Dispenser for transporting a satellite as well as satellite

Abstract

A dispenser (1) for receiving and transporting a satellite (2) and a satellite (2) that can be transported with such a dispenser (1) are described. The dispenser (1) has a housing (3) for storing the satellite (2) in a transport position during transport, wherein a guide (4) is provided inside the housing (3) along which the satellite (2) can be moved at least nearly in a straight line relative to the transport position. Furthermore, an ejection element (8) is provided by which the satellite (2) can be moved along the guide (4) from the transport position to an ejection position in which the satellite (2) is located outside the housing (3).The described technical solution is characterized in that the guide (4) has a central guide rod (5) which is arranged inside the housing (3) of the dispenser (1) and is at least partially surrounded by the satellite (2) arranged in the transport position, wherein a sliding element (6) of the satellite (2) is movable along the guide rod (5) in such a way that the satellite (2) can be guided in a linear movement relative to the transport position.

Description

The invention relates to a dispenser for transporting at least one satellite and to a satellite which can be arranged in such a dispenser for its transport. The dispenser has a housing for storing the satellite during transport in a transport position, wherein a guide is provided in the interior of the housing, along which guide the satellite is movable at least almost linearly relative to the transport position. Furthermore, an ejection element is provided, by means of which a movement of the satellite along the guide from the transport position into an ejection position outside the housing can be initiated.In the field of space technology, dispensers are understood to mean devices in which satellites, in particular small satellites, are arranged during their transport with a carrier rocket to the required flight height. After reaching the flight altitude provided for the respective satellite, an ejection mechanism provided in the dispenser is activated and the satellite is then ejected from the dispenser into the provided position. Dispensers of this type are used above all for the transport of small satellites. Small satellites are divided into a plurality of different satellite classes, the invention described below being suitable in particular for nanosatellites having a weight of 1 to 10 kg. In this context, what are known as cube-shaped substrates are known, which are distinguished by a cube-shaped basic structure. Satellites of this type were used for the first time in 2004 and have become established as an industrial standard in the meantime. These small satellites are used above all for so-called low cost technology testing missions, but also for carrying out close-to-ground experiments.The development and use of small satellites represent a fast growing market in the space industry. Small satellites, such as CubeAts, can be mounted on carrier rockets as a so-called secondary payload because of their low mass and can be ejected when the desired deployment height is reached. In order not to compromise the transport sequence, the small satellites are inserted into so-called dispensers, which exclude all interactions between the satellites and the carrier rocket. Dispensers serve on the one hand to protect the satellites to be transported and on the other hand they have suitable ejection elements by means of which the respective satellite is ejected at the desired flight height and position. In the known cube-seat, the respective required printed circuit boards are stacked, spacers being provided between the individual printed circuit boards. The printed circuit board stack is arranged within a cube-shaped frame structure, wherein guide rails are located at the outer edges, which can be guided along suitable counter elements in the interior of a dispenser. With the aid of these guide rails and the counter elements provided in the dispenser, a satellite can be pushed into a dispenser and ejected from the dispenser in a linear direction when the required ejection height is reached.Usually, when a satellite is inserted into a dispenser, a compression spring of the ejection mechanism is tensioned and the satellite and the ejection mechanism are tensioned in a transport position by means of a hold-down-on-release mechanism (HDRM). The ejection of the satellite is initiated by the release of the HDRM, so that the compression spring relaxes and the satellite accelerates.In this context, DE 20 2014 008 902 U1 discloses a device for transporting and ejecting small satellites. The described device comprises a container with a lid, guide rails, an ejection spring, a locking mechanism for the lid and a locking spring. The essential aspect of the described technical solution is that the small satellite to be transported is fixed in its transport position in the three spatial directions by means of additional clamps and spring elements. After the insertion of a satellite into the described container, a pull rod coupled to the pivoting movement of the cover is moved. The pull rod actuates pressure pieces which press the small satellite laterally against the guide rails. Furthermore, when the cover is finally closed, a ball-and-spring system installed over a cover generates a force acting perpendicularly thereto on the side struts of the small satellite, so that the satellite is locked in the three possible degrees of freedom. The described dispenser is intended to ensure during transport that the satellite is securely fixed in all three spatial directions.The known transport systems for small satellites consisting of the satellite and a dispenser have a plurality of different components, which in particular with regard to production is a disadvantage, above all due to the high number of individual components and a comparatively high assembly effort caused thereby. Furthermore, the known arrangement of the guide rails on the outer sides of the known small satellites limits the useful surface available for the attachment of functional elements, such as solar panels or antennas.Proceeding from the solutions known from the prior art and the problems described above, the object of the invention is to specify a dispenser and a satellite, in particular a small satellite, which can be produced in a comparatively simple, efficient manner and at the same time ensure that a satellite can be both inserted into a dispenser in a comparatively simple manner and transported and ejected in a reliable and reliable manner. Furthermore, the technical solution to be specified should be distinguished in that no guide elements, such as guide rails, are required on the outer sides of the satellite to be transported for the directed, guided movement of the satellite. In this case, it should be ensured that as far as possible the entire outer surfaces of a satellite are available for the attachment of solar panels or functional elements, for example antennas.The system for transporting satellites to be specified should moreover allow simple assembly or production of the main components satellite and dispenser and preferably open up the possibility of production by means of additive production methods. Furthermore, it is important that both dispensers and satellites, in particular small satellites, can be provided in different sizes and the technical solution to be specified enables simple scalability of the transport system for satellites.The object described above is achieved by means of a dispenser according to claim 1 and a satellite according to claim 11. Advantageous embodiments of the invention are the subject of the dependent claims and are explained in more detail in the following description with partial reference to the figures.The invention relates to a dispenser for transporting and later ejecting a satellite, in particular a small satellite, having a housing which can have a supporting structure with individual struts connected to one another, which is suitable for storing the satellite during transport in a transport position and which has a guide along which the satellite can be moved at least virtually rectilinearly relative to the transport position. Furthermore, the dispenser has an ejection element, by means of which the satellite can be moved in a targeted manner, in particular as soon as the flight height provided for the satellite is reached, along the guide from the transport position into an ejection position outside the housing. A dispenser embodied according to the invention is distinguished in that the guide has a central guide rod which is arranged in the interior of the housing and is surrounded at least in regions by the satellite arranged in the transport position, wherein a sliding element of the satellite can be moved along the guide rod in such a way that the satellite can be guided in a linear movement relative to the transport position. Thus, a central guide rod arranged in the interior of the housing, i.e. between outer boundaries such as boundary surfaces, is essential for the invention, which guide rod extends in the longitudinal direction of the dispenser and which permits both a simple insertion of the satellite into the transport position and a targeted guidance of the satellite during its movement from the transport position into the ejection position.By providing a central guide rod arranged in the interior of the housing of a dispenser, which guide rod can be designed with different profiles, it is ensured that no further guide elements are required in the region of outer surfaces of a satellite which is to be transported with a correspondingly configured dispenser, and thus the entire outer region of the satellite can be used for the arrangement of solar panels or functional elements, such as antennas. In this respect, the invention relates to a dispenser, a satellite and a system consisting of a dispenser and at least one satellite, which each use the invention, according to which a guide rod is provided in the interior of the dispenser, along which guide rod the satellite having a suitable counter element can be moved.In a first particular embodiment of the invention, it is provided that the central guide rod extends in the longitudinal direction of the dispenser and is designed as a solid body, that is to say as a body having at least virtually no cavity, or as a hollow body. Furthermore, it is conceivable for the guide rod to have a circular, oval or polygonal, for example square or hexagonal, cross section.Furthermore, a special embodiment of the invention provides that the guide rod is of cylindrical or tubular design. Depending on the respectively selected configuration of the central guide rod, which is arranged in the interior of the housing of the dispenser, the sliding element of the satellite is formed. It is preferably conceivable for the sliding element of a satellite, in particular of a small satellite or even nanosatellite, to be formed as a hollow body which is moved along the guide rod during a movement relative to the transport position. According to a very special development of the invention, the central guide rod of the dispenser is of tubular or cylindrical design, so that the sliding element of the satellite is preferably designed as a hollow cylinder or tube with a larger internal diameter than the external diameter of the guide rod.In a special development of the invention, a cross-sectional surface of the housing running perpendicular to the guide rod, i.e. an outer contour of the housing, has a plurality of corners, in particular six corners, so that the cross-sectional surface in this case has the shape of a hexagon or hexagon. The advantage of such a housing, which has a plurality of edges running in the longitudinal direction on its outer surface, is above all that between adjacent edges the interior space of the housing is bounded by planar outer surfaces, to which solar modules or functional elements can be fastened in a comparatively simple manner. The corresponding solar modules or functional elements thus do not have to have any curvature, as is the case, for example, as soon as the housing of a dispenser has a curved, for example round cross section transversely to the guide rod arranged in the interior. It is conceivable in this context that the outer surfaces of the dispenser housing are closed, wherein these closed outer surfaces are optionally formed by solar modules or functional elements themselves and / or by plate elements. If the housing walls delimiting the interior space with respect to the environment are not formed by solar modules or functional elements, but in some other way, for example by plate-shaped wall elements, it is conceivable to fasten solar modules and / or other functional elements, for example antennas, to the wall elements. According to a special embodiment of the invention, it is provided that the housing has a supporting structure with a plurality of struts, wall elements which at least in regions form an outer surface of the dispenser being connected to outer struts which surround the interior space and the central guide rod. Preferably, the housing of the dispenser according to the invention has outer surfaces which are arranged parallel to the guide rod and are closed with the aid of wall elements, and also has a base surface which is closed perpendicularly to the guide rod and likewise with a wall element at one end of the housing, and also has a housing opening which lies opposite the base surface and can be closed with the aid of a cover element. In the closed state of the housing opening, the interior of the housing in which the guide rod is arranged is thus completely closed. A satellite can be pushed into the transport position through the housing opening when the cover element is open into the interior and can be ejected from the transport position into the ejection position after the desired flight height has been reached. Preferably, the cover is fastened to the housing via at least one hinge. Furthermore, the cover element can be actuated manually and / or with the aid of an opening mechanism, so that the cover element can be transferred in a targeted manner from a closed position into an open position. It is very particularly advantageous if the opening mechanism is coupled, in particular mechanically coupled, to the ejection mechanism and / or an ejection element of the ejection mechanism, such that, when the ejection mechanism is actuated, a movement of the satellite from the transport position into the ejection position is initiated and the cover element is moved such that the opening of the housing is released.In a special embodiment of the invention, the dispenser has at least one ejection mechanism with an ejection element, which preferably has a compression spring designed as a helical spring, by means of which the satellite is accelerated in such a way that it is moved along the guide rod from the transport position into its ejection position. The ejection element, in particular a helical spring, is advantageously designed in such a way that energy is transmitted to the ejection element during the introduction of the satellite to be transported into the housing of the dispenser, said energy being stored in the ejection element. In a particularly preferred manner, this is done by biasing a spring of the ejection mechanism and releasing the stored energy to initiate movement of the transported satellite upon reaching the desired flight altitude. For transport, the satellite is locked in the transport position and the ejection mechanism. Only when the desired flight height of the carrier rocket is reached is the triggering mechanism activated and the locking mechanism released.During the ejection of the satellite, the satellite moves with its sliding element along the guide rod arranged in the interior of the dispenser housing. The movement along the guide rod takes place in an advantageous straight line, wherein the guide provided according to the invention ensures that no tilting of the sliding element of the satellite and of the guide rod of the dispenser occurs during the ejection of the satellite.It is particularly advantageous if the ejection mechanism is activated with the aid of a hold-down and release mechanism (HDRM) and released in such a way that the satellite transported is subsequently accelerated and set in motion. It is preferably conceivable for the hold-down and release mechanism to have a fusible wire which is destroyed by a current flow effected for a short time and as a result the spring force of at least one prestressed spring element which is held at least indirectly by the fusible wire is released. The heating of the fusible wire caused by a current flow is controlled in a targeted manner and preferably initiated from a ground station. Once the hold down and release mechanism (HDRM) activates, thereby releasing the lock on the satellite and placing the ejector into operation, the transported satellite moves along the guide rod of the dispenser from its transport position to the ejection position where the satellite has left the dispenser housing and is separated from the guide rod.According to a further advantageous embodiment, simultaneously or immediately after the hold-down and release mechanism (HDRM) has been activated, the cover element of the dispenser housing is opened, so that the satellite can be ejected from the interior of the housing without problems. Preferably, for this purpose, a mechanical coupling is provided between the hold-down and release mechanism (HDRM) and / or the locking of the satellite and a mechanism for opening the cover element, which can also be an unlocking of a tensioned closure. It is particularly advantageous if the cover element closes the housing interior until the satellite is set in motion.In a particular embodiment of the invention, a housing base which is aligned at least largely perpendicularly to the central guide rod and delimits the interior of the housing with respect to an environment is provided on a first side of the housing of the dispenser. This housing base, which closes off the dispenser on one side, is connected along its circumference to outer side walls of the housing, which are arranged perpendicularly thereto and are formed by housing plates, preferably in a materially bonded manner or else in one piece with the side walls. On the second side of the housing opposite this first side and thus the housing base, an opening is provided for the insertion and ejection of the satellite, which opening can preferably be closed by a cover element mounted in a foldable, pivotable or slidable manner. The cover element is preferably plate-shaped and connected at least indirectly via suitable joints and / or hinges to at least one of the outer side walls of the housing, which are oriented parallel to the central guide rod. For the targeted movement of the cover element, a piston rod and / or a spring element is preferably provided. It is likewise conceivable that, for opening the cover element, a holding element which holds the cover element in the closed position against a spring force of a spring is released, for example by using a hold-down and release mechanism (HDRM).According to a particular embodiment of the invention, the outer walls of the housing, which delimit the dispenser on the first side and on the sides, are formed by plate-shaped wall elements or housing plates, which are preferably planar. The individual wall elements can be fastened here with the aid of suitable fastening elements or in a materially integral manner to one another and / or to struts of a supporting structure. It is likewise conceivable for the housing of a dispenser, in particular the housing base provided on the first side and the side walls arranged parallel to the guide rod, to be embodied in one piece. Suitable production methods are in particular additive methods, such as injection molding or 3D-chuck, for example fused deposition modelling. As material for producing at least parts of the housing, preferably at least one plastic is used. The corresponding plate-shaped housing elements reliably protect the outer surfaces of the satellite to be transported, on which solar modules and or functional elements can be located.In a special development of the invention, it is provided that the ejection element has a spring element which is relaxed for initiating the movement of the satellite from the transport position into the ejection position, and a pressure element which is arranged between the spring element and the satellite in the transport position of the satellite. The pressure element advantageously has a connecting structure which can be brought into positive engagement with a counter structure of the satellite. As soon as a carrier rocket has reached the flight altitude at which the transported satellite is to be ejected from the dispenser, the triggering mechanism is activated and, according to this embodiment, the spring is released, the spring force is introduced into the satellite via the pressure element and the satellite is moved along the guide rod from the transport position into the ejection position. In this case, according to the described special embodiment, the form-fitting structure of the pressure plate is in engagement with the counter-structure of the satellite, so that it is ensured that the satellite is moved in the longitudinal direction along the guide rod without the latter executing a rotational movement caused by forces acting on the satellite transversely with respect to the longitudinal movement of the latter. Corresponding lateral forces are absorbed by the positive connection between the connecting structure of the pressure plate and the counter structure of the satellite. In this context, it is conceivable for the pressure plate to be fastened to the spring or to the satellite and to remain either on the satellite or on the spring accordingly after the ejection of the satellite. It is essential to this technical solution that an at least almost rectilinear transmission of the spring force into the satellite to be ejected is effected, independent of laterally entered forces.In addition to a particularly designed dispenser, the invention also relates to a satellite, in particular a small satellite and very particularly preferably a nanosatellite, which is suitable for being arranged in a receptacle of a dispenser according to at least one of the previously described configurations of a dispenser according to the invention in a transport position and moved from the transport position into an ejection position. The satellite according to the invention has at least one sliding element which is movable along a central guide rod of a dispenser designed according to the invention and enables secure guidance and rectilinear movement of the satellite relative to the transport position. It is particularly advantageous here if the shape of the outer surfaces and / or the contour of the satellite, in particular the configuration of the cross-sectional surfaces perpendicular to the longitudinal direction of the sliding element, are adapted to the circumferential shape of the cross-sectional surfaces of the dispenser housing.In this context, it is particularly advantageous if the cross-sectional surface of the satellite arranged perpendicular to the sliding element is formed polygonal, for example hexagonal, that is to say has a corresponding plurality of side edges running in the longitudinal direction. A particularly effective transport of the satellite or utilization of the useful volume provided by a dispenser can be realized in this case if the dispenser used has the same outer contour with a corresponding number of side edges running in the longitudinal direction and in particular has no curved surfaces. In this way, planar solar modules or other functional elements can be attached to the surface of the satellite over the entire area and distributed over the entire circumference and can be introduced into the dispenser together with the satellite in a simple manner and ejected therefrom.According to a further particular embodiment, it is provided that the satellite has a base structure which is formed by a plurality of rod elements or struts connected to one another and which is preferably connected to the sliding element of the satellite arranged in the interior of the base structure. On the one hand, plate-shaped elements, in particular solar panels, can be fastened to this base structure, which forms a support frame, on the outer surfaces in a relatively simple manner, and on the other hand, support elements can be arranged in the interior in addition to the sliding element, which support elements are suitable, for example, for receiving electrical or electronic components, energy stores and / or test setups. According to a special embodiment of the satellite according to the invention, it is thus provided that at least one, preferably a plurality of such plate-shaped support elements are provided, which are arranged transversely to the longitudinal direction of the sliding element provided in the interior. Preferably, at least one of the support elements is designed as a printed circuit board or board on which electronic components and the required conductor tracks and contact pins for contacting are arranged. It is likewise conceivable for components, assemblies, drive elements, reaction vessels, processors, data transmission elements provided for carrying out the tests provided to be arranged on the support elements and / or for components required for the energy supply and energy storage. It is particularly advantageous if the individual plate-shaped support elements surround the centrally arranged sliding element of the satellite at least in regions, preferably over the entire circumference. With a plurality of such supporting elements arranged one above the other, compartments or plates for fastening electronic components, energy stores, test setups and / or other functional elements can be provided as required in different planes.It is particularly advantageous here if the sliding element which projects centrally in the longitudinal direction through the satellite is designed as a tube, a circular cylinder, an oval cylinder and as a polygonal column.The technical solution according to the invention has the advantage that a dispenser and / or satellite can be scaled at least almost arbitrarily with regard to size. In addition, it is conceivable that a dispenser is designed or dimensioned in such a way that it can accommodate and transport a satellite or a plurality of satellites in the interior. The satellite or satellites can each be moved along the central guide rod, which is arranged in the interior of the dispenser, in the longitudinal direction of the dispenser. The satellite or satellites embodied according to the invention are introduced into the dispenser in the longitudinal direction and, when the desired flight height is reached, are ejected from the dispenser in the opposite direction. The provision of a central guide rod in the dispenser and a sliding element which is movable relative to the guide rod and is arranged in the interior of the satellite offers the advantage that no elements are required in the outer region of the satellite for its guidance along the dispenser guide.In the following, the invention is explained in more detail without limiting the general inventive concept on the basis of specific exemplary embodiments with reference to the figures. Identical components are identified in the different figures by the same reference numerals. The following are shown: FIG. 1 : Cross-sectional representation of a dispenser designed according to the invention with a satellite arranged therein in a transport position, FIG. 2 : Perspective illustration of a dispenser designed according to the invention with closed outer walls and a lifted-off lid, FIG. 3 : satellite formed according to the invention with a hexagonal cross-sectional area arranged perpendicular to the longitudinal direction and a number of carrier plates to be varied according to need, FIG. 4 : Oblique view from below onto a satellite with a central structure and a supporting frame extension, and FIG. 5 : satellite designed according to the invention with a circular cross-sectional surface arranged perpendicular to the longitudinal direction and a number of carrier plates to be varied according to requirements, and FIG. 6 : satellite formed according to the invention with a hexagonal cross-sectional area arranged perpendicular to the longitudinal direction and a supporting central structure for receiving a comparatively large number of carrier plates.FIG. 1 shows a cross-sectional representation of a dispenser 1 designed according to the invention, in which a satellite 2, here a small satellite, such as a nanosatellite with a weight of less than 10 kg, is arranged in a transport position. Before the satellite 2 is transported with a launch vehicle to the desired flight height at which the satellite 2 is to remain, it is pushed into the dispenser 1 and finally locked in the transport position. When the desired flight height is reached, the satellite 2, as will be explained in more detail below, is pushed out from its transport position into the ejection position outside the dispenser 1. It is essential for the dispenser 1 shown in FIG. 1 and the satellite 2 stored therein that a central guide 4 with a guide rod 5 of the dispenser 1 and a sliding element 6 of the satellite 2 is provided for secure movement of the satellite into the transport position and from the transport position into the ejection position, said central guide ensuring secure movement relative to the transport position in the longitudinal direction of the dispenser 1 and of the satellite 2.The dispenser 1 has a central guide rod 5 which is arranged in the interior of the dispenser 1, while the satellite 2 to be transported has a sliding element 6 with a suitable mating contour, for example in the form of a bushing, a tube or a long hollow body which extends in the longitudinal direction and is movable along the guide rod 5 and ensures a guided movement in the longitudinal direction of the dispenser 1, namely both in the direction of the transport position and from the transport position into the ejection position in which there is no longer any connection between the dispenser 1 and the satellite 2.The dispenser 1 shown in FIG. 1 has a housing 3 with housing plates 23 which form a protective outer wall, so that ultimately an enclosed interior space is provided which ensures secure transport of a satellite 2. Furthermore, the housing 3 has a housing base 24, to which the individual housing plates 23 and, centrally on the side facing the interior, a guide rod 5 are fastened or formed integrally with the housing base 24, for example by using an additive manufacturing method. Preferably, rods or braces for fastening the housing plates 23 are also provided on the inner side at the lateral edges of the housing plates 23 at which they abut against one another, which rods or braces are in turn connected to the housing base 24.Furthermore, the dispenser 1 shown in FIG. 1 has a cover 10, which can be detachably, preferably foldable, connected at the top side of the housing 3 at least indirectly to the housing plates 23 and / or the guide rod 5 and closes the housing opening 25 of the dispenser 1 with respect to the environment during transport. For the insertion and ejection of a satellite 2, the cover 10 can be opened in a targeted manner, so that the satellite 2 can be moved through the housing opening 25 of the dispenser 1 when the cover 10 is open.According to the embodiment shown in FIG. 1, the satellite 2 arranged in the interior of the dispenser 1 has a centrally arranged sliding element 6 in the form of a guide tube, which slides over the guide rod 5 of the dispenser 1 during a movement of the satellite 2 relative to the transport position and thus enables secure guidance, in particular reliably prevents tilting.During the insertion of the satellite 2 into the dispenser 1, a spring element 9, in particular a compression spring, of an ejection element 8 of the dispenser 1 arranged in the region of the housing base 24 is prestressed in such a way that the ejection force required for the later ejection of the satellite 2 is stored in the spring 9 during transport. In order to be able to achieve a specific release of the stored spring force, the spring element 9, here a helical spring designed as a compression spring, can be locked with the aid of a hold-down and release mechanism (HDRM) 22 until the intended ejection of the satellite 2 from the dispenser 1. When the desired flight altitude is reached, at which the satellite 2 is to be ejected, this hold-down and release mechanism (HDRM) 22 is released, for example by destroying a fusible wire, so that the compressive force exerted by the spring element 9 on the satellite 2 is released and the latter is then pushed out of the dispenser 1. Either just before or while the ejection element 8 is activated and the hold down and release mechanism (HDRM) 22 is released, the lid 10 is also unfolded, so that the dispenser housing opening 25 is released for the ejection of the satellite 2. In this context, it is advantageous if the mechanism for opening the cover 10 is coupled to the ejection mechanism or the ejection element 8, in particular the hold-down and release mechanism (HDRM) 22.According to the embodiment shown in FIG. 1, a pressure element 11 designed as a pressure plate is arranged between the satellite 2 arranged in the dispenser 1 and the spring element 9, said pressure element having a connecting structure 12. This connecting structure 12 is designed in such a way that it engages in a form-fitting manner in a mating contour 13 provided in a lower supporting frame 16 of the satellite 2. This form-fitting connection ensures that, while the satellite 2 moves in the longitudinal direction of the dispenser 1 during its ejection, no forces acting in the lateral direction are transmitted and, in particular, an undesired rotational movement is prevented.The cross-sectional area of the dispenser 1 shown in FIG. 1 and of the satellite 2 stored therein has a plurality of corners and is preferably of hexagonal, i.e. hexagonal, design. This has the advantage above all that plate-shaped elements, in particular planar solar panels, can be fastened on the outside to the frame structure 14 of the satellite 2.FIG. 2 shows a dispenser 1 designed according to the invention, which has as essential components a housing 3, a guide rod 5 connected to the housing base 24 and arranged centrally or centrally in the interior of the dispenser 1, and a cover 10 with which the housing opening 25 can be closed. Inside the dispenser 1 there is an ejection element 8 which has a spring element 9 in the form of a compression spring and a plate-shaped pressure element 11 adjoining the latter, as shown in detail view "A". During the transport of a satellite 2, which is then arranged in its transport position in the housing interior, the plate-shaped pressure element 11 or a pressure plate is located between the prestressed spring element 9 and the satellite 2 and the cover 10 closes the opening 25 of the housing 3. Only when the ejection element 8 is actuated is the cover 10 lifted from the housing opening 25 and the spring element 9 activated, so that the transported satellite 2 is ejected at the desired flight height from the interior of the dispenser 1 by utilizing the released spring force.FIG. 3 shows a perspective illustration of a satellite 2 designed according to the invention, which satellite has a frame structure 14 with a centrally arranged, tubular sliding element 6, an upper and a lower supporting frame 15, 16 and four reinforcing struts 20 running in the longitudinal direction and distributed uniformly over the circumference. According to the illustrated exemplary embodiment, five carrier plates are provided as carrier elements 21 in the form of printed circuit boards, which are suitable for receiving electrical and / or electronic components, energy stores or for fastening the required test setups. The individual plate-shaped support elements 21 in the form of circuit boards are each traversed in their middle by the tubular sliding element 6. In addition, the upper and the lower supporting frames 15, 16 are connected via the sliding element 6 and the reinforcing struts 20 additionally arranged in the outer region. In this way, a comparatively stiff frame structure 14 with low twist is created with comparatively few components, which can be fastened to one another or can be embodied in one piece, which nevertheless provides a large amount of space for the required electrical, electronic components or for the components required for carrying out the planned tests in different planes by supplementing them with support elements 21, in particular support plates.The satellite 2 shown in FIG. 3 can preferably be transported in a dispenser 1 having a congruent geometry, so that the volume provided for the transport can be effectively used in the interior of the dispenser 1. This is achieved above all in that the satellite 2 and the suitably designed dispenser 1 have a plurality of lateral edges running in the longitudinal direction, in this case six, and no elements are provided in the outer region of the satellite 2, which elements are required for guidance thereof during the insertion or ejection of the satellite 2. The guide 4 provided centrally in the center of the satellite 2 or a dispenser 1 used for transport allows a controlled and secure movement of the satellite 2 in its longitudinal direction without the need for guide elements in the outer region.The satellite 2 according to the configuration shown in FIG. 3 has a cross-sectional area with a hexagonal circumferential line. It is likewise conceivable to provide a cross section with a different number of corners, for example a square or else a circular cross section. When using the frame structure 14 shown, a number of the available support elements 21, preferably in the form of carrier plates, in particular circuit boards, can be adapted according to requirements. Furthermore, the size of the satellite 2 can be scaled in a simple manner by changing the cross-sectional area and / or the length of the centrally arranged sliding element 6 and the reinforcing struts 20. As will be shown in the following, it is further conceivable to provide, in addition to the upper and lower support frames 15, 16, further support frames 17 between and / or beyond the upper and / or lower support frames 15, 16, an extension 18 of the frame structure 14 in the form of a support frame extension.In addition, FIG. 4 likewise shows a perspective illustration of a satellite 2, which is preferably embodied as a small satellite, in particular as a nanosatellite. The satellite 2 again has the structure described in connection with FIG. 3, in particular a hexagonal cross section, an upper and a lower supporting frame 15, 16 and a centrally arranged, tubular sliding element 6, which serves for secure guidance during the insertion and ejection of the satellite 2. In addition, however, in the lower region of the satellite 2, below the lower supporting frame 16, an extension 18 of the frame structure 14 in the form of a supporting frame extension is provided, which is connected to the remaining frame structure 14. While the lower and the upper supporting frames 16, 15 are connected to one another by the sliding element 6, the supporting frame 26 terminating the extension 18 of the frame structure 14 at the bottom is connected to the remaining frame structure 14 via the reinforcing struts 20 provided on the outer circumference. There is no direct connection between the supporting frame 26 closing the extension 18 of the frame structure 14 downwards and the sliding element 6.In the middle, this support frame 26, which terminates the extension 18 of the frame structure 14 at the bottom, has a recess 19 in which the ejection element 8 is at least partially located during the position of the satellite 2 in its transport position within a dispenser 1, in particular a spring element 9 which is held by a hold-down and release mechanism 22, and a pressure element 11 which establishes a connection between the spring element 9 and the satellite 2.Furthermore, on the underside of the lower supporting frame 16, both a suitable counter-structure 13, which can be brought into positive engagement with a guide structure 12 of the pressure element 11, and a break-out, which is suitable for the integration of activation switches, are provided. Furthermore, planar plates 27 are fastened on the outside of the frame structure 14, which may optionally be solar panels and / or other functional elements, such as antennas.FIG. 5 shows a further particular embodiment of a satellite 2 designed according to the invention. Just like the satellite 2 shown in FIG. 4, it also has a frame structure 14 with a plurality of support elements 21 in the form of carrier plates arranged in different planes. Again, the upper and lower support frames 15, 16 are interconnected by a centrally located slide member 6 in the form of a tube suitable for guiding the satellite 2. According to the embodiments of a satellite 2 according to the invention shown in FIGS. 4 and 5, the frame structure 14 is embodied in one piece with the tubular sliding element 6, wherein production is preferably carried out by a 3-D printing method.In contrast to the exemplary embodiment described above, the satellite 2 shown in FIG. 5 has a circular cross section and three reinforcing struts 20 arranged on the circumference. Both these three reinforcing struts 20 and the tubular sliding element 6, which is in turn arranged centrally in the center of the frame structure 14, pass through the five supporting elements 21, which are designed in the form of printed circuit boards and in turn make it possible to arrange electrical and / or electronic components and other components, for example components required for carrying out tests, on different planes.The described embodiments illustrate that satellites 2 which use the invention can have different cross-sectional shapes and sizes, can be scaled almost arbitrarily with respect to the surfaces provided for use, in particular can offer a different number of support elements 21, such as, for example, printed circuit boards, for accommodating electrical and electronic components and / or test setups. Furthermore, satellites 2 according to the invention can be enlarged with the aid of suitable extensions 18 of the supporting frame structure 14, without having to deviate from the essential principle of the central arrangement of a guide 4 for insertion into and ejection from a dispenser 1. As likewise explained above, it is likewise conceivable that a dispenser 1 designed according to the invention, which has a central guide 4 in the form of a guide rod 5, can accommodate one or a plurality of satellites 2 for transport. If a plurality of satellites 2 are accommodated in a dispenser 1, it is conceivable in this context that they are ejected from the dispenser 1 at the desired flight height simultaneously or at a time interval, wherein the satellites 2 are each moved with their sliding element 6 along the guide rod 5 of the dispenser 1.In order to clarify the almost arbitrary scalability of a satellite 2 designed according to the invention, FIG. 6 shows in the views a) and b) that both the sliding element 6 arranged centrally in the interior of a satellite 2 and the reinforcing struts 20, and thus satellites 2 as a whole, can be almost arbitrarily scaled with respect to their length. According to the specific embodiment shown in FIG. 6, the satellite shown has a double length in relation to the main extension direction in comparison with the satellites according to FIGS. 3 to 5.In this case, FIG. 6 a) shows the main components of the satellite 2, namely the lower supporting frame 16 embodied in one piece with the sliding element 6, on the one hand, and the plate-shaped supporting elements 21 connected via the reinforcing struts 20 and having the upper supporting frame 15 fastened to the reinforcing struts 20, on the other hand, separately from one another. In contrast, FIG. 6 b ) shows the aforementioned components in the assembled state.The satellite 2 shown in FIG. 6 is comparatively large, offers a large amount of space for different components in the individual planes arranged between the supporting elements 21 and, in order to ensure the required stability, additionally has, centrally, a further, central supporting frame 17 which is connected to the sliding element 6 and the outer reinforcing struts 20.The invention thus enables the realization of a system consisting of satellite 2 and dispenser 1, which is almost arbitrarily scalable with respect to the size of the satellites 2 to be transported and, furthermore, ensures, due to the configuration of the satellite 2 and the dispenser 1 provided for its transport with a centrally arranged guide 4, that the outer surfaces of the satellite 2 are also usable at most for large-area elements, in particular for solar panels and antennas.List of reference characters1 Dispenser 2 Satellite 3 Housing 4 Guide 5 Guide rod 6 Sliding element 7 Guide groove / guide rail 8 Ejection element 9 Spring element 10 Cover 11 Pressure element 12 Connecting structure 13 Counter-structure 14 Frame structure 15 Upper supporting frame 16 Lower supporting frame 17 Middle supporting frame 18 Widening of the frame structure 19 Recess in the widening of the frame structure 20 Reinforcing strut 21 Supporting element 22 Hold-down-and-release mechanism 23 Housing plate 24 Housing base 25 Housing opening 26 Supporting frame which closes off the widening of the frame structure 27 Plates

Claims

Dispenser (1) for receiving and transporting a satellite (2), having a housing (3) for storing the satellite (2) during transport in a transport position, wherein a guide (4) is provided in the interior of the housing (3), along which guide the satellite (2) can be moved at least virtually in a straight line relative to the transport position, and having an ejection element (8), by means of which the satellite (2) can be moved along the guide (4) from the transport position into an ejection position, in which the satellite (2) is located outside the housing (3), characterized in that the guide (4) has a central guide rod (5), which is arranged in the interior of the housing (3) and is surrounded at least in regions by the satellite (2) arranged in the transport position, wherein a sliding element (6) of the satellite (2) can be moved along the guide rod (5) in such a way, the satellite (2) can be guided in a linear movement relative to the transport position.Dispenser according to claim 1, characterised in that a guide groove and / or a guide rail (7) is arranged at least in sections on the central guide rod (5).Dispenser according to claim 1 or 2, characterised in that the guide rod (5) has a circular, oval or square cross-section.Dispenser according to one of the preceding claims, characterized in that the guide rod (5) is of cylindrical or tubular design.Dispenser according to one of the preceding claims, characterized in that a cross-sectional area of the housing (3) arranged perpendicularly to the guide rod (5) has a plurality of corners, in particular six corners.Dispenser according to one of the preceding claims, characterized in that the ejection element (8) has a spring element (9).Dispenser according to one of the preceding claims, characterized in that the ejection element (8) has a hold-down and release mechanism (22), by means of which a spring element (9) can be locked in a prestressed position.Dispenser according to one of the preceding claims, characterized in that outer surfaces of the housing (3) are formed at least partially by closed housing plates (23).Dispenser according to one of the preceding claims, characterized in that a housing base (24) aligned at least approximately perpendicularly to the guide rod (5) is provided on a first side of the housing, and a housing opening (25) closable by a cover (10) is provided on a second side opposite the first side.Dispenser according to one of the preceding claims, characterized in that the ejection element (8) has a spring element (9) which is relaxed in order to initiate the movement of the satellite (2) from the transport position into the ejection position, and a pressure element (11) which is arranged between the spring element (9) and the satellite (2) in the transport position of the satellite (2), wherein the pressure element (11) has a connecting structure (12) which can be brought into positive engagement with a mating structure (13) of the satellite (2).Satellite (2) which is suitable for being arranged in a transport position inside a housing (3) of a dispenser (2) according to at least one of the preceding claims and for being moved from the transport position into an ejection position, and which has at least one sliding element (6) which is movable along a central guide rod (5) arranged in the interior of the housing (3).Satellite according to Claim 11, characterized in that a frame structure (14) is provided which is formed by a plurality of rod-shaped struts or rods which are connected to one another and to which the sliding element (6) arranged in the interior of the frame structure (14) is connected at least indirectly and to which at least one plate-shaped supporting element (21), which surrounds the sliding element (6) at least in regions, is fastened for fastening functional elements of the satellite (2).Satellite according to Claim 11 or 12, characterized in that the sliding element (6) is designed as a tube, circular cylinder, oval cylinder and / or polygonal column.Satellite according to one of Claims 11 to 13, characterized in that a cross-sectional area of the frame structure (14) which is arranged at least virtually perpendicularly to the longitudinal direction of the sliding element (6) has a plurality of corners, in particular six corners.Satellite according to one of Claims 11 to 14, characterized in that the frame structure (14) has a lower and an upper supporting frame (15, 16) which are connected or can be connected to one another via the sliding element (6).Satellite according to Claim 15, characterized in that it is fastened or can be fastened to the upper or to the lower supporting frame (15, 16) on the side of an extension (18) of the frame structure (14) which is remote from the respective other supporting frame (16, 15).Satellite according to Claim 15 or 16, characterized in that at least one central supporting frame (17) is arranged between the upper and the lower supporting frames (15, 16).

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