A deployable satellite platform unit for large spacecraft

Abstract

Provided is an expandable satellite platform unit for large spacecraft, comprising a support frame, a first component and / or a second component, wherein the support frame comprises a first frame providing a first mounting surface, a second frame providing a second mounting surface, a connecting end and a folding structure, wherein the folding structure is connected to the first frame and the second frame, and is used to adjust the spacing between the first frame and the second frame, thereby switching the storage state and the expansion state of the satellite platform unit; the connecting end is arranged on both sides of the first frame and the second frame, and is used to connect with other satellite platform units; the first component is arranged on the first mounting surface; and the second component is arranged on the second mounting surface. The above-mentioned satellite platform unit has a high space utilization rate and can be expanded to hundreds of meters to kilometers, and is suitable for large spacecraft.

Description

Technical Field

[0001] The present invention relates to the field of aerospace vehicles, and in particular to the field of trusses of aircraft. Background Art

[0002] The traditional truss of traditional spacecraft is a foldable structure, which is loaded into the spacecraft and launched together, and unfolded in space at one time to form the main structure of a large spacecraft. Since it needs to be folded in a limited space, the truss cannot be installed with other components and can only be used as a single frame; limited by the structure, volume and weight of the spacecraft, the size of the truss after unfolding is limited, and it is only suitable for spacecraft such as tens of meters or less than 100 meters, and cannot be expanded to form large spacecraft of tens of meters, hundreds of meters or kilometers. Summary of the invention

[0003] It is an object of the present invention to provide a deployable satellite platform unit for use with a large spacecraft.

[0004] To achieve the above-mentioned purpose, the satellite platform unit includes a support frame, a first component and / or a second component. The support frame includes a first frame providing a first mounting surface, a second frame providing a second mounting surface, a connecting end and a folding structure. The folding structure is connected to the first frame and the second frame, and is used to adjust the distance between the first frame and the second frame, thereby switching the storage state and the unfolded state of the satellite platform unit; the connecting end is arranged on both sides of the first frame and the second frame, and is used to connect with other satellite platform units; the first component is arranged on the first mounting surface; the second component is arranged on the second mounting surface.

[0005] In one or more embodiments, the folding structure is configured to enable the first frame and the second frame to generate relative movement along a single dimension.

[0006] In one or more embodiments, the folding structure includes a plurality of folding units, each of the folding units including: a support rod including a first end and a second end; a rotating portion provided on one of the first frame and the second frame; and a receiving groove provided on the other of the first frame and the second frame; wherein the first end is rotatably connected to the first frame or the second frame through the rotating portion, and the second end is slidably provided in the receiving groove.

[0007] In one or more embodiments, the length of the accommodating groove is greater than or equal to the height of the supporting rod.

[0008] In one or more embodiments, the depth of the accommodating groove is smaller than the width of the supporting rod, so that the minimum distance between the first frame and the second frame is not zero.

[0009] In one or more embodiments, a sunken notch is further provided at the end of the accommodating groove, and the sunken notch is used to accommodate the rotating part.

[0010] In one or more embodiments, the first frame and the second frame are further provided with a first connecting hole, the first connecting hole is connected to the sinking groove, and the second end is provided with a second connecting hole for connecting to the first connecting hole by means of a connecting piece to make the support rod, the first frame, and the second frame relatively fixed.

[0011] In one or more embodiments, the connecting end includes an insert and a receiving hole, and both the insert and the receiving hole are provided with a third connecting hole, and the third connecting hole is used to cooperate with the connecting piece.

[0012] In one or more embodiments, one side of the first frame is provided with one of the insert and the receiving hole, and the other side is provided with the other of the insert and the receiving hole; one side of the second frame is provided with one of the insert and the receiving hole, and the other side is provided with the other of the insert and the receiving hole.

[0013] In one or more embodiments, the first frame and the second frame include a surface without protrusions, and the surface of the connecting member after being fixed to the third connecting hole is arranged to be flush with the surface.

[0014] In one or more embodiments, the first component is a solar panel and the second component is an antenna component.

[0015] The above-mentioned expandable satellite platform unit has the following advantages: the switching between the storage state and the unfolded state is achieved through the folding structure, and the unit in the storage state is compressed into a planar structure, so it can be stacked with other satellite platform units for easy storage; since it is not connected to the spacecraft body during launch, and the storage components that store the satellite platform units are detachably connected to the main satellite of the spacecraft, the number of storage units determines the extended length of the platform. The satellite platform can extend to hundreds of meters or even thousands of meters without being restricted by the spacecraft, and is suitable for building large spacecraft; when stacked, the satellite platform units are separated from each other and the first mounting surface and the second mounting surface are not affected, so the platform unit can carry components with other functions, so that the platform space is fully utilized. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0017] Figure 1A It is a separate diagram of the components of the satellite platform unit;

[0018] Figure 1Bis a schematic diagram of an embodiment of a satellite platform unit;

[0019] Figure 2 is a schematic diagram of satellite platform units arranged in a stack;

[0020] Figure 3 is a schematic diagram of a satellite platform unit in the process of deployment;

[0021] Figure 4 It is a schematic diagram when the support rod and the first frame and the second frame are relatively fixed;

[0022] Figure 5A It is a schematic diagram when the support rod is located outside the sinking slot;

[0023] Figure 5B is a schematic diagram of the sinking notch and the first connecting hole;

[0024] Fig. 6A It is a schematic diagram when the support rod is located inside the sinking slot;

[0025] Figure 6B is a schematic diagram of a connecting member and a first connecting hole;

[0026] Figure 7 is a schematic diagram of adjacent satellite platform units in an independent state;

[0027] Figure 8 is a schematic diagram of adjacent satellite platform units in a docked state;

[0028] Fig. 9 is an enlarged view of the insert;

[0029] Fig.10 is an enlarged view of the receiving hole;

[0030] Fig.11 It is a schematic diagram of the spacecraft. DETAILED DESCRIPTION

[0031] The present invention is further described below in conjunction with specific embodiments and drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description herein. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0032] It should be noted that these and other subsequent drawings are only examples and are not drawn to scale, and should not be used to limit the actual scope of protection required by the present invention.

[0033] Single deployable satellite platform unit 1 for large spacecraft Figures 1A to 4 It is understood that it includes a support frame 10, a first component 20 and / or a second component 30. A single deployable satellite platform unit 1 is a single truss independent structure.

[0034] The support frame 10 includes a first frame 11 , a second frame 12 , a folding structure 13 and a connecting end 14 .

[0035] The first frame 11 and the second frame 12 include at least two parallel beams, which are used to respectively define the first mounting surface 110 and the second mounting surface 120. For example, the first frame 11 and the second frame 12 are H-shaped structures or mouth-shaped structures. The structures of the first frame 11 and the second frame 12 can be the same or different.

[0036] The first mounting surface 110 and the second mounting surface 120 are used to load functional components of the satellite, for example, the first component 20 is a solar panel, which is arranged on the first mounting surface 110; the second component 30 is a microwave antenna, which is arranged on the second mounting surface 120. It can be understood by those skilled in the art that the first component 20 and the second component 30 include but are not limited to the above embodiments, for example, other antennas, battery arrays arranged in flat panels, and other load components that are small enough to be integrated inside the frame.

[0037] The connection ends 14 are respectively arranged on both sides of the first frame 11 and the second frame 12, and are used to connect with other satellite platform units, such as Figure 8 and Fig.11 As shown, a plurality of satellite platform units 1, 1' are connected to each other to form the main truss structure of a large spacecraft.

[0038] The folding structure 13 connects the first frame 11 and the second frame 12, and is used to adjust the distance between the first frame 11 and the second frame 12, thereby switching the satellite platform unit between the storage state and the deployment state. When the distance between the first frame 11 and the second frame 12 is the smallest, the satellite platform unit is in the storage state, such as Figure 2 Preferably, the folding structure 13 is used to make the first frame 11 and the second frame 12 move relative to each other along a single dimension, for example, the first frame 11 only moves along Figure 3 The upward and downward directions shown are lifted or lowered without misalignment.

[0039] In some embodiments, the folding structure 13 includes a plurality of folding units 130. Figure 4 In the illustrated embodiment, the folding structure 13 includes four folding units 130 .

[0040] Each folding unit 130 includes a support rod 31, a rotating portion 32 and a receiving groove 33. The rotating portion 32 and the receiving groove 33 are respectively located in one of the first frame 11 and the other of the second frame 12. The first end 318 of the support rod 31 is rotatably connected to the first frame 11 or the second frame 12 through the rotating portion 32, and the second end 319 is slidably disposed in the receiving groove 33. Figure 3 In the illustrated embodiment, the rotating portion 32 includes a connecting lug, which extends from the first frame 11 or the second frame 12 and is axially connected to the support rod 31. In other embodiments, the rotating portion may also be a hinge structure or other rotating structures.

[0041] Preferably, the receiving groove 33 is along Figure 5A The length in the left-right direction is set to be greater than or equal to the length of the support rod 31. Figure 4 The height in the vertical direction is such that when the platform unit is in the storage state, the support rod 31 can be accommodated in the accommodation groove 33 as a whole. Figure 2 As shown, the gap between the first frame 11 and the second frame 12 is made as small as possible to save storage space.

[0042] Continue to refer to Figure 5A-5B As shown, the end of the receiving groove 33 is also provided with a sinking notch 335. When the support rod 31 is entirely received in the receiving groove 33 and the platform unit is in the storage state, the rotating portion 32 is received in the sinking notch 335. When the support rod 31 is rotated to be perpendicular to the first frame 11 or the second frame 12, the second end 319 of the support rod 31 is located above the sinking notch 335. Figure 5A As shown, at this time, the distance between the first frame 11 and the second frame 12 is the largest. The second end 319 can be further pressed down along the direction P to the sinking notch 335, as shown in FIG. Figure 6A-6B In order to fix the relative position of the support rod 31 and the first frame 11 and the second frame 12, so that the satellite platform unit remains in the unfolded state and does not retract, the first frame 11 and the second frame 12 are further provided with a first connecting hole 115, and the first connecting hole 115 is connected to the sinking notch 335. The second end 319 of the support rod 31 is provided with a second connecting hole 317, which is used to connect with the first connecting hole 115 by means of a connecting member U, so that the support rod 31 and the first frame 11 and the second frame 12 are relatively fixed.

[0043] On the basis of the above embodiment, the receiving groove 33 is Figure 5A The depth in the vertical direction is preferably set to be smaller than the depth along the support rod 31. Figure 5A The width in the left and right direction is such that when the support rod 31 is accommodated in the accommodation groove 33 and the platform unit is in the storage state, the minimum spacing between the first frame 11 and the second frame 12 is not 0, and the first frame 11 and the second frame 12 always maintain a gap of 100, such as Figure 2As shown, the gap 100 facilitates the platform unit to return to the deployed state. For example, the lifting of the first frame 11 is provided by a lifting member inserted into the gap 100.

[0044] The folding structure includes but is not limited to the above-mentioned embodiments. For example, in another embodiment, the folding structure includes a plurality of rods located between the first frame 11 and the second frame 12 and pivotally connected to each other, and is automatically unfolded or retracted by an electric structure.

[0045] The folding structure compresses the satellite platform unit into a flat structure for easy storage in a stacked manner. At the same time, the first support surface 110 and the second support surface 120 are not affected during storage or unfolding, so the first support surface 110 and the second support surface 120 can carry the functional components of the satellite at the same time, such as solar panels, microwave antennas, power interfaces and other components installed in the support surface, which can fully utilize the internal space of the platform compared to the traditional satellite structure platform.

[0046] Figures 7 to 10 An embodiment of the satellite platform unit connection end is shown. The connection end 14 includes an insert 141 and a receiving hole 142. The insert 141 and the receiving hole 142 are both provided with a third connection hole 143. The third connection hole 143 is used to cooperate with a connector N such as a rivet to fasten the docked satellite platform units, thereby connecting adjacent satellite platform units 1, 1'. Fastening by the connector can not only simplify the connection method, but also improve the connection reliability and longitudinal stability of the platform unit, so that the connected satellite platform is not easy to return to the folded state and remains relatively fixed. Preferably, the insert 141 and the receiving hole 142 have a slide groove design to reduce the alignment accuracy requirements.

[0047] Since two adjacent satellite platform units need to be docked and matched, the first frame 11 is arranged along Figure 8 One of the inserting member 141 and the receiving hole 142 is disposed on one side in the left-right direction, and the other of the inserting member 141 and the receiving hole 142 is disposed on the other side. The second frame 12 is disposed in the same manner. For example, the inserting member 141 is disposed on the left side of the first frame 11 and the second frame 12, and the receiving hole 142 is disposed on the right side of the first frame 11 and the second frame 12.

[0048] Preferably, in some embodiments, the first frame 11 and the second frame 12 include a surface 116 without protrusions so that the surface 116 is flat, and after the connecting member N is fixed to the third connecting hole 143, the surface is set to be flush with the surface without protrusions, so that the first frame, the second frame and the connecting end form a track Y for the components with slide grooves to move flexibly along the track.

[0049] In some embodiments, Figure 1BAs shown, as a major component of the main structure of a large spacecraft, the satellite platform unit also has a contact-type electrical interface 16, which is used to connect the payload. Since the connection is made during post-assembly in a space environment, there is no need to consider the problem of the interface loosening due to vibration during launch. The interface can be a magnetic suction interface, which is convenient for connection during installation and subsequent replacement and maintenance of the payload. Figure 1B In the embodiment shown, the insert 141 and the receiving hole 142 are provided with an electrical connection structure, and a digital power transmission line is integrated inside the frame. The structure formed by connecting a plurality of frames can transmit digital power, thereby connecting various loads, components, and the main star. For example, the electrical interface 145 adopts a spring design, and after the male and female ends are mechanically connected and locked, the two springs are pressed against each other to form digital power transmission.

[0050] The use process of the satellite platform unit is as follows: the platform unit in the initial state is in a stacked storage state. After being taken out, the support rod 31 is rotated until it is perpendicular to the accommodating groove 33. After the platform unit is fully unfolded, the first frame 11 is pressed down, and the second end 319 of the support rod 31 is pressed into the sinking groove 335. The second connecting hole 317 is aligned with the first connecting hole 115, and the connecting part U is installed to make the first frame 11, the second frame 12 and the folding structure 13 relatively fixed.

[0051] Combined with the introduction of the above-mentioned deployable satellite platform unit, we can also understand a large spacecraft, which refers to a spacecraft with a total length of more than ten meters. Fig.11 As shown, the spacecraft includes a main satellite 5 and a storage component 6, and the storage component 6 is detachably connected to the main satellite 5, for example, the storage component 6 is docked below and / or above the main satellite 5. The storage component 6 is used to accommodate Figure 2 The plurality of satellite platform units 1 shown are stacked and each satellite platform unit 1 is in a stored state.

[0052] This design makes the total length of the truss 7 determined by the number of satellite platform units stored, and is not limited by the size of the launch vehicle envelope or the volume of the spacecraft. When the truss length needs to be extended, the storage component 6 connected to the main satellite 5 can be launched. After docking, the space robot will take out the satellite platform units in the storage state in turn in the storage component 6, and unfold, dock and install them to meet the length requirements of the extended truss. The above-mentioned spacecraft can be used as a large spacecraft that can be expanded to tens of meters, hundreds of meters or even kilometers without being limited by the size of the spacecraft.

[0053] It should be noted that the use of terms such as "first" and "second" to limit components is only to facilitate the distinction between corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of this application.

[0054] At the same time, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0055] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A large spacecraft, characterized in that: The invention comprises a storage component, wherein the storage component is used to accommodate a plurality of satellite platform units in a storage state and stacked, and the satellite platform unit comprises: Support frame, comprising: A first frame provides a first mounting surface; a second frame providing a second mounting surface; A folding structure connected to the first frame and the second frame, used to adjust the distance between the first frame and the second frame, thereby switching the satellite platform unit between a stowed state and an unfolded state; Connecting ends, arranged on both sides of the first frame and the second frame, for connecting with other satellite platform units; A first component is arranged on the first mounting surface; and / or A second component is arranged on the second mounting surface; the folding structure is arranged to enable the first frame and the second frame to move relative to each other along a single dimension; The folding structure comprises a plurality of folding units, each of which comprises: A support rod including a first end and a second end; A rotating part, arranged on one of the first frame and the second frame; A receiving groove, provided on the other of the first frame and the second frame; Wherein, the first end is rotatably connected to the first frame or the second frame through the rotating portion, and the second end is slidably disposed in the accommodating groove.

2. The large spacecraft according to claim 1, characterized in that: The length of the accommodating groove is greater than or equal to the height of the supporting rod.

3. The large spacecraft according to claim 2, characterized in that: The depth of the accommodating groove is smaller than the width of the supporting rod, so that the minimum distance between the first frame and the second frame is not zero.

4. The large spacecraft according to claim 1, characterized in that: A sinking notch is also provided at the end of the accommodating groove, and the sinking notch is used to accommodate the rotating part.

5. The large spacecraft according to claim 4, characterized in that: The first frame and the second frame are further provided with a first connecting hole, and the first connecting hole is communicated with the sinking notch. The second end is provided with a second connecting hole for connecting with the first connecting hole via a connecting member so as to relatively fix the support rod, the first frame and the second frame.

6. The large spacecraft according to claim 1, characterized in that: The connecting end comprises an insert and a receiving hole. Both the insert and the receiving hole are provided with a third connecting hole. The third connecting hole is used to cooperate with the connecting piece.

7. The large spacecraft according to claim 6, characterized in that: One side of the first frame is provided with one of the insert and the receiving hole, and the other side of the first frame is provided with the other of the insert and the receiving hole; One of the inserting member and the receiving hole is disposed on one side of the second frame, and the other of the inserting member and the receiving hole is disposed on the other side of the second frame.

8. The large spacecraft according to claim 6, characterized in that: The first frame and the second frame include surfaces without protrusions, and after the connecting member is fixed to the third connecting hole, the surface of the connecting member is arranged to be flush with the surface.

9. The large spacecraft according to claim 1, characterized in that: The first component is a solar panel, and the second component is an antenna component.

10. The large spacecraft according to claim 1, characterized in that: A plurality of the satellite platform units in the deployed state are connected to each other to form the main truss structure of the large spacecraft.

11. The large spacecraft according to claim 1, characterized in that: The spacecraft further includes a main satellite which is detachably connected to the storage component.

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