A multi-functional service spacecraft configuration

Abstract

This invention provides a multi-functional service spacecraft configuration. The multi-functional service spacecraft consists of a power module and an instrument module, and is equipped with major equipment such as a robotic arm, toolbox, propellant replenishment device, and spacecraft docking mechanism. The multi-functional service spacecraft employs a unique double-load-bearing cylinder configuration: the upper instrument module uses a sealed central load-bearing cylinder configuration; the lower power module, with the outer load-bearing cylinder as its main force transmission structure, is connected to the central load-bearing cylinder of the instrument module via a truncated cone section, and also contains a sealed inner load-bearing cylinder, forming a sealed space together with the central load-bearing cylinder of the instrument module. This multi-functional service spacecraft operates in orbit for extended periods, performing orbital maneuvers as needed, and is primarily used to provide on-orbit services including cargo transportation, orbit maintenance, repair and maintenance, and propellant replenishment.

Description

Technical Field

[0001] This invention relates to the field of spacecraft design, and more specifically to a multi-functional service spacecraft configuration. Background Technology

[0002] With the development of aerospace technology, spacecraft are becoming increasingly powerful, with longer service lives and higher development costs. If a spacecraft experiences a major malfunction in orbit that cannot be resolved by ground-based tracking and control systems, it faces the risk of complete on-orbit failure, resulting in enormous losses. Therefore, on-orbit servicing technology has emerged. On-orbit servicing technology generally involves a servicing spacecraft equipped with specialized tools providing services to a spacecraft equipped with corresponding interfaces. To date, on-orbit servicing applications include:

[0003] (1) Transportation services: Typically, cargo spacecraft transport and resupply cargo to the space station;

[0004] (2) Propellant replenishment service: This generally involves the servicing spacecraft carrying propellant to replenish the spacecraft being serviced;

[0005] (3) Attitude and orbit control takeover service: Generally, the servicing spacecraft and the servicing spacecraft need to be docked as a combined unit, and the former takes over the attitude and orbit control of the latter as a whole.

[0006] In addition, there are robotic satellites under research, equipped with robotic arms and maintenance tools, capable of performing on-orbit maintenance on faulty satellites.

[0007] The aforementioned spacecraft that have been deployed or are about to be deployed for on-orbit servicing are all single-function spacecraft with insufficient service capabilities, and their on-orbit value has not been maximized. One of the major challenges of integrating multiple on-orbit servicing functions into a spacecraft is the complexity of its configuration design. Summary of the Invention

[0008] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a spacecraft configuration that can integrate multiple functions such as space cargo transportation services, on-orbit maintenance services, on-orbit propellant replenishment services, attitude and orbit control takeover services, and return capsule reentry and return support services, thereby achieving the goal of integrating multiple on-orbit service functions.

[0009] The technical solution of the present invention is: a multi-functional service spacecraft configuration, wherein the spacecraft configuration is a hybrid structure of sealed and unsealed cabins, including an instrument cabin and a cargo cabin;

[0010] The equipment within the spacecraft platform is installed in the instrument compartment, while the cargo compartment serves as storage space for propellants and cargo.

[0011] The instrument compartment has a central load-bearing cylinder combined with a box-plate configuration, including a sealed central load-bearing cylinder and an unsealed box-plate configuration; the cargo compartment has an inner and outer double load-bearing cylinder configuration, including a sealed inner load-bearing cylinder and an unsealed outer load-bearing cylinder.

[0012] A sealed hatch is provided at one end of the sealed central support cylinder of the instrument compartment, and the other end is sealed to one end of the sealed inner support cylinder of the cargo compartment. A sealed hatch is also provided at the other end of the sealed inner support cylinder of the cargo compartment. After the sealed central support cylinder of the instrument compartment and the sealed inner support cylinder of the cargo compartment are sealed together, a sealed space is formed.

[0013] The instrument compartment is also equipped with a first docking and berthing mechanism, which is connected to the sealed door of the sealed central load-bearing cylinder on the instrument compartment;

[0014] The cargo hold is also equipped with a second docking and berthing mechanism; it is connected to the sealed hatch of the sealed inner load-bearing cylinder on the cargo hold.

[0015] Before the separation of the spacecraft from the rocket, the second docking and berthing mechanism on the cargo compartment is connected to the launch vehicle, serving as the main load-bearing and force-transmitting structure of the entire multi-functional service spacecraft.

[0016] During cargo transport to the space station, the first docking mechanism on the instrument module docks with the reentry capsule, and the second docking mechanism on the cargo module docks with the space station. Astronauts inside the space station enter the sealed space formed by the sealed central support cylinder of the instrument module and the sealed support cylinder in the cargo module to handle cargo, thereby realizing cargo transport services.

[0017] Preferably, in the instrument compartment, the sealed central load-bearing cylinder has a cylindrical and truncated conical structure, and the non-sealed box plate has an octagonal prism structure.

[0018] Preferably, in the cargo compartment, the sealed inner support cylinder is a cylindrical structure with an inverted truncated cone, and the unsealed outer support cylinder is a cylindrical structure.

[0019] Preferably, the inner diameter of the sealed central load-bearing cylinder of the instrument compartment should be no less than [number] meters to ensure that one astronaut can pass through.

[0020] Preferably, the diameter of the non-sealed outer support cylinder of the cargo compartment is designed by taking into account the volume requirements of a single cargo transport and the interface constraints with the launch vehicle. Specifically, the diameter of the non-sealed outer support cylinder of the cargo compartment should be larger than the diameter of the space required to meet the volume of a single cargo transport, and smaller than the diameter of the envelope space of the launch vehicle fairing.

[0021] Preferably, the sealed central support cylinder of the instrument compartment and the unsealed external support cylinder of the cargo compartment are made of aluminum alloy.

[0022] Preferably, the sealed central support cylinder of the instrument compartment and the sealed support cylinder in the cargo compartment are each provided with an inverted T-shaped sealing groove on their sealing end faces. A lace-shaped sealing element is installed in the groove. After the two are joined together, they are fixed together by screws. The lace-shaped sealing element is deformed under pressure to form a double seal.

[0023] Preferably, the instrument compartment is equipped with a robotic arm for capturing the servicing spacecraft equipped with the cooperative target adapter. After capture, the servicing spacecraft can be accurately moved to dock with the first docking and berthing mechanism or propellant replenishment device under the action of the robotic arm. After docking, the robotic arm is released.

[0024] Preferably, the propellant replenishment device on the instrument compartment has a propellant replenishment function, and after the servicing spacecraft docks with the propellant replenishment device, the multi-functional servicing spacecraft can provide on-orbit propellant replenishment services to it.

[0025] Preferably, after the servicing spacecraft docks with the first docking and berthing mechanism, the multi-functional servicing spacecraft can perform attitude and orbit control takeover services on it, using its own propulsion system to control the attitude and orbit of the combined spacecraft; the multi-functional servicing spacecraft can also use a robotic arm to perform on-orbit maintenance and replacement services on the servicing spacecraft.

[0026] Preferably, the instrument compartment is equipped with a clamping and separation device, which consists of three swing arms. The front end of each swing arm is hemispherical and has a gas nozzle. When not in use, the three swing arms are open and close to the inner wall of the sealed compartment. When in use, the three swing arms rotate synchronously towards the center until the front hemispherical part clamps the return capsule. When the return capsule is ejected, the three swing arms unload the clamping force, and the nozzles simultaneously eject high-pressure gas to eject the small return capsule.

[0027] Compared with existing similar technologies, the beneficial technical effects of the present invention are:

[0028] (1) Compared with existing on-orbit service spacecraft that only serve satellites, the multi-functional service spacecraft and its configuration provided by the present invention can not only serve various unmanned satellites, but also provide sealed cargo transportation services and return capsule reentry support services to manned space stations by setting up sealed spaces.

[0029] (2) The multi-functional service spacecraft and its configuration provided by the present invention can provide a variety of on-orbit service functions and greatly enhance service capabilities;

[0030] (3) The multi-functional service spacecraft and its configuration provided by the present invention can be replenished with propellant, thereby extending its on-orbit life;

[0031] (4) The multi-functional service spacecraft and its configuration provided by the present invention can transfer the cargo package launched by the launch vehicle through on-orbit docking via a robotic arm and docking mechanism, thereby expanding the on-orbit cargo transportation service capability.

[0032] (5) The multi-functional service spacecraft and its configuration of the present invention have the advantages of diverse mission functions, strong mission flexibility and good comprehensive economy, and can be applied to the on-orbit service of various satellites, manned space stations, near-Earth orbit stations and other spacecraft. Attached Figure Description

[0033] A multi-functional service spacecraft and its configuration according to the present invention are given by the following embodiments and figures.

[0034] Figure 1 This is a schematic diagram of the overall shape of the device according to a preferred embodiment of the present invention.

[0035] Figure 2 This is a schematic diagram of the overall configuration of a preferred embodiment of the present invention.

[0036] Figure 3 This is a schematic diagram of the sealed space according to a preferred embodiment of the present invention.

[0037] Figure 4 This is a schematic diagram of the release of the return capsule according to a preferred embodiment of the present invention.

[0038] Markings in the diagram: 1-Cargo compartment, 101-Sealed inner support cylinder, 102-Unsealed outer support cylinder, 103-First docking mechanism, 2-Instrument compartment, 201-Robotic arm, 202-Second docking mechanism, 203-Propellant replenishment device, 204-Sealed central support cylinder, 205-Unsealed box plate Detailed Implementation

[0039] The following will combine Figures 1-4 The present invention will now be described in further detail.

[0040] Figure 1 This is a schematic diagram of a multi-functional servicing spacecraft according to the present invention. This multi-functional servicing spacecraft can capture, reposition, dock, and berth the servicing spacecraft, thereby enabling on-orbit maintenance, on-orbit propellant replenishment, and attitude and orbit control takeover services. The multi-functional servicing spacecraft has a special hybrid structure configuration of sealed and unsealed compartments, consisting of two sections: an instrument compartment 2 and a cargo compartment 1. The instrument compartment 2 is located on top, and the cargo compartment 1 is located below.

[0041] The equipment layout within the spacecraft platform is installed in the instrument compartment 2, while the cargo compartment 1 mainly serves as a space for propellant and cargo storage.

[0042] The instrument compartment 2 is a central load-bearing cylinder combined with a box-plate configuration, including a sealed central load-bearing cylinder 204 and a non-sealed box-plate 205;

[0043] Cargo compartment 1 has a double-load-bearing cylinder configuration, including a sealed inner load-bearing cylinder 101 and a non-sealed outer load-bearing cylinder 102;

[0044] A sealed door is provided at one end of the sealed central support cylinder 204 in the instrument compartment, and the other end is sealed to one end of the sealed inner support cylinder 101 in the cargo compartment. A sealed door is also provided at the other end of the inner sealed inner support cylinder 101 in the cargo compartment. After the sealed central support cylinder 204 in the instrument compartment and the inner sealed inner support cylinder 101 in the cargo compartment are sealed together, a sealed space is formed.

[0045] The instrument compartment 2 is also equipped with a first docking and berthing mechanism 202, which is connected to the sealed door of the sealed central load-bearing cylinder 204 on the instrument compartment;

[0046] The cargo compartment 1 is also equipped with a second docking and berthing mechanism 103, which is connected to the sealed hatch of the sealed inner load-bearing cylinder 101 on the cargo compartment.

[0047] Before the separation of the spacecraft from the rocket, the second docking and berthing mechanism 103 on the cargo compartment is connected to the launch vehicle, serving as the main load-bearing and force-transmitting structure of the entire multi-functional service spacecraft.

[0048] During cargo transportation to the space station, the first docking mechanism 202 on instrument module 2 docks with the reentry capsule, and the second docking mechanism 103 on cargo module 1 docks with the space station. Astronauts inside the space station enter the sealed space formed by the sealed central support cylinder 204 in the instrument module and the sealed support cylinder 101 in the cargo module to handle cargo, thereby realizing cargo transportation services.

[0049] Figure 2 This is a schematic diagram of the configuration of a multi-functional service spacecraft according to the present invention.

[0050] In the instrument compartment 2, the sealed central load-bearing cylinder 204 has a cylindrical and truncated conical structure, while the non-sealed box plate 205 has an octagonal prism structure.

[0051] In the cargo compartment 1, the sealed inner support cylinder 101 is a cylindrical structure with an inverted truncated cone, and the non-sealed outer support cylinder 102 is a cylindrical structure.

[0052] The sealed central support cylinder 204 of the instrument compartment should have an internal diameter of not less than 0.8 meters, preferably about 1 meter, to ensure that one astronaut can pass through.

[0053] The diameter of the non-sealed outer support cylinder 102 of the cargo compartment is designed considering both the volume requirements for a single cargo transport and the interface constraints with the launch vehicle. Specifically, the diameter of the non-sealed outer support cylinder 102 of the cargo compartment should be larger than the diameter of the space required to meet the volume requirements for a single cargo transport, while being smaller than the diameter of the envelope space of the launch vehicle fairing. In a specific embodiment of the present invention, the diameter of the non-sealed outer support cylinder 102 of the cargo compartment 2 is designed to be 2 meters, taking into account both the volume requirements for a single cargo transport and the interface constraints with the launch vehicle. A 2-meter strap can be used for connection with the launch vehicle.

[0054] The sealed central load-bearing cylinder 204 of the instrument compartment and the unsealed external load-bearing cylinder 102 of the cargo compartment must simultaneously ensure load-bearing efficiency, sealing performance, and lightweight, and are made of aluminum alloy.

[0055] Figure 3 This is a schematic diagram of the sealed space of a multi-functional service spacecraft according to the present invention. Each of the sealed central support cylinder 204 of the instrument compartment and the sealed support cylinder 101 in the cargo compartment has an inverted T-shaped sealing groove on its sealing end face. A lace-shaped sealing element is installed in the groove. After the two are joined, they are fixed together by screws. The lace-shaped sealing element deforms under pressure, forming a double seal, ultimately making the central support cylinder 204 of the instrument compartment and the support cylinder 101 in the cargo compartment form a sealed space.

[0056] The multi-functional service spacecraft can dock with the space station via the docking mechanism 103 equipped on the cargo compartment 1. Astronauts on the station can enter the sealed space formed by the central support cylinder 204 of the instrument compartment and the support cylinder 101 of the cargo compartment to carry out cargo handling, thereby realizing cargo transportation services.

[0057] The instrument compartment 2 is equipped with two robotic arms 201, which are used to capture the servicing spacecraft equipped with the cooperative target adapter. After capture, the servicing spacecraft can be accurately moved to dock with the first docking mechanism 202 or the propellant replenishment device 203 by the robotic arms 201. After docking, the robotic arms 201 are released.

[0058] The propellant replenishment device 203 on the instrument compartment 2 has a propellant replenishment function. After the servicing spacecraft docks with the propellant replenishment device 203, the multi-functional servicing spacecraft can provide on-orbit propellant replenishment services.

[0059] After the servicing spacecraft docks with the first docking and berthing mechanism 202, the multi-functional servicing spacecraft can perform attitude and orbit control takeover services, using its own propulsion system to control the attitude and orbit of the combined spacecraft; the multi-functional servicing spacecraft can also use its robotic arm to perform on-orbit maintenance and replacement services for the servicing spacecraft.

[0060] The instrument compartment 2 is equipped with a clamping and separation device 206. The main body of this clamping and separation device consists of three swing arms. The front end of the swing arms is hemispherical and has a gas nozzle. The outlet gas pressure is 0.01MPa to 0.02MPa. When the three swing arms are not working, they are open and close to the inner wall of the sealed compartment to avoid affecting personnel movement. When working, the three swing arms rotate synchronously towards the center until the front hemispherical part clamps the return capsule. When the small return capsule is ejected, the three swing arms unload the clamping force, and the nozzles spray high-pressure gas at the same time to eject the small return capsule.

[0061] Figure 4 This is a schematic diagram of a multi-functional service spacecraft for releasing a return capsule according to the present invention. When the multi-functional service spacecraft docks with the space station, astronauts can enter the multi-functional service spacecraft and install a small return capsule (preferably, an airbag-type reentry return) and its ejection device into the central support cylinder 204 of the instrument compartment. After separating from the space station, the multi-functional service spacecraft vents the gas inside the capsule, then maneuvers to the separation orbit, provides a suitable separation attitude and speed, and ejects the small return capsule, thereby completing the reentry support service.

[0062] The spacecraft reentry and return method based on the above-mentioned multi-functional service spacecraft includes the following steps:

[0063] (1) Transport the small return capsule into the sealed cabin of the multi-functional service spacecraft;

[0064] (2) The three swing arms of the separation device rotate inward until they clamp the small return capsule.

[0065] (3) The multi-functional service spacecraft vents the gas inside its sealed cabin after separating from the space station;

[0066] (4) The multi-functional service spacecraft maneuvers to the separation orbit and opens the hatch of the first docking mechanism;

[0067] (5) The attitude control engines on the multi-functional service spacecraft operate to provide the appropriate attitude;

[0068] (6) The separation device unloads the clamping force with three swing arms, and high-pressure gas is ejected from the front end of the swing arms at the same time to eject the small return capsule, thereby completing the reentry and return support service.

[0069] The aforementioned multi-functional service spacecraft and its configuration can transfer cargo packages launched by launch vehicles via on-orbit docking through robotic arms and docking mechanisms, thereby expanding the capability of on-orbit cargo transportation services.

[0070] The aforementioned multi-functional service spacecraft and its configuration can be replenished through docking and propellant replenishment devices, thus enabling them to remain in orbit for extended periods and provide services to other spacecraft multiple times.

[0071] The embodiments of the present invention described above are merely illustrative of the invention. These embodiments were selected and specifically described to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize it. The embodiments do not exhaustively describe all details, nor do they limit the invention to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification, and all of these fall within the scope of protection of the present invention.

Claims

1. A multi-functional service spacecraft configuration, characterized in that, The spacecraft configuration is a hybrid structure of sealed and unsealed compartments, including an instrument compartment and a cargo compartment; The equipment layout within the spacecraft platform is installed in the instrument compartment (2), and the cargo compartment (1) is used as a propellant and cargo storage space; the instrument compartment (2) is a central load-bearing cylinder combined with a box-plate configuration, including a sealed central load-bearing cylinder (204) and an unsealed box plate (205); the cargo compartment (1) is an inner and outer double load-bearing cylinder configuration, including a sealed inner load-bearing cylinder (101) and an unsealed outer load-bearing cylinder (102); A sealed door is provided at one end of the sealed central support cylinder (204) of the instrument compartment, and the other end is sealed to one end of the sealed inner support cylinder (101) of the cargo compartment. A sealed door is also provided at the other end of the inner sealed inner support cylinder (101) of the cargo compartment. After the sealed central support cylinder (204) of the instrument compartment and the inner sealed inner support cylinder (101) of the cargo compartment are sealed together, a sealed space is formed. The instrument compartment (2) is also equipped with a first docking and stopping mechanism (202), which is connected to the sealed door of the sealed central load-bearing cylinder (204) on the instrument compartment; The cargo compartment (1) is also equipped with a second docking and berthing mechanism (103); which is connected to the sealed hatch of the sealed inner load-bearing cylinder (101) on the cargo compartment; Before the separation of the spacecraft from the rocket, the second docking and berthing mechanism (103) on the cargo compartment is connected to the launch vehicle, serving as the main load-bearing and force-transmitting structure of the entire multi-functional service spacecraft; During cargo transportation to the space station, the first docking mechanism (202) on the instrument module (2) docks with the reentry capsule, and the second docking mechanism (103) on the cargo module (1) docks with the space station. Astronauts in the space station enter the sealed space formed by the sealed central support cylinder (204) of the instrument module and the sealed inner support cylinder (101) of the cargo module to carry out cargo handling, thereby realizing cargo transportation services. The propellant replenishment device (203) on the instrument compartment (2) has a propellant replenishment function. After the servicing spacecraft docks with the propellant replenishment device (203), the multi-functional servicing spacecraft can provide on-orbit propellant replenishment services to it. After the servicing spacecraft docks with the first docking and berthing mechanism (202), the multi-functional servicing spacecraft can perform attitude and orbit control takeover services on it and use its own propulsion system to control the attitude and orbit of the combined spacecraft; the multi-functional servicing spacecraft can also use a robotic arm to perform on-orbit maintenance and replacement services on the servicing spacecraft. The instrument compartment (2) is equipped with a clamping and separation device (206). The main body of the clamping and separation device consists of three swing rods. The front end of the swing rod is hemispherical and has a gas nozzle. When the three swing rods are not working, they are open and close to the inner wall of the sealed compartment. When working, the three swing rods rotate synchronously towards the center until the front hemispherical part clamps the return capsule. When the return capsule is ejected, the three swing rods unload the clamping force, and the nozzles spray high-pressure gas at the same time to eject the small return capsule.

2. The multi-functional service spacecraft configuration according to claim 1, characterized in that, In the instrument compartment (2), the sealed central load-bearing cylinder (204) is a cylindrical and truncated cone structure, and the non-sealed box plate (205) is an octagonal prism structure.

3. The multi-functional service spacecraft configuration according to claim 1, characterized in that, In the cargo compartment (1), the sealed inner support cylinder (101) is a cylindrical structure with an inverted truncated cone, and the unsealed outer support cylinder (102) is a cylindrical structure.

4. The multi-functional service spacecraft configuration according to claim 1, characterized in that, The sealed central support cylinder (204) of the instrument compartment should have an internal diameter of not less than 0.8 meters to ensure that an astronaut can pass through.

5. The multi-functional service spacecraft configuration according to claim 1, characterized in that, The diameter of the non-sealed outer support cylinder (102) of the cargo compartment is designed in accordance with the volume requirements of a single cargo transport and the interface constraints with the launch vehicle. Specifically, the diameter of the non-sealed outer support cylinder (102) of the cargo compartment should be greater than the diameter value of the space required to meet the volume of a single cargo transport, and smaller than the diameter value of the envelope space of the launch vehicle fairing.

6. The multi-functional service spacecraft configuration according to claim 1, characterized in that, The sealed central support cylinder (204) of the instrument compartment and the unsealed external support cylinder (102) of the cargo compartment are made of aluminum alloy.

7. A multi-functional service spacecraft configuration according to claim 1, characterized in that, The sealed central support cylinder (204) of the instrument compartment and the sealed inner support cylinder (101) of the cargo compartment each have an inverted T-shaped sealing groove on their sealing end faces. A lace-shaped sealing element is installed in the groove. After the two are joined together, they are fixed together by screws. The lace-shaped sealing element is deformed under pressure to form a double seal.

8. A multi-functional service spacecraft and its configuration according to claim 1, characterized in that, The instrument compartment (2) is equipped with two robotic arms (201) for capturing the servicing spacecraft equipped with the cooperative target adapter. After capture, the servicing spacecraft can be accurately moved to dock with the first docking mechanism (202) or the propellant replenishment device (203) under the action of the robotic arms (201). After docking, the robotic arms (201) are released.

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