A communication satellite platform configuration

Abstract

This invention discloses a communication satellite platform configuration, including a support cylinder, an upper service module plate, a lower service module plate, and a propulsion system. The support cylinder has a receiving cavity, and its length is L1, 3.7m ≤ L1 ≤ 5m. The upper and lower service module plates are fitted onto the support cylinder, and the upper and lower service module plates are sequentially spaced along a first direction to form the service module, where the first direction is the direction of the support cylinder's length extension. The propulsion system includes a first energy supply module located within the receiving cavity and at least two first helium gas chambers located outside the receiving cavity, with the first helium gas chambers located on the upper side of the upper service module plate. Alternatively, the propulsion system includes a second energy supply module located within the receiving cavity and at least two second helium gas chambers and at least two xenon gas chambers located outside the receiving cavity, with the second helium gas chambers and xenon gas chambers located on the upper side of the upper service module plate, arranged along the first direction. By extending the support cylinder, the internal and external spaces of the support cylinder are increased, which helps to improve the space available for the propulsion system.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a communication satellite platform configuration. BACKGROUND

[0002] In the prior art, the satellite launch weight is generally not more than 5300Kg, and the effective payload carrying capacity is 600Kg.

[0003] With the increasing demand of users for satellite use, the effective payload carrying capacity is at least 900Kg, so the propulsion force needs to be improved, and the layout space of the propulsion system needs to be increased.

[0004] However, in the prior art, the propulsion system of the satellite has the problem of insufficient layout space. SUMMARY

[0005] The present application aims to at least solve one of the problems in the prior art. To this end, one object of the present application is to provide a communication satellite platform configuration which can solve the problem of insufficient layout space of the propulsion system.

[0006] The communication satellite platform configuration according to the embodiment of the present application comprises a load cylinder, a service cabin upper layer plate, a service cabin lower layer plate and a propulsion system.

[0007] The load cylinder has a receiving cavity, and the length of the load cylinder is L1, 3.7m≤L1≤5m. The service cabin upper layer plate is sleeved on the load cylinder, and the service cabin lower layer plate is sleeved on the load cylinder. The service cabin lower layer plate and the service cabin upper layer plate are sequentially and spaced apart along a first direction to form a service cabin, and the first direction is the length extension direction of the load cylinder.

[0008] The propulsion system comprises a first energy supply cabin and at least two first helium cabins. The first energy supply cabin is arranged in the receiving cavity, and the first helium cabin is connected to the outer surface of the side wall of the load cylinder, and the first helium cabin is located on the upper side of the service cabin upper layer plate, or

[0009] The propulsion system comprises a second energy supply cabin, at least two second helium cabins and at least two xenon cabins. The second energy supply cabin is arranged in the receiving cavity, and the second helium cabin and the xenon cabin are connected to the outer surface of the side wall of the load cylinder, and the second helium cabin and the xenon cabin are located on the upper side of the service cabin upper layer plate, and the second helium cabin and the xenon cabin are arranged in the first direction.

[0010] According to the embodiment of the present application, the communication satellite platform configuration of the present application can make full use of the inner and outer space of the load cylinder, which helps to increase the layout space of the propulsion system; the elongated load cylinder also increases the layout space on the inner and outer sides of the load cylinder, which helps to arrange each cabin of the propulsion system and increase its storage volume, thereby increasing the satellite propulsion capacity and improving the satellite effective payload capacity.

[0011] According to some embodiments of the present application, the propulsion system comprises a first energy supply cabin and at least two first helium cabins, the at least two first helium cabins are arranged equiangularly relative to the load-carrying cylinder,

[0012] The first helium cabin has an upper end and a lower end, the lower end of the first helium cabin abuts against the upper deck of the service cabin, the outer surface of the sidewall of the load-carrying cylinder is provided with a first connecting part, and the upper end of the first helium cabin is connected to the first connecting part.

[0013] According to some embodiments of the present application, the first connecting part is a first connecting rod, and the upper end of the first helium cabin is connected to the outer surface of the sidewall of the load-carrying cylinder through the first connecting rod.

[0014] According to some embodiments of the present application, the propulsion system comprises a second energy supply cabin, at least two second helium cabins and at least two xenon cabins, the at least two second helium cabins are arranged equiangularly relative to the load-carrying cylinder, the at least two xenon cabins are arranged equiangularly relative to the load-carrying cylinder, and the xenon cabins and the second helium cabins are arranged in sequence along a first direction.

[0015] According to some embodiments of the present application, the second helium cabin and the xenon cabin are arranged in alignment in the first direction.

[0016] According to some embodiments of the present application, the second helium cabin comprises an upper end and a lower end, the xenon cabin comprises an upper end and a lower end, the outer surface of the sidewall of the load-carrying cylinder is sequentially provided with a third connecting part, a supporting part and a second connecting part along the first direction,

[0017] The lower end of the second helium cabin abuts against the supporting part, the upper end of the second helium cabin is connected to the second connecting part, the lower end of the xenon cabin abuts against the upper deck of the service cabin, and the upper end of the xenon cabin is connected to the third connecting part.

[0018] According to some embodiments of the present application, the second connecting part is a second connecting rod, the third connecting part is a third connecting rod, the upper end of the second helium cabin is connected to the outer surface of the sidewall of the load-carrying cylinder through the second connecting rod, and the upper end of the xenon cabin is connected to the outer surface of the sidewall of the load-carrying cylinder through the third connecting rod.

[0019] According to some embodiments of the present application, the first energy supply cabin comprises a first oxygen cabin and a first fuel cabin arranged in sequence along the first direction, or,

[0020] The second energy supply cabin comprises a second oxygen cabin and a second fuel cabin arranged in sequence along the first direction.

[0021] According to some embodiments of the present application, when the propulsion system is provided with the second energy supply cabin, the propulsion system further comprises an electric propulsion part, the electric propulsion part is arranged in the service cabin, the volume of the second oxygen cabin is smaller than the volume of the first oxygen cabin, and the volume of the second fuel cabin is smaller than the volume of the first fuel cabin.

[0022] According to some embodiments of the present application, the inner surface of the side wall of the bearing cylinder is provided with a first oxygen cabin mounting portion for mounting the first oxygen cabin and a first fuel cabin mounting portion for mounting the first fuel cabin, the distance between the first oxygen cabin mounting portion and the service cabin upper deck is L2, and the distance between the first fuel cabin mounting portion and the service cabin upper deck is L3; or,

[0023] The inner surface of the side wall of the bearing cylinder is provided with a second oxygen cabin mounting portion for mounting the second oxygen cabin and a second fuel cabin mounting portion for mounting the second fuel cabin, the distance between the second oxygen cabin mounting portion and the service cabin upper deck is L2, and the distance between the second fuel cabin mounting portion and the service cabin upper deck is L3.

[0024] Wherein, 1.4m≤L2≤1.6m, 3m≤L3≤3.6m.

[0025] Additional aspects and advantages of the present application will be in part apparent and in part pointed out below in the description of the application. BRIEF DESCRIPTION OF DRAWINGS

[0026] The above and / or additional aspects and advantages of the present application will become apparent and be readily appreciated from the description of the embodiments, given below with reference to the following drawings, wherein:

[0027] Figure 1 is a structural schematic diagram of a communication satellite platform configuration according to an embodiment of the present application;

[0028] Figure 2 is a first energy supply cabin arrangement schematic diagram according to an embodiment of the present application;

[0029] Figure 3 is another communication satellite platform configuration structural schematic diagram according to an embodiment of the present application Figure 1 ;

[0030] Figure 4 is another communication satellite platform configuration structural schematic diagram according to an embodiment of the present application Figure 2 ;

[0031] Figure 5 is a second energy supply cabin arrangement schematic diagram according to an embodiment of the present application;

[0032] REFERENCE NUMERALS:

[0033] Bearing cylinder 10, first oxygen cabin mounting portion 11, first fuel cabin mounting portion 12, second oxygen cabin mounting portion 13, second fuel cabin mounting portion 14;

[0034] The service cabin upper layer plate 21, the service cabin lower layer plate 22, the first energy supply cabin 31, the first oxygen cabin 311, the first fuel cabin 312, the second energy supply cabin 32, the second oxygen cabin 321, the second fuel cabin 322, the first helium cabin 41, the second helium cabin 42, and the xenon cabin 50.

[0035] The first connecting part 61, the second connecting part 62, the third connecting part 63, and the supporting part 64.

[0036] The south partition plate 71, the west partition plate 72, the east partition plate 73, and the electric propulsion mounting plate 80. DETAILED DESCRIPTION

[0037] Embodiments of the present application are described in detail below with reference to the attached drawings, wherein like or similar elements are denoted by the same or similar reference numerals throughout the drawings. The embodiments described below are exemplary only, and are not intended to limit the present application.

[0038] The following disclosure provides many different embodiments, or examples, for implementing different structures of the present application. For the purpose of simplicity, the elements and acts of the various examples are described in a particular, correlated sequence in the following description. It should be noted, however, that this description is not an limitation on the scope or function of the present application. Indeed, many different sequences can be used to implement this application, and other steps can be used. It is therefore intended that the present application embrace all such alternatives. Further, it should be noted that the present application can be embodied in one or more of the different examples described below, and combinations thereof.

[0039] A communication satellite platform configuration according to an embodiment of the present application is described below with reference to the drawings.

[0040] As shown in the drawings, the communication satellite platform configuration according to an embodiment of the present application includes a load-bearing cylinder 10, a service cabin upper layer plate 21, a service cabin lower layer plate 22, and a propulsion system. Figures 1-5

[0041] The load-bearing cylinder 10 has a receiving cavity, and the length of the load-bearing cylinder 10 is L1, 3.7m≤L1≤5m. The service cabin upper layer plate 21 is sleeved on the load-bearing cylinder 10, and the service cabin lower layer plate 22 is sleeved on the load-bearing cylinder 10. The service cabin lower layer plate 22 and the service cabin upper layer plate 21 are sequentially and spaced apart along a first direction to form a service cabin, and the first direction is the length extension direction of the load-bearing cylinder 10.

[0042] The propulsion system includes a first energy supply cabin 31 and at least two first helium cabins 41. The first energy supply cabin 31 is arranged in the receiving cavity, and the first helium cabin 41 is connected to the outer surface of the side wall of the load-bearing cylinder 10 and located on the upper side of the service cabin upper layer plate 21. Alternatively,​

[0043] The propulsion system comprises a second energy supply cabin 32, at least two second helium cabins 42 and at least two xenon cabins 50. The second energy supply cabin 32 is arranged in the accommodating cavity. The second helium cabins 42 and the xenon cabins 50 are connected to the outer surface of the side wall of the bearing cylinder 10 and are located above the service cabin upper deck 21. The second helium cabins 42 and the xenon cabins 50 are arranged in the first direction.

[0044] It should be noted that the extension direction of the bearing cylinder 10 is the C1 direction in FIG. 4. Figure 1 、 3

[0045] In actual application, the satellite launch weight is generally not more than 5300 Kg, and the payload carrying capacity is 600 Kg. Therefore, the length of the bearing cylinder 10 is less than 3.7 m, which can provide sufficient propulsion system layout space and thus sufficient power to meet the above requirements.

[0046] With the increasing demand of users for satellite use, the payload carrying capacity is at least 900 Kg.

[0047] Therefore, the length of the bearing cylinder 10 is extended, and the length of the bearing cylinder 10 can be L1, 3.7 m≤L1≤5 m, thereby increasing the propulsion system layout space and thus improving the payload carrying capacity.

[0048] Specifically, when the propulsion system adopts the first mode: the propulsion system comprises a first energy supply cabin 31 and at least two first helium cabins 41. The first energy supply cabin 31 is arranged in the accommodating cavity. The first helium cabins 41 are connected to the outer surface of the side wall of the bearing cylinder 10 and are located above the service cabin upper deck 21.

[0049] It should be noted that the space occupied by the first energy supply cabin 31 is greater than the space occupied by the first helium cabin 41. The first energy supply cabin 31 is arranged in the bearing cylinder 10, and the first helium cabin 41 is arranged outside the bearing cylinder 10. In this way, the inner and outer spaces of the bearing cylinder 10 can be fully utilized, which helps to improve the propulsion system layout space.

[0050] In addition, the extended bearing cylinder 10 increases the accommodating cavity of the bearing cylinder 10, and the first energy supply cabin 31 can increase its storage volume, which helps to increase the satellite propulsion capacity and thus improve the satellite payload capacity. Similarly, the extended bearing cylinder 10 also increases the layout space outside the bearing cylinder 10, and the first helium cabin 41 can increase its storage volume, which helps to increase the satellite propulsion capacity and thus improve the satellite payload capacity.

[0051] ​When the propulsion system adopts the second mode, the propulsion system comprises a second energy supply cabin 32, at least two second helium cabins 42 and at least two xenon cabins 50, the second energy supply cabin 32 is arranged in the accommodating cavity, the second helium cabin 42 and the xenon cabin 50 are connected to the outer surface of the side wall of the bearing cylinder 10 and are located on the upper side of the service cabin upper deck 21, and the second helium cabin 42 and the xenon cabin 50 are arranged in the first direction.

[0052] It should be noted that the space occupied by the second energy supply cabin 32 is greater than the space occupied by the second helium cabin 42 and the xenon cabin 50, the second energy supply cabin 32 is arranged in the bearing cylinder 10, and the second helium cabin 42 is arranged outside the bearing cylinder 10, so that the space inside and outside the bearing cylinder 10 can be fully utilized, and the arrangement space of the propulsion system is improved.

[0053] In addition, the elongated bearing cylinder 10 increases the accommodating cavity, the second energy supply cabin 32 can increase the storage capacity, the satellite propulsion capacity is improved, and the satellite payload capacity is improved. Similarly, the elongated bearing cylinder 10 also increases the arrangement space outside the bearing cylinder 10, the second helium cabin 42 and the xenon cabin 50 can increase the storage capacity, the satellite propulsion capacity is improved, and the satellite payload capacity is improved. The second helium cabin 42 and the xenon cabin 50 can be arranged in the first direction in sequence, or the xenon cabin 50 and the second helium cabin 42 can be arranged in the first direction in sequence, so that the arrangement space outside the bearing cylinder 10 is further fully utilized, and the arrangement space of the propulsion system is improved.

[0054] In summary, the communication satellite platform structure of the embodiment of the application can fully utilize the space inside and outside the bearing cylinder 10, and improve the arrangement space of the propulsion system. The elongated bearing cylinder 10 also increases the arrangement space inside and outside the bearing cylinder 10, and helps to arrange the various cabins of the propulsion system to increase the storage capacity, thereby increasing the satellite propulsion capacity and improving the satellite payload capacity.

[0055] The embodiment of the application will be described in detail below:

[0056] In some embodiments of the application, the propulsion system comprises a first energy supply cabin 31 and at least two first helium cabins 41, the at least two first helium cabins 41 are arranged at equal angles about the bearing cylinder 10, the first helium cabin 41 has an upper end and a lower end, the lower end of the first helium cabin 41 abuts against the service cabin upper deck 21, the outer surface of the side wall of the bearing cylinder 10 is provided with a first connecting part 61, and the upper end of the first helium cabin 41 is connected to the first connecting part 61.

[0057] It should be noted that, as Figure 1 and Figure 2As shown, the at least two first helium cabins 41 are arranged at equal angles relative to the bearing cylinder 10, that is, the two first helium cabins 41 are symmetrically arranged relative to the bearing cylinder 10, or a plurality of first helium cabins 41 are arranged at equal angles relative to the bearing cylinder 10. In this way, the force effect of the bearing cylinder 10 is reasonable, which helps to improve the stability of the bearing cylinder 10.

[0058] The lower end of the first helium cabin 41 abuts against the upper layer plate 21 of the service cabin, which can ensure the support strength of the first helium cabin 41. The outer surface of the side wall of the bearing cylinder 10 is provided with a first connecting portion 61, which can be integrally formed with the outer surface of the side wall of the bearing cylinder 10 or can be separately arranged.

[0059] Further, the first connecting portion 61 is a first connecting rod, and the upper end of the first helium cabin 41 is connected to the outer surface of the side wall of the bearing cylinder 10 through the first connecting rod. In this way, the overall weight of the first connecting portion 61 can be reduced.

[0060] Specifically, as shown in the drawings, Figure 1 one end of the two first connecting rods is arranged in a preset larger manner, and the upper end of the first helium cabin 41 is hung on the end of the two first connecting rods; the other end of the two first connecting rods is respectively connected to the outer surface of the side wall of the bearing cylinder 10.

[0061] In some embodiments of the present application, the propulsion system comprises a second energy supply cabin 32, at least two second helium cabins 42 and at least two xenon cabins 50, the at least two second helium cabins 42 are arranged at equal angles relative to the bearing cylinder 10, and the at least two xenon cabins 50 are arranged at equal angles relative to the bearing cylinder 10, and the xenon cabins 50 and the second helium cabins 42 are sequentially arranged in the first direction.

[0062] It should be noted that, as shown in the drawings, Figure 3 and Figure 4 the at least two second helium cabins 42 and the xenon cabins 50 are arranged at equal angles relative to the bearing cylinder 10, that is, the two second helium cabins 42 are symmetrically arranged relative to the bearing cylinder 10, and the two xenon cabins 50 are symmetrically arranged relative to the bearing cylinder 10; or a plurality of second helium cabins 42 are arranged at equal angles relative to the bearing cylinder 10, and a plurality of xenon cabins 50 are arranged at equal angles relative to the bearing cylinder 10. In this way, the force effect of the elongated bearing cylinder 10 is reasonable, which helps to improve the stability of the bearing cylinder 10.

[0063] The second helium cabin 42 stores helium, and the xenon cabin 50 stores xenon, and the density of xenon is greater than that of helium. In the first direction, the xenon cabin 50 is located on the lower side of the second helium cabin 42, which can reduce the overall gravity center of the satellite, and help to improve the stability of the satellite. In addition, it can also suppress the response (gravitational acceleration) of the end of the bearing cylinder 10 close to the service cabin, thereby improving the force effect on the bearing cylinder 10 and improving the stability of the bearing cylinder 10.

[0064] Furthermore, the second helium chamber 42 is aligned with the xenon chamber 50 in the first direction. This further utilizes the space outside the load-bearing cylinder 10, which helps to increase the space available for the propulsion system.

[0065] In some embodiments of the present invention, the second helium chamber 42 includes an upper end and a lower end, the xenon chamber 50 includes an upper end and a lower end, and the outer surface of the side wall of the load-bearing cylinder 10 is provided with a third connecting part 63, a support part 64 and a second connecting part 62 in sequence along the first direction.

[0066] The lower end of the xenon chamber 50 abuts against the upper deck 21 of the service compartment, and the upper end of the xenon chamber 50 is connected to the third connecting part 63; the lower end of the second helium chamber 42 abuts against the support part 64, and the upper end of the second helium chamber 42 is connected to the second connecting part 62.

[0067] It should be noted that the second and third connecting parts and the support part 64 can be integrally formed with the outer surface of the side wall of the load-bearing cylinder 10, or they can be set separately. The lower end of the xenon chamber 50 abuts against the upper plate 21 of the service compartment, which can ensure the support strength of the xenon chamber 50.

[0068] Furthermore, the second connecting part 62 is a second connecting rod, the third connecting part 63 is a third connecting rod, the upper end of the second helium chamber 42 is connected to the outer surface of the side wall of the support cylinder 10 through the second connecting rod, and the upper end of the xenon chamber 50 is connected to the outer surface of the side wall of the support cylinder 10 through the third connecting rod.

[0069] Specifically, such as Figure 3 and Figure 4 As shown, one end of each of the two second connecting rods is pre-arranged at a larger size, and the upper end of the second helium chamber 42 is hung on this end of the two second connecting rods; the other ends of the two second connecting rods are respectively connected to the outer surface of the side wall of the support cylinder 10. A support portion 64 is formed by protruding from the outer surface of the side wall of the support cylinder 10. The support portion 64 is plate-shaped, and the lower end of the second helium chamber 42 abuts against the support portion 64.

[0070] One end of each of the two third connecting rods is pre-arranged at a larger size, and the upper end of the xenon chamber 50 is attached to this end of the two third connecting rods; the other ends of the two third connecting rods are respectively connected to the outer surface of the side wall of the load-bearing cylinder 10. The lower end of the xenon chamber 50 abuts against the upper deck plate 21 of the service compartment.

[0071] The above configuration can reduce the overall weight of the second connecting part 62 and the third connecting part 63.

[0072] In some embodiments of the present invention, the first energy supply compartment 31 includes a first oxygen compartment 311 and a first fuel compartment 312 arranged sequentially along a first direction, or the second energy supply compartment 32 includes a second oxygen compartment 321 and a second fuel compartment 322 arranged sequentially along a first direction.

[0073] It should be noted that the oxygen density in the oxygen tank is greater than the density of the storage medium in the fuel tank. The oxygen tank and the fuel tank are arranged in sequence along the first direction, which can reduce the overall center of gravity of the satellite, help improve the stability of the satellite. In addition, it can also inhibit the response (gravitational acceleration) of the load-bearing cylinder 10 near the end of the service tank, thereby improving the force acting effect on the load-bearing cylinder 10 and improving the stability of the load-bearing cylinder 10.

[0074] In a specific embodiment, as shown in Figure 2 , when the propulsion system is provided with the first energy supply tank 31, the inner surface of the side wall of the load-bearing cylinder 10 is provided with a first oxygen tank mounting portion 11 for mounting the first oxygen tank 311 and a first fuel tank mounting portion 12 for mounting the first fuel tank 312, the distance between the first oxygen tank mounting portion 11 and the service tank upper deck 21 is L2, and the distance between the first fuel tank mounting portion 12 and the service tank upper deck 21 is L3. Wherein, 1.4m≤L2≤1.6m, 3m≤L3≤3.6m.

[0075] Preferably, L2=1.5m, L3=3.3m.

[0076] In another specific embodiment, as shown in Figure 5 , when the propulsion system is provided with the second energy supply tank 32, the inner surface of the side wall of the load-bearing cylinder 10 is provided with a second oxygen tank mounting portion 13 for mounting the second oxygen tank 321 and a second fuel tank mounting portion 14 for mounting the second fuel tank 322, the distance between the second oxygen tank mounting portion 13 and the service tank upper deck 21 is L2, and the distance between the second fuel tank mounting portion 14 and the service tank upper deck 21 is L3. Wherein, 1.4m≤L2≤1.6m, 3m≤L3≤3.6m.

[0077] Preferably, L2=1.5m, L3=3.3m.

[0078] It should be noted that when the propulsion system is provided with the second energy supply tank 32, the propulsion system further includes an electric propulsion device, and the electric propulsion device is arranged in the service tank. The volume of the second oxygen tank 321 is smaller than that of the first oxygen tank 311, and the volume of the second fuel tank 322 is smaller than that of the first fuel tank 312.

[0079] As shown in Figure 3 and Figure 4 , the service tank is provided with an east partition plate 73, a west partition plate 72, a south partition plate 71 and a north partition plate (not shown), and the east, west, south and north partition plates are arranged at equal angles about the load-bearing cylinder 10. An electric propulsion mounting plate 80 is arranged on the south partition plate 71 and the north partition plate respectively, and the electric propulsion mounting plate 80 is used to mount the electric propulsion device. The electric propulsion device provides a part of the energy that can be replaced, so the volume of the second oxygen tank 321 is smaller than that of the first oxygen tank 311, and the volume of the second fuel tank 322 is smaller than that of the first fuel tank 312.

[0080] In some embodiments of the application, the service pod is further provided with a service pod south battery panel, a service pod north battery panel, a service pod south instrument panel, and a service pod north instrument panel.

[0081] In the description of the present application, it needs to be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, which are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0082] In the description of the present application, "first feature" and "second feature" can include one or more of the features.

[0083] In the description of the present application, "a plurality of" means two or more.

[0084] In the description of the present application, "above" or "below" the first feature of the second feature can include that the first and second features are in direct contact, or can include that the first and second features are not in direct contact but are in contact through another feature between them.

[0085] In the description of the present application, "above", "over" and "on" the first feature of the second feature includes that the first feature is directly above and obliquely above the second feature, or only means that the first feature is higher than the second feature in horizontal height.

[0086] In the description of the present application, the description with reference to the terms "one embodiment", "some embodiments", "exemplary embodiment", "example", "specific example", or "some examples" and the like means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the present specification, the exemplary description of the above terms does not necessarily mean the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0087] Although embodiments of the present application have been shown and described, those skilled in the art can understand that various changes, modifications, replacements and variations can be made to these embodiments without departing from the principles and spirit of the present application, and the scope of the present application is defined by the claims and their equivalents.

Claims

1. A communications satellite, characterized by, The communication satellite comprises: a force-bearing cylinder (10) having a receiving cavity, the force-bearing cylinder (10) having a length L1, 3.7m≤L1≤5m; a service-cabin upper deck (21) sleeved on the force-bearing cylinder (10); a service-cabin lower deck (22) sleeved on the force-bearing cylinder (10), the service-cabin upper deck (21) and the service-cabin lower deck (22) being sequentially and spaced apart along a first direction to form a service cabin, the first direction being a length extension direction of the force-bearing cylinder (10); a propulsion system comprising a second energy supply cabin (32), at least two second helium cabins (42) and at least two xenon cabins (50), the second energy supply cabin (32) being arranged in the receiving cavity, the second helium cabins (42) and the xenon cabins (50) being connected to an outer surface of a side wall of the force-bearing cylinder (10), and the second helium cabins (42) and the xenon cabins (50) being located on an upper side of the service-cabin upper deck (21), the second helium cabins (42) and the xenon cabins (50) being arranged in the first direction; the at least two second helium cabins (42) are arranged at equal angles about the force-bearing cylinder (10), the at least two xenon cabins (50) are arranged at equal angles about the force-bearing cylinder (10), and the xenon cabins (50) and the second helium cabins (42) are sequentially arranged along the first direction; the second helium cabins (42) and the xenon cabins (50) are arranged in alignment in the first direction; the xenon cabins (50) are located on a lower side of the second helium cabins (42) in the first direction.

2. The communication satellite of claim 1, wherein, the second helium cabins (42) comprise upper ends and lower ends, the xenon cabins (50) comprise upper ends and lower ends, and an outer surface of a side wall of the force-bearing cylinder (10) sequentially has a third connecting portion (63), a supporting portion (64) and a second connecting portion (62) along the first direction, lower ends of the second helium cabins (42) abut against the supporting portion (64), upper ends of the second helium cabins (42) are connected to the second connecting portion (62), lower ends of the xenon cabins (50) abut against the service-cabin upper deck (21), and upper ends of the xenon cabins (50) are connected to the third connecting portion (63).

3. The communication satellite of claim 2, wherein, the second connecting portion (62) is a second connecting rod, the third connecting portion (63) is a third connecting rod, upper ends of the second helium cabins (42) are connected to the outer surface of the side wall of the force-bearing cylinder (10) through the second connecting rod, and upper ends of the xenon cabins (50) are connected to the outer surface of the side wall of the force-bearing cylinder (10) through the third connecting rod.

4. The communication satellite of claim 1, wherein, the second energy supply cabin (32) comprises a second oxygen cabin (321) and a second fuel cabin (322) sequentially arranged along the first direction.

5. The communication satellite of claim 1, wherein, the propulsion system further comprises an electric propulsion device, and the electric propulsion device is arranged in the service cabin.

6. The communication satellite according to claim 4, wherein The inner surface of the side wall of the force bearing cylinder (10) is provided with a second oxygen cabin mounting part (13) for mounting the second oxygen cabin (321) and a second fuel cabin mounting part (14) for mounting the second fuel cabin (322), the distance between the second oxygen cabin mounting part (13) and the service cabin upper deck (21) is L2, and the distance between the second fuel cabin mounting part (14) and the service cabin upper deck (21) is L3. Wherein, 1.4m≤L2≤1.6m, 3m≤L3≤3.6m.

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