Satellite transport and delivery device

Abstract

Satellite transport and delivery device with at least one lower support (6) and a further support (5) arranged above it and thus vertically spaced apart by means of a lower support structure (8) for receiving at least one satellite (2, 3), characterized in that the lower support structure (8) is pivotably mounted on at least one of the supports (5, 6) by means of a joint (9).

Description

[0001] The invention relates to a satellite transport and delivery device according to the preamble of claim 1.

[0002] These devices are typically located in the orbital stages of rockets and serve to transport satellites, which are launched by the rocket into orbital altitude, and to deploy them at their desired orbital position. Typically, in so-called "ride-sharing" mode, four to twelve or more satellites are deployed into low Earth orbits, with the transport and deployment device forming the connection between the satellites to be deployed and the rocket (launch vehicle).

[0003] In known satellite launch and delivery systems, the satellites to be transported are attached laterally to a central, vertical support structure and extend horizontally from it. The support structure has a base through which it is connected to the rocket's orbital stage. The satellites can be jettisoned laterally for deployment once the appropriate altitude is reached. During rocket launch and subsequent maneuvers, the satellites are subjected to high acceleration forces of up to 10 g, particularly bending forces during launch and vibration forces during engine thrust. The attachment devices between the satellites and the support structure must withstand these high g-forces and be designed accordingly, which is technologically complex and expensive, and also increases the weight of the launch and delivery system, thus reducing the payload capacity.

[0004] With known transport and deployment systems, there is only one designated space, namely at the very top of the support structure, known as the "cake topper slot." Satellites placed there do not require lateral support, making acceleration forces much easier to manage. However, since, as described above, up to twelve satellites, sometimes more, are launched into space in "ride-sharing" mode, all other satellites that do not fit in the "cake topper slot" must be attached laterally, with the disadvantages mentioned above.

[0005] To address this problem, efforts have already been made to position multiple satellites in a transport and delivery device in such a way that easier attachment is possible.

[0006] EP 1 104 743 B1 describes a two-tiered satellite platform deployment device enclosed within the fairing of a launch vehicle. The device comprises a lower platform assembly and an upper platform assembly attached to a central pylon. Multiple satellites can be independently deployed from openings on each of the two platform assemblies using conventional separating devices. The entire weight of each satellite is supported by its respective platform assembly.

[0007] CN 115246494 A discloses a satellite transport system with two satellite mounting plates for receiving ten to twelve satellites, wherein the satellite mounting plates have launching devices by which the satellites can be released parallel or perpendicular to the satellite mounting plates.

[0008] The subject of US Patent 5,199,672 A is a stack for transporting a group of satellites for a launch vehicle, arranged within a launch vehicle fairing. The stack comprises several pallets, each carrying four satellites, although arrangements with more or fewer satellites are also possible. Each pallet has a kick motor. Once the entire stack reaches a predetermined position and orientation, it is separated from the launch vehicle, and then the individual satellites are released from their respective pallets.

[0009] US patent 12,258,151 B2 discloses a satellite launching system for stacking multiple satellite systems, specifically for stacking satellite sub-stacks. In addition to upper and lower columns, the satellite launching system includes diagonal struts for stabilizing a lower satellite sub-stack and diagonal struts for stabilizing the entire stack. These are attached to a base via strut mounts. Furthermore, strut couplings for connecting the diagonal struts and strut couplings with support rods are disclosed.

[0010] Other publications describing a stacking of satellites are US 11,254,453 B2, CN 111216924 A, CN 113955156 B, CN 115230989 A, EP 3 699 097 B1 and EP 3 717 357 B1.

[0011] Based on the aforementioned EP 1 104 743 B1, the task is to design a satellite transport and delivery device in such a way that the delivery of several satellites is possible in the simplest, most space-saving, weight-saving and cost-effective manner.

[0012] This problem is solved by the characterizing features of claim 1. Advantageous embodiments can be found in the dependent claims.

[0013] The invention relates to a satellite transport and delivery device with at least one lower support and a further support arranged above it and thus vertically spaced apart by means of a lower support structure for receiving at least one satellite, wherein the lower support structure is pivotably mounted on at least one of the supports by means of a joint.

[0014] Advantageously, the joint has a drive mechanism for pivoting it.

[0015] Preferably, the lower support structure can be pivoted outwards at least partially relative to the lower support.

[0016] Advantageously, the lowest support plate is the payload adapter of the orbital stage of a launch vehicle or is permanently attached to it. This eliminates the need for additional support plates and also saves weight.

[0017] Preferably, the support structure is designed in the form of one or more struts. Alternatively, the support structure can also be plate-shaped. In both cases, the advantage lies in a secure connection between adjacent support plates.

[0018] Advantageously, adjacent support plates are connected to each other by at least one pair of two A-shaped struts. This results in high stiffness, as the two A-shaped struts together with the lower support plate form a kind of filigree triangle.

[0019] Preferably, adjacent support plates are connected to each other via several pairs of A-shaped struts, with adjacent pairs being able to be connected to the lower support plate at the same point. This results in a filigree structure that exhibits exceptional rigidity.

[0020] Preferably, the struts of adjacent pairs are connected to the lower support at the same point. This results in a cohesive structure.

[0021] Advantageously, an upper support beam is positioned above the lower beam, and each beam is connected to the beam below it via a support structure. This allows multiple satellites to be transported one above the other.

[0022] Preferably, each pair of adjacent beams is detachably connected to at least one of the supporting structures. This allows the support structure to be separated from the beam, enabling different output configurations of the satellite. Preferably, at least one beam has a curved or angled shape adapted to the respective load exerted by the support structure and satellite. This shape can be calculated, for example, using artificial intelligence and optimized for the load.

[0023] Preferably, the support or each support is round, with the support structure being connected to it at equal intervals along the circumference of the support.

[0024] Alternatively, each support can be polygonal, e.g. triangular, quadrilateral, pentagonal, hexagonal, heptagonal or octagonal, with the supporting structure being connected to the support at the corners of the support.

[0025] In a preferred embodiment, at least one support structure is completely detachable from the support structure and includes functional components for performing tasks or conducting tests in orbit. This allows the support structure to be used multiple times and effectively.

[0026] Preferably, in this case, the support has fold-out sunshades to supply energy to the functional components.

[0027] Advantageously, more than two carrier plates are arranged one above the other, e.g., three, four, five, or six carrier plates, and each is connected to the others by an arrangement of support structures. In this way, a large number of satellites can be transported and dispensed using the satellite transport and delivery device.

[0028] Advantageously, the upper of each pair of adjacent support plates is detachably connected to at least one of the supporting structures. This allows the upper support plate to be detached.

[0029] Some embodiments of the invention are explained in more detail below with reference to the accompanying drawings. These show: Fig. 1 A perspective view of a satellite transport and delivery device according to the invention with three satellites arranged one above the other in transport position; Fig. 2 A representation according to Fig. 1 with detached topmost satellite; Fig. 3 A representation according to Fig. 2 with open upper support structure; Fig. 4 A representation according to Fig. 3 with detached central satellite; Fig. 5 A representation according to Fig. 4 with open lower support structure, where here in deviation from Fig. 4 the upper support structure is shown closed again; Fig. 6 A representation according to Fig. 5 with detached lower satellite.

[0030] The arrangement shown in the figures is located in the orbital stage of a rocket, which serves to place the satellite transport and delivery device into space, in particular into an orbital path. The lower support 6 shown in the figures can either coincide with the top of the orbital stage of a launch vehicle or be rigidly connected to it.

[0031] As from Fig. As can be seen in Figure 1, a lower support structure is connected to the lower support 6, which can be rigidly connected to the orbital stage of a rocket, via first joints 9. The lower support structure 8 consists of individual struts arranged in pairs such that each pair of struts forming an A-shape is positioned side by side. The spacing of the first joints 9 is chosen so that an integer number of pairs of struts can be arranged side by side along the circumference of the lower support 6. The function of the first joints 9 is described below. Above the lower support structure 8, which consists of the A-shaped pairs of struts, is another support 5, which can be attached to the struts of the lower support structure 8 via second joints 10. The space between the lower support 6 and the other support 5 is dimensioned to accommodate a lower satellite 3.

[0032] Above the further support 5, connected to it by unspecified joints, is an upper support structure 7, which can likewise consist of struts, each A-shaped and running along the circumference of the further support 5, with the upper support 4, also a plate, located at the upper ends of these struts. Here too, the space between the further support 5 and the upper support 4 is dimensioned to accommodate a medium satellite 2.

[0033] Finally, an upper satellite 1 can be located on the front of the upper support structure 4, which then stands freely, so to speak, meaning it is no longer encapsulated by a support structure. The entire assembly is located within the orbital stage of a launch vehicle and is surrounded by an outer protective shell, which must be jettisoned before the satellites are deployed into orbit.

[0034] To deploy satellites 1 to 3, the launch vehicle is first placed into orbit. Then, the outer shell separates from the launch vehicle's orbital stage, and the upper satellite 1 can be detached from the upper support structure 4, as shown in Fig. 2 is shown. The upper satellite 1 then assumes its desired position in orbit.

[0035] In the next step, the upper support structure 7 opens as the struts are pivoted outwards around the second joints 10, with each pair of struts pivoting outwards around the same axis in the further support 5. The upper support 4 can either be detached (which is not shown in the illustration) or remain attached to the tip of a pair of struts, i.e., only secured at points, as shown in Fig. 3 is shown. If the struts forming the upper support structure are swung far enough outwards, the upper support 4 comes into a position in which the middle satellite 2 can be ejected unhindered, as shown in Fig. Figure 4 shows that the middle satellite 2 then assumes the desired position in orbit.

[0036] In a third step, the lower support structure 8 also opens, as described in Fig. Figure 5 shows the pairs of adjacent struts, connected at their tips, moving outwards around the first joints 9 so that the lower satellite is now in a position allowing its release. This release of the lower satellite 3 is shown in Fig. Figure 6 shows that this satellite can now also assume its desired position in orbit.

[0037] The Fig. 5 and Fig. 6 differ from the Fig. 3 and Fig. 4 such that after the deployment of the middle satellite 2, the upper support structure 7 is closed again and covered by the upper support 4, leaving an empty cage. This can then be pivoted together again around the second joints 10 of the lower support structure, so that two empty cages remain and can be used for other purposes if necessary.

[0038] In the Fig. 7 and Fig.Figure 8 shows the first joints 9 and the second joints 10 in more detail, indicating the dashed axes of rotation around which the joints 9 and 10 rotate when actuated. This actuation can be effected by a drive mechanism, which is not shown in detail. The dashed axes of rotation show that the adjacent struts, which act on the same first joint 9 and second joint 10 respectively, can be pivoted outwards in the same direction around an axis of rotation that runs tangentially to the outer edge of the lower support 6 and the further support 5, respectively.

[0039] The illustrations show that each of the three satellites, 1 to 3, is located in a central position within the satellite transport and delivery device and also in a central position with respect to the longitudinal axis of the rocket. Therefore, the lateral and bending forces acting on the satellite mountings are negligible, as there is only a supporting force against the respective carrier, which, however, does not exert any torque on the satellites.

[0040] Not shown are possible drive devices for the joints, which are necessary for pivoting the support structures or struts. These could be electric or hydraulic drive devices.

[0041] Preferably, the struts of adjacent pairs can be connected to the lower support 6 at the same point, with an upper support arranged above the further support 5 and each support connected to the support below it via one of the support structures. It is therefore also possible that further support structures with corresponding supports along the same axis are provided above the two support structures 7 and 8 shown in the figures.

[0042] In the figures, the individual supports are depicted as hexagonal plates. However, it is also possible to adapt the supports to the respective load by, for example, making some areas thicker and others thinner, or by giving the supports a curved or angled shape, as can be calculated using finite element methods or artificial intelligence.

[0043] The girders can also be polygonal instead of round, or form various types of rectangles, such as triangles, quadrilaterals, pentagons, hexagons, heptagons, or octagons. The girders can either remain attached to the support structure or be completely detachable from it. They can also incorporate functional components for performing tasks or conducting surveys or tests within orbit. Furthermore, the girders can include deployable solar panels to power these functional components, which are not shown in detail here. Reference sign 1 Upper Satellite 2 Medium Satellite 3 Lower Satellite 4 Upper beam 5. Further carrier 6 Lower beam 7 Upper support structure 8 Lower support structure 9 First joints 10 Second Joints QUOTES INCLUDED IN THE DESCRIPTION

[0000] This list of documents cited by the applicant was automatically generated and is included solely for the reader's convenience. The list is not part of the German patent or utility model application. The DPMA accepts no liability for any errors or omissions. Cited patent literature

[0000] EP 1 104 743 B1 [0006, 0011] CN 115246494 A

[0007] US 5,199,672 A

[0008] US 12,258,151 B2

[0009] US 11,254,453 B2

[0010] CN 111216924 A

[0010] CN 113955156 B

[0010] CN 115230989 A

[0010] EP 3 699 097 B1

[0010] EP 3 717 357 B1

[0010]

Claims

[1] Satellite transport and delivery device with at least one lower support (6) and a further support (5) arranged above it and thus vertically spaced apart by means of a lower support structure (8) for receiving at least one satellite (2, 3), characterized by , that the lower support structure (8) is pivotably mounted on at least one of the supports (5, 6) by means of a joint (9). [2] Device according to claim 1, characterized by , that the joint (9) has a drive for its pivoting. [3] Device according to one of the preceding claims, characterized by , that the lower support structure (8) can be pivoted outwards at least partially relative to the lower support (6). [4] Device according to one of the preceding claims, characterized by , that the lower support (6) is the payload adapter of the orbital stage of a launch vehicle or is rigidly connected to it. [5] Device according to one of the preceding claims, characterized by , that the lower support structure (8) is designed as one or more struts. [6] Device according to claim 5, characterized by , that the lower and the further support (6, 5) are connected by at least one pair of two A-shaped struts. [7] Device according to claim 6, characterized by , that the lower and the further support (6, 5) are connected to each other via several pairs of A-shaped struts. [8] Device according to claim 7, characterized by , that the struts of adjacent pairs are connected to the lower support (6) at the same point. [9] Device according to any one of the preceding claims, characterized by , that an upper beam (4) is arranged above the further beam (5) and each beam is connected to the beam below via a support structure. [10] Device according to any one of the preceding claims, characterized by , that each of two adjacent beams is detachably connected to at least one of the supporting structures that carry them. [11] Device according to any one of the preceding claims, characterized by that at least one support has a curved or angled shape adapted to the respective load from the support structure and satellites. [12] Device according to any one of the preceding claims, characterized by that the or each support is round and the supporting structure is connected to it at equal intervals along the circumference of the support. [13] Device according to any one of claims 1 to 11, characterized by that the or each support is triangular, quadrilateral, pentagonal, hexagonal, heptagonal or octagonal and that the supporting structure is connected to the support at the corners of the support. [14] Device according to any one of the preceding claims, characterized by, that at least one support structure is completely detachable from the support structure and has functional components for performing tasks or for carrying out tests in orbit. [15] Device according to claim 14, characterized by that the carrier has fold-out sunshades for supplying energy to the functional building elements.

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