One-rocket three-satellite combination structure of medium and high orbit communication satellites

Abstract

The invention belongs to the technical field of aerospace, and discloses a medium and high orbit communication satellite one-rocket three-satellite combination structure which comprises a satellite A, a satellite B and a satellite C. The satellite A comprises a first cabin and a center bearing cylinder, the center bearing cylinder is sleeved with the first cabin, the center bearing cylinder is used for being connected with a carrier, and the satellite B and the satellite C are not connected with the carrier. The satellite B and the satellite C are respectively connected with the top surface of the first cabin body through a separating device, and a separating spring is arranged between the satellite B and the satellite C; the position relation of the satellite B and the satellite C meets the condition that the satellite B rotates by 180 degrees along the center line in the width direction of the first cabin body to form the position of the satellite C. The satellite A is connected with the carrier, the satellite B and the satellite C are not connected with the carrier, and the satellite B and the satellite C do not need to be loaded with large-mass fuel, so that the sizes of the satellite B and the satellite C can be reduced, the outer envelope size of the whole satellite is within the envelope size range of the carrier fairing, the carrier envelope requirement is met, and therefore the requirements for three-satellite one-rocket launching can be met, the launching efficiency is improved, and the multiple launching cost is saved.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aerospace technology, and particularly relates to a middle-high orbit communication satellite one-launcher three-satellite combination configuration. BACKGROUND

[0002] With the development of aerospace technology, multi-satellite rapid deployment to the target orbit is an important technical direction in the current aerospace field, especially with the development of satellite constellation demand, efficient and low-cost multi-satellite launch technology has become the key. At present, middle-high orbit communication satellites are mostly launched by one-launcher one-satellite due to the large amount of fuel carried, large overall satellite mass, and launch capacity constraints, etc. The single launch cost is high, and the constellation deployment efficiency is low. Therefore, under the condition of meeting the launch capacity, the middle-high orbit communication satellite one-launcher multi-satellite launch configuration design can solve the high cost of multiple launches and achieve the purpose of rapid deployment.

[0003] For low-orbit satellite constellations, due to the small satellite mass, one-launcher multi-satellite launch and rapid deployment to the low orbit can be achieved under the current launch capacity. Patent document CN117382910A discloses a satellite batch launch system based on a stacking method, and patent document CN222080904U discloses a low-orbit satellite stacking architecture. The above patents all face the flat-plate stacked satellite configuration invented for low-orbit satellite constellations, which can meet the one-launcher multi-satellite launch. The disadvantage is that after the satellite and the launcher are separated and deployed to the low orbit, the satellite cannot climb to the middle-high orbit due to the propulsion system and fuel constraints.

[0004] For middle-high orbit communication satellites, patent document CN111994307A discloses a main-sub-satellite double-satellite system suspension type sub-satellite connection structure plate. The sub-satellite is hung on the side plate of the main satellite. After the main-sub-satellite enters the target orbit, the sub-satellite is separated from the main satellite to establish a main-sub-satellite double-satellite system. This configuration design is based on a double-satellite configuration design. The disadvantage is that the sub-satellite cannot meet the requirements of the launch envelope once the mass is large, and only one sub-satellite is hung.

[0005] In summary, the existing low-orbit satellites cannot climb to the middle-high orbit by themselves, and the middle-high orbit satellites mostly use one-launcher one-satellite launch, which has high single launch cost and low constellation deployment efficiency. SUMMARY

[0006] In view of the above problems, the present application provides a middle-high orbit communication satellite one-launcher three-satellite combination configuration, which comprises A star, B star and C star. The A star comprises a first cabin body and a central load-bearing cylinder. The first cabin body is sleeved on the outside of the central load-bearing cylinder. The central load-bearing cylinder is used for connection with the launch. The B star and the C star are arranged along the length direction of the top surface of the first cabin body and are not connected with the launch. The B star and the C star are connected with the top surface of the first cabin body through a separation device respectively. A separation spring is arranged between the B star and the C star. The positional relationship of the B star and the C star satisfies: the B star is rotated by 180° along the center line in the first cabin body width direction to the position of the C star.

[0007] Further, the B star is connected with the top surface of the first cabin body through a first set of separation devices, the first set of separation devices comprising a plurality of separation devices arranged along the bottom surface of the B star, and the C star is connected with the top surface of the first cabin body through a second set of separation devices, the second set of separation devices comprising a plurality of separation devices arranged along the bottom surface of the C star.

[0008] Further, the plurality of separation springs are uniformly distributed along the connecting surface of the B star and the C star.

[0009] Further, the first cabin body comprises a first bottom plate, a first top plate, a first side plate, a second side plate, a third side plate, a fourth side plate, a fifth side plate, a sixth side plate, a seventh side plate and an eighth side plate. The first side plate, the second side plate, the third side plate, the fourth side plate, the fifth side plate, the sixth side plate, the seventh side plate and the eighth side plate are sequentially connected to form a first cylinder with an octagonal cross section, the first bottom plate is arranged at the bottom of the first cylinder, and the first top plate is arranged at the top of the first cylinder.

[0010] Further, the A star further comprises a first solar array and a first antenna unit, the first side plate and the fifth side plate are oppositely arranged and parallel to each other, one first solar array is arranged on each of the first side plate and the fifth side plate, and the first antenna unit is arranged on the first side plate and located below the first solar array.

[0011] Further, the central load-bearing cylinder comprises a straight cylinder portion and a tapered cylinder portion. The top of the straight cylinder portion is connected with the first top plate, the bottom of the straight cylinder portion is connected with the top of the tapered cylinder portion, the bottom of the tapered cylinder portion penetrates the first bottom plate, and the diameter of the tapered cylinder portion gradually increases from the top to the bottom.

[0012] Further, the first cabin body further comprises a plurality of fuel tanks, the plurality of fuel tanks are fixedly arranged in a cavity between the first cylinder and the central load-bearing cylinder, and are arranged in a circumferential direction of the central load-bearing cylinder.

[0013] Further, the B star and the C star each comprise a second cabin body, two second solar arrays and a second antenna unit, the second cabin body comprises a second bottom plate, a second top plate, a first cabin plate, a second cabin plate, a third cabin plate and a fourth cabin plate. The first cabin plate, the second cabin plate, the third cabin plate and the fourth cabin plate are sequentially connected to form a second cylinder with a quadrangular cross section, the second bottom plate is arranged at the bottom of the second cylinder, the second top plate is arranged at the top of the second cylinder, and the second bottom plate is connected with the top surface of the first cabin body through a separation device. A second solar array is arranged on the second cabin plate, and another second solar array is connected to the fourth cabin plate through a connecting frame, the second solar array on the fourth cabin plate is pressed on the first cabin plate in the folded state, and is located on one side of the fourth cabin plate and is symmetrical to the unfolded second solar array on the second cabin plate in the unfolded state; the second antenna unit is arranged on the third cabin plate.

[0014] Further, the second cabin body is further provided with a second partition plate, a third partition plate, a second storage tank plate and a storage tank support plate; The second partition plate is provided with two second partition plates, and the two second partition plates are arranged at intervals, the top of the second partition plate is connected with the second top plate, the bottom of the second partition plate is connected with the second bottom plate, and the two second partition plates are parallel to the first cabin plate and the third cabin plate. The two ends of the second storage tank plate are connected with a second partition plate respectively, and the second storage tank plate has a gap between the second storage tank plate and the second bottom plate, the bottom of the storage tank support plate is connected with the second bottom plate, the top of the storage tank support plate is connected with the bottom of the second storage tank plate, and the second storage tank plate is provided with a second through hole; The third partition plate is arranged between the two second partition plates and above the second storage tank plate, the two sides of the third partition plate are connected with the two second partition plates respectively, the top of the third partition plate is connected with the middle part of the second top plate, and the bottom of the second partition plate is connected with the middle part of the second storage tank plate.

[0015] Further, when the B star and the C star are combined with the A star, the positional relationship satisfies that the fourth cabin plate of the B star is opposite to the fourth cabin plate of the C star, the first cabin plate of the B star and the third cabin plate of the C star are located on the same side of the A star, the third cabin plate of the B star and the first cabin plate of the C star are located on the same side of the A star, and the second cabin plate of the B star is opposite to and parallel to the second cabin plate of the C star; the second solar array of the B star is located above one first solar array of the A star, and the second solar array of the C star is located above the other first solar array of the A star.

[0016] The beneficial effects of the present application are as follows: 1. In the three-star combination of the present application, the A star is connected with the carrier, and the B star and the C star are not connected with the carrier, so that the B star and the C star do not need to carry heavy fuel, the size of the B star and the C star can be smaller, so that the overall star envelope size is within the carrier fairing envelope size range, meeting the carrier envelope requirement, so that three-star one-rocket launch can be realized, the launch efficiency is improved, and multiple launch costs are saved.

[0017] 2. The A star of the present application is connected with the carrier through a central load-bearing cylinder, the central load-bearing cylinder has strong load-bearing capacity, and multiple fuel storage tanks are distributed around the central load-bearing cylinder, so that the influence of fuel consumption on the displacement deviation of the overall star mass center is small, and the overall star attitude and orbit control system is controllable.

[0018] 3. The second solar array of the B star and the C star of the application is asymmetric in the retracted state and symmetrically distributed in the deployed state, which can meet the envelope constraints of the launch state and the symmetry requirements of the solar array on both sides in the on-orbit flight state.

[0019] Other features and advantages of the present application will be set forth in the description that follows, and in part will be apparent from the description, or can be learned by practice of the present application. The purposes and other advantages of the present application will be realized and attained by the structure particularly pointed out in the description and the appended drawings. BRIEF DESCRIPTION OF DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without creative labor.

[0021] Figure 1 A structural schematic diagram of a three-star combination configuration according to an embodiment of the present application is shown; Figure 2 An internal structural schematic diagram of the A star according to an embodiment of the present application is shown; Figure 3 A bottom view of the A star according to an embodiment of the present application is shown; Figure 4 A structural schematic diagram of the B star according to an embodiment of the present application is shown; Figure 5 A second solar array installation schematic diagram of the B star according to an embodiment of the present application is shown; Figure 6 An internal structural schematic diagram of the B star according to an embodiment of the present application is shown; Figure 7 An initial orbit state schematic diagram of the three-star combination according to an embodiment of the present application is shown; Figure 8 A three-star state schematic diagram after separation of the three-star combination according to an embodiment of the present application is shown; Figure 9 A second solar array deployed state schematic diagram after separation of the B / C star according to an embodiment of the present application is shown.

[0022] In the figure: 1, A star; 2, B star; 3, C star; 11, first cabin body; 12, central force cylinder; 13, first solar array; 14, first antenna unit; 4, separation device; 5, separation spring; 1101, first bottom plate; 1102, first top plate; 1103, first side plate; 1104, fifth side plate; 1105, fuel tank; 1106, first tank plate; 1107, first partition plate; 1108, layer plate; 21, second cabin body; 22, second solar array; 23, second antenna unit; 24, connecting frame; 2101, second bottom plate; 2102, second top plate; 2103, first cabin plate; 2104, second cabin plate; 2105, third cabin plate; 2106, second partition plate; 2107, third partition plate; 2108, second tank plate; 2109, tank support plate. DETAILED DESCRIPTION

[0023] To make the objects, technical solutions and advantages of the embodiments of the present application clearer, the following will clearly and completely explain the technical solutions in the embodiments of the present application with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are some but not all of the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work belong to the scope of protection of the present application.

[0024] It should be noted that the terms "first", "second", and the like in the present application are used to distinguish similar objects, and do not necessarily have to describe a specific order or sequence. It should be understood that the data thus used can be interchanged under appropriate circumstances, so that the embodiments of the present application described herein. In the present application, the terms "up", "down", "left", "right", "front", "back", "top", "bottom", "in", "out", "middle", "vertical", "horizontal", "lateral", "longitudinal", and the like indicate the orientation or positional relationship shown in the drawings.

[0025] The embodiments of the present application provide a medium-high orbit communication satellite one rocket three star combination configuration, which can meet the deployment requirements of medium-high orbits, can be launched by one rocket three stars, improve the launch efficiency, and save the cost of multiple launches.

[0026] As shown in Figure 1 A medium-high orbit communication satellite one rocket three star combination configuration, comprising A star 1, B star 2 and C star 3, wherein A star 1 is a large satellite, and B star 2 and C star 3 are relatively small.

[0027] As shown in Figure 1 and Figure 2As shown, the A star 1 includes a first cabin body 11 and a central bearing cylinder 12, the first cabin body 11 is sleeved outside the central bearing cylinder 12, the central bearing cylinder 12 is used for being connected with a carrier, for example, the central bearing cylinder 12 is connected with the carrier through a bag belt, and the first cabin body 11 is symmetrically provided with a first solar array 13 on two sides.

[0028] The B star 2 and the C star 3 are arranged along the length direction of the top surface of the first cabin body 11 and are not connected with the carrier, the cross-sectional area of the B star 2 and the C star 3 is not greater than the area of the top surface of the first cabin body 11, for example, the B star 2 and the C star 3 are arranged in a 180° layout, the B star 2 and the C star 3 are respectively connected with the top surface of the first cabin body 11 through a separation device 4, and a separation spring 5 is arranged between the B star 2 and the C star 3 to prevent the B star 2 and the C star 3 from colliding due to a small safety distance after being separated from the A star 1.

[0029] As shown in the figure, Figure 1 The B star 2 and the C star 3 are the same in structure, wherein the positional relationship of the B star 2 and the C star 3 satisfies that the B star 2 is rotated by 180° along the center line in the width direction of the first cabin body 11 to be in the position of the C star 3.

[0030] Due to the limitation of the carrying capacity, strict weight constraints are put forward for the three stars, if the three stars are separately connected with the carrier and enter the target orbit, the B star 2 and the C star 3 need to be loaded with more fuel, the configuration size of the B star 2 and the C star 3 becomes larger, which exceeds the limitation of the carrier fairing envelope, and the mass of the whole star also exceeds the carrying capacity, in the three-star combination body of the embodiment of the present application, the A star 1 is connected with the carrier, and the B star 2 and the C star 3 are not connected with the carrier, the B star 2 and the C star 3 do not need to be loaded with large mass fuel, so that the size of the B star 2 and the C star 3 can be smaller, thereby the whole star envelope size is within the carrier fairing envelope size range, which meets the carrier envelope requirement.

[0031] As shown in the figure, Figure 1 and Figure 2 For example, the B star 2 is connected with the top surface of the first cabin body 11 through a first group of separation devices 4, the first group of separation devices 4 includes a plurality of separation devices 4 arranged along the bottom surface of the B star 2, for example, the first group of separation devices 4 includes four separation devices 4 connected at four corner positions of the bottom surface of the B star 2 respectively.

[0032] For example, the C star 3 is connected with the top surface of the first cabin body 11 through a second group of separation devices 4, the second group of separation devices 4 includes a plurality of separation devices 4 arranged along the bottom surface of the C star 3, for example, the second group of separation devices 4 includes four separation devices 4 connected at four corner positions of the bottom surface of the C star 3 respectively.

[0033] As shown in the figure, Figure 4As shown, for example, a plurality of separation springs 5 are arranged between the B star 2 and the C star 3, and the plurality of separation springs 5 are uniformly distributed along the connecting surface of the B star 2 and the C star 3, for example, four separation springs 5 are arranged, and the four separation springs 5 are respectively located at the four vertices of the rectangle, for example, two separation springs 5 are arranged along one diagonal of the rectangle on the B star 2, and two separation springs 5 are arranged along the other diagonal of the rectangle on the C star 3, after the B star 2 and the C star 3 are arranged along the length direction of the top surface of the first cabin body 11, four-point separation thrust is formed at the corners of the rectangle.

[0034] As shown in Figure 2 and Figure 3 For example, the first cabin body 11 is a ten-faced structure, including a first bottom plate 1101, a first top plate 1102, a first side plate 1103, a second side plate, a third side plate, a fourth side plate, a fifth side plate 1104, a sixth side plate, a seventh side plate, and an eighth side plate, wherein the first side plate 1103, the second side plate, the third side plate, the fourth side plate, the fifth side plate 1104, the sixth side plate, the seventh side plate, and the eighth side plate are sequentially connected to form a first cylinder with an octagonal cross section, the first bottom plate 1101 is arranged at the bottom of the first cylinder, and the first top plate 1102 is arranged at the top of the first cylinder, thereby forming a ten-faced structure.

[0035] For example, the first side plate 1103 and the fifth side plate 1104 are oppositely arranged and parallel to each other, and one first solar array 13 is arranged on each of the first side plate 1103 and the fifth side plate 1104, and the two first solar arrays 13 are symmetrical after being folded and unfolded.

[0036] For example, the first bottom plate 1101 and the first top plate 1102 are oppositely arranged and parallel to each other, and eight separation devices 4 are arranged on the top surface of the first top plate 1102.

[0037] The central load-bearing cylinder 12 includes a straight cylinder portion and a tapered cylinder portion, the top portion of the straight cylinder portion is connected with the first top plate 1102, the bottom portion of the straight cylinder portion is connected with the top portion of the tapered cylinder portion, and the bottom portion of the tapered cylinder portion penetrates the first bottom plate 1101, and the diameter of the tapered cylinder portion gradually increases from the top portion to the bottom portion.

[0038] As shown in Figure 2 For example, the A star 1 further includes a first antenna unit 14, and the first antenna unit 14 is arranged on the first side plate 1103 and is not located below the first solar array 13.

[0039] As shown in Figure 3 For example, the first cabin body 11 further includes a plurality of fuel tanks 1105, and the plurality of fuel tanks 1105 are fixedly arranged in a cavity between the first cylinder and the central load-bearing cylinder 12 and are arranged in the circumferential direction of the central load-bearing cylinder 12.

[0040] As shown in Figure 2 and Figure 3As shown, for example, the first cabin body 11 further comprises a first tank plate 1106, six first partitions 1107 and a layer plate 1108, wherein the six first partitions 1107 are uniformly distributed along the circumferential direction of the central load-bearing cylinder 12, and the six first partitions 1107 divide the cavity between the first cylinder body and the central load-bearing cylinder 12 into six containing cavities.

[0041] Among the four containing cavities, one fuel tank 1105 is arranged in each containing cavity, and the four fuel tanks 1105 are symmetrically and uniformly distributed along the center line of the central load-bearing cylinder 12 in pairs. Each fuel tank 1105 is connected to the inner wall of the containing cavity through a first tank plate 1106. For example, the first tank plate 1106 is provided with a first through hole, and the fuel tank 1105 is fixed in the first through hole. In addition, the other two containing cavities are each provided with a layer plate 1108, and the layer plate 1108 is connected to the inner wall of the containing cavity.

[0042] For example, the first tank plate 1106 is parallel to the first top plate 1102 and the first bottom plate 1101, the layer plate 1108 is parallel to the first top plate 1102 and the first bottom plate 1101, the top of the first partition 1107 is connected to the first top plate 1102, the bottom of the first partition 1107 is connected to the first bottom plate 1101, one side of the first partition 1107 is connected to the outer side wall of the central load-bearing cylinder 12, and the other side of the first partition 1107 is connected to the inner wall of the first cylinder body.

[0043] For example, the first tank plate 1106 and the layer plate 1108 are coplanar, and the first tank plate 1106 and the layer plate 1108 are connected to the straight cylinder portion of the central load-bearing cylinder 12.

[0044] The four fuel tanks 1105 of the embodiment of the present application are distributed around the central load-bearing cylinder 12, and have less impact on the displacement deviation of the whole satellite mass center when the fuel is consumed, and the whole satellite attitude and orbit control system is controllable. At the same time, the central load-bearing cylinder 12 has strong load-bearing capacity, and in addition to bearing the weight of the A satellite 1 itself, the first top plate 1102 connected to the central load-bearing cylinder 12 bears the weight of the B satellite 2 and the C satellite 3.

[0045] As shown in Figure 4 and Figure 5 As shown, for example, the B satellite 2 and the C satellite 3 each comprise a second cabin body 21, as shown in Figure 6As shown, the second cabin body 21 is a hexahedral cabin plate structure, and the second cabin body 21 includes a second bottom plate 2101, a second top plate 2102, a first cabin plate 2103, a second cabin plate 2104, a third cabin plate 2105, and a fourth cabin plate. The first cabin plate 2103, the second cabin plate 2104, the third cabin plate 2105, and the fourth cabin plate are sequentially connected to form a second cylinder with a quadrilateral cross section, the second bottom plate 2101 is arranged at the bottom of the second cylinder, and the second top plate 2102 is arranged at the top of the second cylinder, so as to form a hexahedral cabin plate structure. The second bottom plate 2101 is connected to the top surface of the first cabin body 11 through the separation device 4.

[0046] For example, the first cabin plate 2103 and the third cabin plate 2105 are oppositely arranged and parallel to each other, and the second cabin plate 2104 and the second cabin plate 2104 are oppositely arranged and parallel to each other.

[0047] As shown in Figure 5 and Figure 6 For example, the B star 2 and the C star 3 further include two second solar arrays 22, one second solar array 22 is arranged on the second cabin plate 2104, and the other second solar array 22 is connected to the fourth cabin plate through a connecting frame 24. When the second solar array 22 on the fourth cabin plate is in the folded state, it is pressed on the first cabin plate 2103, and when the second solar array 22 on the fourth cabin plate is in the unfolded state, it is located on one side of the fourth cabin plate and is symmetrical to the unfolded second solar array 22 on the second cabin plate 2104.

[0048] The second solar array 22 of the embodiment of the present application adopts a configuration design of non-array in the folded state and symmetry in the unfolded state, which can meet the envelope constraint in the launch state and the symmetry requirement on both sides of the solar array in the on-orbit flight state.

[0049] As shown in Figure 5 and Figure 6 For example, the B star 2 and the C star 3 further include a second antenna unit 23, and the second antenna unit 23 is arranged on the third cabin plate 2105.

[0050] The second bottom plate 2101 of the B star 2 and the C star 3 of the embodiment of the present application is used to be connected to the A star 1, the second top plate 2102 can be used to arrange other components, the four cabin plates are respectively used to arrange the second solar array 22 and the second antenna unit 23, the surface space of the second cabin body 21 is reasonably arranged, and the space is fully utilized.

[0051] As shown in Figure 6As shown, for example, the second cabin body 21 is further provided with a second partition plate 2106, a third partition plate 2107, a second storage tank plate 2108 and a storage tank support plate 2109, wherein the second partition plate 2106 is provided with two second partition plates 2106, the two second partition plates 2106 are arranged at intervals, the top of the second partition plate 2106 is connected with the second top plate 2102, the bottom of the second partition plate 2106 is connected with the second bottom plate 2101, the two second partition plates 2106 are parallel to the first cabin plate 2103 and the third cabin plate 2105, and the two second partition plates 2106 divide the second cylinder cavity into three cavities.

[0052] The two ends of the second storage tank plate 2108 are respectively connected with a second partition plate 2106, the second storage tank plate 2108 is parallel to the second top plate 2102 and the second bottom plate 2101, there is a gap between the second storage tank plate 2108 and the second bottom plate 2101, the bottom of the storage tank support plate 2109 is connected with the second bottom plate 2101, the top of the storage tank support plate 2109 is connected with the bottom of the second storage tank plate 2108, the second storage tank plate 2108 is provided with a second through hole, and for example, the storage tank support plate 2109 is parallel to the two second partition plates 2106.

[0053] The third partition plate 2107 is arranged between the two second partition plates 2106 and above the second storage tank plate 2108, the third partition plate 2107 is parallel to the second cabin plate 2104 and the fourth cabin plate, the two sides of the third partition plate 2107 are respectively connected with the two second partition plates 2106, the top of the third partition plate 2107 is connected with the middle part of the second top plate 2102, and the bottom of the second partition plate 2106 is connected with the middle part of the second storage tank plate 2108.

[0054] As shown in the drawings, Figure 1 As shown, when the B star 2 and the C star 3 are combined with the A star 1, the position relationship satisfies that the fourth cabin plate of the B star 2 is opposite to the fourth cabin plate of the C star 3, the fourth cabin plate of the B star 2 is provided with two separation devices 4 along the diagonal line, the fourth cabin plate of the C star 3 is provided with two separation devices 4 along the diagonal line, four points of the rectangular corner points form the separation thrust, the first cabin plate 2103 of the B star 2 and the third cabin plate 2105 of the C star 3 are located on the same side of the A star 1, the third cabin plate 2105 of the B star 2 and the first cabin plate 2103 of the C star 3 are located on the same side of the A star 1, the second cabin plate 2104 of the B star 2 is opposite to and parallel to the second cabin plate 2104 of the C star 3, the second solar array 22 of the B star 2 is above one first solar array 13 of the A star 1, and the second solar array 22 of the C star 3 is above another first solar array 13 of the A star 1.

[0055] The three-star combination of the application makes all the solar arrays and antenna units located on the outer side of the satellite, and reasonably utilizes the space.

[0056] As shown in the drawings, Figure 7As shown, the three-satellite combination of the embodiment of the application is launched into an initial orbit in a three-satellite manner, and then the three-satellite combination is separated from the carrier, the first solar array 13 on the two sides of the first cabin body 11 of the A satellite 1 is unfolded, and the three-satellite combination enters a target orbit after five times of orbit transfer, as shown in Figure 8 As shown, the B satellite 2 and the C satellite 3 are separated from the A satellite 1, and the second solar array 22 of the B satellite 2 and the C satellite 3 is unfolded after the three satellites are separated and the distance is pulled apart, as shown in Figure 9

[0057] The three-satellite combination configuration of the embodiment of the application comprehensively considers the carrier fairing envelope, the carrying capacity, the three-satellite connection mode, the multiple orbit transfer, the fuel consumption and other factors, solves the problem that the number of satellites launched by a single launch vehicle is small, the load cylinder connection can only have a single satellite connection interface, and a plurality of satellites cannot be launched at one time to meet the orbit deployment, and simultaneously meets a plurality of constraint conditions such as the carrier envelope constraint, the center of mass constraint, the three-satellite one-time launch constraint, the three-satellite and carrier connection constraint, and the two-side array distribution constraint after the solar array is unfolded.

[0058] Although the application is described in detail with reference to the foregoing embodiments, those skilled in the art should understand that the technical solutions recorded in the foregoing embodiments can be modified, or some technical features can be replaced by equivalents; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the application.​

Claims

1. A medium-high orbit communication satellite one-launch three-satellite assembly configuration, characterized in that, The A star (1), the B star (2) and the C star (3) are included. The A star (1) comprises a first cabin body (11) and a central bearing cylinder (12), the first cabin body (11) is sleeved on the outside of the central bearing cylinder (12), the central bearing cylinder (12) is used for being connected with a carrier, the B star (2) and the C star (3) are arranged along the length direction of the top surface of the first cabin body (11) and are not connected with the carrier, the B star (2) and the C star (3) are connected with the top surface of the first cabin body (11) through a separation device (4) respectively, and a separation spring (5) is arranged between the B star (2) and the C star (3). The position relationship of the B star (2) and the C star (3) satisfies that the B star (2) is rotated by 180 degrees along the central line in the width direction of the first cabin body (11) to be the position of the C star (3).

2. The MEO communication satellite one-launch-three-satellite constellation configuration of claim 1, wherein, The B star (2) is connected with the top surface of the first cabin body (11) through a first group of separation devices (4), the first group of separation devices (4) comprises a plurality of separation devices (4) arranged along the bottom surface of the B star (2), the C star (3) is connected with the top surface of the first cabin body (11) through a second group of separation devices (4), and the second group of separation devices (4) comprises a plurality of separation devices (4) arranged along the bottom surface of the C star (3).

3. The MEO communication satellite one-launch-three-satellite constellation configuration of claim 1, wherein, A plurality of separation springs (5) are uniformly distributed along the connecting surface of the B star (2) and the C star (3).

4. The multi-satellite-per-launch constellation configuration of any of claims 1-3, wherein, The first cabin body (11) comprises a first bottom plate (1101), a first top plate (1102), a first side plate (1103), a second side plate, a third side plate, a fourth side plate, a fifth side plate (1104), a sixth side plate, a seventh side plate and an eighth side plate. The first side plate (1103), the second side plate, the third side plate, the fourth side plate, the fifth side plate (1104), the sixth side plate, the seventh side plate and the eighth side plate are sequentially connected to form a first cylinder body with an octagonal cross section, the first bottom plate (1101) is arranged at the bottom of the first cylinder body, and the first top plate (1102) is arranged at the top of the first cylinder body.

5. The MEO communication satellite one-launch-three-satellite constellation configuration of claim 4, wherein, The A star (1) further comprises a first solar array (13) and a first antenna unit (14), the first side plate (1103) and the fifth side plate (1104) are oppositely arranged and parallel to each other, one first solar array (13) is arranged on each of the first side plate (1103) and the fifth side plate (1104), and the first antenna unit (14) is arranged on the first side plate (1103) and located below the first solar array (13).

6. The multi-satellite-per-launch constellation configuration of claim 4, wherein, The central bearing cylinder (12) comprises a straight cylinder portion and a tapered cylinder portion. The top of the straight cylinder portion is connected with the first top plate (1102), the bottom of the straight cylinder portion is connected with the top of the tapered cylinder portion, the bottom of the tapered cylinder portion penetrates through the first bottom plate (1101), and the diameter of the tapered cylinder portion gradually increases from the top to the bottom.

7. The MEO communication satellite one-launch-three-satellite constellation configuration of claim 4, wherein, The first cabin body (11) further comprises a plurality of fuel storage tanks (1105) fixedly arranged in a cavity between the first cylinder body and the central force bearing cylinder (12) and arranged circumferentially along the central force bearing cylinder (12).

8. The multi-satellite-per-launch constellation configuration of claim 4, wherein, The B star (2) and the C star (3) each comprise a second cabin body (21), two second solar arrays (22) and a second antenna unit (23), the second cabin body (21) comprises a second bottom plate (2101), a second top plate (2102), a first cabin plate (2103), a second cabin plate (2104), a third cabin plate (2105) and a fourth cabin plate; The first cabin plate (2103), the second cabin plate (2104), the third cabin plate (2105) and the fourth cabin plate are sequentially connected to form a second cylinder body with a quadrilateral cross section, the second bottom plate (2101) is arranged at the bottom of the second cylinder body, and the second top plate (2102) is arranged at the top of the second cylinder body; the second bottom plate (2101) is connected to the top surface of the first cabin body (11) through the separation device (4); One of the second solar arrays (22) is arranged on the second cabin plate (2104), and the other second solar array (22) is connected to the fourth cabin plate through a connecting frame (24); when the second solar array (22) on the fourth cabin plate is in a folded state, it is pressed against the first cabin plate (2103); when the second solar array (22) on the fourth cabin plate is in an unfolded state, it is located on one side of the fourth cabin plate and is symmetrical to the unfolded second solar array (22) on the second cabin plate (2104); and the second antenna unit (23) is arranged on the third cabin plate (2105).

9. The MEO communication satellite one-launch-three-satellite constellation configuration of claim 8, wherein, The second cabin body (21) further comprises a second partition plate (2106), a third partition plate (2107), a second storage tank plate (2108) and a storage tank support plate (2109); The second partition plate (2106) is arranged in pairs and is spaced apart, the top of the second partition plate (2106) is connected to the second top plate (2102), the bottom of the second partition plate (2106) is connected to the second bottom plate (2101), and the first cabin plate (2103) and the third cabin plate (2105) are parallel to the second partition plate (2106); The two ends of the second storage tank plate (2108) are respectively connected to one of the second partition plates (2106), and the second storage tank plate (2108) has a gap between the second bottom plate (2101); the bottom of the storage tank support plate (2109) is connected to the second bottom plate (2101), the top of the storage tank support plate (2109) is connected to the bottom of the second storage tank plate (2108), and the second storage tank plate (2108) is provided with a second through hole; The third partition plate (2107) is arranged between two second partition plates (2106) and above the second storage tank plate (2108), two sides of the third partition plate (2107) are connected with the two second partition plates (2106) respectively, the top of the third partition plate (2107) is connected with the middle part of the second top plate (2102), and the bottom of the second partition plate (2106) is connected with the middle part of the second storage tank plate (2108).

10. The MEO communication satellite one-launch-three-satellite constellation configuration of claim 8, wherein, When the B star (2), the C star (3) and the A star (1) are combined, the positional relationship satisfies that the fourth cabin plate of the B star (2) is opposite to the fourth cabin plate of the C star (3), the first cabin plate (2103) of the B star (2) and the third cabin plate (2105) of the C star (3) are located on the same side of the A star (1), the third cabin plate (2105) of the B star (2) and the first cabin plate (2103) of the C star (3) are located on the same side of the A star (1), the second cabin plate (2104) of the B star (2) is opposite and parallel to the second cabin plate (2104) of the C star (3); the second solar array (22) of the B star (2) is above one first solar array (13) of the A star (1), and the second solar array (22) of the C star (3) is above another first solar array (13) of the A star (1).

Images