclusively, the posts 12 Thus, advantageously, the longitudinal dimension of the posts 12 is greater than that of the body 2, and even more advantageously, it is greater than that of the body 2 taking into account equipment such as solar panels 10 when they are folded. More specifically, and according to the example presented, the distal end 13 and the proximal end 14 are found at least at the same level as the folded solar panels 10, or even extend beyond. For this purpose, each locking device of each satellite 1 may have two states: a locked state, in which the locking device is attached to another complementary locking device, for example a locking device of another satellite 1, so that the two satellites 1 are integral with each other; an unlocked state, in which the locking device 15 is released from any other locking device, so that the satellite 1 finds itself physically independent of any other satellite 1.
    Two satellites 1 are therefore stacked by placing their respective posts 12 opposite each other and in the same longitudinal direction A, for example by bringing the distal end 13 of the posts 12 of a first satellite 1 of the end 14 proximal posts 12 of a second satellite. Then the locking devices of the first satellite are brought into cooperation with the locking devices of the second satellite, and each locking device is put in the locked state. The two satellites 1 are then integral with each other.
    As will be explained below, each satellite stack comprises a device for controlling the satellites 1 locking devices of the stack for separating the satellites to drop them into space.
    The posts 12 are distributed around the periphery of the body 2 so as to ensure a better recovery of the forces between the satellites 1, while taking into account the bulk in the environment of the body 2 of the satellite 1. Indeed, the more posts 12 are away from the center C of geometry of the body 2, and therefore from each other, the stability of the stack of two satellites 1 is greater, and the shear stresses on the stacked columns 12 are high. The distance between the posts 12 and the center C geometry sought is therefore the largest possible given the congestion both around the body 2 of the satellites and in the launcher. Therefore, this minimizes the amount of material needed for the posts while maximizing the mechanical strength of the satellite.
    Such an arrangement of the posts 12 also makes it possible, on the one hand, to maximize the space available for the arrangement of the satellite 1 and, on the other hand, to minimize the overall size of a satellite stack under the launcher cover by allowing the satellites from above or below to extend partially inside the satellite 1. In order to limit the shear deformation of the posts 12 when the stacked satellites are subjected to forces, each satellite 1 further comprises a reinforcement structure 16 rigidly and transversely connecting each pole 12 of the satellite 1 to at least two other posts 12 of the satellite 1.
    The reinforcing structure 16 comprises reinforcing elements in the form of branches 17, which connect the posts 12 to each other. The number of branches 17 is then equal to the number of posts 12. According to the example of Figures 2 and 3, the branches 17 are four in number and are arranged along the diagonals of the square or the rectangle formed by the posts 12. More specifically, each branch 17 is fixed rigidly on the one hand to a pole 12 and on the other hand to the same center of attachment of the body 2, which is confused, according to the example presented here, with the geometric center C of the body 2 Each branch 17 of the reinforcing structure 16 may have a longitudinal dimension substantially equal to the longitudinal dimension of the post 12 on which it is fixed.
    Thus, the branches 17 of the reinforcing structure 16 stiffen the posts 12 subjected to efforts tending to deform them transversely, including shear deformations.
    The branches 17 of the reinforcement structure 16, forming a spider inside the body 2, increase the space inside the body 2 of the satellite 1 negligibly. Indeed, the thickness of the branches 17, that is to say their dimension in the transverse plane, can be adapted to be able to arrange the space inside the body 2. For example, as shown in FIGS. and 3, the space inside the body 1 remains available to place four tanks 18, the branches 17 defining two by two a compartment.
    Alternatively, the reinforcing structure 16 may be formed by walls of the body 2, in this case according to the example shown, the walls embodying the faces 3, 4 West, East and 7, 8 Earth, anti-Earth satellite 1, which, being fixed on the posts 12 and connecting them two by two, also provide rigidity. In this case, the reinforcing structure 16 does not increase at all the bulk of the body 2 of the satellite 1.
    The reinforcement structure 16 may furthermore comprise shear consolidation elements 19, to further increase the rigidity of the posts with respect to the shear forces, and connecting the branches 17 in pairs.
    The posts 12, the branches 17 and the shear consolidation elements 19 are sized according to the dimensions and weight of the satellites 1, as well as the forces expected in the launcher. In particular, the posts 12 may be hollow and used to pass conduits or cables for satellite equipment 1, but may also be full to withstand high stresses. The section of the posts 12 may also be of circular, rectangular, T-shaped cross section, etc. depending on the constraints to bear. The shape of the cross section may vary along its length. Their material can be of any type such as: aluminum, titanium, composite, or another material.
    Figures 4 to 7 are schematic representations of the posts 12, four in number arranged at the vertices of a square, connected by branches 17 as presented above, and shear consolidation elements 19 according to two embodiments. According to a first embodiment (FIGS. 4 and 5), the consolidation elements 19 are arranged transversely between two branches 17. For example, the consolidation elements 19 are in the form of a longitudinal succession of triangular plates, extending in the compartment formed between two adjacent branches 17. According to a second embodiment (FIGS. 6 and 7), the consolidation elements 19 are arranged longitudinally between two adjacent branches 17 and are in the form of a rectangular plate. In this case, the walls of the body 2 embodying the faces 3, 4 West, East and 7, 8 Earth, anti-Earth of the satellite 1 can act as consolidation elements 19 in shear.
    The structure of the satellite thus described makes it possible for the satellites 1 to be stacked in a launcher 20, so that the transmission of the forces between the satellites 1 passes mainly, or even exclusively, by the posts 12. The stacked satellites 1 are placed in the launcher which comprises conventionally a vehicle interface structure 21. The vehicle interface structure 21 is a prior art structure known in itself by those skilled in the art for interfacing a satellite with a launcher, and to secure them. Optionally, depending on the launcher in question, the vehicle interface structure 21 can be broken down into two parts: a lower cone 21a secured directly to the launcher and corresponding to the conventional launcher interfaces, and an adapter 21b located between the lower cone 21a. and the stack of the satellites 1. The adapter 21b makes it possible to transform the distribution of the forces provided by the stack of the satellites 1 into a distribution of the forces compatible with the specification of the chosen launcher and its standard lower cone 21a. The adapter 21b is considered as being able to be supplied with the stack of the satellites 1.
    Figures 8 and 9 illustrate an example of a stack of six satellites 1 on the vehicle interface structure 21 using a lower cone 21a and an adapter 21b. The posts 12 of the satellites are all oriented in the same longitudinal direction A from the interface structure 21, so that the distal end 13 of the posts 12 of a first satellite 1 is opposite the the proximal end of the posts 12 of a second satellite, the distal end 13 of the posts 12 of the second satellite 1 facing the proximal end of the posts 12 of a third satellite, and so on. to the sixth and last satellite 1. In other words, the north face 5 of a satellite 1 faces the south face 6 of the adjacent satellite 1 in the stack according to the example presented here.
    Preferably, the longitudinal dimension of the posts 12 is such that the solar panels of two adjacent satellites 1 are not in contact. In general, two adjacent satellites 1 of a stack are in contact only with their posts 12.
    The releasable locking devices are all preferably identical, facilitating the manufacture and management of the satellites 1.
    The posts 12 make it possible to stack the satellites in such a way as to optimize the undercap space in a launcher, in particular by making it possible to stack the satellites by alternating the orientation of the satellites 1 so that the equipment of two adjacent satellites does not interfere. not. For example, the satellites 1 of a stack may all have their faces 7 Earth and 8 anti-Earth oriented in the transverse direction as illustrated, or all in the longitudinal direction. The orientation around the longitudinal direction can also be alternated between the stacked satellites 1: for example, as illustrated in FIGS. 8 and 9, respectively the west face 3 and the earth face 7 of a satellite 1 can be oriented to the earth. opposite respectively of the west face 3 and the face 7 Earth of the adjacent satellite 1, so that the antennas 9 of the two adjacent satellites 1 do not interfere with each other. More generally, the orientation of the satellites 1 stacked in the launcher depends directly on the bulk on the different faces 3 to 8 of the bodies 2.
    In order to place the satellites 1 in a launcher 20 provided with a structure 21 of vehicle interface, the stack of satellites 1 is first formed as described above. The proximal end 14 of each post 12 of the first satellite 1 is then placed opposite the interface structure 21, under the cap 22 of the launcher 20. The interface structure 21 is then adapted to cooperate with the releasable locking devices of the first satellite 1. As for the other satellites 1, the first satellite 1 of the stack, fixed on the interface structure 21, is in contact with the structure 21 preferably only 12. Optionally, the first satellite 1 of the stack may comprise an adapter 21b already coupled with the proximal end 14 of each of its posts 12 and which will then be coupled with a lower cone 21a already installed in the launcher. Alternatively, the satellites 1 can be installed one by one in the launcher 20. No intermediate structure is required between the cap 22 of the launcher 20 and the satellites 1. This results in a gain in space and weight. In addition, it is thus possible to adapt the number of satellites 1 according to the capacity of the launcher 20.
    The number of stacked satellites 1 does not affect the design of the posts 12 and the structure 16 of satellite reinforcement. Indeed, to stack the satellites, it is understood that only a requirement relating to the disposition of the posts 12 is required to allow the matching of the ends 13, 14 of the posts 12 of two satellites 1. Thus, it is possible to produce the satellites 1 identical, in series. It is also possible to dimension the posts 12, the branches 17 and shear consolidation elements 19 according to the position of the satellite 1 in the stack. In fact, the first satellite 1, the closest to the vehicle interface structure 21, is generally the one that bears the most effort because of the weight of all the other satellites 1 stacked. Thus, the posts 12 and the reinforcement structure 16 of the first satellite 1 may be oversized relative to the other satellites 1 of the stack. Similarly, for the last satellite 1 of the stack, the posts 12 and the reinforcing structure 16 may be undersized.
    In FIG. 12, there is shown an exemplary embodiment of releasable locking devices 15 between the distal end 13a of a pole 12a of a first satellite and the proximal end 14b of a pole 12b of a second satellite . According to this example, the releasable locking devices are one-sided, i.e. a single transition from the locked state to the unlocked state is provided, and a return to the locked state is not planned. The costs of releasable locking devices are thus low. However, it is not excluded another embodiment in which the releasable locking devices can be locked again after unlocking, to allow ground test phases for these devices.
    According to this example, the posts 12a, 12b are hollow, at least from their ends.
    The releasable locking device 15 on the pole 12a of the first satellite comprises a male part 23 inserted into the distal end 13a of the post 12a and is rigidly fixed thereto, for example by screws 25. The releasable locking device 15 on the post 12b of the second satellite is complementary to that of the first satellite, and comprises a female part 24 inserted in the proximal end 14b of the post 12b and is likewise fixed rigidly by screws 25. To pass the releasable locking devices 15 in the locked state the male part 23 is inserted into the female part 24, and locking means 26, for example of the screw type, connect the two parts 23, 24. Preferably, a clearance is provided between the two parts 23, 24, so that to allow a longitudinal clearance between the two posts 12a, 12b. Damping means 27, diagrammatically illustrated by springs in FIG. 12, can be mounted on the male part 23, so that when the post 12b of the second satellite approaches the post 12a of the first satellite, for example under FIG. effect of shock and / or vibration the contact between the two posts 12a, 12b is damped. The locking means 26 are coupled to unlocking means, not shown in FIG. 12. These unlocking means make it possible to eliminate the connection between the male part 23 and the female part 24, so that the locking devices are in the unlocked state. It may be for example pyrotechnic means for removing the locking means 26 screw type. In a variant, the locking means 26 comprise a magnetic element, such as an electromagnet: the supply of a current makes it possible to connect the two parts 23, 24, putting the locking devices in the locked state. It then suffices to cut the power supply to put the locking devices in the unlocked state. Alternatively, the locking means 26 could be located around the ends of each post.
    During the phase of satellite dropping, the damping means 27 also facilitate the separation of two previously stacked satellites, allowing their respective distance following the passage of the locking means 26 in the unlocked state.
    A second example of satellite 100 is shown in FIGS. 13 to 15.
    The satellite 100 according to the second example also comprises a body 102 having four faces called faces 105 North, face 106 South, face 107 East, face 108 West, with reference to the terrestrial cardinal points, and two faces called face 104 Earth and face 103 anti -Terre, with reference to the orientation of these faces with respect to the Earth. Equipment, such as antennas 109, solar panels 110 shown folded on the faces 105 North and 106 South, are assembled on the body 102. Antennas 111 may also be provided on the face 104 Earth. This is for example a telecommunications satellite.
    The satellite 100 also comprises posts 112. According to this second example, the posts 112 are placed at the outer periphery of the body 102 of the satellite 100, and extend as previously in the same longitudinal direction A, perpendicular to the faces 105 North and 106 South. More specifically, according to this second example, two posts 112 are arranged against the face 104 Earth and two other posts are disposed against the face 103 anti-Earth.
    The arrangement of the posts 112 is a compromise between the bulk around the body 102 of the satellite 100 and the mechanical strength requirements of the stack of the satellites 100.
    Indeed, as before, the posts 112 are each provided with at least one, in practice two, each disposed at one end 13, 14 of a post 12, releasable locking devices 115 to allow the assembly of 100 satellites between them and possibly with a satellite interface structure 121 of a launcher 120. As before, the satellite interface structure 121 may comprise two elements not shown, namely a lower cone launcher side and a side adapter. satellites. Releasable locking devices 115 are substantially identical to those already described. The reinforcing structure 116 is substantially identical to that of the first example, and comprises branches 117 in the form of braces, connecting the posts 112 to each other through the geometric center C of the satellite body 102. The walls bearing the faces North 105, South 106, Earth 104, and anti-Earth 103 can either replace the branches 117 and form in themselves the reinforcing structure 116, or participate in the shear strength of the posts 112 as consolidation elements in shear. The stack of satellites 100 according to the second example is substantially identical to the stacks already described with reference to the first embodiment. Thus, the stacked satellites 100 are facing each other by their faces 105 North and 106 South, and can be oriented differently from each other around the longitudinal direction according to the space requirement and the space available under the cover 122 of the launcher 120 .
    The satellite 1, 100 thus described makes it possible to envisage heterogeneous stacks, that is to say having more than one type of satellite. Thus, for the same stack to be placed in a launcher 220, it is possible to consider several satellites 1, 100, in this case five according to the present example according to FIG. 16 denoted S1, S2, S3, S4, S5, from several production sites, labeled PROD1, PROD2, PROD3 and PROD4, and different from each other, and form the stack once at the launch site. For example, the satellite S1 and the satellite S2 come from the same production site PROD1. The satellite S2 is itself formed by assembling the elements E1 and E2, which can be intended to be released later and separately in space. The production site PROD1 then provides a group comprising the satellite S1 stacked on the satellite S2, the devices 15, 115 for locking between the two satellites S1 and S2 then being in the locked state. The satellite S3 comes from the production site PROD2, the satellite S4 comes from the production site PROD3, and the satellite S5 is formed of three elements E3, E4, E5 coming from the production site PROD4. On the launch site, therefore, are the group comprising satellites S1 and S2, satellite S3, satellite S4 and satellite S5. The posts 12, 112 of the five satellites S1 to S5 may be different, but they are arranged to allow stacking.
    The satellite S4 is first locked on the satellite interface structure 221 of the launcher 220. Optionally, the satellite S4 may be previously coupled with an adapter which will then be coupled, in the launcher, with a lower cone already installed in the launcher . Then, a new group is formed outside the launcher 220, locking the satellite S5 under the group formed by the satellites S1 and S2. The new group of satellites S5, S2, S1 is then stacked on the satellite S4, in the launcher 220, by putting in the locked state the locking devices 15 between the satellite S4 and the satellite S5. Finally, the satellite S3 is locked on the satellite S1 of the new satellite group S5, S2, S1. The device for controlling the state of the locking devices can be either on board the launcher or comprise several modules each aboard one of the satellites S1 to S5 or a satellite of a group. The control can be programmed in the control device or emitted from the ground. The satellites S3 and S4 do not necessarily have a structure according to the invention comprising poles, but they nevertheless have compatible locking / unlocking means as well as the ability to withstand the forces exerted during launch by the satellite stack with which they are interconnected.
    The stacking and assembly sequence in the launcher 220 can be adapted according to what is provided by the production sites and the order in which the satellites S1 to S5 are to be dropped into space.
    Once the launcher 220 in space, the satellites S1 to S5 can be released through the device of the state control of the locking devices. For example, the satellite S3 is first dropped by passing in the unlocked state the locking devices between the satellite S3 and the satellite S1. Then, the satellite group S5, S2, S1 can be dropped in block, by putting in the unlocked state the locking devices 15 between the satellite S4 and the satellite S5. The satellites S5, S2, S1 can then be separated later from each other once dropped in space. Finally, the satellite S4 is separated from the satellite interface structure 221. The latch state control device can program the satellite drop sequence in advance.
    The release sequence does not have to take into account possible balancing problems within the launcher.
    The space vehicle according to the invention is suitable for any type of space mission (telecommunications, navigation, space vehicles for earth observation, science, space exploration), whatever their orbit (LEO, GEO, MEO, HEO).
    In addition, equipment alone can also be dropped into space through this structure. Satellites of a constellation can also be dropped in groups (eg, orbital plane) or one by one.
    The space vehicle according to the invention is well suited for a mass of satellites generally 1 ton or more, but could also be applied, without loss of generality, to smaller satellites of a few kilograms, allowing to have one or several stacks located "side by side" under the launcher's cap.
    权利要求:
    Claims (18)
    [1" id="c-fr-0001]
    A spacecraft (1, 100), such as a satellite, for orbiting a planet, the vehicle (1, 100) comprising: at least one carrier module (2, 102), for supporting vehicle equipment (1, 100); at least three posts (12, 112) extending at least partially in the same longitudinal direction (A) and at the periphery of the equipment carrying module (2, 102), each post (12, 112) being provided with minus one releasable locking device (15, 115) for taking two states: o a locked state, wherein the locking device (15, 115) is attached to a complementary locking device (15, 115), o a state unlocked, wherein the locking device (15, 115) is released from any other locking device (15, 115); a reinforcing structure (16, 116) rigidly interconnecting each post (12, 112) with at least two other posts (12, 112).
    [2" id="c-fr-0002]
    The space vehicle (1, 100) according to claim 1, wherein the reinforcing structure (16, 116) comprises branch-shaped reinforcing elements (17, 117) whose number corresponds at least to the number of poles ( 12, 112), each leg (17, 117) being fixed between two posts (12, 112).
    [3" id="c-fr-0003]
    Spatial vehicle (1, 100) according to claim 2, wherein the legs (17, 117) coincide with the walls of the equipment carrying module (2, 102), the support walls for vehicle equipment (1). , 100).
    [4" id="c-fr-0004]
    The space vehicle (1, 100) according to claim 1, wherein the reinforcing structure (16, 116) comprises branch-shaped reinforcing elements (17, 117) whose number corresponds at least to the number of poles ( 12, 112), each leg (17, 117) being fixed on the one hand to a pole (12, 112) and on the other hand to the same center (C) of attachment.
    [5" id="c-fr-0005]
    5. Vehicle (1, 100) according to any one of claims 2 to 4, wherein the branches (17, 117) of reinforcement are connected in pairs by shear consolidation elements (19).
    [6" id="c-fr-0006]
    6. Vehicle (1, 100) according to any one of the preceding claims, wherein the posts (12, 112) are three in number and are distributed at the vertices of an equilateral triangle.
    [7" id="c-fr-0007]
    7. Vehicle (1, 100) according to any one of claims 1 to 5, wherein the posts (12, 112) are four in number and are distributed at the vertices of a parallelogram.
    [8" id="c-fr-0008]
    The vehicle (1, 100) according to any one of the preceding claims wherein each releasable locking device (15, 115) comprises a magnetic element.
    [9" id="c-fr-0009]
    9. Vehicle (1, 100) according to any one of the preceding claims wherein each releasable locking device (15, 115) comprises a pyrotechnic element.
    [10" id="c-fr-0010]
    The vehicle (1, 100) according to any one of the preceding claims, wherein each post (12, 112) is provided with two releasable locking devices (15, 115).
    [11" id="c-fr-0011]
    11. Vehicle (1, 100) according to any one of the preceding claims, wherein each post extends longitudinally between two ends (13, 14), each end (13, 14) being provided with a device (15, 115) lock.
    [12" id="c-fr-0012]
    12. A method of assembling at least two vehicles (1, 100) according to one of claims 1 to 11, comprising the steps of: placing in position the at least two vehicles (1, 100) so that the poles (12, 112) of a first vehicle (1, 100) extend at least partially in the same longitudinal direction as the posts (12, 112) of the second vehicle (1, 100); interlocking each locking device (15, 115) of the first vehicle (1, 100) with a device (15, 115) for locking the second vehicle (1, 100); locking the first vehicle (1, 100) locking devices (15, 115) to the locking devices (15, 115) of the second vehicle (1, 100) in the locked state.
    [13" id="c-fr-0013]
    13. Stack of vehicles (1, 100) according to any one of claims 1 to 11, comprising at least two vehicles (1, 100) integral with each other, the at least one device (15, 115). releasably locking each post (12, 112) of a first vehicle (1, 100) in the locked state with a latch device (15, 115) on a pole (12, 112) of the second vehicle (1 , 100), the posts (12, 112) of each vehicle extending in the same direction (A) longitudinal, the stack further comprising a device for controlling the state of the locking devices (15, 115).
    [14" id="c-fr-0014]
    The stack of vehicles (1, 100) according to claim 13, wherein the vehicles (1, 100) are satellites comprising a face (7, 104) Earth and an anti-Earth face (8, 103), the faces Earth and anti-Earth being oriented in the direction (A) longitudinal poles (12, 112).
    [15" id="c-fr-0015]
    Vehicle stack according to claim 13, wherein the vehicles (1, 100) are satellites comprising a face (7, 104) of the Earth and an anti-Earth face (8, 103), the faces (7, 104). Earth and (8, 103) anti-Earth being oriented in a direction transverse to the posts (12, 112).
    [16" id="c-fr-0016]
    16. Launcher (20, 120, 220) of space vehicles (1, 100), the launcher comprising a vehicle interface structure (21, 121, 221) and at least a first stack of vehicles (1, 100) according to the invention. any one of claims 13 to 15, wherein at least the first vehicle (1, 100) of the stack is a vehicle (1, 100) according to claim 10 or claim 11, a first device (15, 115) each pole (12, 112) of the first vehicle (1, 100) being in the locked state on a device (15, 115) for locking the second vehicle (1, 100), the second device (15, 115) ) of each pole (12, 112) of the first vehicle (1, 100) being in the locked state on the vehicle interface structure (21, 121, 221).
    [17" id="c-fr-0017]
    17. A method of releasing vehicles (1, 100) by means of a launcher (21, 121, 221) according to claim 16, comprising a step of separating a vehicle (1, 100) to be dumped and a vehicle (1 , 100) intended to remain in the launcher by setting the unlocking devices (15, 115) between the two vehicles (1, 100) in the unlocked state to release a single vehicle (1, 100).
    [18" id="c-fr-0018]
    18. A method of releasing vehicles (1, 100) by means of a launcher (21, 121, 221) according to claim 16, comprising a step of separating a group of vehicles (1, 100) to be dumped and a vehicle. (1, 100) for remaining in the launcher by setting in the unlocked state the devices (15, 115) for locking between a vehicle (1, 100) of the group to be released and the vehicle (1, 100) intended to remain in the launcher (20, 120, 220), so as to drop the group of vehicles (1, 100).
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    同族专利:
    公开号 | 公开日
    FR3040978B1|2017-10-06|
    CN108137172B|2021-02-05|
    US20180111707A1|2018-04-26|
    JP6448855B2|2019-01-09|
    JP2018527243A|2018-09-20|
    EP3259190B1|2018-07-18|
    US10017279B2|2018-07-10|
    CN108137172A|2018-06-08|
    WO2017046497A1|2017-03-23|
    EP3259190A1|2017-12-27|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5199672A|1990-05-25|1993-04-06|Orbital Sciences Corporation|Method and apparatus for deploying a satellite network|
    WO1996039328A1|1995-06-06|1996-12-12|Aerospatiale Societe Nationale Industrielle|Tilting adapter device for carrying a plurality of payloads on a single launch vehicle|
    WO2000009396A2|1998-08-10|2000-02-24|The Boeing Company|Multiple spacecraft carrier on launcher|
    US20080078886A1|2006-08-22|2008-04-03|The Boeing Company|Launch vehicle cargo carrier|
    US20150232205A1|2014-02-14|2015-08-20|Carey LIVELY|Dual spacecraft design and deployment system and method of use thereof|CN111674567A|2020-06-18|2020-09-18|中国科学院微小卫星创新研究院|Constellation satellite configuration|
    CN112193441A|2020-09-29|2021-01-08|哈尔滨工业大学|Multi-satellite locking ejection mechanism in space|US5411226A|1993-10-13|1995-05-02|Martin Marietta Corporation|Spacecraft adapter and dispenser|
    US5522569A|1994-02-04|1996-06-04|Orbital Sciences Corporation|Satellite having a stackable configuration|
    US5605308A|1994-06-06|1997-02-25|Mcdonnell Douglas Corp.|Space vehicle dispenser|
    US5884866A|1996-09-17|1999-03-23|Mcdonnell Douglas Corporation|Satellite dispenser|
    DE19856670B4|1998-12-09|2004-12-02|Eads Space Transportation Gmbh|Satellite launching device|
    US7832687B1|2004-08-24|2010-11-16|Lockheed Martin Corporation|On-orbit storage, plane change, and injection to final orbit of space vehicles|
    US8016240B2|2007-03-29|2011-09-13|The Boeing Company|Satellites and satellite fleet implementation methods and apparatus|
    FR2954284B1|2009-12-18|2012-05-04|Thales Sa|DEVICE FOR DEPLOYING AND POINTING STRUCTURING ELEMENTS IN A SPATIAL ENVIRONMENT|
    US8939409B2|2012-05-07|2015-01-27|The Johns Hopkins University|Adaptor system for deploying small satellites|
    US8915472B2|2012-05-11|2014-12-23|The Boeing Company|Multiple space vehicle launch system|
    CN103303494B|2013-05-30|2016-02-17|西北工业大学|There is the Performances of Novel Nano-Porous satellite structure from carrying and launch function|
    EP3012194B1|2014-10-24|2020-07-08|Thales|Manipulation of a satellite in space|US10351268B2|2016-12-08|2019-07-16|The Boeing Company|Systems and methods for deploying spacecraft|
    US11072441B2|2017-03-03|2021-07-27|Northrop Grumman Systems Corporation|Stackable spacecraft|
    US11059609B2|2017-08-04|2021-07-13|Rocket Lab Usa, Inc.|Satellite deployer with externally adjustable payload restraint|
    KR102002306B1|2018-01-08|2019-07-22|주식회사 버츄얼랩|Cubesat Space Deployer|
    IL258729A|2018-04-16|2021-12-01|Israel Aerospace Ind Ltd|Nano-satellite|
    CN112319853B|2020-11-16|2021-09-24|三亚中科遥感研究所|Microsatellite configuration design adapting to cylindrical fairing space one-rocket multi-satellite launching|
    法律状态:
    2016-09-27| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-17| PLSC| Search report ready|Effective date: 20170317 |
    2017-09-25| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-16| ST| Notification of lapse|Effective date: 20200910 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1558695A|FR3040978B1|2015-09-16|2015-09-16|SPATIAL VEHICLE COMPRISING STACKS FOR FORMING A STACK, STACKING COMPRISING AT LEAST TWO SUCH VEHICLES PLACED IN A LAUNCHER AND METHOD OF LAGGING THE VEHICLES|FR1558695A| FR3040978B1|2015-09-16|2015-09-16|SPATIAL VEHICLE COMPRISING STACKS FOR FORMING A STACK, STACKING COMPRISING AT LEAST TWO SUCH VEHICLES PLACED IN A LAUNCHER AND METHOD OF LAGGING THE VEHICLES|
    CN201680059293.8A| CN108137172B|2015-09-16|2016-09-12|Spacecraft comprising a mast forming a stack, stack comprising at least two such spacecraft housed in a launcher, and method for airdropping a spacecraft|
    US15/564,816| US10017279B2|2015-09-16|2016-09-12|Space vehicle comprising posts for forming a stack, stack comprising at least two such vehicles placed in a launcher, and method for releasing the vehicles|
    JP2018513521A| JP6448855B2|2015-09-16|2016-09-12|A spacecraft with pillars for forming a stack, a stack with at least two such spacecraft installed in a launcher, and a method for lowering a spacecraft|
    PCT/FR2016/052287| WO2017046497A1|2015-09-16|2016-09-12|Space vehicle comprising posts for forming a stack, stack comprising at least two such vehicles placed in a launcher, and method for releasing the vehicles|
    EP16775300.3A| EP3259190B1|2015-09-16|2016-09-12|Space vehicle comprising posts for forming a stack, stack comprising at least two such vehicles placed in a launcher, and method for releasing the vehicles|
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