High-maneuverability multi-satellite parallel-serial combined configuration and use method thereof

Abstract

The invention provides a high-maneuverability multi-satellite parallel-serial combined configuration and a use method thereof, the high-maneuverability multi-satellite parallel-serial combined configuration comprises a main satellite, an orbital transfer cabin and sub-satellites, the main satellite is connected in series to the top of the orbital transfer cabin, the sub-satellites are uniformly arranged on the peripheral side of the orbital transfer cabin, and the sub-satellites are connected in parallel with the orbital transfer cabin; an orbital transfer cabin storage box is arranged in the orbital transfer cabin, a sub-satellite storage box is arranged in any sub-satellite, and any sub-satellite storage box is communicated with the orbital transfer cabin storage box. When the multi-satellite combination body is launched, the storage box in the orbital transfer cabin is in a propellant full box state, the storage box in the sub-satellite cabin body is in an empty box state, the high-rigidity design of the orbital transfer cabin is fully utilized, and the lightweight design of the multi-satellite combination body structure is achieved; the orbital transfer cabin and the child satellites are provided with floating disconnectors respectively, the orbital transfer cabin serves as a fuel tank, the child satellites are launched again after fuel supply is completed through the orbital transfer cabin, and efficient utilization of fuel carried by the orbital transfer cabin is achieved. The problem that the space of the fairing of the multi-satellite launching active section is limited is solved, and efficient utilization of fuel of the orbital transfer cabin can be achieved.

Description

Technical Field

[0001] This invention relates to the field of spacecraft structure technology, specifically to a highly maneuverable multi-satellite parallel-serial combination configuration and its usage method. Background Technology

[0002] For medium- and high-orbit satellites with high maneuverability requirements, two orbital insertion methods are commonly used.

[0003] First, for satellites to autonomously enter orbit, a large-capacity propellant tank is required inside the satellite, typically using a "central main load-bearing structure + flat-laid propellant tank" configuration. Reference: Design and Implementation of Structural Subsystems of Chang'e-3 Lander (Science in China: Technological Sciences, 2014, 44(4): 391-397) shows a central cross-supported main load-bearing structure with four propellant tanks laid flat around it; Patent: Adjustable Installation Structure for Large-Size Thin-Walled Propellant Tanks Applicable to High-Orbit Satellites (CN107738761A) shows a central load-bearing cylinder structure with four propellant tanks laid flat around it. This configuration carries approximately 50% to 65% of the total satellite launch weight, but because the propellant tanks are laid flat around the main load-bearing structure, the overall satellite stiffness is low, and the structural weight accounts for a relatively high proportion to meet the satellite's fundamental frequency requirements.

[0004] Secondly, an independent orbit-changing module is designed. The energy, control, and propulsion resources of the satellite module during the orbit insertion phase are integrated and reused efficiently. During the on-orbit phase, the orbit-changing module separates from the satellite, eliminating satellite redundancy and improving platform maneuverability. Patent: The propulsion module structure with independent high-orbit satellite platform function (CN104260903A) features an independent orbit-changing module. The satellite module adopts a tandem split configuration, with the orbit-changing module operating independently during the orbit insertion phase and separating autonomously after the satellite module enters orbit. This configuration increases the on-orbit velocity increment by more than 30% compared to the integrated orbit insertion method. However, this configuration is suitable for one orbit-changing module and one main satellite, without carrying multiple sub-satellites.

[0005] Therefore, for launching multiple satellites in a single launch, a highly maneuverable multi-satellite parallel configuration is needed, which not only employs an independent orbit-changing module but also meets the requirement of sending a primary satellite and several secondary satellites into medium-high orbits. Summary of the Invention

[0006] To address the shortcomings of existing technologies, the purpose of this invention is to provide a highly maneuverable multi-satellite parallel-serial combination configuration and its usage method.

[0007] According to the present invention, a high-maneuverability multi-satellite parallel and series combination configuration includes: a main satellite, a maneuvering module and sub-satellites. The main satellite is connected in series on the top of the maneuvering module, and a plurality of sub-satellites are evenly arranged around the maneuvering module and connected in parallel with the maneuvering module. The orbit-changing cabin is equipped with an orbit-changing cabin storage tank, and each of the sub-satellites is equipped with a sub-satellite storage tank. Each of the sub-satellite storage tanks is connected to the orbit-changing cabin storage tank.

[0008] Preferably, the main satellite comprises a cabin-type structure composed of aluminum honeycomb sandwich panels, and the bottom of the main satellite is point-connected to the top of the orbit-changing module.

[0009] Preferably, multiple inter-satellite unlocking and separation devices are provided between the main satellite and the orbit-changing module. Each inter-satellite unlocking and separation device has a flanged flange at its upper and lower ends, which are fastened to the bottom plate of the main satellite and the orbit-changing module respectively. A pyrotechnic device is provided inside the inter-satellite unlocking and separation device.

[0010] Preferably, each of the subsatellites is provided with a passive end of a floating disconnector, and multiple active ends of floating disconnectors are correspondingly provided on the periphery of the orbit change cabin. The orbit change cabin tank is connected to the subsatellite tank through the active ends and passive ends of the floating disconnectors.

[0011] Preferably, the orbit change cabin includes a conical-cylindrical structure composed of an aluminum honeycomb sandwich structure, the active end of the floating disconnector is installed on the cylindrical outer wall of the orbit change cabin, and the active end of the floating disconnector is connected to the orbit change cabin tank through a propellant pipeline inside the orbit change cabin.

[0012] Preferably, a carbon fiber reinforcing frame is embedded in the cylindrical sidewall of the orbit-changing cabin at the docking point with the satellite.

[0013] Preferably, the subsatellite comprises a cabin-type structure composed of aluminum honeycomb sandwich panels, the passive end of the floating disconnector is installed on the docking surface between the subsatellite and the orbit change cabin, and the passive end of the floating disconnector is connected to the subsatellite's storage tank through propellant pipelines inside the subsatellite.

[0014] Preferably, an inter-satellite unlocking and separation device is provided between each of the aforementioned sub-satellites and the orbit-changing module.

[0015] Preferably, during launch of the high-maneuverability multi-satellite parallel combination configuration, the orbit-changing capsule's propellant tank is in a full propellant state, while the sub-satellite's propellant tank is in an empty state.

[0016] A method for using a high-maneuverability multi-satellite parallel-serial combination configuration according to the present invention includes the following steps: Step S: After the high-maneuverability multi-satellite parallel combination configuration is put into orbit, the main satellite and the orbit-changing module are unlocked and separated. Step S: The remaining propellant inside the orbit change module's storage tank is added to the satellite's storage tank; Step S: The orbital maneuvering module is unlocked and separated from the satellite.

[0017] Compared with the prior art, the present invention has the following beneficial effects: This invention connects the main satellite and the orbit-changing module in series, with several sub-satellites evenly distributed around the orbit-changing module and connected in parallel. The orbit-changing module carries multiple large propellant tanks, while the sub-satellite modules carry smaller propellant tanks. During multi-satellite launch, the propellant tanks inside the orbit-changing module are full, while the propellant tanks inside the sub-satellite modules are empty. This fully utilizes the high rigidity design of the orbit-changing module to achieve a lightweight design for the multi-satellite combination structure. The orbit-changing module and the sub-satellites are each equipped with a floating disconnector. The orbit-changing module acts as a fuel tank, and the sub-satellites are refueled through the orbit-changing module before being launched again, achieving efficient utilization of the fuel carried by the orbit-changing module. This invention solves the problem of limited space in the fairing during the active phase of multi-satellite launches and also enables efficient utilization of the fuel in the orbit-changing module. Attached Figure Description

[0018] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a structural schematic diagram illustrating the highly maneuverable multi-satellite parallel-serial combination configuration of the present invention; Figure 2 This is a schematic diagram illustrating the structure of the inter-satellite unlocking and separation device, which is the main feature of this invention. Figure 3 This is a schematic diagram illustrating the structure of the passive end of the floating disconnector, which is the main feature of this invention. Figure 4 This is a schematic diagram illustrating the structure of the active end of the floating disconnector, which is the main feature of this invention. Figure 5 This is a schematic diagram illustrating the structure of the orbit change chamber storage tank, which is the main feature of this invention. Figure 6 This is a schematic diagram illustrating the structure of the sub-satellite storage tank, which is the main feature of this invention.

[0019] The diagram shows: main satellite 1, orbit change module 2, sub-satellite 3, inter-satellite unlocking and separation device 4, passive end of floating disconnector 5, active end of floating disconnector 6, orbit change module tank 7, sub-satellite tank 8. Detailed Implementation

[0020] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0021] like Figure 1-6As shown, a high-maneuverability multi-satellite parallel-serial combination configuration provided by the present invention includes: a main satellite 1, a maneuvering module 2, and sub-satellites 3. The main satellite 1 is connected in series on the top of the maneuvering module 2, and multiple sub-satellites 3 are evenly arranged around the maneuvering module 2, and the multiple sub-satellites 3 are connected in parallel with the maneuvering module 2. The maneuvering module 2 is provided with a maneuvering module storage tank 7, and each sub-satellite 3 is provided with a sub-satellite storage tank 8, and each sub-satellite storage tank 8 is connected to the maneuvering module storage tank 7.

[0022] The main satellite 1 consists of a cabin-type structure composed of aluminum honeycomb sandwich panels, which are connected by screws. The bottom of the main satellite 1 is connected to the top of the orbit-changing cabin 2 by a point connection.

[0023] Multiple inter-satellite unlocking and separation devices 4 are installed between the main satellite 1 and the orbit-changing module 2. The bottom of the main satellite 1 is connected to the orbit-changing module 2 through several inter-satellite unlocking and separation devices 4. The upper and lower ends of the inter-satellite unlocking and separation devices 4 are respectively provided with flanged flanges, which provide installation interfaces for fastening connection with the bottom plate of the main satellite 1 and the orbit-changing module 2. The inter-satellite unlocking and separation devices 4 are equipped with pyrotechnic devices. The unlocking and separation of the main satellite 1 and the orbit-changing module 2 are ensured by powering the pyrotechnic devices to detonate.

[0024] Each subsatellite 3 is equipped with a passive end 5 of a floating disconnector, and multiple active ends 6 of floating disconnectors are correspondingly arranged on the periphery of the orbit change cabin 2. The orbit change cabin storage tank 7 is connected to the subsatellite storage tank 8 through the active ends 6 and the passive ends 5 of the floating disconnectors.

[0025] The orbit change chamber 2 includes a conical cylindrical structure composed of an aluminum honeycomb sandwich structure. The active end 6 of the floating disconnector is installed on the cylindrical outer wall of the orbit change chamber 2. The active end 6 of the floating disconnector is connected to the orbit change chamber tank 7 through the propellant pipeline inside the orbit change chamber 2.

[0026] A carbon fiber reinforcing frame is embedded in the cylindrical sidewall of the orbit change module 2 at the junction with the satellite 3 to ensure the connection rigidity and strength between the orbit change module 2 and the satellite 3.

[0027] Subsatellite 3 includes a cabin-type structure composed of aluminum honeycomb sandwich panels. The passive end 5 of the floating disconnector is installed on the docking surface between Subsatellite 3 and the orbit change cabin 2. The passive end 5 of the floating disconnector is connected to the subsatellite tank 8 through the propellant pipeline inside Subsatellite 3.

[0028] Each satellite 3 and orbit change module 2 is equipped with an inter-satellite unlocking and separation device 4. The inter-satellite unlocking and separation device is installed on the docking surface of satellite 3 and orbit change module 2, providing a stable connection between satellite 3 and orbit change module 2 during satellite entry and safe separation between satellite 3 and orbit change module 2 after entry into orbit.

[0029] The method of using the high-mobility multi-star parallel-series combination configuration of this application includes the following steps: Step S1: After the high-maneuverability multi-satellite parallel combination configuration is put into orbit, the main satellite 1 and the orbit change module 2 are unlocked and separated. Step S2: The remaining propellant inside the orbit change cabin tank 7 is added to the satellite tank 8; Step S3: The orbital change module 2 and the sub-satellite 3 are unlocked and separated.

[0030] Generally, the four storage tanks inside the orbit change cabin 2 are connected to the active end 6 of the floating disconnector via pipelines inside the orbit change cabin, and the storage tank 8 inside the sub-satellite 3 is connected to the passive end 5 of the floating disconnector via pipelines inside the sub-satellite 3. The pipelines inside the orbit change cabin 2 and the sub-satellite 3 can achieve a one-to-many correspondence between storage tanks 7 and 8.

[0031] After the main satellite 1, the orbit change module 2 and the sub-satellite 3 combination enter orbit, the main satellite 1 first separates from the orbit change module 2 and the sub-satellite 3 combination. The orbit change module 2 and the sub-satellite 3 are propelled through the active end 6 and the passive end 5 of the floating disconnector. The remaining propellant in the orbit change module tank 7 is added to the sub-satellite tank 8. Then the orbit change module 2 and the sub-satellite 3 are unlocked and separated.

[0032] This application applies to the simultaneous launch of a primary satellite (1) and several secondary satellites (3) to a medium-high orbit via a single rocket launcher. It fully utilizes the space within the active fairing, arranging several secondary satellites (3) in parallel around the orbit-changing module (2), and connecting the primary satellite (1) in series at the top of the module. This achieves a high-strength, low-response design for the mounting interface of the primary satellite (1) and secondary satellites (8). Simultaneously, the orbit-changing module (2) serves as a fuel tank, equipped with a floating disconnector. The secondary satellites (3) are refueled through the module and then separate again, achieving efficient utilization of the fuel carried by the module.

[0033] During the launch of the multi-satellite assembly, the propellant tank 7 inside the orbit-changing module 2 is full, while the propellant tank 8 inside the sub-satellite 3 module is empty. This fully utilizes the high rigidity design of the orbit-changing module 2 to achieve a lightweight design for the multi-satellite assembly structure. Both the orbit-changing module 2 and the sub-satellite 3 are equipped with floating disconnectors. Using the orbit-changing module 2 as a fuel tank, the sub-satellite 3 can be refueled through the orbit-changing module 2 before launching again, achieving efficient utilization of the fuel carried by the orbit-changing module 2. This application solves both the problem of limited space in the active phase fairing of multi-satellite launches and the efficient utilization of fuel in the orbit-changing module 2.

[0034] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0035] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A highly maneuverable multi-satellite parallel-serial combination configuration, characterized in that, include: The main star (1), the orbit change module (2), and the sub-stars (3) are connected in series on the top of the orbit change module (2), and multiple sub-stars (3) are evenly arranged around the orbit change module (2) and connected in parallel with the orbit change module (2). The orbit change cabin (2) is equipped with an orbit change cabin storage tank (7), and each of the sub-satellites (3) is equipped with a sub-satellite storage tank (8), and each of the sub-satellite storage tanks (8) is connected to the orbit change cabin storage tank (7).

2. The high-mobility multi-satellite parallel-serial combination configuration as described in claim 1, characterized in that, The main star (1) comprises a cabin-type structure composed of aluminum honeycomb sandwich panels, and the bottom of the main star (1) is point-connected to the top of the orbit-changing cabin (2).

3. The high-mobility multi-satellite parallel-serial combination configuration as described in claim 1, characterized in that, Multiple inter-satellite unlocking and separation devices (4) are provided between the main star (1) and the orbit change cabin (2). The inter-satellite unlocking and separation device (4) has flanges at its upper and lower ends, which are fastened to the bottom plate of the main star (1) and the orbit change cabin (2) respectively. The inter-satellite unlocking and separation device (4) is equipped with a pyrotechnic device inside.

4. The high-mobility multi-satellite parallel-serial combination configuration as described in claim 1, characterized in that, Each of the sub-satellites (3) is provided with a passive end (5) of a floating disconnector, and a plurality of active ends (6) of floating disconnectors are provided on the periphery of the orbit change cabin (2). The orbit change cabin tank (7) is connected to the sub-satellite tank (8) through the active end (6) and the passive end (5) of the floating disconnector.

5. The high-mobility multi-satellite parallel-serial combination configuration as described in claim 4, characterized in that, The orbit change chamber (2) includes a conical column structure composed of an aluminum honeycomb sandwich structure. The active end (6) of the floating disconnector is installed on the outer cylindrical wall of the orbit change chamber (2). The active end (6) of the floating disconnector is connected to the orbit change chamber tank (7) through the propellant pipeline inside the orbit change chamber (2).

6. The high-mobility multi-satellite parallel-serial combination configuration as described in claim 5, characterized in that, The cylindrical sidewall of the orbit-changing cabin (2) is embedded with a carbon fiber reinforcing frame at the junction with the sub-star (3).

7. The high-maneuverability multi-satellite parallel-serial combination configuration as described in claim 4, characterized in that, The sub-satellite (3) includes a cabin-type structure composed of aluminum honeycomb sandwich panels. The passive end (5) of the floating disconnector is installed on the docking surface between the sub-satellite (3) and the orbit change cabin (2). The passive end (5) of the floating disconnector is connected to the sub-satellite tank (8) through the propellant pipeline inside the sub-satellite (3).

8. The high-mobility multi-satellite parallel-serial combination configuration as described in claim 1, characterized in that, An inter-satellite unlocking and separation device (4) is provided between any of the sub-satellites (3) and the orbit change cabin (2).

9. The high-mobility multi-satellite parallel-serial combination configuration as described in claim 1, characterized in that, When the high-mobility multi-satellite parallel combination configuration is launched, the orbit-changing capsule (7) is in a full propellant state, and the sub-satellite capsule (8) is in an empty state.

10. A method of using the high-maneuverability multi-satellite parallel-tank combination configuration according to any one of claims 1-9, characterized in that, Includes the following steps: Step S1: After the high-maneuverability multi-satellite parallel combination configuration is put into orbit, the main satellite (1) and the orbit change module (2) are unlocked and separated. Step S2: The remaining propellant inside the orbit change cabin tank (7) is added to the satellite tank (8); Step S3: The orbital module (2) and the satellite (3) are unlocked and separated.

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