Large simulation gravity system

Abstract

A large-scale simulation gravity system comprises a power rotating wheel working cabin, an I-type gravity field simulation cabin and an II-type gravity field simulation cabin. The power rotating wheel working cabin comprises a sealed working cabin, a motor, a rotating wheel, an out-cabin solar wing and a docking port device; each of the I-type gravity field simulation cabin and the II-type gravity field simulation cabin comprises a gravity field simulation cabin, a head docking port, a tail docking port, a solar wing device and a gravity field simulation cabin forward docking port; wherein the middle part of the I-type gravity field simulation cabin is connected with a rotating wheel connecting rod through a turnover mechanism; the I-type gravity field simulation cabin and the II-type gravity field simulation cabin are connected to form a polyhedral structure, and the power rotating wheel working cabin drives the polyhedral structure to rotate to form a gravity simulation field. Based on in-orbit construction and maintenance of the system, the construction period is short, and the maintainability is good.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of spacecraft design and on-orbit construction, and in particular to a large-scale simulated gravity system. BACKGROUND

[0002] With the continuous extension of human exploration of space, long-term on-orbit work and life has become possible, and the continuous on-orbit residence time has increased from the initial few days to half a year, and the longest record has even exceeded 1 year. With the advancement of human deep space exploration missions, the physiological hazards caused by long-term on-orbit residence of astronauts are becoming increasingly prominent. Building a space cabin that can generate artificial gravity is one of the means to simulate gravity.

[0003] In related simulated gravity technologies:

[0004] 1. Linear acceleration scheme: simulate gravity by linear acceleration, that is, the spacecraft always flies at an acceleration of ±1g during flight, so the overloading of the astronauts in it will always remain at a level of 1g, and there will be no weightlessness. However, the propellant consumption is huge, and it is only suitable for short-term missions.

[0005] 2. Inverse magnetic gravity scheme: artificial gravity is generated by using inverse magnetic mechanisms, but the inverse magnetic device needs to keep the vicinity of the magnetic field free of any other magnetic device interference, and also needs to carry several tons of magnets to create a low-temperature superconducting environment, resulting in the fact that this scheme is not feasible on existing spacecraft platforms;

[0006] 3. Short-arm centrifuge scheme: the short-arm centrifuge device installed on the International Space Station by the Russian Energy Rocket Company uses the centrifugal force generated by rotation to simulate gravity, but this device can only generate gravity locally when the centrifuge is running, and cannot provide a continuous weightless environment for the entire cabin.

[0007] In view of the above problems, the international space field proposes to build a large-scale rotating space station to generate sustained artificial gravity, but the traditional single launch integral structure is limited by the size of the fairing of the launch vehicle, and it is difficult to achieve the requirement of a hundred-meter radius of rotation. The existing on-orbit assembly technology mostly adopts the truss expansion mode, and the cabin body is difficult to replace, making it difficult to achieve efficient collaboration of gravity generation, system maintenance and mission expansion. SUMMARY

[0008] The present application provides a large-scale simulated gravity system, which solves the problem of how to achieve efficient collaboration of gravity generation, system maintenance and mission expansion for a large-scale rotating space station.

[0009] To achieve the above purpose, the technical scheme adopted by the present application is as follows:

[0010] In a first aspect, a large-scale simulated gravity system is provided, comprising a power runner working cabin, an I-type gravity field simulation cabin and a II-type gravity field simulation cabin.

[0011] The power rotating wheel working cabin comprises a sealed working cabin, a motor, a foldable outboard solar wing and a docking interface device;

[0012] The motor is arranged in the sealed working cabin, and an electric rotating shaft is arranged at an output end of the motor; a plurality of rotating shaft connecting rods are arranged circumferentially and perpendicularly to an axial direction of the electric rotating shaft; and a rotating wheel is connected through the plurality of rotating shaft connecting rods; the rotating wheel is a polygonal structure composed of a plurality of rotating wheel connecting rods, wherein at least part of the rotating wheel connecting rods that are not connected with the rotating shaft connecting rods are provided with connecting rod locking interfaces for connecting the I-type gravity field simulation cabin;

[0013] The I-type gravity field simulation cabin and the II-type gravity field simulation cabin both comprise a gravity field simulation cabin, and a head docking interface and a tail docking interface are arranged at two ends of the gravity field simulation cabin respectively to support the connection between the cabin bodies;

[0014] A foldable solar wing device is arranged on a circumferential side of the gravity field simulation cabin close to the head docking interface, and a gravity field simulation cabin forward docking interface for realizing the on-orbit docking of a carrier spaceship is arranged;

[0015] The I-type gravity field simulation cabin is connected with the rotating wheel connecting rod through a turnover mechanism at a middle part of an outer side of the gravity field simulation cabin, and the rotating wheel connecting rod is used for connecting with the connecting rod locking interface of the rotating wheel;

[0016] The rotating wheel connecting rod is formed to realize the turnover movement from parallel to the length direction of the gravity field simulation cabin to perpendicular to the length direction of the gravity field simulation cabin through the turnover mechanism;

[0017] The I-type gravity field simulation cabin and the II-type gravity field simulation cabin are connected to form a polyhedral structure.

[0018] In a first possible implementation manner of the first aspect, the gravity field simulation cabin of the I-type gravity field simulation cabin is provided with a turning mechanism interface for capturing a turning mechanism at a position close to the head docking interface, and the turning mechanism is arranged in the II-type gravity field simulation cabin.

[0019] In a second possible implementation manner of the first aspect, the gravity field simulation cabin of the I-type gravity field simulation cabin and the II-type gravity field simulation cabin is provided with a double-layer cabin body structure at a part close to the tail docking interface;

[0020] The double-layer cabin body structure comprises an outer cabin body and an inner cabin body, the tail docking interface is arranged at one end of the inner cabin body, a metal soft cylindrical pipe is arranged at the other end of the inner cabin body, the metal soft cylindrical pipe is communicated with the gravity field simulation cabin, the outer cabin body is wrapped outside the inner cabin body and the metal soft cylindrical pipe and is connected with the gravity field simulation cabin as a whole, an outer cabin body opening is arranged at an end of the outer cabin body, the tail docking interface is arranged to protrude from the outer cabin body opening and forms a structure for supporting the connection at an angle of 30° with an adjacent gravity field simulation cabin.

[0021] In a third possible implementation manner of the first aspect, based on the first possible implementation manner of the first aspect, the rotating mechanism is arranged on the double-layer cabin structure of the II-type gravity field simulation cabin, and the rotating mechanism is selectively locked by a rotating mechanism parking device arranged on the gravity field simulation cabin.

[0022] In a fourth possible implementation manner of the first aspect, the docking interface device is rotatably connected to the end of the sealed working cabin away from the rotating wheel, and the docking interface device includes five docking interfaces, i.e., a forward docking interface, a rearward docking interface, a skyward docking interface, a left-side docking interface, and a right-side docking interface.

[0023] In a fifth possible implementation manner of the first aspect, based on any possible implementation manner of the first aspect, the I-type gravity field simulation cabin and the II-type gravity field simulation cabin are connected to form an at least 12-sided structure.

[0024] The large-scale simulated gravity system has the following advantages:

[0025] The large-scale simulated gravity system provided by the application can be continuously and sustainably ensured to operate for a long time by the carrier spacecraft, the on-orbit construction method based on the system can shorten the system construction period, and the maintenance method can ensure the reliability and availability of the system for long-term on-orbit operation.

[0026] The system capacity can be continuously expanded, the system scale is large, a plurality of carrier spacecraft can be docked at the same time, and the practicability is high.

[0027] The system can be continuously updated, thereby ensuring long-life use of the system, a large-scale and long-life on-orbit large-scale gravity field simulation environment can be obtained after assembly, the system can be expanded from a 12-sided polygonal structure to a 16-, 20- or even more-sided polygonal structure, and the expansibility is good.

[0028] The power rotating wheel working cabin is used as a power output platform, and orbit maneuvering and multi-orbit operation can be realized. BRIEF DESCRIPTION OF DRAWINGS

[0029] Figure 1 An on-orbit flight schematic diagram of a large-scale simulated gravity system provided by an embodiment of the application;

[0030] Figure 2 A schematic diagram of rocket loading and upward movement provided by an embodiment of the application;

[0031] Figure 3 An on-orbit installation flowchart of a large-scale simulated gravity system provided by an embodiment of the application;

[0032] Figure 4 A schematic diagram of a carrier spacecraft provided by an embodiment of the application;

[0033] Figure 5A multi-ship carrying spaceship and simulated gravity system on-orbit docking schematic provided for the embodiments of the present application;

[0034] Figure 6 A large simulated gravity system on-orbit replacement process schematic provided for the embodiments of the present application;

[0035] Figure 7 A double-layer cabin body structure schematic of a gravity field simulation cabin provided for the embodiments of the present application;

[0036] Figure 8 A turning mechanism working process schematic provided for the embodiments of the present application.

[0037] Reference signs:

[0038] 1-sealing working cabin; 2-electric rotating shaft; 3-rotating shaft connecting rod; 4-rotating wheel; 5-rotating wheel connecting rod; 6-gravity field simulation cabin; 7-head docking interface; 8-tail docking interface; 9-solar wing device; 10-gravity field simulation cabin forward docking interface; 11-leftward docking interface; 12-forward docking interface; 13-skyward docking interface; 14-rightward docking interface; 15-backward docking interface; 16-carrying spaceship head fairing; 17-outer space solar wing; 18-carrying spaceship docking device; 19-connecting rod docking interface; 20-rotating wheel connecting rod; 22-outer cabin body; 23-outer cabin body opening; 24-turning mechanism parking device; 26-inner cabin body; 27-metal soft cylindrical pipe; 29-turning mechanism. DETAILED DESCRIPTION

[0039] In order to further clarify the technical means and effects taken by the present application to achieve the predetermined purpose, the technical solutions in the embodiments of the present application are described clearly. Obviously, the described embodiments are part of the embodiments of the present application, not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art belong to the scope of protection of the present application.

[0040] The terms "first", "second", etc. in the specification and claims of the present application are used to distinguish similar objects, not to describe a specific order or sequence. It should be understood that the terms used in this way can be interchanged under appropriate circumstances, so that the embodiments of the present application can be implemented in an order other than those illustrated or described herein, and the objects distinguished by "first", "second", etc. are usually a class, not limited to the number of objects, for example, the first object can be one or more. In addition, "and / or" in the specification and claims means at least one of the connected objects, and the character " / ", generally indicates that the front and rear associated objects are in an "or" relationship.

[0041] The description of the method flow in the specification of the present application and the steps of the flowchart in the drawings of the present application are not necessarily strictly executed in the order of the steps, and the method steps can change the execution order. Moreover, some steps can be omitted, a plurality of steps can be combined into one step, and / or one step can be divided into a plurality of steps.

[0042] The large-scale simulated gravity system and the on-orbit construction and maintenance method thereof provided by the embodiments of the present application will be described in detail below in combination with the drawings and preferred embodiments.

[0043] To solve a series of problems such as on-orbit operation and maintenance of the large-scale simulated gravity system, and to solve the problem of on-orbit material supplement, a large-scale simulated gravity system and an on-orbit construction and maintenance method thereof are provided.

[0044] The large-scale simulated gravity system is composed of a power runner working cabin, an I-type gravity field simulation cabin, a II-type gravity field simulation cabin, and a carrier spaceship, and is launched into orbit by multiple carrier rockets in batches and finally assembled into a 12-sided expandable structure (which can be expanded to 16, 20, and other polygons in the future) in orbit. The system generates centrifugal force to simulate gravity by rotation (the rotation speed is 4 r / min, and the target gravity is 1g), while supporting orbit maneuvering, on-orbit maintenance, and function expansion.

[0045] The large-scale simulated gravity system of the embodiments of the present application will be described in detail below.

[0046] The large-scale simulated gravity system of the embodiments of the present application includes a power runner working cabin, an I-type gravity field simulation cabin, and a II-type gravity field simulation cabin.

[0047] Please refer to Figure 1 , which shows the power runner working cabin; the power runner working cabin includes a sealed working cabin 1, a motor, foldable outboard solar wings, and a docking port device;

[0048] The motor is arranged in the sealed working cabin 1, and the motor output end is provided with an electric rotating shaft 2, a plurality of rotating shaft connecting rods 3 are arranged circumferentially and perpendicularly to the axial direction of the electric rotating shaft 2, and a rotating wheel 4 is connected through the plurality of rotating shaft connecting rods 3; the rotating wheel 4 is a polygonal structure composed of a plurality of rotating wheel connecting rods 5, wherein at least part of the rotating wheel connecting rods 5 that are not connected with the rotating shaft connecting rods 3 are provided with a connecting rod locking interface for connecting the I-type gravity field simulation cabin;

[0049] The docking port device is rotatably connected to the end of the sealed working cabin 1 away from the rotating wheel 4, and is used for docking a spaceship or a space cabin; the docking port device includes five docking ports, i.e., a leftward docking port 11, a forward docking port 12, a skyward docking port 13, a rightward docking port 14, and a rearward docking port 15.

[0050] In the embodiment, the sealed working cabin 1 is used for astronauts to stay on orbit, and the motor for driving the whole gravity field to rotate is arranged in the cabin, so that the working environment is good, and the motor is easy to maintain and repair. When the power wheel working cabin goes up, the outer solar wing is folded and collected, and after entering the orbit, the outer solar wing is unfolded to provide power for the working cabin. The sealed working cabin 1 is connected with the electric rotating shaft 2 through the motor transmission device, the motor rotating shaft is connected with the rotating wheel 4 through the rotating shaft connecting rod 3, the motor and the motor transmission device are driven to rotate through the power supply of the outer solar wing, the rotating wheel 4 is driven to rotate, and the power wheel working cabin can provide power and control for orbit maintenance and orbit change of the whole system. The propellant can be transported by the carrier spaceship, and the astronauts can add the propellant on orbit. The sealed working cabin 1 has five docking interfaces, including a front interface, a rear interface, a sky interface, a left side interface and a right side interface, and can be connected with five spaceships or space cabins at the same time. The spaceship or the space cabin is generally connected with the sealed working cabin 1 through the rear interface, and the position of the spaceship or the space cabin is changed through the position changing mechanism 29 on the sealed working cabin 1. When flying on orbit, the sealed working cabin 1 is perpendicular to the flight direction of the system, and the rotating wheel 4 is parallel to the flight direction of the system.

[0051] Please refer to Figure 1 , which shows the I-type gravity field simulation cabin. The I-type gravity field simulation cabin includes a gravity field simulation cabin 6, and a rotating wheel connecting rod 5 is connected to the middle part of the outer side of the gravity field simulation cabin 6 through a turnover mechanism. The rotating wheel connecting rod 5 is used to be connected with the connecting rod locking interface of the rotating wheel 4.

[0052] The gravity field simulation cabin 6 is provided with a head docking interface 7 and a tail docking interface 8 at two ends respectively, which are used to support the connection between the cabin bodies.

[0053] The gravity field simulation cabin 6 is provided with a foldable solar wing device 9 on the side close to the head docking interface 7, and a gravity field simulation cabin front docking interface 10 for realizing the on-orbit docking of the carrier spaceship.

[0054] The rotating wheel connecting rod 5 is turned over from parallel to the length direction of the gravity field simulation cabin 6 to vertical through the turnover mechanism,

[0055] The part close to the tail docking interface 8 of the gravity field simulation cabin 6 is a double-layer cabin structure, please refer to Figure 7 , which shows the double-layer cabin structure. The double-layer cabin structure includes an outer cabin body 22 and an inner cabin body 26. The tail docking interface 8 is arranged at one end of the inner cabin body 26. A metal soft cylindrical pipe 27 is arranged at the other end of the inner cabin body 26. The metal soft cylindrical pipe 27 is communicated with the gravity field simulation cabin 6. The outer cabin body 22 is wrapped outside the inner cabin body 26 and the metal soft cylindrical pipe 27 and is connected with the gravity field simulation cabin 6 as a whole. The outer cabin body 22 is provided with an outer cabin body 22 opening 23 at the end. The tail docking interface 8 extends out of the outer cabin body 22 opening 23 and forms a structure for supporting the connection with the II-type gravity field simulation cabin at an angle of 30°.

[0056] The gravity field simulation cabin 6 is provided with a rotation mechanism 29 interface for capturing the rotation mechanism 29 near the head docking interface 7, and the rotation mechanism 29 is arranged in the II-type gravity field simulation cabin.

[0057] Please refer to Figure 1 , which shows the II-type gravity field simulation cabin; the II-type gravity field simulation cabin is the same as the I-type gravity field simulation cabin, including the gravity field simulation cabin 6, and the gravity field simulation cabin 6 is provided with a head docking interface 7 and a tail docking interface 8 at both ends, respectively, for supporting the connection between the cabin bodies.

[0058] The gravity field simulation cabin 6 is provided with a foldable solar wing device 9 near the circumferential side of the head docking interface 7, and a forward docking interface 10 of the gravity field simulation cabin for realizing the on-orbit docking of the carrier spaceship.

[0059] The part of the gravity field simulation cabin 6 near the tail docking interface 8 is a double-layer cabin structure, including an outer cabin body 22 and an inner cabin body 26, and the tail docking interface 8 is arranged at one end of the inner cabin body 26. The inner cabin body 26 is provided with a metal soft cylindrical tube 27 at the other end, which is communicated with the gravity field simulation cabin 6. The outer cabin body 22 is wrapped outside the inner cabin body 26 and the metal soft cylindrical tube 27 and connected with the gravity field simulation cabin 6 as a whole. The outer cabin body 22 is provided with an outer cabin body 22 opening 23 at the end, and the tail docking interface 8 extends out of the outer cabin body 22 opening 23 and forms a structure for supporting the connection at an angle of 30° with the II-type gravity field simulation cabin or the I-type gravity field simulation cabin.

[0060] Compared with the I-type gravity field simulation cabin, the II-type gravity field simulation cabin is not provided with a rotating wheel connecting rod 5, but is also provided with a rotation mechanism 29 on the double-layer cabin structure. Specifically, the II-type gravity field simulation cabin is provided with a rotation mechanism 29 on the double-layer cabin structure, and the rotation mechanism 29 is selectively locked by the rotation mechanism 29 parking device 24 arranged in the gravity field simulation cabin 6.

[0061] The I-type gravity field simulation cabin and the II-type gravity field simulation cabin are connected to form a polyhedral structure, and the polyhedral structure is rotated by the power rotating wheel working cabin to form a gravity simulation field. The I-type gravity field simulation cabin and the II-type gravity field simulation cabin provide living and experimental space for astronauts.

[0062] In the implementation process, the power rotating wheel working cabin is launched into orbit by the first launch rocket. The I-type gravity field simulation cabin is launched into orbit by the second launch rocket. After the I-type gravity field simulation cabin is launched into orbit, the rotating wheel connecting rod 5 is unlocked, opened by 90 degrees, locked, and then the rotating wheel 4 is stopped. At this time, the connecting rod locking interface on one side of the rotating wheel 4 needs to be kept facing the I-type gravity field simulation cabin. After the simulation cabin captures the interface, the on-orbit connection and locking are completed. There are four I-type gravity field simulation cabins, and each I-type simulation cabin is separated by 90 degrees. After one I-type gravity field simulation cabin is installed, the rotating wheel 4 is rotated by 90 degrees, and the four I-type gravity field simulation cabins are sequentially installed in place. At this time, the solar wings of the simulation cabins are unlocked but not unfolded. After the II-type gravity field simulation cabin is completely installed, the solar wings are unfolded. The II-type gravity field simulation cabin is launched into orbit by the third launch rocket. The rotating wheel 4 is rotated to a position where the I-type gravity field simulation cabin docking interface is in a horizontal position, and then stopped. The II-type gravity field simulation cabin is close, captured, and connected. The II-type gravity field simulation cabin is rotated by 30 degrees by using the rotating mechanism 29 and locked (see Figure 8 When the II-type gravity field simulation cabin is connected and locked with the I-type gravity field simulation cabin, the rotating mechanism 29 is unlocked and rotated to be coaxial with the I-type gravity field simulation cabin. The rotating mechanism 29 is captured and locked with the interface on the I-type gravity field simulation cabin. After the rotating mechanism 29 is rotated by 30 degrees around the rotating shaft on the II-type gravity field simulation cabin and locked, the rotating mechanism 29 is locked in position. The rotating wheel 4 is rotated again to rotate the just-installed II-type gravity field simulation cabin to be parallel to the flight direction, and then stopped. The next II-type gravity field simulation cabin is close, captured, and connected. The II-type gravity field simulation cabin is rotated by 30 degrees by using the rotating mechanism 29 and locked. The above process is performed until the eight II-type gravity field simulation cabins are installed. Then, the solar wings of the total 12 gravity field simulation cabins (four I-type and eight II-type) are unfolded.

[0063] The carrier spaceship is used for personnel and cargo transportation after the system is built. The carrier spaceship can be connected with the power rotating wheel working cabin or the docking interface (the gravity field simulation cabin forward docking interface 10) on the gravity field simulation cabin. The on-orbit connection can be completed by using the existing rendezvous and docking technology. When the carrier spaceship is connected with the gravity field simulation cabin, the carrier spaceship is also in the simulated gravity field environment while the rotating wheel 4 is rotating. The carrier spaceship has the ability to go to space and return to the earth, and can be reused.

[0064] The on-orbit construction and maintenance method of the large-scale simulation gravity system in the embodiment of the application is described in detail below.

[0065] Referring to Figure 3 The on-orbit construction method of the large-scale simulation gravity system in the embodiment of the application is based on the above large-scale simulation gravity system and includes the following steps.

[0066] Step S1, the power rotating wheel working cabin goes up with the first launch rocket, and after entering the orbit, the solar wing is unfolded, and the motor drives the rotating wheel.

[0067] Specifically, the power rotating wheel working cabin goes up with the first launch rocket, as shown in Figure 2 , and after entering the orbit, it is separated from the rocket, and the power rotating wheel working cabin rotates at an angular velocity of 4r / min by the motor driving the rotating wheel 4.

[0068] Step S2, the four I-type gravity field simulation cabins go up with the second launch rocket, and after each gravity field simulation cabin enters the orbit, the rotating wheel connecting rod is unlocked and unfolded by 90°, and is locked with the rotating wheel of the power rotating wheel working cabin; every time one I-type gravity field simulation cabin is installed, the rotating wheel rotates by 90°.

[0069] Specifically, the four I-type gravity field simulation cabins go up with the second launch rocket, as shown in Figure 2 , and after entering the orbit, they are sequentially separated from the rocket, and the first I-type gravity field simulation cabin is separated from the rocket to a safe distance, the rotating wheel connecting rod 5 is unlocked, the rotating wheel connecting rod 5 is rotated from parallel to the sealed cabin body to perpendicular to the sealed cabin body, and the I-type gravity field simulation cabin is installed. The cabin flies and approaches the rotating wheel 4, the power rotating wheel working cabin rotates the rotating wheel 4 in advance, so that the connecting rod docking port 19 on the rotating wheel 4 stays at the position of the rotating wheel connecting rod 5 on the I-type gravity field simulation cabin, and the power rotating wheel working cabin stops rotating the rotating wheel 4; the rotating wheel connecting rod 5 on the I-type gravity field simulation cabin is docked and locked with the rotating wheel 4, and the installation of the first I-type gravity field simulation cabin is completed; then the power rotating wheel working cabin rotates the rotating wheel 4 again, and the installation process of the first I-type gravity field simulation cabin is sequentially completed. The on-orbit installation of the second to fourth I-type gravity field simulation cabins is completed.

[0070] Step S3, eight II-type gravity field simulation cabins go up with the third launch rocket; the rotating wheel is adjusted to the tail docking port 8 of the I-type gravity field simulation cabin, which stops at the position of the head docking port of the first II-type gravity field simulation cabin flying in place, and after the head docking port of the II-type gravity field simulation cabin is docked and locked with the tail docking port of the I-type gravity field simulation cabin, the first II-type gravity field simulation cabin is rotated by 30° to the system center shaft direction by the indexing mechanism and locked.

[0071] The rotating wheel 4 is adjusted to the tail docking port of the first II-type gravity field simulation cabin, which stops at the position of the head docking port of the second II-type gravity field simulation cabin flying in place, and after docking, the second II-type gravity field simulation cabin is rotated by 30° to the system center shaft direction by the indexing mechanism and locked.

[0072] The third, fifth, and seventh type II gravity field simulation cabin installation steps are the same as the first type II gravity field simulation cabin installation step; the fourth, sixth, and eighth type II gravity field simulation cabin installation steps are the same as the second type II gravity field simulation cabin installation step.

[0073] Specifically, the type II gravity field simulation cabins (a total of eight) are launched into space by the third launch vehicle, see Figure 2 , and are separated from the launch vehicle in turn after entering orbit. The first type II gravity field simulation cabin is in a head-to-head docking interface 7 facing forward and parallel to the flight direction, and the solar wing is unlocked but not opened. The power rotating wheel working cabin rotates a certain type I gravity field simulation cabin connected to the rotating wheel 4 to a horizontal state in advance, so that the tail docking interface 8 stops at a position directly opposite the head docking interface 7 of the type II gravity field simulation cabin flying horizontally. The head docking interface 7 of the type II gravity field simulation cabin is docked and locked with the tail docking interface 8 of the type I gravity field simulation cabin. The tail position mechanism 29 of the type I gravity field simulation cabin is horizontally rotated 30° toward the central rotating shaft, and then the position mechanism 29 is locked.

[0074] The second type II gravity field simulation cabin is separated from the launch vehicle. The type II gravity field simulation cabin is in a head-to-head docking interface 7 facing forward and parallel to the flight direction, and the solar wing is unlocked but not opened. The power rotating wheel working cabin stops the tail docking interface 8 of the first type II gravity field simulation cabin at a position directly opposite the head docking interface 7 of the second type II gravity field simulation cabin flying horizontally in advance. The head docking interface 7 of the type II gravity field simulation cabin is docked and locked with the tail docking interface 8 of the first type II gravity field simulation cabin. The tail position mechanism 29 of the first type II gravity field simulation cabin is horizontally rotated 30° toward the central rotating shaft, and is docked and locked with the head docking interface 7 of the adjacent second type I gravity field simulation cabin.

[0075] Step S4: When all the gravity field simulation cabins are installed, the solar wings of all the cabins are unfolded to form a complete 12-faced structure.

[0076] Specifically, the third, fifth, and seventh type II gravity field simulation cabin installation processes are the same as the first type II gravity field simulation cabin installation process; the fourth, sixth, and eighth type II gravity field simulation cabin installation processes are the same as the second type II gravity field simulation cabin installation process; when all the simulation cabins are installed to form a complete 12-faced structure, the solar wings of all the simulation cabins are unfolded and locked in turn.

[0077] The method can be launched into orbit by a 3-launch vehicle, and a 12-faced (expandable) spacecraft structure is formed by on-orbit docking and assembly. The entire simulation gravity system is driven by a motor to rotate at a speed of 4 r / min, generating a gravity of 1g.

[0078] Further, referring to 5, the embodiment of the present application provides a method for on-orbit docking of a carrier spacecraft, comprising:

[0079] Step A1, the carrier spacecraft is launched into orbit by a rocket;

[0080] Step A2, the power turbine working cabin rotates the rotating wheel to make the forward docking interface of a certain gravity field simulation cabin face the flight direction of the carrier spacecraft, and then stops rotating the rotating wheel 4;

[0081] Step A3, the carrier spacecraft completes docking and locking with the gravity field simulation cabin through the docking device, and rotates with the rotating wheel.

[0082] The carrier spacecraft is launched into orbit by a rocket, approaches the simulated gravity system, unlocks the head fairing 16 of the carrier spacecraft (see Figure 4 ), rotates and opens the fairing to the locked position, the power turbine working cabin rotates the rotating wheel 4 to make the forward docking interface on a certain gravity field simulation cabin face the flight direction of the carrier spacecraft, and then stops rotating the rotating wheel 4; the carrier spacecraft captures the forward docking interface on the gravity field simulation cabin through the docking device 18, approaches and completes docking and locking.

[0083] Further, referring to Figure 6 , the embodiment of the present application provides a method for on-orbit maintenance of a large simulated gravity system, which is based on the above-mentioned large simulated gravity system for on-orbit maintenance, comprising:

[0084] Step B1, stop the rotating wheel at a position where the axial direction of the faulty gravity field simulation cabin is parallel to the flight direction;

[0085] Step B2, unlock the tail docking interface of the faulty gravity field simulation cabin, and rotate the tail positioning mechanism of the gravity field simulation cabin connected to the head of the faulty gravity field simulation cabin by 30° away from the center shaft direction;

[0086] Step B3, rotate the rotating wheel 4 while unlocking the head docking interface of the faulty gravity field simulation cabin, and complete the separation of the faulty gravity field simulation cabin.

[0087] Step B4, replace the new gravity field simulation cabin according to the above-mentioned on-orbit construction method.

[0088] When a certain gravity field simulation cabin needs to be replaced on-orbit due to a major failure, stop the power output of the power turbine working cabin, stop the rotating wheel 4 at a position where the axial direction of the faulty gravity field simulation cabin is parallel to the flight direction, unlock the tail docking interface 8 of the faulty gravity field simulation cabin, rotate the tail positioning mechanism 29 of the gravity field simulation cabin connected to the head of the faulty gravity field simulation cabin by 30° away from the center shaft direction, rotate the rotating wheel 4 while unlocking the head docking interface 7 of the faulty gravity field simulation cabin, and complete the separation of the faulty gravity field simulation cabin. The installation process of the replaced gravity field simulation cabin is the same as the above-mentioned on-orbit construction method.

[0089] Through the method, each cabin in the system can be replaced in orbit as a whole, a long-term stable large non-weightlessness environment can be provided, orbit change maneuver can be realized, the mission compatibility and usability of the system are improved, the on-orbit service life of the system is prolonged, and the use efficiency of the system is improved.

[0090] Based on the technical scheme, the application provides an on-orbit construction and maintenance method of a large simulated gravity system, and has the following advantages:

[0091] 1. The large simulated gravity system and the on-orbit construction and maintenance method thereof provided by the application are mainly constructed by a power runner working cabin, an I-type gravity field simulation cabin and a II-type gravity field simulation cabin, the whole system can be continuously and stably ensured to operate by a carrier spaceship, the on-orbit construction method can shorten the construction period of the system, and the maintenance method can ensure the reliability and usability of the long-term on-orbit operation of the system.

[0092] 2. The on-orbit construction and maintenance method provided by the application can realize continuous expansion of the system capacity, the system has a large scale, can be docked with multiple carrier spaceships at the same time, and has high practicability; the maintenance and replacement of any gravity field simulation cabin can be realized, and the maintainability is good.

[0093] 3. The method provided by the application supports continuous updating of the system, thereby ensuring long-life use of the system, a large-scale and long-life on-orbit large gravity field simulation environment can be obtained after assembly, and the method has good expansibility and can be expanded from a 12-sided polygon to a 16-, 20- or even more-sided polygon.

[0094] 4. The method provided by the application uses the power runner working cabin as a power output platform, and can realize orbit maneuver and multi-orbit operation.

[0095] It should be noted that in this document, the terms "comprising", "containing", or any other variant thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements not only includes those elements, but also includes other elements not explicitly listed, or inherent to such a process, method, article or apparatus. Without more limitations, the element defined by the statement "comprising a" does not exclude the presence of additional identical elements in the process, method, article or apparatus that includes the element. In addition, it should be pointed out that the scope of the methods and devices in the embodiments of the application is not limited to performing functions in the order shown or discussed, but can also include performing functions in a substantially simultaneous manner or in reverse order, for example, the described method can be performed in an order different from that described, and various steps can also be added, omitted or combined. In addition, the features described with reference to certain examples can be combined in other examples.

[0096] It can be understood that the embodiments of the present application are described above in conjunction with the drawings, but the present application is not limited to the specific embodiments described above, and the specific embodiments described above are only illustrative but not restrictive, and various changes or equivalent replacements can be made to the features and embodiments without departing from the spirit and scope of the present application, which are known to those skilled in the art. In addition, under the inspiration or teaching of the present application, those skilled in the art can modify the features and embodiments to adapt to specific conditions and materials without departing from the spirit and scope of the present application. Therefore, the present application is not limited by the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of the present application are within the scope of protection of the present application.

Claims

1.A large-scale simulated gravity system, characterized in that, it comprises a power rotating wheel working cabin, an I-type gravity field simulation cabin and a II-type gravity field simulation cabin; the power rotating wheel working cabin comprises a sealed working cabin, a motor, foldable cabin-outside solar wings and a docking port device; the motor is arranged in the sealed working cabin, and an electric rotating shaft is arranged at the output end of the motor, a plurality of rotating shaft connecting rods are arranged circumferentially and perpendicularly to the axial direction of the electric rotating shaft, and a rotating wheel is connected through the plurality of rotating shaft connecting rods; the rotating wheel is a polygonal structure composed of a plurality of rotating wheel connecting rods, wherein at least part of the rotating wheel connecting rods that are not connected with the rotating shaft connecting rods are provided with connecting rod locking interfaces for connecting the I-type gravity field simulation cabin; the I-type gravity field simulation cabin and the II-type gravity field simulation cabin each comprise a gravity field simulation cabin, and a head docking port and a tail docking port are arranged at both ends of the gravity field simulation cabin respectively for supporting the connection between cabin bodies; a foldable solar wing device is arranged on the circumferential side of the gravity field simulation cabin close to the head docking port, and a gravity field simulation cabin forward docking port for realizing the on-orbit docking of a carrier spacecraft is arranged; wherein the middle part of the outer side of the gravity field simulation cabin of the I-type gravity field simulation cabin is connected with a rotating wheel connecting rod through a turnover mechanism, and the rotating wheel connecting rod is used for connecting with the connecting rod locking interface of the rotating wheel; the structure of the rotating wheel connecting rod is formed by the turnover mechanism to realize the turnover motion from parallel to the length direction of the gravity field simulation cabin to vertical; the I-type gravity field simulation cabin and the II-type gravity field simulation cabin are connected to form a polyhedral structure. 2.The large-scale simulated gravity system according to claim 1, characterized in that, the position of the gravity field simulation cabin of the I-type gravity field simulation cabin close to the head docking port is provided with a turning mechanism interface for capturing a turning mechanism, and the turning mechanism is arranged in the II-type gravity field simulation cabin. 3.The large-scale simulated gravity system according to claim 1, characterized in that, the part of the gravity field simulation cabin of the I-type gravity field simulation cabin and the II-type gravity field simulation cabin close to the tail docking port is a double-layer cabin structure; the double-layer cabin structure comprises an outer cabin body and an inner cabin body, the tail docking port is arranged at one end of the inner cabin body, a metal soft cylindrical tube is arranged at the other end of the inner cabin body, the metal soft cylindrical tube is communicated with the gravity field simulation cabin, the outer cabin body is wrapped outside the inner cabin body and the metal soft cylindrical tube and is connected with the gravity field simulation cabin as a whole, an outer cabin body opening is arranged at the end of the outer cabin body, the tail docking port extends out of the outer cabin body opening, and a structure for supporting the connection between adjacent gravity field simulation cabins at an angle of 30° is formed. 4.The large-scale simulated gravity system according to claim 2, characterized in that, the turning mechanism is arranged on the double-layer cabin structure of the II-type gravity field simulation cabin and is selectively locked by a turning mechanism parking device arranged in the gravity field simulation cabin. 5.The large-scale simulated gravity system according to claim 1, characterized in that, the docking port device is rotatably connected to the end of the sealed working cabin away from the rotating wheel, and the docking port device comprises five docking ports, i.e., a forward docking port, a rearward docking port, a skyward docking port, a left-side docking port and a right-side docking port. 6.The large-scale simulated gravity system according to any one of claims 1-5, characterized in that, The type I gravity field simulation chamber and the type II gravity field simulation chamber are connected to form an at least 12-faced structure.

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