Dispenser for transporting a satellite and satellite

Abstract

The invention relates to a dispenser (1) for receiving and transporting a satellite (2) and to a satellite (2) which can be transported using such a dispenser (1). The dispenser (1) comprises a housing (3) for storing the satellite (2) in a transport position during transport, wherein the interior of the housing (3) is provided with a guide (4) along which the satellite (2) can be moved in at least an almost straight line relative to the transport position. Further, an ejection element (8) is provided, via which the satellite (2) can be moved along the guide (4) out of the transport position into an ejection position, in which the satellite (2) is located outside of the housing (3).

Description

[0001] Dispenser for transporting a satellite and satellite

[0002] The invention relates to a dispenser for transporting at least one satellite, as well as to a satellite that can be arranged in such a dispenser for its transport. The dispenser has a housing for storing the satellite in a transport position during transport, wherein a guide is provided inside the housing, along which the satellite can be moved 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.

[0003] In the field of space technology, dispensers are devices in which satellites, particularly small satellites, are positioned during their transport by a launch vehicle to the required flight altitude. Once the intended flight altitude for the respective satellite has been reached, an ejection mechanism provided in the dispenser is activated, and the satellite is then ejected from the dispenser into the designated position. Such dispensers are primarily used for the transport of small satellites. Small satellites are divided into several different satellite classes, with the invention described below being particularly suitable for nanosatellites weighing between 1 and 10 kg. In this context, so-called CubeSats are known, which are characterized by a cube-shaped basic structure.Such satellites were first deployed in 2004 and have since become the industry standard. These small satellites are used primarily for low-cost technology testing missions, but also for conducting near-Earth experiments.

[0004] The development and use of small satellites represents a rapidly growing market in the space industry. Due to their low mass, small satellites such as CubeSats can be mounted on launch vehicles as secondary payloads and ejected once the desired altitude is reached. To ensure that the transport process is not compromised, the small satellites are inserted into dispensers that prevent any interaction between the satellites and the launch vehicle. Dispensers serve to protect the satellites being transported and also incorporate suitable ejection elements to eject the respective satellite at the desired altitude and position. In the familiar CubeSats, the required circuit boards are stacked, with spacers provided between the individual circuit boards.The PCB stack is arranged within a cube-shaped frame structure, with guide rails along the outer edges that can be guided along suitable counter elements inside a dispenser. Using these guide rails and the counter elements provided in the dispenser, a satellite can be inserted into the dispenser and ejected from the dispenser in a linear direction once the required ejection height is reached.

[0005] Typically, when a satellite is inserted into a dispenser, a compression spring of the ejection mechanism is tensioned, and the satellite and ejection mechanism are held in a transport position by a hold-down and release mechanism (HDRM). Satellite ejection is initiated by releasing the HDRM, which relaxes the compression spring and accelerates the satellite.

[0006] In this context, a device for transporting and ejecting small satellites is known from DE 20 2014 008 902 U1. The described device comprises a container with a lid, guide rails, an ejection spring, a locking mechanism for the lid, and a locking spring. A key feature of the described technical solution is that the small satellite to be transported is secured in its transport position in three spatial directions using additional clamps and spring elements. After a satellite has been inserted into the described container, a pull rod coupled to the pivoting movement of the lid is moved. The pull rod actuates pressure pieces that press the small satellite laterally against the guide rails.Furthermore, when the lid is finally closed, a ball-and-spring system installed above the lid generates a perpendicular force on the side struts of the small satellite, locking the satellite in its three possible degrees of freedom. The dispenser described above is intended to ensure that the satellite is securely fixed in all three spatial directions during transport.

[0007] The known transport systems for small satellites, consisting of the satellite and a dispenser, have a multitude of different components, which is a disadvantage, especially with regard to manufacturing, due to the high number of individual components and the resulting comparatively high assembly effort. Furthermore, the familiar arrangement of the guide rails on the outer edges of the known small satellites limits the usable space available for the attachment of functional elements, such as solar panels or antennas.Based on the solutions known from the prior art and the problems described above, the object of the invention is to provide a dispenser and a satellite, in particular a small satellite, which can be manufactured in a comparatively simple and efficient manner and at the same time ensure that a satellite can be inserted into a dispenser relatively easily and can also be transported and ejected safely and reliably. Furthermore, the technical solution to be specified should be characterized by the fact 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, if possible, the entire outer surfaces of a satellite are available for the attachment of solar panels or functional elements, such as antennas.

[0008] The proposed satellite transport system should also enable simple assembly and production of the main components, the satellite and the dispenser, and preferably allow for production using additive manufacturing processes. Furthermore, it is important that both dispensers and satellites, especially small satellites, can be provided in different sizes, and that the proposed technical solution enables easy scalability of the satellite transport system.

[0009] The above-described object is achieved by means of a dispenser according to claim 1 and a satellite according to claim 12. 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.

[0010] The invention relates to a dispenser for transporting and subsequently ejecting a satellite, in particular a small satellite, comprising a housing that may have a support structure with individual, interconnected struts, which is suitable for storing the satellite in a transport position during transport, and which has a guide along which the satellite can be moved at least almost linearly 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, particularly once the intended flight altitude for the satellite has been reached, along the guide from the transport position into an ejection position outside the housing.A dispenser designed according to the invention is characterized in that the guide has a central guide rod which is arranged inside the housing and is at least partially surrounded by the satellite arranged in the transport position, wherein a sliding element of the satellite is movable along the guide rod such that the satellite can be guided in a linear movement relative to the transport position. Essential to the invention is therefore a central guide rod arranged inside the housing, i.e. between outer boundaries, such as boundary surfaces, which extends in the longitudinal direction of the dispenser and which enables both easy insertion of the satellite into the transport position and targeted guidance of the satellite during its movement from the transport position to the ejection position.

[0011] By providing a central guide rod arranged inside the housing of a dispenser, which can be designed with different profiles, it is ensured that no further guide elements are required in the area of ​​the outer surfaces of a satellite that is to be transported with a correspondingly designed dispenser, and thus the entire outer area 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, each of which utilizes the invention, according to which a guide rod is provided inside the dispenser, along which the satellite, which has a suitable counter element, can be moved.

[0012] In a first particular embodiment of the invention, the central guide rod extends in the longitudinal direction of the dispenser and is designed as a solid body, i.e., a body with 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.

[0013] Furthermore, a special embodiment of the invention provides that the guide rod is cylindrical or tubular. The sliding element of the satellite is designed depending on the respectively selected design of the central guide rod, which is arranged inside the housing of the dispenser. Preferably, it is conceivable that the sliding element of a satellite, in particular a small or even nanosatellite, is designed 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 tubular or cylindrical, so that the sliding element of the satellite is preferably designed as a hollow cylinder or tube with a larger inner diameter than the outer diameter of the guide rod.

[0014] In a specific development of the invention, a cross-sectional area of ​​the housing running perpendicular to the guide rod, i.e. a housing outer contour, has a plurality of corners, in particular six corners, so that the cross-sectional area in this case has the shape of a hexagon. The advantage of such a housing, which has a plurality of longitudinally running edges on its outer surface, is primarily that the interior of the housing is delimited between adjacent edges by flat outer surfaces to which solar modules or functional elements can be attached relatively easily. The corresponding solar modules or functional elements therefore do not have to have a curvature, as is the case, for example, when the housing of a dispenser has a curved, for example round, cross-section transverse to the guide rod arranged in the interior.In this context, it is conceivable for the outer surfaces of the dispenser housing to be closed, with these closed outer surfaces being formed optionally by solar modules or functional elements themselves and / or by plate elements. If the housing walls delimiting the interior from 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 attach solar modules and / or other functional elements, for example antennas, to the wall elements. According to a particular embodiment of the invention, the housing has a supporting structure with a plurality of struts, with wall elements being connected to outer struts surrounding the interior and the central guide rod, which wall elements form an outer surface of the dispenser at least in part.The housing of the dispenser designed according to the invention preferably has outer surfaces that are arranged parallel to the guide rod and closed by means of wall elements, furthermore has a base surface at one end of the housing that is perpendicular to the guide rod and also closed by a wall element, and also has a housing opening opposite the base surface that can be closed by means of a cover element. When the housing opening is closed, the interior of the housing, in which the guide rod is arranged, is therefore completely closed. With the cover element open, a satellite can be pushed into the interior into the transport position through the housing opening and, once the desired flight altitude has been reached, can be ejected from the transport position into the ejection position. The cover is preferably attached to the housing via at least one hinge.Furthermore, the cover element can be operated manually and / or with the aid of an opening mechanism, so that the cover element can be specifically moved from a closed position to an open position. It is 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, so that actuation of the ejection mechanism initiates a movement of the satellite from the transport position to the ejection position, and the cover element is moved in such a way that the opening of the housing is released.

[0015] In a specific 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 spiral spring, by means of which the satellite is accelerated such that it is moved along the guide rod from the transport position into its ejection position. Advantageously, the ejection element, in particular a spiral spring, is designed such that during the introduction of the satellite to be transported into the housing of the dispenser, energy is transferred to the ejection element and stored in the ejection element. In a particularly preferred manner, this is achieved by pretensioning a spring of the ejection mechanism and releasing the stored energy to initiate a 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 is locked.Only when the launch vehicle reaches the desired altitude is the release mechanism activated and the lock released.

[0016] During ejection, the satellite moves with its sliding element along the guide rod located inside the dispenser housing. The movement along the guide rod is advantageously linear, with the guide provided according to the invention ensuring that the sliding element of the satellite and the guide rod of the dispenser do not become jammed during ejection.

[0017] It is particularly advantageous if the ejection mechanism is activated and released using a hold-down-and-release mechanism (HDRM) in such a way that the transported satellite is then accelerated and set in motion. It is preferably conceivable for the hold-down-and-release mechanism to have a fuse wire that is destroyed by a brief current flow, thereby releasing the spring force of at least one pre-tensioned spring element previously held at least indirectly by the fuse wire. The heating of the fuse wire caused by a current flow is specifically controlled and preferably initiated from a ground station.As soon as the hold-down and release mechanism (HDRM) is activated, thereby releasing the satellite lock and activating the ejection element, the transported satellite moves along the guide rod of the dispenser from its transport position to the ejection position, in which the satellite has left the housing of the dispenser and is separated from the guide rod.

[0018] According to a further advantageous embodiment, the lid element of the dispenser housing is opened simultaneously or immediately after the hold-down-and-release mechanism (HDRM) has been activated, allowing the satellite to be easily ejected from the interior of the housing. For this purpose, a mechanical coupling is preferably provided between the hold-down-and-release mechanism (HDRM) and / or the locking mechanism of the satellite and a mechanism for opening the lid element, which can also be a release of a tensioned closure. It is particularly advantageous if the lid element closes the interior of the housing until the satellite begins to move.

[0019] In a particular embodiment of the invention, a housing base is provided on a first side of the dispenser housing, which is aligned at least largely perpendicular to the central guide rod and delimits the interior of the housing from the surroundings. This housing base, which closes off the dispenser on one side, is connected along its circumference to outer side walls of the housing arranged perpendicularly thereto, which are formed by housing plates, preferably by a material fit or formed integrally 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 inserting and ejecting the satellite, which opening can preferably be closed with a hinged, pivotable, or slidably mounted cover element.The cover element is preferably plate-shaped and connected at least indirectly to at least one of the outer side walls of the housing, which are aligned parallel to the central guide rod, via suitable joints and / or hinges. A piston rod and / or a spring element is preferably provided for the targeted movement of the cover element. It is also conceivable that, to open the cover element, a retaining element, which holds the cover element in the closed position against the spring force of a spring, is released, for example by using a hold-down-and-release mechanism (HDRM).

[0020] 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 flat. The individual wall elements can be fastened to one another and / or to struts of a supporting structure using suitable fastening elements or by means of a material bond. It is also 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 designed as a single piece. Additive processes, such as injection molding or 3D printing, for example fused deposition modeling, are particularly suitable as manufacturing methods. At least one plastic is preferably used as the material for manufacturing at least parts of the housing.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 may be located.

[0021] In a specific development of the invention, the ejection element has a spring element that is released to initiate the movement of the satellite from the transport to the ejection position, and a pressure element that is arranged between the spring element and the satellite in the transport position of the satellite. Advantageously, the pressure element has a connecting structure that can be brought into positive engagement with a counterstructure of the satellite. As soon as a launch vehicle has reached the altitude at which the transported satellite is to be ejected from the dispenser, the trigger 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 to the ejection position.According to the special design described, the positive-locking structure of the pressure plate engages with the counter-structure of the satellite, ensuring that the satellite is moved longitudinally along the guide rod without rotating due to forces acting transversely to the satellite's longitudinal movement. 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 that the pressure plate is attached to the spring or the satellite and, after the satellite has been ejected, remains either on the satellite or the spring. The key to this technical solution is that the spring force is transmitted to the ejected satellite in an at least almost linear manner, independent of lateral forces.

[0022] In addition to a specially designed dispenser, the invention further 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 embodiments of a dispenser according to the invention in a transport position and for being moved from the transport position to an ejection position. The satellite according to the invention has at least one sliding element that 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 if the shape of the outer surfaces and / or the contour of the satellite, in particular the design 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.

[0023] In this context, it is particularly advantageous if the cross-sectional area of ​​the satellite arranged perpendicular to the sliding element is polygonal, for example hexagonal, i.e. has a corresponding plurality of side edges running in the longitudinal direction. Particularly effective transport of the satellite or utilization of the usable volume provided by a dispenser can be achieved 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, does not have any curved surfaces. In this way, flat 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 easily inserted into the dispenser and ejected from it together with the satellite.

[0024] According to a further particular embodiment, the satellite has a basic structure formed by a plurality of interconnected rod elements or struts, which is preferably connected to the satellite's sliding element arranged inside the basic structure. On this basic structure, which forms a support frame, plate-shaped elements, in particular solar panels, can be relatively easily attached to the outer surfaces. On the other hand, in addition to the sliding element, support elements can be arranged inside, which are suitable, for example, for accommodating electrical or electronic components, energy storage devices, and / or test setups.

[0025] According to a specific 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 circuit board on which electronic components as well as the necessary conductor tracks and contact pins for contacting are arranged. It is also conceivable that components, assemblies, drive elements, reaction vessels, processors, data transmission elements and / or components required for energy supply and energy storage required for carrying out the intended experiments are arranged on the support elements. It is particularly advantageous if the individual plate-shaped support elements surround the centrally arranged sliding element of the satellite at least in part, preferably completely.With a plurality of such support elements arranged one above the other, compartments or plates for fastening electronic components, energy storage devices, test setups and / or other functional elements can be provided at different levels as required.

[0026] It is particularly advantageous if the sliding element extending centrally through the satellite in the longitudinal direction is designed as a tube, circular cylinder, oval cylinder or polygonal column.

[0027] An advantage of the technical solution according to the invention is that a dispenser and / or satellite can be scaled to at least almost any desired size. Furthermore, it is conceivable for a dispenser to be designed or dimensioned in such a way that it can accommodate and transport one or more satellites inside. The satellite(s) can each be moved in the longitudinal direction of the dispenser along the central guide rod arranged inside the dispenser. The satellite(s) designed according to the invention are inserted into the dispenser in the longitudinal direction and, upon reaching the desired flight altitude, are ejected from the dispenser in the opposite direction.The provision of a central guide rod in the dispenser and a sliding element that is movable relative to the guide rod and arranged inside the satellite offers the advantage that no elements are required outside the satellite to guide it along the dispenser guide. The invention is explained in more detail below, without limiting the general inventive concept, using specific exemplary embodiments with reference to the figures. Identical components are designated by the same reference numerals in the different figures. Herein:

[0028] Fig. 1: Cross-sectional view of an inventively designed

[0029] Dispenser with satellite arranged therein in a transport position, Fig. 2: perspective view of an inventive

[0030] Dispensers with closed outer walls and a lifted lid,

[0031] Fig. 3: Satellite designed according to the invention with a vertical to the

[0032] Hexagonal cross-sectional area arranged longitudinally and a number of support plates that can be varied as required,

[0033] Fig. 4: oblique view from below of a satellite with a central structure and a support frame extension as well as

[0034] Fig. 5: Satellite designed according to the invention with a vertical to the

[0035] longitudinally arranged circular cross-sectional area and a number of support plates that can be varied as required, and Fig. 6: satellite designed according to the invention with a perpendicular to the

[0036] Longitudinally arranged hexagonal cross-sectional area and a supporting central structure for accommodating a comparatively large number of carrier plates.

[0037] Fig. 1 shows a cross-sectional view of a dispenser 1 designed according to the invention, in which a satellite 2, here a small satellite, such as a nanosatellite weighing less than 10 kg, is arranged in a transport position. Before the satellite 2 is transported by a launch vehicle to the desired altitude at which the satellite 2 is to remain, it is inserted into the dispenser 1 and finally locked in the transport position. Upon reaching the desired altitude, the satellite 2 is ejected from its transport position into the ejection position outside the dispenser 1, as will be explained in more detail below.1 and the satellites 2 stored therein is 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 safe movement of the satellite into the transport position and from the transport to the ejection position, which ensures safe movement relative to the transport position in the longitudinal direction of the dispenser 1 and 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 counter-contour, for example in the form of a bushing, a tube or a long hollow body extending in the longitudinal direction, which is movable along the guide rod 5 and ensures a guided movement in the longitudinal direction of the dispenser 1, 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.

[0038] The dispenser 1 shown in Fig. 1 has a housing 3 with housing plates 23 that form a protective outer wall, ultimately providing an enclosed interior space that ensures the safe 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 space, a guide rod 5 are attached or formed integrally with the housing base 24, for example by using an additive manufacturing process. Preferably, rods or struts for attaching the housing plates 23 are also provided on the inside at the lateral edges of the housing plates 23 where they abut one another, and these rods or struts are in turn connected to the housing base 24.

[0039] Furthermore, the dispenser 1 shown in Fig. 1 has a lid 10, which is detachably, preferably foldably, connectable to the top of the housing 3, at least indirectly, to the housing plates 23 and / or the guide rod 5, and which closes the housing opening 25 of the dispenser 1 from the environment during transport. To insert and eject a satellite 2, the lid 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 with the lid 10 open.

[0040] 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 safe guidance, in particular reliably prevents tilting.

[0041] 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 pretensioned such that the ejection force required for the subsequent ejection of the satellite 2 is stored in the spring 9 during transport. In order to achieve a targeted release of the stored spring force, the spring element 9, here a spiral spring designed as a compression spring, can be locked using a hold-down-and-release mechanism (HDRM) 22 until the planned ejection of the satellite 2 from the dispenser 1. When the desired flight altitude at which the satellite 2 is to be ejected is reached, this hold-down-and-release mechanism (HDRM) 22 is released, for example by destroying a fuse wire, so that the pressure force exerted by the spring element 9 on the satellite 2 is released and the satellite is then ejected from the dispenser 1.Either shortly 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 opened, so that the housing opening 25 of the dispenser is released for the ejection of the satellite 2. In this context, it is advantageous if the mechanism for opening the lid 10 is coupled to the ejection mechanism or the ejection element 8, in particular the hold-down-and-release mechanism (HDRM) 22.

[0042] 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. This pressure element 11 has a connecting structure 12. This connecting structure 12 is designed such that it engages positively with a counter-contour 13 provided in a lower support frame 16 of the satellite 2. This positive 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.

[0043] The cross-sectional area of ​​the dispenser 1 shown in Fig. 1, as well as the satellite 2 stored therein, has a plurality of corners and is preferably hexagonal. This has the primary advantage that plate-shaped elements, in particular flat solar panels, can be attached to the outside of the frame structure 14 of the satellite 2.

[0044] 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 inside the dispenser 1, and a lid 10 with which the housing opening 25 can be closed. Located inside the dispenser 1 is an ejection element 8, which has a spring element 9 in the form of a compression spring and an adjoining, plate-shaped pressure element 11, 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 lid 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 from the interior of the dispenser 1 at the desired flight altitude by utilizing the released spring force.

[0045] Fig. 3 shows a perspective view of a satellite 2 designed according to the invention, which has a frame structure 14 with a centrally arranged, tubular sliding element 6, an upper and a lower support frame 15, 16 and four longitudinally extending, evenly distributed over the circumference reinforcing struts 20. According to the illustrated embodiment, five carrier plates are provided as support elements 21 in the form of circuit boards, which are suitable for receiving electrical and / or electronic components, energy storage devices or for attaching the required test setups. The individual plate-shaped support elements 21 in the form of circuit boards are each penetrated at their center by the tubular sliding element 6. Furthermore, the upper and lower support frames 15, 16 are connected via the sliding element 6 and the additional reinforcing struts 20 arranged in the outer region.In this way, with comparatively few components, which can be fastened to one another or designed as a single piece, a comparatively rigid, torsion-resistant frame structure 14 is created, which nevertheless, by adding supporting elements 21, in particular support plates, provides a lot of space in different levels for the required electrical, electronic or components required for carrying out the planned experiments.

[0046] The satellite 2 shown in Fig. 3 can preferably be transported in a dispenser 1 with a congruent geometry, so that the volume provided for transport inside the dispenser 1 can be effectively utilized. This is achieved primarily by the fact that the satellite 2 and the suitably designed dispenser 1 have a plurality of side edges running in the longitudinal direction, here six, and no elements are provided in the outer region of the satellite 2 that are required for guiding the satellite 2 during insertion or ejection. The guide 4 provided centrally in the middle of the satellite 2 or of a dispenser 1 used for transport enables a controlled and safe movement of the satellite 2 in its longitudinal direction without the need for guide elements in the outer region.

[0047] The satellite 2 according to the embodiment shown in Fig. 3 has a cross-sectional area with a hexagonal circumference. It is also conceivable to provide a cross-section with a different number of corners, such as a square or a circular cross-section. When using the frame structure 14 shown, a number of the provided support elements 21, preferably in the form of carrier plates, in particular circuit boards, can advantageously be adapted as needed. Furthermore, the size of the satellite 2 can be easily scaled 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 below, it is also 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.

[0048] In addition, Fig. 4 also shows a perspective view of a satellite 2, which is preferably designed 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 support frame 15, 16 and a centrally arranged, tubular sliding element 6, which serves to securely guide the satellite 2 during insertion and ejection. In addition, however, in the lower region of the satellite 2, below the lower support frame 16, an extension 18 of the frame structure 14 in the form of a support frame extension, which is connected to the remaining frame structure 14, is provided.While the lower and upper support frames 16, 15 are connected to each other by the sliding element 6, the support frame 26, which closes off 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 support frame 26, which closes off the extension 18 of the frame structure 14 at the bottom, and the sliding element 6.

[0049] In the middle, this support frame 26, which closes off the extension 18 of the frame structure 14 downwards, has a recess 19 in which the ejection element 8 is at least partially located while the satellite 2 is 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, as well as a pressure element 11, which establishes a connection between the spring element 9 and the satellite 2.

[0050] Furthermore, a suitable counterstructure 13, which can be positively engaged with a guide structure 12 of the pressure element 11, as well as a cutout suitable for the integration of activation switches, are provided on the underside of the lower support frame 16. Furthermore, flat plates 27 are attached to the outside of the frame structure 14, which can optionally be solar panels and / or other functional elements, such as antennas.

[0051] Fig. 5 shows a further particular embodiment of a satellite 2 constructed according to the invention. Just like the satellite 2 shown in Fig. 4, this also has a frame structure 14 with a plurality of support elements 21 in the form of carrier plates arranged in different planes. The upper and lower support frames 15, 16 are again connected to one another by a centrally arranged sliding element 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 constructed as a single piece with the tubular sliding element 6, with production preferably taking place by means of a 3D printing process.

[0052] In contrast to the previously described embodiment, the satellite 2 shown in Fig. 5 has a circular cross-section and three reinforcing struts 20 arranged around the circumference. Both these three reinforcing struts 20 and the tubular sliding element 6, which is again arranged centrally in the middle of the frame structure 14, project through the five support elements 21 designed in the form of circuit boards, which in turn enable the arrangement of electrical and / or electronic components as well as other components, for example those required for carrying out experiments, on different levels.

[0053] The described embodiments illustrate that satellites 2 utilizing the invention can have different cross-sectional shapes and sizes, are scalable almost arbitrarily with regard to the areas provided for use, and in particular can offer a different number of support elements 21, such as 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 also explained above, it is also 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 several satellites 2 are accommodated in a dispenser 1, it is conceivable in this context that they are ejected from the dispenser 1 simultaneously or at different times at the desired flight altitude, wherein the satellites 2 are each moved with their sliding element 6 along the guide rod 5 of the dispenser 1.

[0054] To illustrate the virtually unlimited scalability of a satellite 2 constructed according to the invention, Fig. 6 shows in views a) and b) that both the sliding element 6 arranged centrally inside a satellite 2 and the reinforcing struts 20, and thus the satellite 2 as a whole, are virtually infinitely scalable in terms of their length. According to the specific embodiment shown in Fig. 6, the satellite shown has twice the length in the main extension direction compared to the satellites according to Figs. 3 to 5.

[0055] Here, in Fig. 6 a), the main components of the satellite 2, namely the lower support frame 16, which is constructed in one piece with the sliding element 6, on the one hand, and the plate-shaped support elements 21 connected via the reinforcing struts 20 to the upper support frame 15, which is attached to the reinforcing struts 20, on the other hand, are shown separately from one another. In contrast, Fig. 6 b) shows the aforementioned components in an assembled state.

[0056] The satellite 2 shown in Fig. 6 is comparatively large, offers a lot of space for different components in the individual levels arranged between the support elements 21 and, in order to ensure the required stability, has a further, central support frame 17 in the middle, which is connected to the sliding element 6 and the outer reinforcing struts 20.

[0057] The invention thus enables the realization of a system consisting of satellite 2 and dispenser 1, which is almost arbitrarily scalable with regard to the size of the satellites 2 to be transported and, furthermore, due to the design of the satellite 2 and the dispenser 1 provided for its transport with a centrally arranged guide 4, ensures that the outer surfaces of the satellite 2 can also be used to the maximum for large-area elements, in particular for solar panels and antennas.

[0058] 1 dispenser

[0059] 2 satellites

[0060] 3 housings

[0061] 4 Leadership

[0062] 5 Guide rod

[0063] 6 Sliding element

[0064] 7 Guide groove / guide rail

[0065] 8 Ejection element

[0066] 9 Spring element

[0067] 10 lids

[0068] 11 Pressure element

[0069] 12 Connection structure

[0070] 13 Counterstructure

[0071] 14 Frame structure

[0072] 15 upper support frame

[0073] 16 lower support frame

[0074] 17 middle support frame

[0075] 18 Extension of the framework structure

[0076] 19 Recess in the extension of the frame structure

[0077] 20 reinforcement strut

[0078] 21 Support element

[0079] 22 hold down and release mechanism

[0080] 23 Housing plate

[0081] 24 Case back

[0082] 25 Housing opening

[0083] 26 Supporting frame that completes the extension of the frame structure

[0084] 27 plates

Claims

Patent claims 1. Dispenser (1) for receiving and transporting a satellite (2), comprising a housing (3) for storing the satellite (2) during transport in a transport position, wherein a guide (4) is provided inside the housing (3), along which the satellite (2) can be moved at least almost linearly relative to the transport position, and comprising 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 inside the housing (3) and is at least partially surrounded 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) such that the satellite (2) can be guided in a linear movement relative to the transport position.

2. Dispenser according to claim 1, characterized in that a guide groove and / or a guide rail (7) is arranged at least in sections on the central guide rod (5).

3. Dispenser according to claim 1 or 2, characterized in that the guide rod (5) has a circular, oval or square cross-section.

4. Dispenser according to one of the preceding claims, characterized in that the guide rod (5) is cylindrical or tubular.

5. Dispenser according to one of the preceding claims, characterized in that a cross-sectional area of ​​the housing (3) arranged perpendicular to the guide rod (5) has a plurality of corners, in particular six corners.

6. Dispenser according to one of the preceding claims, characterized in that the ejection element (8) has a spring element (9).

7. 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 pre-tensioned position.

8. Dispenser according to one of the preceding claims, characterized in that outer surfaces of the housing (3) are at least partially formed by closed housing plates (23).

9. Dispenser according to one of the preceding claims, characterized in that on a first side of the housing there is provided a housing base (24) aligned at least almost perpendicular to the guide rod (5) and on a second side opposite the first side there is provided a housing opening (25) which can be closed by a cover (10).

10. Dispenser according to one of the preceding claims, characterized in that the ejection element (8) has a spring element (9) which is relaxed 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 counter-structure (13) of the satellite (2).

11. 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 inside the housing (3).

12. Satellite according to claim 13, characterized in that a frame structure (14) is provided which is formed by a plurality of interconnected rod-shaped struts or rods, to which the sliding element (6) arranged in the interior of the frame structure (14) is at least indirectly connected and to which at least one plate-shaped support element (21) is fastened, at least partially surrounding the sliding element (6), for fastening functional elements of the satellite (2).

13. Satellite according to claim 12 or 13, characterized in that the sliding element (6) is designed as a tube, circular cylinder, oval cylinder and / or polygonal column.

14. 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 almost perpendicular to the longitudinal direction of the sliding element (6), has a plurality of corners, in particular six corners.

15. Satellite according to one of claims 11 to 14, characterized in that the frame structure (14) has a lower and an upper support frame (15, 16) which are or can be connected to one another via the sliding element (6).

16. Satellite according to claim 15, characterized in that an extension (18) of the frame structure (14) is fastened or can be fastened to the upper or lower support frame (15, 16) on the side facing away from the other support frame (16, 15).

17. Satellite according to claim 15 or 16, characterized in that at least one middle support frame (17) is arranged between the upper and the lower support frame (15, 16).

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