A stacked multi-satellite launch system

Abstract

The present invention discloses a stacked one-rocket-multiple-satellite launch system, comprising a fairing and a stacked assembly arranged in the fairing. The stacked assembly comprises a multi-layer satellite group, a plurality of support columns, a bottom support structure and a plurality of compression and unlocking parts. Each layer of satellite group comprises a plurality of satellites symmetrically arranged around the central axis of the last stage of a carrier rocket. The support column comprises a plurality of support assemblies stacked along the central axis, the support assembly comprises a first support and a second support respectively connected to adjacent surfaces of two adjacent satellites in the same layer of satellite group, and the first support and the second support are stacked in sequence to form a support column. The bottom support structure is arranged at the bottom of the multi-layer satellite group, and is respectively connected to all the bottom second supports, and the bottom support structure is connected to the fairing. The compression and unlocking part comprises a tension rod, a compression member and an unlocking member, and the three cooperate with each other to compress all the support assemblies in the corresponding support column so that they form a support column.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace technology, and in particular relates to a stacked one-rocket-multiple-satellite launching system. Background Art

[0002] Conventional multiple-satellite-on-one-launch configuration is usually achieved by adding internal and external payload compartments to the final stage of the rocket. Each satellite (payload) is connected to the internal / external payload compartment through its own separate strap connection unlocking device / point connection unlocking device. Each internal / external payload compartment can accommodate multiple satellites, and the internal / external payload compartments are then connected to the final stage of the launch vehicle.

[0003] In the above-mentioned conventional one-rocket-multiple-satellite layout, each satellite's separate strap connection unlocking device / point connection unlocking device (and its adapter), internal / external payload compartment occupy a large amount of space and mass in the launch vehicle's carrying capacity, usually up to 20%~50% of the payload space and 10%~30% of the payload mass. This part of the space and mass cannot be used for the satellite (payload) itself, and becomes the dead weight (invalid payload) of the last stage of the launch vehicle, and does not provide any benefit to the satellite after the separation of the satellite and rocket. Summary of the invention

[0004] The purpose of the present invention is to provide a stacked multi-satellite launch system to solve the serious problem of multi-satellite launch layout in the prior art.

[0005] The technical solution of the present invention is:

[0006] A stacked one-rocket-multiple-satellite launch system comprises a fairing and a stacked assembly installed in the fairing, wherein the stacked assembly comprises:

[0007] A multi-layer satellite group, each layer of the satellite group includes a plurality of satellites symmetrically arranged around the central axis of the last stage of the carrier rocket, and the distribution of the satellites in each layer of the satellite group is the same, and the multi-layer satellite groups are stacked along the central axis;

[0008] A plurality of support columns, all arranged along the central axis, the support column comprising a plurality of support assemblies stacked along the central axis, the support assembly comprising a first support and a second support respectively connected to adjacent surfaces of two adjacent satellites in the satellite group at the same layer, the first support being stacked on the second support, the second support being stacked on the first support corresponding to the satellite group at the next layer, the first support and the second support being stacked in sequence to form one support column;

[0009] A bottom support structure is provided at the bottom of the multi-layer satellite group, and is respectively connected to all the second supports on all the satellite groups at the lowest layer, and the bottom support structure is connected to the fairing;

[0010] A plurality of clamping and unlocking parts respectively correspond to a plurality of the support columns; the clamping and unlocking parts include a tensioning rod, a clamping member and an unlocking member, one end of the tensioning rod is connected to the first support at the uppermost end of the corresponding support column through the clamping member, the other end of the tensioning rod is connected to the bottom support structure through the unlocking member, the tensioning rod, the clamping member and the unlocking member cooperate with each other to clamp all the support components in the corresponding support column so that they form the support column; the unlocking member is unlocked upon receiving an unlocking command to disconnect the tensioning rod and the bottom support component.

[0011] In one embodiment, both ends of the first support and the second support are frustum structures, with one end being a convex surface and the other end being a concave surface, and the convex surface and the concave surface are matched with each other to realize the stacking of the first support and the second support.

[0012] In one embodiment, both the first support and the second support are hollow structures.

[0013] In one embodiment, an elastic component is provided at the stacking position of the first support and the second support to provide separation thrust when the satellite is separated.

[0014] In one embodiment, one of the first support and the second support at the stacking connection is a mounting support, and the other is a separation support;

[0015] The elastic component includes a spring and a spring core shaft, the spring core shaft is arranged in the mounting support, there is a gap between the outer wall of the spring core shaft and the inner wall of the mounting support, and both ends of the spring core shaft are respectively provided with annular bosses protruding outwards;

[0016] The inner wall of the mounting support is provided with a limit platform protruding inwardly, and the limit platform is arranged between the two annular bosses to prevent the spring core shaft from escaping from the mounting support after the satellite is separated;

[0017] The spring is arranged in the installation support and sleeved on the separation support. One end of the spring is connected to the limit platform, and the other end of the spring presses the annular boss close to the separation support against the separation support, and the spring is in a compressed state.

[0018] In one embodiment, it further comprises a plurality of auxiliary support assemblies arranged along the central axis, and each layer of the satellite group is provided with one or more of the auxiliary support assemblies;

[0019] Each of the auxiliary support assemblies includes auxiliary supports having the same number as the satellites in the satellite group in the corresponding layer, the auxiliary supports in the auxiliary support assemblies are respectively connected to the satellites in the satellite group in the corresponding layer, and all the auxiliary supports in the same auxiliary support assembly are stacked in sequence.

[0020] In one embodiment, an elastic component is provided at the stacking position of two adjacent auxiliary supports in the same auxiliary support assembly to provide separation thrust when the satellite is separated.

[0021] In one embodiment, the connection points between the first support and the second support and the satellite surface are both located at the outermost side of the satellite surface relative to the central axis;

[0022] Only one support assembly is arranged between two adjacent satellites in the satellite group on the same floor. The number of the tension rods is the same as the number of the support columns, and the two correspond one to one. The tension rods are tightly buckled on the corresponding support columns toward the central axis.

[0023] In one embodiment, the clamping and unlocking portion includes two tension rods, which are arranged on both sides of the corresponding support column, and the clamping member is respectively connected to the two tension rods to cooperate with the unlocking portion to clamp the support column located between the two tension rods.

[0024] In one embodiment, the unlocking member is a separation nut, and each of the separation nuts is provided with an anti-separation member, one end of the anti-separation member is connected to the tension rod, and the other end is connected to the bottom support assembly through the separation nut;

[0025] The bottom support assembly is connected with a connecting shaft, and the anti-separation member is provided with a movable groove, and the connecting shaft is movably connected in the movable groove. The connecting shaft and the movable groove cooperate to prevent the tension rod from separating from the bottom support assembly after the separation nut breaks and is unlocked.

[0026] Due to the adoption of the above technical solution, the present invention has the following advantages and positive effects compared with the prior art:

[0027] The stacked one-rocket-multiple-satellite launch system provided by the present invention abandons the traditional practice of equipping each satellite with a heavy adapter and an independent satellite-rocket connection unlocking device, and instead uses a modular, lightweight, compact supporting structure (composed of multiple supporting columns) and a compression unlocking part that are directly installed on the satellite.

[0028] In order to maximize the use of the carrying capacity (including payload space and payload mass) provided by the launch vehicle, the present invention abandons the system of the conventional multiple satellites in one rocket with inner / external payload compartments in the prior art with separate strapping / point-type connection unlocking devices, greatly reduces or even eliminates the mass of the inner / external payload compartments and independent single-satellite adapters, and does not lose the overall structural strength and rigidity of the multiple satellites required for launch. Therefore, the present invention solves the problems of heavy layout and low utilization rate of carrying volume in the prior art of multiple satellites in one rocket. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the following detailed description of the preferred embodiment.The drawings are only for the purpose of illustrating the preferred embodiments and are not to be construed as limiting the invention.

[0030] Figure 1 It is a structural schematic diagram of a stacked one-rocket-multiple-satellite launch system of the present invention;

[0031] Figure 2 for Figure 1 Schematic diagram of the installation of the first support, the second support and the auxiliary support on a single satellite in the case;

[0032] Figure 3 for Figure 1 The connection diagram of the auxiliary support acting on the upper and lower two layers of four satellites in the case;

[0033] Figure 4 for Figure 1 Schematic diagram of the separation spring set inside the support in the case;

[0034] Figure 5 for Figure 1 Schematic diagram of the structure near the clamping part in the case;

[0035] Figure 6 for Figure 1 A schematic diagram of the structure of the pressing and unlocking part in the case in the locked state;

[0036] Figure 7 for Figure 1 Schematic diagram of the unlocking state of the pressed unlocking part in the case;

[0037] Figure 8 A schematic diagram of another embodiment of the present invention;

[0038] Fig. 9 It is a schematic diagram of a third implementation case applicable to the present invention.

[0039] Description of reference numerals:

[0040] 1: fairing; 2: support cabin; 3: first support; 4: second support; 5: bottom support structure; 6: tension rod; 7: clamping piece; 8: satellite; 9: auxiliary support; 10: spring; 11: spring core shaft; 12: loading nut; 13: anti-loosening bracket; 14: anti-separation piece; 15: gear shaft; 16: coil spring; 17: separation nut. DETAILED DESCRIPTION

[0041] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the specific implementation methods of the present invention will be described below with reference to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings and other implementation methods can be obtained based on these drawings without creative work.

[0042] In order to simplify the drawings, only the parts related to the present invention are schematically shown in each figure, and they do not represent the actual structure of the product. In addition, in order to simplify the drawings and facilitate understanding, in some figures, only one of the parts with the same structure or function is schematically drawn or marked. In this article, "one" not only means "only one", but also means "more than one".

[0043] See also Figures 1 to 9 This embodiment provides a stacked multi-satellite launch system, including a fairing 1 and a stacked assembly arranged in the fairing 1. The stacked assembly includes a multi-layer satellite group, a plurality of support columns, a bottom support structure 5 and a plurality of pressing and unlocking parts.

[0044] Each layer of satellite groups includes a plurality of satellites 8 symmetrically arranged around the central axis of the last stage of the carrier rocket, and the distribution of satellites 8 in each layer of satellite groups is the same, and the multiple layers of satellite groups are stacked along the central axis.

[0045] Multiple support columns are arranged along the central axis direction, and the support column includes multiple support assemblies stacked along the central axis direction. The support assembly includes a first support 3 and a second support 4 respectively connected to adjacent surfaces of two adjacent satellites 8 in the same layer of satellite group. The first support 3 is stacked on the second support 4, and the second support 4 is stacked on the first support 3 corresponding to the next layer of satellite group. The first support 3 and the second support 4 are stacked in sequence to form a support column.

[0046] The bottom support structure 5 is arranged at the bottom of the multi-layer satellite group. The bottom support structure 5 is respectively connected to the second supports 4 on all the lowest satellite groups, and the bottom support structure 5 is connected to the fairing 1 .

[0047] The plurality of pressing and unlocking parts correspond to the plurality of supporting columns respectively. The pressing and unlocking parts include a tension rod 6, a pressing member 7 and an unlocking member. One end of the tension rod 6 is connected to the uppermost support in the supporting column through the pressing member 7, and the other end of the tension rod 6 is connected to the bottom supporting structure 5 through the unlocking member. The tension rod 6, the pressing member 7 and the unlocking member cooperate with each other to press all the supporting components in the corresponding supporting column so that they form a supporting column. The unlocking member is unlocked after receiving the unlocking command, and the connection between the tension rod 6 and the bottom supporting component is disconnected.

[0048] The structure of this embodiment is now described.

[0049] The stacked multi-satellite launch system provided in this embodiment is suitable for multiple satellites 8 of the same or similar configuration and size. The satellites 8 are arranged in layers, and each layer can be equipped with multiple satellites 8, which are symmetrically distributed about the central axis (specifically, the central axis of the last stage of the launch vehicle).

[0050] In this embodiment, there are 4 layers of satellite groups, each layer of satellite groups includes 4 satellites 8, which are symmetrically arranged around the central axis of the last stage of the carrier rocket. In practical applications, the number of layers of satellite groups and the number of satellites 8 included in each layer of satellite groups can be adjusted accordingly according to the payload available envelope and carrying capacity provided by the carrier rocket and the specific configuration of the launched satellites 8, and are not limited here.

[0051] Both the first support 3 and the second support 4 can adopt a modular design and present a hollow cylindrical structure. The diameter and height of the cylinder are designed in series to accommodate satellites 8 of different heights and configurations. When installed on a rocket, they can be selected or adjusted accordingly according to the height, mass and load conditions of the satellites 8 in the stacking assembly. Both ends of the first support 3 and the second support 4 can adopt a hollow frustum structure, with one end being a convex surface and the other end being a concave surface. The corresponding convex and concave surfaces fit each other to realize the stacking of the first support 3 and the second support 4. After the clamping and unlocking part is pre-tightened, an integral column from top to bottom is formed - the support column, which is used to bear the main loads on the stacking assembly, mainly the axial force and radial force of the entire stacking assembly.

[0052] Specifically, the first support 3 and the second support 4 are both modularly designed, and several modules are continuously connected and connected in series to form a continuous whole, and a support column is formed after the pressing and unlocking part is pre-tightened. The height and diameter of the first support 3 and the second support 4 can be adaptively selected according to the size of the satellite 8.

[0053] The entire stacked assembly is arranged in the fairing 1 and separated at the same time after reaching the predetermined orbit. The first support 3 and the second support 4 are fixedly connected to the threads pre-buried in the satellite 8 by bolts to achieve connection with the satellite 8, and do not separate from the satellite 8 after the satellite-rocket separation. The first support 3 and the second support 4 can also be used as part of the load-bearing structure of the satellite 8, which should be taken into consideration when designing the satellite 8.

[0054] In order to further improve the overall rigidity of the stacked assembly, this embodiment further provides an auxiliary support assembly. Multiple auxiliary support assemblies are arranged along the central axis, and each layer of satellite groups is provided with one or more auxiliary support assemblies. Each auxiliary support assembly includes the same number of auxiliary supports 9 as the number of satellites 8 in the corresponding layer of satellite groups. The auxiliary supports 9 in the auxiliary support assembly are respectively connected to the satellites 8 in the corresponding layer of satellite groups, and all auxiliary supports 9 in the same auxiliary support assembly are stacked in sequence.

[0055] Specifically, the auxiliary support 9 can also adopt a modular design, presenting a hollow ring structure, and the diameter and height of the ring are designed in series to adapt to different multi-star layout requirements. The two ends of the auxiliary support 9 can also be set as a hollow cone structure, one side is convex and the other side is concave. When the auxiliary supports 9 in the same auxiliary support assembly are stacked, the convex and concave surfaces of the two adjacent auxiliary supports 9 are interlocked. The auxiliary support assembly can bear certain axial and radial loads. The volume and mass of the auxiliary support 9 are much smaller than those of the first support 3 and the second support 4, but it can effectively improve the overall stiffness of the stacked assembly.

[0056] The auxiliary support assembly is discontinuous in the entire stacking assembly, and only connects several satellites 8 arranged nearby, so that the number of satellites 8 arranged in each layer of satellite groups and the layout of satellites 8 between different layers have greater flexibility, so that multiple satellites 8 with similar configurations but different sizes can also form a stacking assembly.

[0057] The butt joint surface of the first support 3 / second support 4 / auxiliary support 9 is a hollow conical structure. The hollow design has the characteristics of high strength, high rigidity and light weight. The conical design can effectively bear the axial load. The conical surface can bear radial loads in all directions under the compression of the preload force, and has the function of guiding and centering during butt joint installation.

[0058] Figure 2 The figure shows a schematic diagram of the installation of the support assembly and the auxiliary support assembly on a single satellite 8 in this embodiment. A first support 3, a second support 4, and two auxiliary supports 9 are installed on each satellite 8. It should be noted that, according to the specific configuration and load conditions of the satellite 8, a single satellite 8 may also be provided with other numbers of first supports 3 and second supports 4, but it is recommended that at least one first support 3 and one second support 4 be included on the single satellite 8. A single satellite 8 may also be provided with other numbers of auxiliary supports 9, or no auxiliary supports 9 may be provided.

[0059] Figure 3 The figure shows the connection of the auxiliary support assembly when acting on the upper and lower two layers of four satellites 8 in this embodiment. An auxiliary support 9 is set at the bottom of each of the two upper satellites 8, and an auxiliary support 9 is set at the top of each of the two lower satellites 8, in a staggered arrangement.

[0060] Furthermore, at the stacking place of the first support 3 and the second support 4, and at the stacking place of two adjacent auxiliary supports 9 in the same auxiliary support assembly, an elastic assembly can be provided as needed to provide additional separation thrust for the satellite 8 after unlocking, that is, to provide separation thrust when the satellite 8 is separated. For the convenience of description, in the support assembly, one of the first support 3 and the second support 4 at the stacking connection is called the installation support, and the other is called the separation support; in the auxiliary support assembly, one of the two auxiliary supports 9 at the stacking connection is called the installation support, and the other is called the separation support.

[0061] Specifically, the elastic component includes a spring 10 and a spring core shaft 11. The spring core shaft 11 is arranged in the mounting support. There is a gap between the outer wall of the spring core shaft 11 and the inner wall of the mounting support, and both ends of the spring core shaft 11 are respectively provided with annular bosses protruding outward. The inner wall of the mounting support is provided with a limit platform protruding inward. The limit platform is arranged between the two annular bosses to prevent the spring core shaft 11 from escaping from the mounting support after the satellite 8 is separated. The spring 10 is arranged in the mounting support and sleeved on the spring core shaft 11. One end of the spring 10 is connected to the limit platform, and the other end presses the annular boss close to the separation support against the separation support. When the spring 10 is separated, it is in a compressed state.

[0062] The present embodiment uses a clamping and unlocking part to lock and unlock the entire stacking assembly. In the clamping and unlocking part, the number of tension rods 6 can be adaptively adjusted according to the specific layout of the satellites 8 in the stack. Specifically in the present embodiment, only one support assembly can be provided between two adjacent satellites 8 in the same-layer satellite group, and the connection points between the first support 3 and the second support 4 and the surface of the satellite 8 are both located at the outermost sides of the surface of the satellite 8 relative to the central axis. The number of tension rods 6 is twice the number of supporting columns, and every two tension rods 6 correspond. The bottom of the tension rod 6 is connected to the supporting structure through the locking and unlocking part, and the top is fastened to the corresponding supporting column along the central axis through the clamping part. Each pair of tension rods 6 is locked by the same locking and unlocking part, and at the same time, the first support 3 and the second support 4 of the assembled column are compressed by a pressing part; when unlocking, all tension rods 6 are unlocked at the same time, flipped toward the outside of the rocket body along the rotating axis of the locking and unlocking part, and the whole is in an open state, thereby releasing the pre-tensioning force acting on the first support 3 and the second support 4 of the stacking assembly, and having no contact with the first support 3 and the second support 4. Each satellite 8 in the stacking assembly can be separated from the last stage of the carrier rocket at the same time, thereby releasing all satellites 8 in the stacking assembly.

[0063] In this embodiment, the pressing and unlocking part includes two tension rods 6, such as Figure 5As shown, two tension rods 6 are respectively arranged on both sides of the corresponding supporting columns. The two tension rods 6 are respectively penetrated by the clamping parts 7 and then connected to the loading nuts 12. A pre-tightening force is applied to the tension rods 6. The unlocking part cooperates to clamp the supporting column between the two tension rods 6. At the same time, the loading nut 12 that has been loaded is prevented from loosening by the anti-loosening bracket 13.

[0064] The unlocking member can be a separation nut 17, and each separation nut 17 is provided with an anti-separation member 14, one end of the anti-separation member 14 is connected to the tension rod 6, and the other end is connected to the bottom support assembly through the separation nut 17. When the separation nut 17 is broken after receiving the unlocking command, the pre-tightening tension applied by the support column of the pressing unlocking force disappears, and the first support 3 and the second support 4 in the support column can be separated.

[0065] In order to prevent the clamping part 7, the tensioning rod 6 and other structures from floating in the space after separation, a connecting shaft can be connected to the bottom support assembly, and a movable groove can be set on the anti-separation part 14. The connecting shaft is movably connected in the movable groove. The connecting shaft and the movable groove cooperate to prevent the separation nut 17 from breaking and unlocking the tensioning rod 6 from separating from the bottom support assembly.

[0066] Furthermore, a gear can be sleeved on the connecting shaft and the two are fixedly connected, or the connecting shaft and the gear can be integrally arranged to form a gear shaft 15, and there is no limitation to this; in the present embodiment, a gear shaft 15 is adopted, and the gear shaft 15 is rotatably connected to the bottom supporting structure 5. A coil spring 16 is provided between the gear shaft 15 and the base supporting structure to provide a preload force for driving the gear shaft 15 to rotate. The movable groove can be a waist-shaped groove, and racks meshing with the gear ring on the gear shaft 15 are provided on the two semicircles and one side wall of the waist-shaped groove, and there are no teeth on the other side wall of the waist-shaped groove, so that the movable groove can convert the rotation of the gear shaft 15 into its own translation and rotation. In the locked state, such as Figure 6 As shown, the separation nut 17 connects the bottom support structure 5 and the anti-separation member 14, the gear shaft 15 is located in the top semicircle of the movable groove, and the coil spring 16 is in the energy storage state. Figure 7 As shown, the separation thread breaks and unlocks, and the gear shaft 15 rotates under the release of the elastic potential energy of the coil spring 16, driving the anti-separation member 14 and the tensioning rod 6 to move upward until the gear ring on the gear shaft 15 engages with the rack on the lower semicircle of the movable groove. The gear shaft 15 continues to rotate under the action of the coil spring 16, and the anti-separation member 14 and the tensioning rod 6 rotate outward around the gear shaft 15 as a whole, thereby realizing the unlocking of the stacking assembly.

[0067] In the locked state, the separation nut 17 can be connected to the anti-separation part 14 and the bottom support structure 5 at the same time. After the separation nut 17 breaks, the part connected to the bottom support structure 5 is still connected to the bottom support structure 5; or the separation nut 17 is only connected to the anti-separation part 14, then a collecting device needs to be provided on the bottom support structure 5 to collect the part corresponding to the bottom support structure 5 after the separation nut 17 breaks.

[0068] The function of the bottom support structure 5 is similar to that of the conventional satellite 8 adaptation structure, and is used to install the entire stack assembly on the final stage of the launch vehicle. A support cabin 1 may be provided at the bottom of the stack assembly, the support cabin 1 being provided in the fairing 1, and the bottom support structure 5 being installed on the support cabin 1.

[0069] In summary, in the stacked multi-satellite launch system provided in the present embodiment, satellites 8 and satellites 8 in the same layer of satellite groups in the stack assembly, and layers and layers of the satellite group are connected by modular support structures (including first supports 3, second supports 4 and auxiliary supports 9). Each satellite 8 can be provided with three or more support structures in contact with other satellites 8. Among them, the first support 3 and the second support 4 are close to the outside of each layer, which bear the main longitudinal and lateral loads of the stacked assembly; the auxiliary support 9 is located at the axis of each layer, which is used to enhance the overall strength and rigidity of the stacked assembly. A top reinforcing bracket can also be provided on the top of the stacked assembly as needed to enhance the overall structural strength and rigidity of the stacked assembly.

[0070] The stacking assembly as a whole is compressed and unlocked using the compression and unlocking part. In the compressed state, the tension rod 6 is tightly buckled on the support column formed by the stacking of the first support 3 and the second support, providing a tensile force for pre-tightening the stacking assembly. When unlocking, the tension rod 6 first moves up and then rotates outward to unfold, and the satellite 8 in the stack is simultaneously unlocked and separated from the last stage of the launch vehicle.

[0071] The stacked multi-satellite launch system provided by the present invention abandons the practice of providing each satellite 8 with a separate traditional adapter and connection unlocking mechanism, greatly reduces the space and weight required for installing a single satellite 8 on a carrier rocket, and fully utilizes the carrying capacity of the carrier rocket, so that the carrier rocket can transport more satellites 8 with a heavier total weight at one time. It has the beneficial effects of fast multi-satellite networking with one rocket, rapid construction of large-scale / super-large-scale constellations, high carrying capacity utilization, and greatly reduced single-satellite launch costs.

[0072] Figures 1 to 7 The embodiment shown is a state where each layer of satellite groups has four satellites 8. The present invention can also be applied to other states, including the number of satellites 8 in each layer of satellite groups, the number of layers of satellite groups, etc., which can be adaptively adjusted according to the specific configuration and size of the satellites 8, such as Figure 8 and Fig. 9Two other implementation cases of the stacked one-rocket-multiple-satellite launch system of the present invention are shown.

[0073] The embodiments of the present invention are described in detail above in conjunction with the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, if these changes fall within the scope of the claims of the present invention and their equivalents, they still fall within the protection scope of the present invention.

Claims

1. A stacked multi-satellite launch system, characterized in that: It comprises a fairing and a stacking assembly installed in the fairing, and the stacking assembly comprises: A multi-layer satellite group, each layer of the satellite group includes a plurality of satellites symmetrically arranged around the central axis of the last stage of the carrier rocket, and the distribution of the satellites in each layer of the satellite group is the same, and the multi-layer satellite groups are stacked along the central axis; A plurality of support columns, all arranged along the central axis, the support column comprising a plurality of support assemblies stacked along the central axis, the support assembly comprising a first support and a second support respectively connected to adjacent surfaces of two adjacent satellites in the satellite group at the same layer, the first support being stacked on the second support, the second support being stacked on the first support corresponding to the satellite group at the next layer, the first support and the second support being stacked in sequence to form one support column; A bottom support structure is provided at the bottom of the multi-layer satellite group, and is respectively connected to all the second supports on all the satellite groups at the lowest layer, and the bottom support structure is connected to the fairing; A plurality of pressing and unlocking parts respectively corresponding to the plurality of support columns; the pressing and unlocking parts include a tension rod, a pressing member and an unlocking member, one end of the tension rod is connected to the first support at the uppermost end of the corresponding support column through the pressing member, and the other end of the tension rod is connected to the bottom support structure through the unlocking member, the tension rod, the pressing member and the unlocking member cooperate with each other to press all the support assemblies in the corresponding support column so that they form the support column; the unlocking member is unlocked after receiving an unlocking command, and the connection between the tension rod and the bottom support assembly is disconnected; Wherein, the pressing and unlocking part comprises two tension rods, the two tension rods are arranged on both sides of the corresponding supporting column, and the pressing member is respectively connected to the two tension rods, and is used to cooperate with the unlocking part to press the supporting column located between the two tension rods; The unlocking member is a separation nut, and each of the separation nuts is correspondingly provided with an anti-separation member, one end of the anti-separation member is connected to the tension rod, and the other end is connected to the bottom support assembly through the separation nut; the bottom support assembly is connected to a connecting shaft, and a movable groove is provided on the anti-separation member, and the connecting shaft is movably connected in the movable groove, and the connecting shaft and the movable groove cooperate to prevent the tension rod from being separated from the bottom support assembly after the separation nut is broken and unlocked; Among them, the connecting shaft is a gear shaft, the movable groove is a waist-shaped groove, and racks meshing with the gear ring on the gear shaft are arranged on the two semicircles and one side wall of the waist-shaped groove, and there are no teeth on the other side wall of the waist-shaped groove; the gear shaft is meshed and connected with the rack, and the gear shaft and the waist-shaped groove are used to convert the rotation of the gear shaft into the translation and rotation of the anti-separation part; a coil spring is provided between the gear shaft and the base support structure, and the coil spring is used to provide a preload force to drive the gear shaft to rotate.

2. The stacked one-rocket-multiple-satellite launch system according to claim 1, characterized in that: Both ends of the first support and the second support are frustum structures, one end is a convex surface, and the other end is a concave surface, and the convex surface and the concave surface are matched with each other to realize the stacking of the first support and the second support.

3. The stacked one-rocket-multiple-satellite launch system according to claim 1, characterized in that: The first support and the second support are both hollow structures.

4. The stacked one-rocket-multiple-satellite launch system according to claim 3, characterized in that: An elastic component is provided at the stacking position of the first support and the second support, which is used to provide separation thrust when the satellite is separated.

5. The stacked one-rocket-multiple-satellite launch system according to claim 4, characterized in that: One of the first support and the second support at the stacking connection is a mounting support and the other is a separation support; The elastic component includes a spring and a spring core shaft, the spring core shaft is arranged in the mounting support, there is a gap between the outer wall of the spring core shaft and the inner wall of the mounting support, and both ends of the spring core shaft are respectively provided with annular bosses protruding outwards; The inner wall of the mounting support is provided with a limit platform protruding inwardly, and the limit platform is arranged between the two annular bosses to prevent the spring core shaft from escaping from the mounting support after the satellite is separated; The spring is arranged in the installation support and sleeved on the separation support. One end of the spring is connected to the limit platform, and the other end of the spring presses the annular boss close to the separation support against the separation support, and the spring is in a compressed state.

6. The stacked one-rocket-multiple-satellite launch system according to claim 1, characterized in that: It also includes a plurality of auxiliary support assemblies arranged along the central axis, and each layer of the satellite group is provided with one or more of the auxiliary support assemblies; Each of the auxiliary support assemblies includes auxiliary supports having the same number as the satellites in the satellite group in the corresponding layer, the auxiliary supports in the auxiliary support assemblies are respectively connected to the satellites in the satellite group in the corresponding layer, and all the auxiliary supports in the same auxiliary support assembly are stacked in sequence.

7. The stacked one-rocket-multiple-satellite launch system according to claim 6, characterized in that: An elastic component is provided at the stacking position of two adjacent auxiliary supports in the same auxiliary support assembly, which is used to provide separation thrust when the satellite is separated.

8. The stacked one-rocket-multiple-satellite launch system according to claim 1, characterized in that: The connection points between the first support and the second support and the satellite surface are both located at the outermost side of the satellite surface relative to the central axis; Only one support assembly is arranged between two adjacent satellites in the satellite group on the same floor. The number of the tension rods is the same as the number of the support columns, and the two correspond one to one. The tension rods are tightly buckled on the corresponding support columns toward the central axis.

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