Large simulation gravity system and on-orbit construction and maintenance method thereof

Abstract

The invention discloses a large-scale simulation gravity system and an on-orbit construction and maintenance method thereof. The 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 is provided with an indexing mechanism interface for capturing the indexing mechanism, and the indexing mechanism is arranged in the II-type gravity field simulation cabin; 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 invention relates to the technical field of spacecraft design and on-orbit construction, and in particular to a large-scale simulated gravity system and an on-orbit construction and maintenance method thereof. Background Art

[0002] As human beings continue to explore space, long-term work and life in orbit have become possible. The continuous stay in orbit has increased from a few days to half a year, and the longest record has even exceeded one year. With the advancement of human deep space exploration missions, the physiological hazards of weightlessness caused by astronauts' long-term stay in orbit have become increasingly prominent. Building a space capsule that can generate artificial gravity is one of the means to simulate gravity.

[0003] Related gravity simulation technology: 1. Linear acceleration scheme: Use linear acceleration to simulate gravity. That is, the spacecraft flies at an acceleration of ±1g during the flight. The overload on the astronauts will always be maintained at 1g, and there will be no weightlessness. However, the propellant consumption is huge and it is only suitable for short-term missions.

[0004] 2. Reverse magnetic gravity scheme: using reverse magnetic mechanism to generate artificial gravity, but the reverse magnetic device needs to keep the magnetic field free from any interference from other magnetic devices, and also needs to carry several tons of magnets to create a low-temperature superconducting environment, which makes this scheme not feasible on the existing spacecraft platform; 3. Short-arm centrifuge solution: The short-arm centrifuge device installed by the Russian Energia Rocket Company on the International Space Station uses the centrifugal force generated by rotation to simulate gravity. However, the device can only generate gravity locally when the centrifuge is running and cannot provide a continuous weightless environment for the entire cabin.

[0005] In response to the above problems, the international aerospace community has proposed building a large rotating space station to generate continuous artificial gravity. However, the traditional single-launch integral structure is limited by the size of the launch vehicle fairing and is difficult to achieve the requirement of a 100-meter rotation radius. Existing on-orbit assembly technology mostly uses a truss expansion mode, which makes it difficult to replace the cabin and achieve efficient coordination of gravity generation, system maintenance and mission expansion. Summary of the invention

[0006] The present invention provides a large-scale simulated gravity system and an on-orbit construction and maintenance method thereof, which solves the problem of how a large-scale rotating space station can achieve efficient coordination of gravity generation, system maintenance and mission expansion.

[0007] In order to achieve the above objectives, this application adopts the following technical solutions: In a first aspect, a large-scale simulated gravity system is provided, including a power wheel working cabin, a type I gravity field simulation cabin, and a type II gravity field simulation cabin; The power wheel working cabin includes a sealed working cabin, a motor, a foldable outboard solar wing and a docking device; The motor is arranged in a sealed working cabin, an electric shaft is arranged at the output end of the motor, a plurality of shaft connecting rods are arranged in the circumferential direction of the electric shaft perpendicular to the axial direction of the electric shaft, and a rotating wheel is connected through the plurality of shaft connecting rods; the rotating wheel is a polygonal structure composed of a plurality of rotating wheel connecting rods, wherein at least some of the rotating wheel connecting rods that are not connected to the shaft connecting rods are provided with a connecting rod locking interface for connecting to the I-type gravity field simulation cabin; Both the Type I gravity field simulation cabin and the Type II gravity field simulation cabin include a gravity field simulation cabin, and the two ends of the gravity field simulation cabin are respectively provided with a head docking port and a tail docking port for supporting the connection between cabin bodies; A foldable solar wing device is arranged on the peripheral side of the gravity field simulation cabin near the head docking port, and a forward docking port of the gravity field simulation cabin for realizing on-orbit docking of the carrier spacecraft; Among them, the middle part of the outer side of the gravity field simulation cabin of the type I gravity field simulation cabin is connected with a rotating wheel connecting rod through a flip mechanism, and the rotating wheel connecting rod is used to connect with the connecting rod locking interface of the rotating wheel; The rotating wheel connecting rod realizes the flipping movement from parallel to the length direction of the gravity field simulation cabin to vertical through the flipping mechanism. A position of the gravity field simulation cabin of the type I gravity field simulation cabin near the head docking interface is provided with a transfer mechanism interface for capturing the transfer mechanism, and the transfer mechanism is provided in the type II gravity field simulation cabin; The Type I gravity field simulation cabin supports a 30° connection with the Type II gravity field simulation cabin; The Type I gravity field simulation cabin and the Type II gravity field simulation cabin are connected to form a polyhedron structure, and the polyhedron structure is driven to rotate by the power wheel working cabin to form a gravity simulation field.

[0008] In a first possible implementation of the first aspect, a portion of the gravity field simulation cabin of the type I gravity field simulation cabin and the type II gravity field simulation cabin near the tail docking port is a double-layer cabin structure; The double-layer cabin structure includes an outer cabin and an inner cabin, a tail docking port is arranged at one end of the inner cabin, a metal soft cylindrical tube is arranged at the other end of the inner cabin, the metal soft cylindrical tube is connected to the gravity field simulation cabin, the outer cabin is wrapped around the inner cabin and the metal soft cylindrical tube and is connected to the gravity field simulation cabin as a whole, an outer cabin opening is arranged at the end of the outer cabin, the tail docking port extends out from the outer cabin opening, and forms a structure for supporting a 30° connection with an adjacent gravity field simulation cabin.

[0009] Based on the first possible implementation of the first aspect, in a second possible implementation of the first aspect, the transfer mechanism is provided on the double-layer cabin structure of the Type II gravity field simulation cabin, and the transfer mechanism can be selectively locked by a transfer mechanism parking device arranged on the gravity field simulation cabin.

[0010] In a third possible implementation 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 is used to dock a spacecraft or a space capsule. The docking interface device includes five docking interfaces: forward, rearward, skyward, left and right.

[0011] Based on any possible implementation of the first aspect, in a fourth possible implementation of the first aspect, when flying in orbit, the axial direction of the sealed working cabin is perpendicular to the flight direction of the system, and the circumference of the rotating wheel is parallel to the flight direction of the system.

[0012] In a second aspect, a method for on-orbit construction of a large-scale simulated gravity system is provided, and on-orbit construction is performed based on the large-scale simulated gravity system as described in the first aspect, comprising: The power wheel working cabin goes up with the first rocket, unfolds the solar panels after entering orbit, and starts the motor to drive the rotating wheel; Four Type I gravity field simulation cabins were launched upward with the second rocket. After each gravity field simulation cabin entered orbit, the rotating wheel connecting rod was unlocked and unfolded 90°, docked and locked with the rotating wheel of the power wheel working cabin; each time a Type I gravity field simulation cabin was installed, the rotating wheel rotated 90°; Eight Type II gravity field simulation cabins are launched upward with the third rocket; the rotating wheel is adjusted to the tail docking port of the Type I gravity field simulation cabin to stop at the head docking port position facing the first Type II gravity field simulation cabin in level flight, and after the head docking port of the Type II gravity field simulation cabin is docked and locked with the tail docking port of the Type I gravity field simulation cabin, the first Type II gravity field simulation cabin is rotated 30° toward the system center axis direction and locked through the transfer mechanism; The rotating wheel is adjusted to the tail docking port of the first type II gravity field simulation cabin and stops at the head docking port position facing the second type II gravity field simulation cabin in level flight. After docking, the second type II gravity field simulation cabin is rotated 30° toward the central axis of the system through the transfer mechanism and locked; The installation steps of the 3rd, 5th and 7th Type II gravity field simulation cabins are the same as the installation steps of the 1st Type II gravity field simulation cabin; the installation steps of the 4th, 6th and 8th Type II gravity field simulation cabins are the same as the installation steps of the 2nd Type II gravity field simulation cabin; When all the gravity field simulation cabins are installed, the solar wings will be unfolded uniformly to form a complete dodecahedron structure.

[0013] In a third aspect, an on-orbit maintenance method for a large-scale simulated gravity system is provided, and on-orbit maintenance is performed based on the large-scale simulated gravity system as described in the first aspect, comprising: Stop the rotating wheel at a position where the axis of the fault gravity field simulation cabin is parallel to the flight direction; The lock of the docking interface with the tail of the faulty gravity field simulation cabin is released, and the tail transfer mechanism of the gravity field simulation cabin connected to its head is rotated 30° away from the central rotation axis of the system; Rotate the rotating wheel and release the lock of the head docking interface of the faulty gravity field simulation cabin at the same time, so as to complete the separation of the faulty gravity field simulation cabin; A new gravity field simulation cabin is replaced according to the on-orbit construction method as described in the second aspect.

[0014] In a fourth aspect, a method for on-orbit docking of a carrier spacecraft is provided, wherein the method is based on the large-scale simulated gravity system as described in the first aspect to perform on-orbit docking of a carrier spacecraft, and comprises: The carrier spacecraft is launched into orbit with the rocket; The power wheel working cabin rotates the rotating wheel so that the gravity field simulation cabin forward docking port of a certain gravity field simulation cabin faces the flying direction of the carrier spacecraft, and then stops rotating the rotating wheel; The carrier spacecraft completes docking and locking with the gravity field simulation cabin through the docking device, and rotates with the rotating wheels.

[0015] The present invention has the following advantages: The large-scale simulated gravity system and its on-orbit construction and maintenance method provided by the present invention can sustainably ensure the long-term continuous operation of the entire system through a carrier spacecraft. The proposed on-orbit construction method can shorten the system construction cycle, and the maintenance method can ensure the reliability and availability of the system's long-term on-orbit operation. The system can achieve continuous expansion of system capacity, the system is large in scale, and can dock with multiple carrier spacecraft at the same time, which is highly practical; it can realize the maintenance and replacement of any gravity field simulation cabin, and has good maintainability; It supports continuous updating of the system to ensure the long life of the system. After assembly, a large-scale, long-life on-orbit large-scale gravity field simulation environment can be obtained. It can be expanded from a 12-sided polygon to a polygonal structure with 16, 20 or even more sides, with good scalability.

[0016] By using the power wheel working cabin as the power output platform, orbital maneuvering and multi-track operation can be achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A schematic diagram of an on-orbit flight of a large-scale simulated gravity system provided in an embodiment of the present application; Figure 2 A schematic diagram of a rocket loading and ascending provided in an embodiment of the present application; Figure 3A schematic diagram of an on-orbit installation process of a large-scale simulated gravity system provided in an embodiment of the present application; Figure 4 A schematic diagram of a carrier spacecraft provided in an embodiment of the present application; Figure 5 A schematic diagram of on-orbit docking of multiple carrier spacecraft with a simulated gravity system provided in an embodiment of the present application; Figure 6 A schematic diagram of an on-orbit replacement process of a large-scale simulated gravity system provided in an embodiment of the present application; Figure 7 A schematic diagram of a double-layer cabin structure of a gravity field simulation cabin provided in an embodiment of the present application; Figure 8 A schematic diagram of the working process of a transfer mechanism provided in an embodiment of the present application.

[0018] Reference numerals: 1-sealed 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 port; 8-tail docking port; 9-solar wing device; 10-forward docking port of gravity field simulation cabin; 11-left docking port; 12-forward docking port; 13-sky direction docking port; 14-right docking port; 15-backward docking port; 16-carrier spacecraft head fairing; 17-outside cabin solar wing; 18-carrier spacecraft docking device; 19-connecting rod docking port; 20-rotating wheel connecting rod; 22-outer cabin; 23-outer cabin opening; 24-transfer mechanism parking device; 26-inner cabin; 27-metal soft cylindrical tube; 29-transfer mechanism. DETAILED DESCRIPTION

[0019] In order to further explain the technical means and effects adopted by the present invention to achieve the predetermined purpose, the technical solutions in the embodiments of the present application are clearly described. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field belong to the scope of protection of the present application.

[0020] The terms "first", "second", etc. in the specification and claims of the present application are used to distinguish similar objects, and are not used to describe a specific order or sequence. It should be understood that the terms used in this way are interchangeable where appropriate, 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 generally of one type, and the number of objects is not limited. For example, the first object can be one or more. In addition, "and / or" in the specification and claims represents at least one of the connected objects, and the character " / " generally indicates that the objects associated with each other are in an "or" relationship.

[0021] 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 specification do not have to be strictly executed according to the step numbers, and the method steps can be executed in a different order. Moreover, some steps can be omitted, multiple steps can be combined into one step, and / or one step can be decomposed into multiple steps.

[0022] The large-scale simulated gravity system and its on-orbit construction and maintenance methods provided in the embodiments of the present application are described in detail below in conjunction with the accompanying drawings and preferred embodiments.

[0023] In order to solve a series of problems such as the ascent, on-orbit operation and maintenance of a large-scale simulated gravity system, as well as the on-orbit material replenishment and other problems, a large-scale simulated gravity system and its on-orbit construction and maintenance method are provided.

[0024] This large-scale simulated gravity system consists of four parts: a power wheel working cabin, a type I gravity field simulation cabin, a type II gravity field simulation cabin, and a carrier spacecraft. It is launched into orbit in batches by multiple carrier rockets and finally assembled into a 12-sided expandable structure on orbit (expandable to 16, 20, etc. polygons in the future). The system generates centrifugal force to simulate gravity through rotation (the speed is 4r / min, and the target gravity is 1g), while supporting orbital maneuvers, on-orbit maintenance, and functional expansion.

[0025] The large-scale simulated gravity system of an embodiment of the present application is described in detail below.

[0026] The large-scale simulated gravity system of the embodiment of the present application includes a power wheel working cabin, a type I gravity field simulation cabin and a type II gravity field simulation cabin.

[0027] See also Figure 1 , showing a power wheel working cabin; the power wheel working cabin comprises a sealed working cabin 1, a motor, a foldable outboard solar wing and a docking device; The motor is arranged in a sealed working cabin 1, and an electric rotating shaft 2 is arranged at the output end of the motor. 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 a portion of the rotating wheel connecting rods 5 that are not connected to the rotating shaft connecting rods 3 are provided with a connecting rod locking interface for connecting to the type I gravity field simulation cabin; The docking interface device is rotatably connected to the end of the sealed working cabin 1 away from the rotating wheel 4, and is used to dock a spacecraft or a space capsule. The docking interface device includes a left docking interface 11, a forward docking interface 12, a skyward docking interface 13, a right docking interface 14 and a rearward docking interface 15, a total of five docking interfaces.

[0028] During specific implementation, the sealed working cabin 1 is used for astronauts to be on-orbit on-duty. At the same time, the motor that drives the entire gravity field to rotate is placed in the cabin, which provides a good working environment and is easy to inspect and maintain. When the power wheel working cabin is ascending, the solar wings outside the cabin are folded and retracted, and unfolded in orbit after entering orbit to provide power for the working cabin. The sealed working cabin 1 is connected to the electric shaft 2 through a motor transmission device, and the motor shaft is connected to the rotating wheel 4 through a shaft connecting rod 3. The motor and the motor transmission device are powered by the solar wings outside the cabin to rotate, driving the rotating wheel 4 to rotate. At the same time, the power wheel working cabin can provide the entire system with power and control for orbit maintenance and orbit change. The propellant can be replenished by transporting the carrier spacecraft upward and replenished by astronauts on orbit. The sealed working cabin 1 has a total of 5 docking ports, namely forward, backward, facing the sky, left and right, and can dock with up to 5 spacecraft or space capsules at the same time. The spacecraft or space capsule is generally docked with the sealed working cabin 1 through the rear docking port, and the transfer is completed by the transfer mechanism 29 on the sealed working cabin 1. When flying on orbit, the axial direction of the sealed working cabin 1 is perpendicular to the flight direction of the system, and the circumferential direction of the rotating wheel 4 is parallel to the flight direction of the system.

[0029] See also Figure 1 , showing a type I gravity field simulation cabin; the type I gravity field simulation cabin includes a gravity field simulation cabin 6, a rotating wheel connecting rod 5 is connected to the middle of the outer side of the gravity field simulation cabin 6 through a flip mechanism, and the rotating wheel connecting rod 5 is used to connect with the connecting rod locking interface of the rotating wheel 4; The gravity field simulation cabin 6 is provided with a head docking port 7 and a tail docking port 8 at both ends thereof, respectively, for supporting the connection between cabin bodies; The gravity field simulation cabin 6 is provided with a foldable solar wing device 9 on the peripheral side close to the head docking port 7, and a gravity field simulation cabin forward docking port 10 for achieving on-orbit docking of the carrier spacecraft; The rotating wheel connecting rod 5 realizes a flipping motion from parallel to the length direction of the gravity field simulation cabin 6 to vertical through a flipping mechanism. The part of the gravity field simulation cabin 6 near the tail docking port 8 is a double-layer cabin structure, see Figure 7 The double-layer cabin structure includes an outer cabin 22 and an inner cabin 26. The tail docking port 8 is arranged at one end of the inner cabin 26. A metal soft cylindrical tube 27 is arranged at the other end of the inner cabin 26. The metal soft cylindrical tube 27 is connected to the gravity field simulation cabin 6. The outer cabin 22 is wrapped outside the inner cabin 26 and the metal soft cylindrical tube 27 and is connected to the gravity field simulation cabin 6 as a whole. An outer cabin 22 opening 23 is arranged at the end of the outer cabin 22. The tail docking port 8 extends out from the outer cabin 22 opening 23 and forms a structure for supporting a 30° connection with the Type II gravity field simulation cabin.

[0030] A transfer mechanism 29 interface for capturing the transfer mechanism 29 is provided at a position of the gravity field simulation cabin 6 near the head docking interface 7. The transfer mechanism 29 is provided in the II type gravity field simulation cabin.

[0031] See also Figure 1 , showing a type II gravity field simulation cabin; the type II gravity field simulation cabin is the same as the type I gravity field simulation cabin, including a gravity field simulation cabin 6, and the two ends of the gravity field simulation cabin 6 are respectively provided with a head docking port 7 and a tail docking port 8 for supporting the connection between cabins; The gravity field simulation cabin 6 is provided with a foldable solar wing device 9 on the peripheral side close to the head docking port 7, and a gravity field simulation cabin forward docking port 10 for achieving on-orbit docking of the carrier spacecraft; The part of the gravity field simulation cabin 6 near the tail docking port 8 is a double-layer cabin structure, which includes an outer cabin 22 and an inner cabin 26. The tail docking port 8 is arranged at one end of the inner cabin 26. A metal soft cylindrical tube 27 is arranged at the other end of the inner cabin 26. The metal soft cylindrical tube 27 is connected to the gravity field simulation cabin 6. The outer cabin 22 is wrapped around the inner cabin 26 and the metal soft cylindrical tube 27 and is connected to the gravity field simulation cabin 6 as a whole. An outer cabin 22 opening 23 is arranged at the end of the outer cabin 22. The tail docking port 8 extends out from the outer cabin 22 opening 23 and forms a structure for supporting a 30° connection with a Type II gravity field simulation cabin or a Type I gravity field simulation cabin.

[0032] Compared with the Type I gravity field simulation cabin, the Type II gravity field simulation cabin does not have a rotating wheel connecting rod 5, and is also provided with a transfer mechanism 29 on the double-layer cabin structure; specifically, the Type II gravity field simulation cabin has a transfer mechanism 29 on the double-layer cabin structure, and the transfer mechanism 29 can be selectively locked by a transfer mechanism 29 parking device 24 provided on the gravity field simulation cabin 6.

[0033] The type I gravity field simulation cabin and the type II gravity field simulation cabin are connected to form a polyhedron structure, and the power wheel working cabin drives the polyhedron structure to rotate to form a gravity simulation field. The gravity field simulation cabin 6 of the type I gravity field simulation cabin and the type II gravity field simulation cabin provides living and experimental space for astronauts.

[0034] In the specific implementation process, the power wheel working cabin is launched into orbit by the first rocket. The type I gravity field simulation cabin is launched into orbit by the second rocket. After the type I gravity field simulation cabin enters orbit, the rotating wheel connecting rod 5 is unlocked, opened, rotated 90° and locked, and then the rotating wheel 4 is stopped. At this time, it is necessary to keep a connecting rod locking interface on the surface of the rotating wheel 4 facing the type I gravity field simulation cabin. After the simulation cabin captures the interface, the on-orbit connection and locking are completed; there are 4 type I gravity field simulation cabins, each type I simulation cabin is 90° apart. After each type I gravity field simulation cabin is installed, the rotating wheel 4 rotates 90°, and the 4 type I gravity field simulation cabins are installed in place in turn. At this time, the solar wing of the simulation cabin is unlocked but not deployed for the time being. The solar wing will be deployed after all the type II gravity field simulation cabins are installed. The Type II gravity field simulation cabin is launched into orbit by the third rocket, and the rotating wheel 4 rotates until a Type I gravity field simulation cabin docking interface is in a horizontal position, and then stops rotating, and the Type II gravity field simulation cabin approaches, captures, and completes docking, and then the Type II gravity field simulation cabin is rotated 30° and locked by the transfer mechanism 29 (see Figure 8 , the transfer mechanism 29 is locked and fixed in the upward state. When the Type II gravity field simulation cabin is docked and locked with the Type I gravity field simulation cabin, the transfer mechanism 29 is unlocked and rotated to a state of coincidence with the axis of the Type I gravity field simulation cabin, and the interface of the transfer mechanism 29 on the Type I gravity field simulation cabin is captured. After locking, the transfer mechanism 29 rotates 30° around the upper rotation axis of the Type II gravity field simulation cabin. The transfer mechanism 29 is limited and locked). The rotating wheel 4 rotates again to rotate the newly installed Type II gravity field simulation cabin to be parallel to the flight direction, and stops rotating. The next Type II gravity field simulation cabin approaches, captures, and completes the docking. The transfer mechanism 29 is then used to rotate the Type II gravity field simulation cabin 30° and lock it. ... Follow the above process until the installation of 8 Type II gravity field simulation cabins is completed, and then the solar wings of a total of 12 gravity field simulation cabins (4 of which are Type I and 8 are Type II) are unfolded.

[0035] The carrier spacecraft is used for the transportation of personnel and cargo after the system is built. It can dock with the power wheel working cabin, and can also dock with the docking port on the gravity field simulation cabin (the forward docking port 10 of the gravity field simulation cabin). The existing rendezvous and docking technology can be used to complete the on-orbit docking. When docking with the gravity field simulation cabin, while the rotating wheel 4 rotates, the carrier spacecraft is also in a simulated gravity field environment. The carrier spacecraft has the ability to travel back and forth between the earth and the sky and is reusable.

[0036] The following is a detailed description of the on-orbit construction and maintenance method of the large-scale simulated gravity system of the embodiment of the present application.

[0037] See also Figure 3 The embodiment of the present application provides an on-orbit construction method of a large-scale simulated gravity system, and the on-orbit construction is performed based on the large-scale simulated gravity system, including: Step S1, the power wheel working cabin goes up with the first rocket, unfolds the solar panels after entering orbit, and starts the motor to drive the rotating wheel.

[0038] Specifically, the power wheel working cabin went up with the first rocket, see Figure 2 After entering orbit, it separates from the rocket, and the power wheel working cabin drives the rotating wheel 4 to rotate at an angular speed of 4r / min through the motor.

[0039] Step S2, four Type I gravity field simulation cabins are launched upward with the second rocket. After each gravity field simulation cabin enters orbit, the rotating wheel connecting rod is unlocked and unfolded 90°, and docked and locked with the rotating wheel of the power wheel working cabin; every time a Type I gravity field simulation cabin is installed, the rotating wheel rotates 90°.

[0040] Specifically, the Type I gravity field simulation cabin (4 in total) was launched upward with the second rocket, see Figure 2 , after entering orbit, they are separated from the rocket in sequence. After the first I-type gravity field simulation cabin is separated from the rocket to a safe distance, the lock of the rotating wheel connecting rod 5 is released, and the rotating wheel connecting rod 5 rotates from parallel to the sealed cabin body to a vertical state with the sealed cabin body, flies horizontally and approaches the rotating wheel 4, and the power runner working cabin rotates the rotating wheel 4 in advance, so that the connecting rod docking port 19 on the rotating wheel 4 stays at a position facing the rotating wheel connecting rod 5 on the I-type gravity field simulation cabin, and the power runner working cabin stops rotating the rotating wheel 4; the rotating wheel connecting rod 5 on the I-type gravity field simulation cabin docks with the rotating wheel 4 and locks, completing the installation of the first I-type gravity field simulation cabin; then the power runner working cabin rotates the rotating wheel 4 again, and refers to the installation process of the first I-type gravity field simulation cabin to complete the on-orbit installation of the second to fourth I-type gravity field simulation cabins in sequence.

[0041] Step S3, 8 Type II gravity field simulation cabins are launched upward along with the third rocket; the rotating wheel is adjusted to the tail docking port 8 of the Type I gravity field simulation cabin to stop at the head docking port position facing the first Type II gravity field simulation cabin in level flight, and after the head docking port of the Type II gravity field simulation cabin is docked and locked with the tail docking port of the Type I gravity field simulation cabin, the first Type II gravity field simulation cabin is rotated 30° toward the system center axis direction and locked by the transfer mechanism; The rotating wheel 4 is adjusted to the tail docking port of the first type II gravity field simulation cabin and stops at the head docking port position facing the second type II gravity field simulation cabin in level flight. After docking, the second type II gravity field simulation cabin is rotated 30° toward the central axis of the system through the transfer mechanism and locked. The installation steps for the 3rd, 5th and 7th Type II gravity field simulation cabins are the same as the installation steps for the 1st Type II gravity field simulation cabin; the installation steps for the 4th, 6th and 8th Type II gravity field simulation cabins are the same as the installation steps for the 2nd Type II gravity field simulation cabin.

[0042] Specifically, the Type II gravity field simulation cabin (8 in total) was launched with the third rocket, see Figure 2 After entering orbit, they separate from the rocket in sequence. The first Type II gravity field simulation cabin flies horizontally close to the rotating wheel 4 with its head docking port 7 facing forward and parallel to the flight direction, releasing the solar wing lock, but not opening it temporarily; the power wheel working cabin rotates a Type I gravity field simulation cabin connected to the rotating wheel 4 to a horizontal state in advance, so that its tail docking port 8 stops at a position facing the head docking port 7 of the Type II gravity field simulation cabin flying horizontally, the head docking port 7 of the Type II gravity field simulation cabin is docked and locked with the tail docking port 8 of the Type I gravity field simulation cabin, and the tail transfer mechanism 29 of the Type I gravity field simulation cabin is horizontally rotated 30° toward the central axis direction, and then the transfer mechanism 29 is locked.

[0043] The second Type II gravity field simulation cabin separates from the rocket, and the Type II gravity field simulation cabin flies horizontally close to the rotating wheel 4 with its head docking port 7 facing forward and parallel to the flight direction, releasing the solar wing lock, but not opening it temporarily; the power rotor working cabin stops the tail docking port 8 of the first Type II gravity field simulation cabin in advance at a position facing the head docking port 7 of the second Type II gravity field simulation cabin in horizontal flight, and the head docking port 7 of the Type II gravity field simulation cabin is docked and locked with the tail docking port 8 of the first Type II gravity field simulation cabin, and the tail transfer mechanism 29 of the first Type II gravity field simulation cabin is horizontally rotated 30° toward the center axis direction to dock and lock it with the adjacent head docking port 7 of the second Type I gravity field simulation cabin.

[0044] Step S4, when all gravity field simulation cabins are installed, all solar wings are uniformly unfolded to form a complete dodecahedron structure.

[0045] Specifically, the installation process of the 3rd, 5th and 7th Type II gravity field simulation cabins is the same as that of the 1st Type II gravity field simulation cabin; the installation process of the 4th, 6th and 8th Type II gravity field simulation cabins is the same as that of the 2nd Type II gravity field simulation cabin; when all simulation cabins are installed to form a complete 12-hedron structure, the solar wings of each simulation cabin will be unfolded and locked in turn.

[0046] This method can be launched into orbit by three launch vehicles, and then assembled and docked on orbit to form a 12-sided (expandable) spacecraft structure. The motor can be used to drive the entire simulated gravity system to rotate at a speed of 4r / min, generating 1g of gravity.

[0047] Further, referring to 5, the embodiment of the present application provides a method for on-orbit docking of a carrier spacecraft, comprising: Step A1, the carrier spacecraft is launched into orbit with the rocket; Step A2, the power wheel working cabin rotates the rotating wheel so that the gravity field simulation cabin forward docking port of a certain gravity field simulation cabin faces the flight direction of the carrier spacecraft, and then stops rotating the rotating wheel 4; 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.

[0048] The carrier spacecraft is launched into orbit with the rocket, flies close to the simulated gravity system, and removes the carrier spacecraft head fairing 16 (see Figure 4 ) is locked, the fairing is rotated open to the locked position, the power wheel working cabin rotates the rotating wheel 4 so that the positive docking port on a gravity field simulation cabin faces the flight direction of the carrier spacecraft, and the rotation of the rotating wheel 4 is stopped; the carrier spacecraft docking device 18 captures the positive docking port on the gravity field simulation cabin, approaches and completes the docking locking.

[0049] Further, see Figure 6 The embodiment of the present application provides an on-orbit maintenance method for a large-scale simulated gravity system, and performs on-orbit maintenance based on the large-scale simulated gravity system, including: Step B1, stop the rotating wheel at a position where the axis of the fault gravity field simulation cabin is parallel to the flight direction; Step B2, unlocking the docking interface with the tail of the faulty gravity field simulation cabin, and rotating the tail transfer mechanism of the gravity field simulation cabin connected to its head by 30° in a direction away from the central rotation axis of the system; Step B3, rotating the rotating wheel 4 and releasing the lock on the head docking interface of the faulty gravity field simulation cabin, thereby completing the separation of the faulty gravity field simulation cabin.

[0050] Step B4, replacing a new gravity field simulation cabin according to the above-mentioned on-orbit construction method.

[0051] When a gravity field simulation cabin has a major fault and needs to be replaced on-orbit, the power output of the power wheel working cabin is shut down, the rotating wheel 4 is stopped at a position where the axis of the faulty gravity field simulation cabin is parallel to the flight direction, the lock on the tail docking interface 8 of the faulty gravity field simulation cabin is released, the tail transfer mechanism 29 of the gravity field simulation cabin connected to its head is rotated 30° away from the central axis, and then the rotating wheel 4 is rotated. At the same time, the lock on the head docking interface 7 of the faulty gravity field simulation cabin is released to complete the separation of the faulty gravity field simulation cabin. The installation process of the replacement gravity field simulation cabin is the same as the above-mentioned on-orbit construction method.

[0052] Through this method, all cabins in the system can be replaced as a whole on-orbit, and a long-term stable large-scale weightlessness-free environment can be provided. Orbital change maneuvers can also be realized, thereby improving the mission compatibility and availability of the system, while extending the system's on-orbit service life and improving the system's use efficiency.

[0053] Based on the above technical solution, this application provides an on-orbit construction and maintenance method for a large-scale simulated gravity system, which has the following advantages: 1. The present invention provides a large-scale simulated gravity system and its on-orbit construction and maintenance method, which is mainly constructed by a power wheel working cabin, a type I gravity field simulation cabin, and a type II gravity field simulation cabin. The carrier spacecraft can sustainably ensure the long-term continuous operation of the entire system. The proposed on-orbit construction method can shorten the system construction cycle, and the maintenance method can ensure the reliability and availability of the system's long-term on-orbit operation; 2. The on-orbit construction and maintenance method provided by the present invention can realize the continuous expansion of system capabilities, the system scale is large, and it can dock with multiple carrier spacecraft at the same time, which is highly practical; it can realize the maintenance and replacement of any gravity field simulation cabin, and has good maintainability; 3. The method provided by the present invention supports continuous updating of the system, thereby ensuring the long life of the system. After assembly, a large-scale, long-life on-orbit large-scale gravity field simulation environment can be obtained; it can be expanded from a 12-sided polygon to a polygonal structure of 16, 20 or even more sides, with good scalability.

[0054] 4. The method provided by the present invention utilizes the power wheel working cabin as a power output platform, which can realize track maneuvering and multi-track operation.

[0055] It should be noted that, in this article, the term "comprises", "includes" or any other variant thereof is intended to cover non-exclusive inclusion, so that the process, method, article or device including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "including one..." do not exclude the presence of other identical elements in the process, method, article or device including the element. In addition, it should be pointed out that the scope of the method and device in the embodiment of the present application is not limited to performing functions in the order shown or discussed, and may also include performing functions in a substantially simultaneous manner or in reverse order according to the functions involved, for example, the described method may be performed in an order different from that described, and various steps may also be added, omitted, or combined. In addition, the features described with reference to certain examples may be combined in other examples.

[0056] It can be understood that the embodiments of the present application are described above in conjunction with the accompanying drawings, but the present application is not limited to the above-mentioned specific embodiments, which are merely illustrative and not restrictive, and those skilled in the art are aware that various changes or equivalent replacements can be made to these features and embodiments without departing from the spirit and scope of the present invention. In addition, those of ordinary skill in the art can modify these features and embodiments to adapt to specific circumstances and materials without departing from the spirit and scope of the present invention under the inspiration or teaching of the present application. Therefore, the present invention is not limited by the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of the present application belong to the scope protected by the present invention.

Claims

1. Large-scale simulated gravity system, characterized by: It includes a power wheel working cabin, a type I gravity field simulation cabin and a type II gravity field simulation cabin; The power wheel working cabin includes a sealed working cabin, a motor, a foldable outboard solar wing and a docking device; The motor is arranged in a sealed working cabin, an electric shaft is arranged at the output end of the motor, a plurality of shaft connecting rods are arranged in the circumferential direction of the electric shaft perpendicular to the axial direction of the electric shaft, and a rotating wheel is connected through the plurality of shaft connecting rods; the rotating wheel is a polygonal structure composed of a plurality of rotating wheel connecting rods, wherein at least some of the rotating wheel connecting rods that are not connected to the shaft connecting rods are provided with a connecting rod locking interface for connecting to the I-type gravity field simulation cabin; Both the Type I gravity field simulation cabin and the Type II gravity field simulation cabin include a gravity field simulation cabin, and the two ends of the gravity field simulation cabin are respectively provided with a head docking port and a tail docking port for supporting the connection between cabin bodies; A foldable solar wing device is arranged on the peripheral side of the gravity field simulation cabin near the head docking port, and a forward docking port of the gravity field simulation cabin for realizing on-orbit docking of the carrier spacecraft; Among them, the middle part of the outer side of the gravity field simulation cabin of the type I gravity field simulation cabin is connected with a rotating wheel connecting rod through a flip mechanism, and the rotating wheel connecting rod is used to connect with the connecting rod locking interface of the rotating wheel; The rotating wheel connecting rod realizes the flipping movement from parallel to the length direction of the gravity field simulation cabin to vertical through the flipping mechanism. A position of the gravity field simulation cabin of the type I gravity field simulation cabin near the head docking interface is provided with a transfer mechanism interface for capturing the transfer mechanism, and the transfer mechanism is provided in the type II gravity field simulation cabin; The Type I gravity field simulation cabin supports a 30° connection with the Type II gravity field simulation cabin; The Type I gravity field simulation cabin and the Type II gravity field simulation cabin are connected to form a polyhedron structure, and the polyhedron structure is driven to rotate by the power wheel working cabin to form a gravity simulation field.

2. The large-scale simulated gravity system according to claim 1, characterized in that: The part of the gravity field simulation cabin near the tail docking port of the type I gravity field simulation cabin and the type II gravity field simulation cabin is a double-layer cabin structure; The double-layer cabin structure includes an outer cabin and an inner cabin, a tail docking port is arranged at one end of the inner cabin, a metal soft cylindrical tube is arranged at the other end of the inner cabin, the metal soft cylindrical tube is connected to the gravity field simulation cabin, the outer cabin is wrapped around the inner cabin and the metal soft cylindrical tube and is connected to the gravity field simulation cabin as a whole, an outer cabin opening is arranged at the end of the outer cabin, the tail docking port extends out from the outer cabin opening, and forms a structure for supporting a 30° connection with an adjacent gravity field simulation cabin.

3. The large-scale simulated gravity system according to claim 1, characterized in that: The transfer mechanism is arranged on the double-layer cabin structure of the Type II gravity field simulation cabin, and the transfer mechanism can be selectively locked by a transfer mechanism parking device arranged on the gravity field simulation cabin.

4. The large-scale simulated gravity system according to claim 1, characterized in that: The docking interface device is rotatably connected to the end of the sealed working cabin away from the rotating wheel, and is used to dock with a spacecraft or a space capsule. The docking interface device includes five docking interfaces, namely forward, rearward, skyward, left and right.

5. The large-scale simulated gravity system according to any one of claims 1 to 4, characterized in that: When flying in orbit, the axial direction of the sealed working cabin is perpendicular to the flight direction of the system, and the circumferential direction of the rotating wheel is parallel to the flight direction of the system.

6. A method for constructing a large-scale simulated gravity system on-orbit, characterized in that: On-orbit construction is performed based on the large-scale simulated gravity system according to any one of claims 1 to 5, comprising: The power wheel working cabin goes up with the first rocket, unfolds the solar panels after entering orbit, and starts the motor to drive the rotating wheel; Four Type I gravity field simulation cabins were launched upward with the second rocket. After each gravity field simulation cabin entered orbit, the rotating wheel connecting rod was unlocked and unfolded 90°, docked and locked with the rotating wheel of the power wheel working cabin; each time a Type I gravity field simulation cabin was installed, the rotating wheel rotated 90°; Eight Type II gravity field simulation cabins are launched upward with the third rocket; the rotating wheel is adjusted to the tail docking port of the Type I gravity field simulation cabin to stop at the head docking port position facing the first Type II gravity field simulation cabin in level flight, and after the head docking port of the Type II gravity field simulation cabin is docked and locked with the tail docking port of the Type I gravity field simulation cabin, the first Type II gravity field simulation cabin is rotated 30° toward the system center axis direction and locked through the transfer mechanism; The rotating wheel is adjusted to the tail docking port of the first type II gravity field simulation cabin and stops at the head docking port position facing the second type II gravity field simulation cabin in level flight. After docking, the second type II gravity field simulation cabin is rotated 30° toward the central axis of the system through the transfer mechanism and locked; The installation steps of the 3rd, 5th and 7th Type II gravity field simulation cabins are the same as the installation steps of the 1st Type II gravity field simulation cabin; the installation steps of the 4th, 6th and 8th Type II gravity field simulation cabins are the same as the installation steps of the 2nd Type II gravity field simulation cabin; When all the gravity field simulation cabins are installed, the solar wings will be unfolded uniformly to form a complete dodecahedron structure.

7. An on-orbit maintenance method for a large simulated gravity system, characterized in that: On-orbit maintenance is performed based on the large-scale simulated gravity system according to any one of claims 1 to 5, comprising: Stop the rotating wheel at a position where the axis of the fault gravity field simulation cabin is parallel to the flight direction; The lock of the docking interface with the tail of the faulty gravity field simulation cabin is released, and the tail transfer mechanism of the gravity field simulation cabin connected to its head is rotated 30° away from the central rotation axis of the system; Rotate the rotating wheel and release the lock of the head docking interface of the faulty gravity field simulation cabin at the same time, so as to complete the separation of the faulty gravity field simulation cabin; A new gravity field simulation cabin replaced according to the on-orbit construction method as described in claim 6.

8. A method for docking a carrier spacecraft on orbit, characterized in that: The method of performing on-orbit docking of a carrier spacecraft based on the large-scale simulated gravity system according to any one of claims 1 to 5 comprises: The carrier spacecraft is launched into orbit with the rocket; The power wheel working cabin rotates the rotating wheel so that the gravity field simulation cabin forward docking port of a certain gravity field simulation cabin faces the flying direction of the carrier spacecraft, and then stops rotating the rotating wheel; The carrier spacecraft completes docking and locking with the gravity field simulation cabin through the docking device, and rotates with the rotating wheels.

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