Manufacturing system for a satellite, satellite and method

Abstract

Described is a manufacturing system for a satellite set up for production of a dimensionally stable boom structure in space. The manufacturing system comprises a provision mechanism for provision of base material in strip form with two surfaces on different sides. The manufacturing system further comprises a solidification mechanism for application of polymerizable solidification material to at least one of the surfaces of the base material provided. The manufacturing system is designed such that the base material forms a dimensionally stable boom structure together with polymerized solidification material that has been applied thereto. Also described are a satellite having the manufacturing system and a method of producing a dimensionally stable boom structure in space.

Description

[0001] Manufacturing system for a satellite, satellite and method

[0002] The present invention relates to a manufacturing system for a satellite, which is configured to produce a dimensionally stable boom structure in space. Furthermore, a satellite is provided with the manufacturing system. The invention also relates to a method for producing a dimensionally stable boom structure in space.

[0003] It is known to equip satellites with deployable structures that are only deployed in orbit. In this case, the deployable structures should be stored in the most space-saving way possible until deployment. To ensure that the structures retain their shape after deployment in space, mechanical connecting elements are often provided, such as hinges that can be locked into a predetermined position and connect individual components of the structure to one another. The greater the number of components of the deployable structure and the greater the number of connecting elements, the greater the likelihood of problems occurring during deployment (e.g. due to an undesired blocking of a hinge). In addition, deployable structures and connecting elements can be damaged during flight into space due to the high acceleration or vibrations, meaning that the structures do not have the desired shape after deployment.

[0004] Against this background, it is an object of the invention to ensure that a boom structure in space has a desired shape, wherein components of the boom structure preferably require little transport space during transport into space and the boom structure can be quickly brought into the desired shape.

[0005] According to the invention, a manufacturing system for a satellite is provided, which is configured to produce a dimensionally stable boom structure in space. The manufacturing system comprises a supply mechanism for supplying base material. The base material is strip-shaped with two surfaces located on opposite sides. The manufacturing system further comprises a solidification mechanism for applying polymerizable solidification material to at least one of the surfaces of the provided base material. The manufacturing system is designed such that the base material, together with the solidification material applied thereto and polymerized thereon, forms the dimensionally stable boom structure.

[0006] The strip-shaped base material, like the polymerizable strengthening material, can be stored in a space-saving manner. By applying the strengthening material to the base material, a cantilever structure can be produced that has a predetermined shape and would require more transport space than the base material and strengthening material before the cantilever structure was manufactured. The polymerized strengthening material serves primarily to ensure the dimensional stability of the cantilever structure and determines its shape.

[0007] The term "manufacturing system for a satellite" means that the manufacturing system is designed to be equipped with, attached to, or / and installed in the satellite. The boom structure may be a boom connected to the satellite. The boom structure may comprise one or more substantially straight sections or be entirely straight. The boom structure extends, in particular, away from the manufacturing system and / or the satellite with the manufacturing system. The boom structure is dimensionally stable at least under space conditions, in particular in orbit or under zero gravity. The boom structure may be elastically deformable.

[0008] The supply mechanism can be configured to move the base material, and the solidification mechanism can be configured to apply the polymerizable solidification material to the at least one surface of the moved base material. The supply mechanism is, in particular, configured to guide the base material (e.g., in a predetermined orientation and / or shape) past an outlet opening of the solidification mechanism, while the polymerizable solidification material is applied to the at least one surface through the outlet opening. The manufacturing system can thus be designed to apply the solidification material to the base material moved past the outlet opening. In this way, the cantilever structure can be manufactured in the desired shape in a time-saving manner.

[0009] The consolidation mechanism can be configured to apply the polymerizable consolidation material in the form of a (e.g., continuous or uninterrupted) strand to the at least one surface of the provided base material. The strand covers, in particular, only a portion of the at least one surface of the base material. The strand can be narrower than the base material in a plan view of the at least one surface. The strand can extend in a direction of advance and / or the longitudinal direction of the provided base material. Thus, the amount of consolidation material required can be kept low while simultaneously ensuring the dimensional stability of the cantilever structure.

[0010] The consolidation mechanism can comprise a nozzle that defines a (e.g., constant or continuous) cross-section of the strand. After polymerization of the consolidation material, the strand can increase the flexural rigidity of the cantilever structure. The cross-section can be selected so that the strand has the highest possible flexural modulus after polymerization. The outlet opening can be part of the nozzle. This ensures the cross-section and thus also the flexural modulus of the strand, allowing the cantilever structure to be manufactured with a predetermined flexural rigidity. The use of a nozzle also minimizes the number of moving components of the consolidation mechanism, which reduces the susceptibility to errors and can save weight.

[0011] The consolidation mechanism is configured, for example, to introduce a fibrous material into the polymerizable consolidation material during application of the polymerizable consolidation material. The fibrous material can comprise one or more continuous fibers or a woven fabric. The fibrous material can be stored in coil form. The fibrous material can comprise glass fibers and / or carbon fibers. The fibrous material can be introduced such that fibers of the fibrous material extend substantially in the direction of advance and / or in the longitudinal direction of the provided base material. This can increase the strength of the polymerized consolidation material, which in turn reduces the required amount of consolidation material.

[0012] The base material can be stored folded (e.g. in a stack) or wound (e.g. on a spool). The provision mechanism is then designed to unfold or unwind the stored base material. The base material can be flexible (e.g. throughout) so that it is not dimensionally stable as such. In order to produce the dimensionally stable cantilever structure, it is therefore not sufficient to provide the base material; the strengthening material must also be applied to the base material. Storing it in folded or wound form reduces the transport space required for transport into space. It is also conceivable for the base material to comprise rigid panels and at least one connecting section that movably connects two or more of the panels to one another.In order to produce a dimensionally stable cantilever structure in this case as well, the strengthening mechanism can be configured to apply the strengthening material to the at least one connecting section. The strengthening material can in particular be applied in such a way that the strengthening material applied and polymerized to the at least one connecting section defines a relative position between the panels connected by the at least one connecting section. The connecting section can be made of flexible material or formed by a hinge. It is therefore possible for the base material not to be flexible throughout, but rather rigid in sections. In this case, it is sufficient to apply the strengthening material to flexible regions of the base material between the rigid regions in order to produce a dimensionally stable cantilever structure.This reduces the consumption of reinforcement material and also makes it possible to use base material in which rigid components such as solar cells are arranged in the area of ​​the panels.

[0013] The strengthening mechanism can be configured to apply the strengthening material, in particular simultaneously, to both surfaces of the base material. The strengthening material can be applied to each of the two surfaces in the form of a respective strand. The two strands can be opposite one another or offset in the transverse direction of the base material, i.e., in particular, transverse to the direction of advance and / or the longitudinal direction of the provided base material. The two strands can have the same cross-section or differ in cross-section. Applying the strengthening material to both sides can further increase the flexural rigidity. This can also counteract deflection of the cantilever structure due to contraction or expansion of the strengthening material on one of the surfaces.

[0014] In one example, at least one through-hole is provided in the base material. The strengthening mechanism can then be configured to apply the strengthening material such that at least a portion of the through-hole is filled with the strengthening material. The strengthening mechanism can then be configured to apply the strengthening material across the through-hole to the at least one surface. Thus, even in the region of the through-hole, a strand of strengthening material can be applied to the base material, in particular a strand with a substantially constant cross-section. This increases the adhesion of the strengthening material to the base material.When the strengthening material is applied on both sides, the through holes can serve as a through-connection between the strengthening material on a first of the surfaces of the base material and the strengthening material on the second of the surfaces, which further increases the stability.

[0015] In one example, the strengthening mechanism is designed to apply different strengthening materials (e.g., simultaneously or staggered) to the base material. For this purpose, the strengthening mechanism can comprise multiple nozzles, each of which is configured to apply a different strengthening material. It is also conceivable to first apply a first strengthening material and then a second strengthening material through a nozzle. The strengthening materials can differ, in particular, in their modulus of elasticity in the polymerized state. It is also conceivable to apply electrically conductive strengthening material to the base material in order to create an electrical conductor for the cantilever structure.

[0016] The solidification mechanism can comprise an irradiation unit configured to initiate photopolymerization of the applied solidification material by means of electromagnetic irradiation. The irradiation unit can comprise one or more light sources, such as light-emitting diodes (LEDs). The wavelength of the irradiation or the emitted light can be matched to the solidification material, in particular to a photoinitiator in the solidification material. For example, the irradiation unit is configured for irradiation in the ultraviolet wavelength spectrum (e.g., using UV LEDs). This enables rapid and targeted polymerization of the solidification material.

[0017] The manufacturing system can be designed such that, after completion of a manufacturing process for producing the cantilever structure, at least a portion of the solidification material remaining in the solidification mechanism polymerizes, thereby securing the solidification mechanism to the cantilever structure. This portion of the solidification material can correspond to the solidification material in the nozzle(s). The nozzle(s) can be equipped with illumination means to initiate the polymerization of the portion of the solidification material. It is also conceivable for the nozzle(s) to be optically transparent, at least in sections, so that irradiation from the irradiation unit can initiate polymerization within the nozzle(s). This enables space-saving and reliable attachment of the manufactured cantilever structure to the manufacturing system.

[0018] The solidification mechanism can comprise a container under internal gas pressure for storing the polymerizable solidification material to be applied. A membrane can be arranged in the container, separating a propellant gas from the stored solidification material. The solidification material is stored in the container, in particular, without gas contact. This enables the dispensing of stored solidification material without an electric actuator.

[0019] Furthermore, a satellite is provided that comprises the manufacturing system according to the invention. The satellite can be a small or micro satellite, in particular a satellite weighing less than 600 kg, less than 200 kg, less than 50 kg, or even less than 10 kg. The manufacturing system can be built into the satellite or attached to the satellite. For example, the base material and / or the strengthening material are stored inside the satellite.

[0020] In one example, the base material comprises electrical cabling for an electrical load (e.g., a camera) attached to the base material or for a solar cell attached to the base material. This electrical cabling can be electrically connected to the satellite, in particular even before the application of the solidification material. The load can be a data generator and, in particular, comprise a sensor and / or an antenna.

[0021] According to a further aspect of the invention, a method for producing a dimensionally stable cantilever structure in space is provided, comprising: providing base material that is strip-shaped with two surfaces located on different sides; applying polymerizable strengthening material to at least one of the surfaces of the provided base material; and polymerizing the applied strengthening material to form the dimensionally stable cantilever structure from the base material and the polymerized strengthening material. For example, the polymerizable strengthening material is applied in the form of a strand with, in particular, a predetermined cross-section to at least one surface of the provided base material (e.g., through the nozzle(s)). During the application of the polymerizable strengthening material, a fiber material can be introduced into the polymerizable strengthening material.The base material can be stored folded or wound and unfolded or unwound for preparation. The base material can comprise rigid panels and at least one connecting section that movably connects two or more of the panels to one another, wherein the strengthening material is applied to the at least one connecting section, in particular such that the strengthening material applied and polymerized to the at least one connecting section defines a relative position between the panels connected by the at least one connecting section. The strengthening material can be applied simultaneously to both surfaces of the base material. At least one through-hole can be provided in the base material, and the strengthening material can be applied such that at least part of the through-hole is filled with the strengthening material.Different strengthening materials can also be applied to the base material. In the method, photopolymerization of the applied strengthening material can be initiated by electromagnetic radiation. In the method, after completion of a manufacturing process for producing the cantilever structure, at least a portion of the strengthening material remaining in a strengthening mechanism can be polymerized, in particular initiated by electromagnetic radiation, thereby attaching the strengthening mechanism to the cantilever structure. The polymerizable strengthening material to be applied can be stored in a container under internal gas pressure.The base material may comprise electrical wiring for an electrical load attached to the base material or for a solar cell attached to the base material, the electrical wiring being electrically connected to the satellite.

[0022] The method can be carried out using the manufacturing system and / or the satellite with the manufacturing system. The manufacturing system and / or the satellite with the manufacturing system can be designed to carry out the method. The method can include further steps that are described herein in connection with the satellite and / or the manufacturing system. Exemplary embodiments of the invention are described below under

[0023] Described with reference to the figures, where

[0024] Fig. 1 shows an exemplary embodiment of a manufacturing system;

[0025] Fig. 2 shows a plan view of a first example of base material with applied strengthening material;

[0026] Fig. 3 shows exemplary cross-sections of strengthening material applied to base material;

[0027] Fig. 4a shows a plan view of a second example of base material with applied strengthening material;

[0028] Fig. 4b shows a side view of the example of Fig. 4a;

[0029] Fig. 5 shows a plan view of a third example of base material with applied strengthening material;

[0030] Fig. 6a shows a first perspective view of an example of a satellite with a manufactured boom structure; and

[0031] Fig. 6b shows a second perspective view of the example from Fig. 6a.

[0032] A manufacturing system 100 for a satellite 200 is provided, which is designed to produce a boom structure 300 that is dimensionally stable under space conditions. As can be seen in Fig. 1, the manufacturing system 100 comprises a supply mechanism 2 for supplying base material 4. The supply mechanism 2 comprises a carrier spool 6. The base material 4 is stored wound on the carrier spool 6. The supply mechanism 2 further comprises a conveyor device 8 for moving the base material 4. In the example shown, the conveyor device 8 comprises three pairs of conveyor rollers 10, 12, 14, each arranged on different sides of the moving base material 4. The conveyor rollers 10, 12, 14 serve to advance the base material 4 in the direction of arrow 16 and position the base material 4 in a desired orientation and shape.For this purpose, the conveyor rollers are in contact with the two opposite surfaces 18, 20 of the base material 4. During the feed movement of the base material 4, the strip-shaped base material 4 held on the spool 6 is unwound from the spool 6. Instead of storing the base material 4 wound on the spool 6, it can also be stored in stacks.

[0033] The manufacturing system 100 further comprises a solidification mechanism 22. The solidification mechanism 22 comprises a container 24 in which polymerizable solidification material 26 is stored. The container 24 is provided with a gas-impermeable membrane 28 inside, which separates the solidification material 26 from a propellant gas 30 in the container 24. The propellant gas creates an overpressure inside the container 24, particularly compared to the vacuum in space, and this overpressure pushes the solidification material 26 toward a dosing unit 32 of the solidification mechanism 22. The dosing unit 32 can be designed as an extruder for viscous media and, in particular, comprise a screw extruder. In the example shown, a shut-off valve 34 is provided downstream of the extruder; this shut-off valve 34 can also be arranged between the container 24 and the dosing unit 32.Instead of the pressurized gas-filled container 24, a chamber filled with the solidifying material 26 can also be provided, which is closed off on one side by a piston. In this case, the solidifying material 26 can be dispensed by deliberately pressing the piston into the chamber. Thus, a separate dosing unit 32 is not required.

[0034] In the example shown, the solidification mechanism 22 also comprises a plurality of nozzles 36, 38 for dispensing the polymerizable solidification material 26 onto the surfaces 18, 20 of the base material 4, wherein only a single nozzle may be provided (e.g., to coat only one of the surfaces with the solidification material 26).

[0035] To produce the cantilever structure 300, the shut-off valve 34 is opened while the base material 4 is being advanced, and the dosing unit 32 doses the release of the strengthening material 26 through the nozzles 36, 38 onto the surfaces 18, 20 of the base material 4 moving past the nozzles. The strengthening mechanism 22 can be designed such that, when the polymerizable strengthening material 26 is applied, it introduces a fiber material 40 into the strengthening material 26. For this purpose, glass fibers, carbon fibers, or fabric material, for example, can be unwound from a spool 42 and fed into the nozzle 38 for embedding in the strengthening material 26. The applied strengthening material 26 must be polymerized to produce the dimensionally stable cantilever structure 300. It is conceivable to store two chemically reactive components of the strengthening material 26 separately (e.g.in different containers 24), and these are combined in the respective nozzles 36, 38 to start the polymerization of the two components. Alternatively, the solidification material 26 can comprise a photoinitiator which initiates the polymerization upon irradiation (e.g. with UV light). In this case, the polymerization of the applied solidification material 26 can be initiated by radiation present in space (e.g. emitted by the sun). In order to ensure faster polymerization and thus guarantee a predetermined shape of the cantilever structure, an irradiation unit 44 is provided. The irradiation unit 44 comprises a plurality of LEDs, in particular UV LEDs, which irradiate the applied solidification material and thus initiate the polymerization reaction. In the example shown, both sides 18, 20 are illuminated by the irradiation unit 44 in order to solidify the solidification material simultaneously on both sides.

[0036] Fig. 1 schematically shows the different polymerization stages of the applied strengthening material 26: immediately after application, the strengthening material 26 is not yet polymerized (see section 46). Polymerization is initiated in the illumination region of the irradiation unit 44 (see section 48), and subsequently the polymerized strengthening material is present (see section 50). It is understood that the regions may differ from the example in Fig. 1 depending on the irradiation intensity, layer thickness of the strengthening material, and feed rate of the base material 4. In section 50, the strengthening material can also be irradiated and (e.g., further) polymerized by radiation present in space (e.g., from the sun). The base material 4, together with the strengthening material 26 applied and polymerized to the surfaces 18, 20, forms the dimensionally stable cantilever structure 300.

[0037] After completion of a manufacturing process for the cantilever structure 300, the solidification material 26 remaining in the nozzles 36, 38 can also be polymerized. For this purpose, an additional irradiation unit can be provided, or light can be directed from the irradiation unit 44 onto the solidification material 26 in the nozzles 36, 38. This creates a rigid connection between the cantilever structure 300 and the nozzles 36, 38, which, in particular, prevents translation of the cantilever structure in or against the feed direction.

[0038] Fig. 2 shows a plan view of a first example of base material 4 with applied and polymerized strengthening material 26. It can be seen that the strengthening material 26 is applied to the base material in strip form in plan view. The individual strips each correspond to a continuous strand 52, 54, 56 of strengthening material 26. In the example shown, the individual strips or strands 52, 54, 56 run in the longitudinal direction of the band-shaped base material 4, i.e. essentially parallel to its feed direction. The strengthening material only covers the base material 4 in sections, i.e. not over its entire surface. Each strand 52, 54, 56 can have been extruded from a different nozzle or a different nozzle opening. The corresponding nozzle 38, 40 specifies a cross-section of the corresponding strand 52, 54, 56. The cross-sections can differ among the strands. The strands can, as shown in Fig.2, can be of different lengths. Thus, it is conceivable to design a strand 54 located in a central region of the base material 4 to be longer and / or with a stiffer cross-section than strands 52, 54 located in an edge region of the base material.

[0039] Exemplary cross-sections of the strengthening material 26 applied to the base material 4 are shown in Fig. 3. It can be seen that the strengthening material 26 can be applied in a channel shape, for example, with a U-shaped, a box-shaped, or a V-shaped cross-section, whereby different orientations of the cross-section relative to the base material 4 are possible. The strengthening material 26 can also be applied in a hollow tube shape.

[0040] In example 58, the strengthening material 26 is applied to the base material 4 in a channel shape with a box-shaped cross-section, wherein the open side of the channel is covered by the base material 4. In example 60, the strengthening material 26 is applied to the base material 4 in the form of an elongated channel with an upwardly open rectangular or box-shaped cross-section, wherein the open side is oriented away from the base material 4. In example 62, the cross-section is rectangular, wherein the short sides of the rectangle run essentially parallel to the base material 4. In example 64, the strengthening material 26 is applied to the base material 4 in a channel shape with a V-shaped cross-section. The cross-section in example 66 has the shape of an equilateral triangle, one side of which rests on the base material 4. In example 68, the strand from example 66 is further provided with a cavity, i.e. it is tubular.In examples 70 and 72, the cross-section is T-shaped, with the strand resting on the base material with the long top side of the "T" in example 70, but with the short base side in example 72. In example 74, the cross-section is H-shaped, with the strand resting on the base material 4 with one leg side of the "H". Other cross-sections are also conceivable; depending on the cross-section, a desired degree of stiffening or a desired flexibility of the cantilever structure 300 can be ensured.

[0041] Fig. 4a and Fig. 4b show a second example of base material 4 with applied strengthening material 26. In this example, through-holes 76 are introduced into the base material 4. The through-holes are spaced apart (e.g. only) in the feed direction and can lie on a line which, in plan view, runs essentially parallel to a side edge of the base material 4. The strengthening material 26 covers a section of the base material 4 in which a plurality of through-holes 76 are present. The through-holes 76 located in this section are filled with the strengthening material 26. This enables a positive connection between the strengthening material 26 and the base material 4. If strengthening material 26 is applied to both sides 18, 20, the two strands 78, 80 can be reliably connected to one another by the strengthening material 26 in the through-holes 76.

[0042] Fig. 5 shows a plan view of a third example of base material 4 with applied strengthening material 26. In this example, the through-holes 76 are slit-like, in particular each with a rectangular outline. The through-holes 76 extend essentially transversely to the feed direction or the longitudinal direction of the base material 4. Different groups of through-holes 76 are provided, wherein the centers of the through-holes 76 of the respective groups are spaced transversely to the feed direction from the centers of the through-holes of the other groups. The strengthening material only fills the through-holes of a first of the groups, and only partially, so that even the filled through-holes 76 continue to comprise free areas free of strengthening agent. This makes it possible to reduce thermal stresses in the cantilever structure 300.

[0043] Fig. 6a and Fig. 6b show an example of a satellite 200 with the manufacturing system

[0044] 100 and the manufactured cantilever structure 300. The polymerized

[0045] The boom structure 300 formed by the solidification material 26 and the base material 4 extends away from the satellite 200. An electrical load 82 is provided at the distal end of the boom structure 300 and is already attached to the base material 4 before it is advanced by the deployment mechanism 2. The load 82 can be, for example, a camera. The camera can be arranged so that its line of sight is directed towards the satellite 200. The base material 4 also includes electrical cabling that connects the load 82 to the satellite 200. The cabling can be embedded in the base material 4 or attached thereto.

[0046] In the example shown, the base material 4 comprises rigid panels 84 which are connected to one another via flexible connecting sections 86. Solar cells 88 are arranged in the area of ​​the panels 84. The rigid panels 84 can be formed, for example, by gluing solar cells 88 onto a flexible base material 4. The strengthening material 26 extends over the connecting sections 86 so that the polymerized strengthening material 26 defines a layer of the panels and thus forms the dimensionally stable cantilever structure. In the example shown, the strengthening material 26 is only applied to the surface 18; the solar cells are located on the opposite surface 20. The solar cells can be connected to the satellite 200 via the cabling. It is also conceivable to apply an electrically conductive strengthening material 26 in order to establish electrical contact between the load 82 and / or the solar cells 88.

[0047] In addition to the manufacturing system 100 and the satellite 200, a corresponding method for manufacturing the boom structure 300 is also provided here.

[0048] It is understood that the manufacturing system, satellite, and their components described herein may be modified. The process may also be adapted accordingly.

Claims

Patent claims 1. A manufacturing system (100) for a satellite (200) configured to produce a dimensionally stable boom structure (300) in space, comprising: a supply mechanism (2) for supplying base material (4) which is strip-shaped with two surfaces (18, 20) located on different sides; and a solidification mechanism for applying polymerizable solidification material (26) to at least one of the surfaces (18, 20) of the provided base material (4), wherein the manufacturing system (100) is configured such that the base material (4) together with the solidification material (26) applied thereon and polymerized thereon forms the dimensionally stable boom structure (300).

2. Manufacturing system (100) according to claim 1, wherein the solidification mechanism is configured to apply the polymerizable solidification material (26) in the form of a strand (52, 54, 56) to the at least one surface (18, 20) of the provided base material (4).

3. Manufacturing system (100) according to claim 2, wherein the solidification mechanism comprises a nozzle (36, 38) which defines a cross-section (58-74) of the strand (52, 54, 56).

4. Manufacturing system (100) according to one of claims 1 to 3, wherein the consolidation mechanism is configured to introduce a fibrous material (40) into the polymerizable consolidation material (26) when applying the polymerizable consolidation material (26).

5. Manufacturing system (100) according to one of claims 1 to 4, wherein the base material (4) is stored folded or wound and the supply mechanism (2) is designed to unfold or unwind the stored base material (4).

6. Manufacturing system (100) according to one of claims 1 to 5, wherein the base material (4) comprises rigid panels (84) and at least one connecting portion (86) which movably connects two or more of the panels (84) together, wherein the strengthening mechanism is configured to apply the strengthening material (26) to the at least one connecting section (86), in particular in such a way that the strengthening material (26) applied and polymerized to the at least one connecting section (86) defines a relative position between the panels (84) connected by the at least one connecting section (86).

7. Manufacturing system (100) according to one of claims 1 to 6, wherein the solidification mechanism is configured to apply the solidification material (26), in particular simultaneously, to both surfaces (18, 20) of the base material (4).

8. Manufacturing system (100) according to one of claims 1 to 7, wherein at least one through-hole (76) is provided in the base material (4) and the solidification mechanism is configured to apply the solidification material (26) such that at least a portion of the through-hole (76) is filled with the solidification material (26).

9. Manufacturing system (100) according to one of claims 1 to 8, wherein the solidification mechanism is designed to apply different solidification materials (26) to the base material (4).

10. Manufacturing system (100) according to one of claims 1 to 9, wherein the solidification mechanism comprises an irradiation unit (44) configured to initiate photopolymerization of the applied solidification material (26) by means of electromagnetic irradiation.

11. Manufacturing system (100) according to one of claims 1 to 10, designed such that after completion of a manufacturing process for producing the cantilever structure (300), at least a portion of the strengthening material (26) remaining in the strengthening mechanism polymerizes and thereby attaches the strengthening mechanism to the cantilever structure (300).

12. Manufacturing system (100) according to one of claims 1 to 11, wherein the solidification mechanism comprises a container (24) under internal gas pressure for storing the polymerizable solidification material (26) to be applied.

13. Satellite (200) comprising the manufacturing system (100) according to any one of the preceding claims.

14. Satellite (200) according to claim 13, wherein the base material (4) comprises an electrical wiring for an electrical load (82) attached to the base material (4) or for a solar cell (88) attached to the base material (4), wherein the electrical wiring is electrically connected to the satellite (200).

15. A method for producing a dimensionally stable cantilever structure (300) in space, comprising: Providing base material (4) which is strip-shaped with two surfaces (18, 20) lying on different sides; Applying polymerizable strengthening material (26) to at least one of the surfaces (18, 20) of the provided base material (4); and Polymerizing the applied strengthening material (26) to form the dimensionally stable cantilever structure (300) from the base material (4) and the polymerized strengthening material (26).

16. The method according to claim 15, wherein: - the polymerizable strengthening material (4) is applied in the form of a strand with a predetermined cross-section to the at least one surface (18, 20) of the provided base material (4); and / or - when applying the polymerizable strengthening material (26), a fiber material (40) is introduced into the polymerizable strengthening material (26); and / or - the base material (4) is stored folded or wound and is unfolded or unwound for provision; and / or - the base material (4) comprises rigid panels (84) and at least one connecting section (86) which movably connects two or more of the panels (84) to one another, wherein the strengthening material (26) is applied to the at least one connecting section (86), in particular such that the strengthening material (26) applied and polymerized to the at least one connecting section (86) defines a relative position between the panels (84) connected by the at least one connecting section (86); and / or - the strengthening material (26) is applied, in particular simultaneously, to both surfaces (18, 20) of the base material (4); and / or - at least one through-hole (76) is provided in the base material (4) and the strengthening material (26) is applied such that at least a part of the through-hole (76) is filled with the strengthening material (26); and / or - different strengthening materials (26) are applied to the base material (4); and / or - a photopolymerization of the applied strengthening material (26) is initiated by means of electromagnetic irradiation; or / and - after completion of a manufacturing process for producing the cantilever structure (300) at least a portion of the solidification material (26) remaining in a solidification mechanism is polymerized, in particular polymerized by electromagnetic irradiation, and the solidification mechanism is thereby fastened to the cantilever structure (300); or / and - the polymerizable solidification material (26) to be applied is stored in a container (24) under internal gas pressure; or / and - the base material (4) comprises an electrical wiring for an electrical load (82) attached to the base material (4) or for a solar cell (88) attached to the base material (4), wherein the electrical wiring is electrically connected to the satellite (200).

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