Modular satellite system

Abstract

The invention relates to a satellite system comprising a number of connectable satellite units, wherein at least one satellite unit is intended as the master unit (1) and a number of further satellite units are intended as subunits (2), wherein the satellite units each take the form of a flat cuboid with substantially identical external dimensions, wherein each satellite unit has a rectangular side surface (3) which is smaller than its base surface (4) and its top surface (5), wherein at least on one edge of a side surface (3) there is a strip-shaped magnetic connecting means (6), wherein the connecting means (6) can be coupled to one another to form a releasable magnetic hinge, and wherein at least on these side surfaces (3) there are a magnetic strip (7) and a mechanical locking device (8) for fixing purposes.

Description

[0001] Modular satellite system

[0002] The invention describes a modular, orbitally configurable satellite system for missions with high energy requirements, such as Earth observation, high-speed communication, manufacturing in space, or the performance of biotechnological and other experiments.

[0003] Modular satellite systems are known from the prior art. For example, KR 102 466480 B1 and DE 102016 108 951 A1 show satellite systems with several interconnectable and essentially cuboid-shaped satellite units.

[0004] In practice, however, connecting the individual satellite units of such satellite systems under weightlessness presents a significant problem.

[0005] The object of the invention is therefore to create a satellite system that is modular, applicable to different applications and easy to manufacture, and whose construction in space is as simple and error-free as possible.

[0006] These and other problems are solved by a satellite system according to claim 1. A satellite system according to the invention comprises several connectable satellite units, wherein at least one satellite unit is designated as the master unit and one or more further satellite units are designated as subunits. The satellite units each have the form of a flat cuboid. At least the subunits, and optionally all satellite units, have identical external dimensions.

[0007] The satellite units are cuboid in shape, each with a rectangular side face that is narrower than its base and top face. The base and top faces are preferably square. A detachable mechanical hinge is located on one edge of the side face, designed to connect to a corresponding hinge on another satellite unit. The hinges of the satellite units can be coupled together to form a linear, articulated satellite chain.

[0008] On the sides of the satellite units where hinges are located, there are electromagnetic docking strips and a mechanical locking device. The locking device serves to mechanically secure the satellite units at their sides to form a rigid satellite chain. Additionally, the locking device enables power and data transmission between the satellite units.

[0009] Due to their flat design, the satellite units according to the invention are lighter than conventional satellite units. At the same time, they retain or increase their performance and application possibilities, since they have a larger energy absorption area compared to their weight.

[0010] According to the invention, the base and top surfaces of the satellite units can have identical side lengths L of approximately 10 cm to approximately 200 cm, in particular approximately 33.6 cm, approximately 50 cm, or approximately 75 cm. The dimensions can be adapted to the payload capacity of a standard satellite. According to the invention, the width of the side surfaces of the master unit can also be the same as the width of the side surfaces of the sub-unit, so that the master unit has the same dimensions as the sub-unit.

[0011] The width B of the subunit's side faces, i.e., its thickness, can be 5 to 25 times, preferably 10 to 20 times, smaller than its side length L. Preferably, the width B is less than 10 cm, more preferably less than 5 cm, for example, about 3 cm, about 2 cm, or about 1 cm. Due to the flat design of the satellite units, several satellite units can be packed into the payload compartment of a single standard satellite.

[0012] The master units can have the same dimensions as the subunits. However, the master units can also be thicker, especially if they have a thruster, as a thruster requires greater thickness. The subunits usually do not require a thruster and ideally can be only a few millimeters thick.

[0013] The base and top surfaces of the subunit and the master unit are essentially identical; however, according to the invention, the width B' of the side surfaces of the master unit can be greater than the width B of the side surfaces of the subunit. Preferably, however, the width B' of the side surfaces of the master unit is less than its side length L, particularly preferably less than 25 cm, for example about 20 cm, about 15 cm, about 10 cm, or about 8 cm.

[0014] According to the invention, solar panels can be arranged on the base and / or top surfaces of the satellite units. This creates a large energy absorption area, resulting in an amount of energy that can be used for various tasks. Excess energy can be stored and shared with other satellite units or functional boxes.

[0015] According to the invention, a camera may be arranged on the side surfaces of the satellite units in the area of ​​the docking strips. The locking device may also be two-part and comprise a plug and a corresponding socket, preferably with a plug or a socket arranged to the left and right of the docking strip.

[0016] According to the invention, the master unit can be provided with a thruster to enable navigation for lateral docking with one or more other satellite units and for additional maneuvers. To control the master unit, magnetic motors can be positioned at its corners in combination with a centrally located reaction wheel. The combination of the reaction wheel and the four magnetic motors enables 360-degree rotation, allowing maneuvers to be executed precisely and minimizing loss of control over the satellite unit.

[0017] The master unit may further comprise a data processing unit, a communication unit, an energy storage unit, and an interface unit. The interface unit may have a data bus, which is preferably routed out through the locking device.

[0018] According to the invention, the subunit can have an interface unit with a data bus that extends through the locking device. The subunit can include an energy storage device which, in the coupled state, can be connected to the energy storage device of the master unit via the locking device to enable bidirectional energy transfer. The subunit can also include a sensor unit which, in the coupled state, can be connected to the interface unit of the master unit to enable bidirectional data transmission via the locking device. The connection device thus functions as a mechanical interface for the transfer of energy and data between docked satellite units.

[0019] According to the invention, the mechanical hinge can be arranged on one of the two longer edges of a side surface. Furthermore, according to the invention, a magnetic hinge can be arranged on one or all of the shorter edges of the side surface. For example, a permanent magnet can be arranged on the edge, which interacts with a corresponding permanent magnet on the edge of another satellite unit like a hinge.

[0020] According to the invention, in addition to the satellite units, a substantially cuboid-shaped functional box is provided for accommodating payloads, production equipment, test devices, and the like. The functional box can also be referred to as a production box or payload box.

[0021] A functional box according to the invention can serve to provide payload. The functional box can be loaded with a customer's payload and launched into orbit via a launch vehicle. It can be equipped with a plug-in docking system to connect with satellite units in orbit.

[0022] According to the invention, the functional box can have a side length that essentially corresponds to the side length of the satellite units. However, the functional box is generally thicker than the subunit and master unit.

[0023] According to the invention, the functional box can be provided with an outer shell and an inner shell, with the payload arranged in the inner shell, and with a gap of at least 3 cm between the outer shell and the inner shell. This gap allows standard satellite components such as control systems (magnetic gate systems, actuators, reaction wheel, etc.), base OBCs, batteries, etc., to be mounted on the inner wall of the outer shell. The inner shell serves to house the payload.

[0024] According to the invention, an electromagnetic docking strip and a locking device can be provided on the side surfaces of the functional box. The satellite units can be connected to the functional box via the docking strip and supply the functional box with power via their power and data bus connection.

[0025] According to the invention, the function box can be provided with an interface unit with a data bus that is led out through the locking device to enable energy and data transmission between the satellite units and the function box.

[0026] The functional box may be equipped with a propulsion unit to maintain its position in orbit and during docking and undocking from the satellite units. The functional box may be designed for re-entry into the Earth's atmosphere and may include a propulsion system and a navigation system.

[0027] The function box can only contain basic satellite components and be supplied with sufficient power and computing resources to perform missions in orbit. Missions include tasks such as data storage, manufacturing, experimentation, Earth observation, and communication. During the docking process, a power and data bus connection is established with the master unit. The function box is first placed under the master unit's on-board computer (OBC), and then the master unit integrates the function box into the satellite system.

[0028] A satellite unit, specifically a subunit, can be coupled to the functional unit to provide power. Certain missions require significant amounts of energy (space manufacturing, 3D printing, testing, or operating laser systems), so these types of missions require a continuous, high power flow that can only be provided by a larger number of subunits. Other missions, such as medical and biotechnological testing, do not require a consistently high power flow, so a smaller number of subunits suffices. The master unit can configure the functional unit according to its mission objectives and types to optimize the performance of the hybrid satellite system.Once the function box has fulfilled its task, it can be separated from the satellite unit and returned to Earth, while the satellite unit can continue its task independently or connect with other satellite units or another function box.

[0029] According to the invention, the locking device of the satellite units can have a frame element that can be extended up to a side length L, so that a space can be created between two coupled satellite units to accommodate the function box. The frame element can, in particular, be telescopically extendable.

[0030] According to the invention, a dispenser unit can be provided to accommodate several satellite units, such as a master unit and several sub-units, which are stacked on top of each other and connected via their hinges in an accordion-like manner.

[0031] According to the invention, several master units can be provided, wherein each master unit connects several subunits in a linear satellite chain, and wherein the satellite chains run essentially parallel to each other and are connected to each other at their sides.

[0032] Further features of the invention will become apparent from the claims, the description of the exemplary embodiments and the figures.

[0033] The invention will now be explained in more detail using exemplary embodiments. These show:

[0034] Fig. 1 shows a schematic 3D view of a subunit according to the invention;

[0035] Fig. 2 shows a schematic 3D view of a master unit according to the invention;

[0036] Figs. 3-4 are schematic views of a satellite chain according to the invention;

[0037] Fig. 5 is a schematic view of a satellite system according to the invention in a “walking unit” arrangement;

[0038] Fig. 6 is a schematic view of a satellite system according to the invention in a partially detached state; Fig. 7 is a schematic view of a satellite system according to the invention with a function box;

[0039] Fig. 8 shows a mechanical connecting device according to the invention;

[0040] Fig. 9 shows a schematic representation of a function box;

[0041] Figs. 10-11 show further satellite systems according to the invention.

[0042] A satellite system according to the invention is a modular and orbitally configurable, flexible system which, due to its design, is capable of serving missions with high energy demands that require a continuous and uninterrupted energy flow. A satellite system according to the invention can be used for storing data or energy.

[0043] The basic modules of the satellite system are satellite units in the form of so-called flat satellites. These flat satellites are designed as particularly thin cuboids and are, for example, only about 3 cm thick. The dimensions of their base and top surfaces can be adapted to the standard dimensions of a cube satellite launcher. Due to the thinness of the flat satellites, more satellite modules can be housed in a standard cube casing.

[0044] Figures 1 and 2 show exemplary embodiments of the flat satellite units in the form of a master unit 1 and a sub-unit 2. The master unit 1 and sub-unit 2 are similar in their external dimensions but differ in their performance and intended use. The master units 1 control a satellite array 11 with several sub-units 2 and share their computing power with connected function boxes 10.

[0045] The subunits 2 function as extensions of the master units 1 within the satellite system. Their purpose is to accommodate additional energy or data storage modules such as batteries or memory cards. When no payload is connected to the satellite system, the subunit 2 can also receive and store general data, for example, for training AI systems. The arrangement and number of master units 1 and subunits 2 in a satellite system or satellite chain depend on the application. In the simplest case, a single master unit 1 and a single subunit 2 are sufficient. Fig. 1 is a schematic three-dimensional view of a satellite unit according to the invention in the embodiment as a subunit 2. The subunit 2 has the shape of a flat cuboid with four rectangular faces 3, which are narrower than its square base 4 and its square top 5.Solar panels (not shown) are arranged on its base surface 4 and top surface 5.

[0046] Subunit 2 units are fully functional satellite units, but they are not equipped with a propulsion system, as they only need to make minor positional adjustments. Subunit 2 units are equipped with actuators for self-navigation and positional stability. Essentially, subunit 2 serves as an energy and data storage unit for the satellite system, since data processing and high-performance functions (OBC, thrusters) are handled by master units 1.

[0047] Subunit 2 is designed to store specific types of data, such as research data transmitted in large quantities by the Hubble Telescope or a Mars rover. Data not selected by the guiding algorithm of the Mars rover or Hubble Telescope can be stored in Subunit 2 until a certain bandwidth is reached, at which point it can be relayed back to Earth or a space station for analysis.

[0048] Due to their dimensions, the satellite units fit into a standard satellite casing or a dispenser unit of a cargo carrier. The satellite units are separably connected at their edges by mechanical hinges 6. A detachable mechanical hinge 6 with an axis running parallel to the edge is arranged on one edge of the side surface 3 of the satellite unit.

[0049] The length L of side surface 3 is approximately 33 cm and the width B of side surface 3 is approximately 3 cm. A docking strip 7 made of electromagnetic, ferromagnetic, or switchable magnetic materials is arranged on side surface 3. Next to the docking strip 7 is a mechanical locking device 8. The locking device 8 is designed for fixing to another satellite unit and also serves for power and data transmission between the docked satellite units.

[0050] The hinge β allows the satellite units to be stacked on top of each other in a dispenser unit while remaining connected. Once released from the dispenser unit into orbit, the mechanical hinges unfold the satellite units into a leporello-like, articulated linear chain. The hinge system prevents the individual satellite units from colliding with each other during deployment into orbit.

[0051] Fig. 2 is a schematic three-dimensional view of a satellite unit according to the invention, designated as master unit 1. The master unit 1 is the brain of a satellite system and has a data processing unit designed to control the satellite system. The data processing unit is capable of analyzing and individually managing a constantly changing and reconfiguring satellite system. It also manages the data flow between the coupled satellite units.

[0052] The master unit 1 has essentially the same dimensions as the sub-unit 2, except that the width B' of the side surface 3 is slightly greater than that of the sub-unit 2 to accommodate a thruster 9. An electromagnetic docking strip 7 is attached to three sides of the side surfaces, and the thruster 9 is located on the fourth side. Cameras can be mounted above the docking strip 7.

[0053] Fig. 3 is a schematic view of a satellite chain 11 according to the invention comprising a master unit 1 with four subunits 2, 2', 2", 2'" linearly coupled to it via mechanical hinges 6. The hinges 6, 6', 6", 6'" are each arranged on opposite edges of the satellite units.

[0054] This arrangement can also be described as accordion-like or leporello-like. In this configuration, the satellite units can be stacked on top of each other within a dispenser unit. This offers the advantage that multiple satellite units can be transported into orbit in a very space-saving manner. When they are released from the dispenser unit at their target position, the satellite units unfold like a leporello or accordion, and the docking process begins.

[0055] The docking process is called the "Flat Satellite Side Soft Docking" process and consists of two main steps. The first step begins after the satellite units have been unfolded by the mechanical hinges 6, but are not yet flat. The magnetic docking strips 7 attached to the side surfaces 3 of the satellite units gently pull the satellite units together.

[0056] The second step is to establish a fixed mechanical connection between the satellite units, enabling a common data bus connection and power flow between them. For this purpose, mechanical locking devices 8 are attached to the side faces of the satellite units, preferably a few centimeters from both ends of the docking strip 7. The locking device 8 exhibits features of a traditional mechanical docking system for small satellites.

[0057] The docking mechanism comprises an electromagnetic docking strip 7, which is attached to the side surfaces of the satellite units, combined with a mechanical locking device 8. After the satellites are released and partially unfolded into a leporello shape, the docking strip 7 gently pulls the satellite units together, thus completing the first phase of the docking process. The second stage of the docking process consists of fixing the satellite units by means of a mechanical locking device 8. After electromagnetic docking is achieved and the two flat sides of the satellites are aligned or clicked together, the mechanical locking devices 8 are activated to fix the position. Fig. 4 is a schematic view of a satellite system according to the invention in the form of a satellite chain 11 comprising a master unit 1 and three subunits 2, 2', 2" in the fully docked state.

[0058] In this state, the mechanical connecting devices of 8 adjacent satellite units are connected to each other and form a data transmission bus and power transmission bus.

[0059] Such a satellite system comprises a satellite chain 11 with multiple satellite units docked at its sides. The satellite system has a distributed data plane and a centralized control plane; that is, telemetry and status updates flow equally, but critical decisions are made via the currently leading master unit 1. When individual satellite units are docked or undocked, the master unit 1 performs a re-initialization and then resumes operation with the updated satellite units.

[0060] A satellite system according to the invention can operate in different modes: firstly, as a common unit with several linearly coupled satellite units; secondly, in a completely detached format in which each satellite unit is completely separated from the satellite chain, for example, to replace it with a new satellite unit.

[0061] Since the satellite system according to the invention is capable of absorbing and storing a large amount of energy, additional functional boxes can be used, enabling the execution of energy-intensive space missions, such as 3D printing in orbit or the testing of certain laser systems, and more. The functional boxes can be used to build a factory in space.

[0062] A functional box serves as a space capsule that carries a payload into orbit, docks with the satellite system, and, after completing its tasks (Earth observation, experiments, production of materials in space, etc.), can be separated from the satellite system and returned to Earth. The functional box has its own propulsion, navigation, and communication systems, but derives the energy for its mission tasks from docking with one or more satellite units.

[0063] Thanks to its internal production unit, the functional box is capable of performing tasks such as manufacturing, service, and production. The functional unit also serves as a re-entry capsule, ensuring the payload's re-entry.

[0064] For accommodating a function box, a satellite system according to the invention has a third mode, which is referred to as the semi-detached mode. The semi-detached mode is shown in Figures 6 and 7 and allows two satellite units to be located apart from each other but remain connected by the mechanical docking system. A gap is created between the two satellite units, while maintaining the connection between the data bus and the power flow. The gap created between the two units serves as a frame for a function box 10, which can dock onto the system.

[0065] Fig. 5 shows a further embodiment of a satellite system according to the invention. According to this embodiment, the satellite units are equipped with additional magnetic hinges 12, each satellite unit having four permanent magnets at its edges. These hinges allow the satellite units to remain magnetically connected at their corner edges after the mechanical hinges 6 have been released from each other.

[0066] After the mechanical hinges 6 are released, the detached satellite unit remains connected to the satellite unit by one edge via the magnetic hinge 12. The magnetic hinge 12 can also have, for example, a wireless data bus and a power connection, so that the power supply and communication are maintained.

[0067] The magnetic hinges 12 enable maximum flexibility of the satellite system, as they allow for the creation of a 'walking unit' structure, enabling a satellite unit to be moved to any position within the system. This flexibility of the hinge allows the mission objective to be changed even while the system is already operating in orbit, providing customers with maximum long-term flexibility.

[0068] Such changes to the satellite system's composition can also be advantageous for operation in orbit: If a single satellite unit experiences a system failure, it can be separated from the overall system and returned to Earth via reentry. Another satellite unit can then be deployed to replace the separated unit and take over its functions. In-orbit repairs are not required.

[0069] Figures 6 and 7 show the docking process with a function box 10 using the semi-detached mode described above. The function box 10 docks to the satellite units via the same docking strips 7 as the satellite units themselves. The satellite units remain connected by a telescopically extendable frame element 13, thus leaving space for the function box 10. The two already docked satellite units can therefore be partially separated to create space for the function box 10.

[0070] The functional box has its own navigation and propulsion system to maintain it in a specific position until the satellite units approach and dock with it. Once docked, the satellite units supply the functional box with power so it can perform its mission and remain in a defined orbit. After completing its mission, the functional box can detach from the satellite units and begin its descent into Earth's atmosphere. Serving as a reentry capsule, the functional box, equipped with an inflatable heat shield and parachute, can withstand the extreme conditions of reentry and land safely on Earth. It is also capable of returning the components of the flat satellite to Earth if an overhaul is required. The functional box includes a thruster to maintain its orbit and to deorbit it after the mission is complete.Furthermore, a magnetic docking strip 7 runs along the three sides of the function box 10 for docking to the satellite units. Fig. 7 shows the function box 10 in the semi-detached mode. In the semi-detached mode, the locking devices 8 of the satellite units have a telescopically extendable frame element 13.

[0071] The data and power connection is continued in the telescopic frame element 13. The semi-detached mode allows a function box 10 to be accommodated between two docked satellite units.

[0072] Fig. 8 shows the connection devices 8 in detail. The locking device 8 comprises a probe (active part) and a drogue (passive part). The probe is designed as a protruding pin or plug 14 that extends toward its counterpart. The drogue is designed as a receiving cup or socket 15 that receives the probe. The docking process enables a stable and permanent connection of the satellite units, with the data and power connection being established by the mechanical locking device 8. After completion of the docking process, a satellite array 11 is ready. The docking process can be controlled via cameras (not shown).

[0073] Figure 9 is a schematic representation of the functional box 10. Inside the functional box 10 is an inner box, which serves as the production unit and can be shipped to the customer for the attachment of the payload. The functional box 10 can be opened automatically to provide flexibility for the specific payload, allowing for internal modifications, such as the addition of robotic arms. The functional box 10 comprises an outer box with docking strips 7 and a thruster 9. The inner box can be unfolded. The mission payload is placed in the inner box and can be modified or repositioned as needed using robotic arms.

[0074] Figures 10 and 11 show embodiments of the satellite system in which several parallel satellite chains 11, 1T, 11" are laterally connected to form a carpet of satellite units. The semi-detached mode allows a functional box 10 to be attached or removed as a payload at any point in the system. Such a satellite system can accommodate a large number of payloads simultaneously. Reference numeral list

[0075] I, 1', 1" Master unit

[0076] 2 subunit

[0077] 3 side surface

[0078] 4 Base area

[0079] 5 Cover area

[0080] 6 hinge

[0081] 7 Magnetic docking strip

[0082] 8 Mechanical locking device

[0083] 9 engine

[0084] 10 Function Box

[0085] II, 11', 11" satellite chain

[0086] 12 Magnetic hinge

[0087] 13 Frame element

[0088] 14 plugs

[0089] 15 sockets

Claims

Patent claims 1. Satellite system with several connectable satellite units, wherein a. at least one satellite unit is provided as a master unit (1) and several further satellite units as subunits (2), wherein b. the satellite units each have the shape of a flat cuboid, and wherein at least the subunits (2) have identical external dimensions, characterized in that c. the satellite units each have a rectangular side surface (3) which is narrower than their base surface (4) and their top surface (5), wherein d. the satellite units each have a detachable mechanical hinge (6) on an edge of their side surface (3), wherein the hinges (6) of the satellite units can be coupled to each other to form a linear, articulated satellite chain (16), and wherein e.at least on these side surfaces (3) of the satellite units an electromagnetic docking strip (7) and a mechanical locking device (8) is arranged, wherein f. the locking device (8) is designed to fix the satellite units to one another, and wherein g. the locking device (8) is also designed for energy and data transmission between the satellite units.

2. Satellite system according to claim 1, characterized in that the base (4) and the top surface (5) of the satellite units are essentially square and preferably have identical side lengths L of about 10 cm to about 200 cm, in particular about 33 cm.

3. Satellite system according to claim 1 or 2, characterized in that the width B of the side surfaces (3) of the subunit (2) is less than the side length L, preferably less than 10 cm, particularly preferably less than 5 cm, for example about 3 cm, about 2 cm or about 1 cm, by a factor of 5 to 25, preferably by a factor of 10 to 20.

4. Satellite system according to claim 2 or 3, characterized in that the width B' of the side surfaces (3) of the master unit (1) is the same as the width B of the side surfaces (3) of the sub unit (2), such that the master unit (1) has the same dimensions as the sub unit (2).

5. Satellite system according to claim 2 or 3, characterized in that the width B' of the side surfaces (3) of the master unit (1) is greater than the width B of the side surfaces (3) of the sub-unit (2), but preferably less than the side length L, particularly preferably less than 25cm, for example about 20cm, about 15cm, about 10cm or about 8cm.

6. Satellite system according to one of claims 1 to 5, characterized in that solar panels are arranged on the base surfaces (4) and / or on the top surfaces (5) of the satellite units.

7. Satellite system according to one of claims 1 to 6, characterized in that a camera is arranged on the side surfaces (3) of the satellite units in the area of ​​the docking strips (7).

8. Satellite system according to one of claims 1 to 7, characterized in that the locking device (8) is two-part and comprises a plug (14) and a corresponding socket (15), wherein preferably a plug (14) or a socket (15) is arranged to the left and right of the docking strip (7).

9. Satellite system according to one of claims 1 to 8, characterized in that the master unit (1 ) comprises a propulsion unit (9), a data processing unit, a communication unit, an energy storage unit and an interface unit, wherein the interface unit comprises a data bus which is brought out through the locking device (8).

10. Satellite system according to claim 9, characterized in that a. the subunit (2) has an interface unit with a data bus which is brought out through the locking device (8), wherein b. the subunit (2) has an energy storage device which, in the coupled state, can be connected to the energy storage device of the master unit (1) through the locking device (8) in order to enable energy transfer via the locking device (8), and wherein c. the subunit (2) has a sensor unit which, in the coupled state, can be connected to the interface unit of the master unit (1) in order to enable bidirectional data transmission via the locking device (8).

11. Satellite system according to one of claims 1 to 10, characterized in that the mechanical hinge (6) is arranged on one of the two longer edges of a side surface (3), wherein optionally a magnetic hinge (12) is arranged on one or all of the shorter edges of the side surface (3), for example in the form of a permanent magnet.

12. Satellite system according to one of claims 1 to 11, characterized in that, in addition to the satellite units, a substantially cuboid functional box (10) is provided for receiving payloads, production equipment, test devices and the like.

13. Satellite system according to one of claims 1 to 12, characterized in that the functional box (10) has an outer shell and an inner shell, wherein the payload is arranged in the inner shell, and wherein a space of at least 3 cm is provided between the outer shell and the inner shell.

14. Satellite system according to claim 12 or 13, characterized in that the functional box (10) has a side length L which substantially corresponds to the side length L of the satellite units, and has on its side surfaces a docking strip (7) and a locking device (8) for coupling with the satellite units.

15. Satellite system according to one of claims 12 to 14, characterized in that the function box has an interface unit with a data bus which is brought out through the locking device (8) to enable energy and data transmission between the satellite units and the function box (10).

16. Satellite system according to one of claims 1 to 15, characterized in that the locking device (8) of the satellite units has a frame element (13) extendable up to the side length L, so that a space can be created between two coupled satellite units to accommodate the function box.

17. Satellite system according to one of claims 12 to 16, characterized in that the functional box is designed for re-entry into the Earth's atmosphere and comprises a propulsion system and a navigation system.

18. Satellite system according to one of claims 1 to 17, characterized in that a dispenser unit is provided for receiving several satellite units lying one above the other and connected accordion-like via their hinges (6).

19. Satellite system according to one of claims 1 to 18, characterized in that several master units (1 , T, 1") are provided, wherein each master unit (1 , T, 1") connects several subunits (2) in a linear satellite chain (11 , 1 T, 11"), and wherein the satellite chains (11 , 1 T, 11") are substantially parallel to each other and are connected to each other at their sides.

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