A reconfigurable airlock module for a space station

Abstract

The application discloses a space station configuration of a reconfigurable airlock cabin, which comprises a core cabin, a second space vehicle and a third space vehicle, the core cabin comprises a node cabin and a first living cabin, and the core cabin further comprises a reconfigurable airlock cabin; the reconfigurable airlock cabin is provided with two docking interfaces, one of which is docked with the node cabin, and the other can be used as a docking interface expansion of other space vehicles; after the core cabin is in orbit, the reconfigurable airlock cabin is transferred from the forward docking interface of the node cabin to the ground docking interface of the node cabin, so that the forward docking interface of the node cabin is released. The application replaces the backup airlock cabin function of the node cabin by taking the reconfigurable airlock cabin as the main airlock cabin or the backup airlock cabin, releases the traffic artery function of the node cabin in a normal state, makes up for the potential risks and deficiencies of the current space station taking the node cabin as the backup airlock cabin, and meanwhile, the reconfigurable airlock cabin is provided with two docking interfaces, so that the number and direction of the docking interfaces of the space station are not affected.

Description

Technical Field

[0001] This invention relates to the field of aerospace overall design, and specifically to a space station configuration with a reconfigurable airlock. Background Technology

[0002] The space station currently consists of a core module, experiment module a, and experiment module b. Except for experiment module a, which has an airlock for astronauts to exit the spacecraft, the core module has a node module as a backup airlock for astronauts to exit the spacecraft.

[0003] When the node module is used as an airlock, it is in a vacuum-exposed state. If a malfunction or accident occurs in the module where the non-occupants are located, such as a space debris impact causing air leakage or a fire, the astronauts inside the module will not be able to reach the malfunctioning module for repairs in time because it takes a long time to close the hatch, restore the pressure inside the node module, and then restore the connection between the three modules. This will result in the loss of the most valuable opportunity to deal with the accident, which will lead to the further development and expansion of the scope of the accident and the level of danger and damage. Summary of the Invention

[0004] To address the aforementioned issues, this invention provides a space station configuration with a reconfigurable airlock module. By using the reconfigurable airlock module as the primary or backup airlock module to replace the backup airlock module function of the node module, the traffic artery function of the node module is normally released. At the same time, the reconfigurable airlock module has two docking ports, which does not affect the number and orientation of the docking ports of the space station.

[0005] The specific technical solution of this invention is as follows:

[0006] A space station configuration with a reconfigurable airlock includes a core module, a second spacecraft, and a third spacecraft. The core module includes a node module and a first living module. The core module also includes a reconfigurable airlock.

[0007] The reconfigurable airlock is equipped with two docking interfaces, one of which is connected to the node module, and the other can be used as an extension docking interface for other spacecraft.

[0008] The node module is connected to the first living module, and the node module has five docking mechanisms (up, down, left, right, and forward) with the direction of flight after entering orbit as forward and the direction of ground as downward, providing five docking interfaces.

[0009] During launch, the core module consists of a reconfigurable airlock, a node module, and a first living module, arranged from top to bottom. These three modules are connected in series, with their axes coinciding with the launch vehicle's axis to accommodate a limited payload envelope. After the core module enters orbit, the reconfigurable airlock, node module, and first living module are arranged from front to back, with the flight direction as the front.

[0010] Preferably, after the core cabin is in orbit, the reconfigurable airlock cabin can be transferred from the forward docking interface of the node cabin to the ground docking interface of the node cabin, while the forward docking interface of the node cabin is released to serve as the main docking interface of the second space vehicle and the third space vehicle launched subsequently.

[0011] Furthermore, after one docking interface of the reconfigurable airlock cabin is transferred to the ground docking interface of the node cabin, the other docking interface of the reconfigurable airlock cabin can continue to serve as a docking interface for other space vehicles.

[0012] Preferably, the second space vehicle comprises a second airlock cabin and a second living cabin, and the second airlock cabin and the reconfigurable airlock cabin of the core cabin are backup airlock cabins for each other.

[0013] The present application has the following beneficial effects:

[0014] The present application replaces the backup airlock cabin function of the node cabin with the reconfigurable airlock cabin as the main airlock cabin or the backup airlock cabin, releases the traffic artery function of the node cabin normally, and optimizes and makes up for the potential risks and deficiencies of the current space station using the node cabin as the backup airlock cabin.

[0015] The space station configuration of the reconfigurable airlock cabin provided by the present application, when astronauts enter and exit the sealed environment in the cabin and the vacuum environment outside the cabin, if the cabin section where the astronauts are located is not damaged by space debris impact, fire, or other accidents, the traffic artery function of the node cabin is not affected, and the astronauts in the cabin can still reach the damaged cabin for maintenance through the node cabin, thereby grasping the most valuable opportunity to handle and eliminate the accident, and controlling the accident impact range and the risk damage level.

[0016] Meanwhile, the reconfigurable airlock cabin provided by the present application has two docking interfaces, which does not affect the number and direction of the docking interfaces of the space station. DETAILED DESCRIPTION

[0017] In order to more clearly illustrate the technical solutions disclosed in the present application, the following will briefly introduce the drawings needed to be used in some embodiments disclosed by the present application. Obviously, the drawings in the following description are only the drawings of some embodiments disclosed by the present application, and other drawings can also be obtained by those skilled in the art according to these drawings. In addition, the drawings in the following description can be regarded as schematic diagrams, and are not limited to the actual size, actual process, etc. of the products involved in the embodiments disclosed by the present application.

[0018] Figure 1 The present application provides a launch state schematic diagram of the core cabin.

[0019] Figure 2A schematic diagram of an on-orbit operation state of the core cabin provided by the present application.

[0020] Figure 3 A schematic diagram of an on-orbit operation state of a space station provided by the reconfigurable airlock cabin provided by the present application.

[0021] The reference signs are: 1, core cabin; 2, second space vehicle; 3, third space vehicle; 4, fourth space vehicle; 5, fifth space vehicle; 6, sixth space vehicle; 7, reconfigurable airlock cabin; 8, node cabin; 9, first living cabin; 10, second airlock cabin; 11, second living cabin. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative efforts belong to the scope of protection of the present application. Therefore, the present application is not limited by the specific embodiments disclosed below.

[0023] As shown in the drawings, Figure 1 The core cabin 1 includes a reconfigurable airlock cabin 7, a node cabin 8 and a first living cabin 9. The reconfigurable airlock cabin 7 is provided with two docking interfaces, one of which is docked with the node cabin, and the other of which can be used as a docking interface extension for other space vehicles. The node cabin 8 is connected with the first living cabin 9, and the node cabin 8 has a flight direction after entering an orbit as a front direction, and a ground direction as a lower direction, and includes upper, lower, left, right and front five docking mechanisms, which can provide five docking interfaces. When the core cabin 1 is launched, the reconfigurable airlock cabin 7, the node cabin 8 and the first living cabin 9 are sequentially arranged from top to bottom, and the three cabin sections are connected in series, and the cabin body axis is coincident with the launch vehicle axis to adapt to the limited launch envelope. After the core cabin 1 enters the orbit, the reconfigurable airlock cabin 7, the node cabin 8 and the first living cabin 9 are sequentially arranged from front to back with the flight direction as the front direction.

[0024] As shown in the drawings, Figure 2 After the core cabin 1 is in on-orbit operation, the reconfigurable airlock cabin 7 can be transferred from the forward docking interface of the node cabin 8 to the ground docking interface of the node cabin 8, and at the same time, the forward docking interface of the node cabin 8 is released to be used as the main docking interface for other space vehicles launched subsequently. Further, after one docking interface of the reconfigurable airlock cabin 7 is transferred to the ground docking interface of the node cabin 8, the other docking interface of the reconfigurable airlock cabin 7 can continue to be used as a docking interface extension for other space vehicles.

[0025] As shown in the drawings, Figure 3As shown, the space station with the reconfigurable airlock cabin provided by the application comprises a core cabin 1, a second spacecraft 2, a third spacecraft 3, a fourth spacecraft 4, a fifth spacecraft 5 and a sixth spacecraft 6. The second spacecraft 2 comprises a second airlock cabin 10 and a second living cabin 11, and the second airlock cabin 10 and the reconfigurable airlock cabin 7 of the core cabin 1 are backup airlock cabins.

[0026] By taking the reconfigurable airlock cabin as the main airlock cabin or the backup airlock cabin, the backup airlock cabin function of the node cabin is replaced, the traffic artery function of the node cabin is released normally, and the potential risks and deficiencies of the current space station taking the node cabin as the backup airlock cabin are optimized and made up.

[0027] The space station configuration with the reconfigurable airlock cabin provided by the application, when an astronaut enters or exits a sealed environment in the cabin and a vacuum environment outside the cabin, if a cabin section where the astronaut is located does not have a failure or an accident such as air leakage caused by space debris impact or a fire, the traffic artery function of the node cabin is not affected, the astronaut in the cabin can still reach the failure cabin through the traffic artery of the node cabin in time to repair, grasp the most valuable opportunity to handle and eliminate the accident, and thus control the influence range and the dangerous damage level of the accident.

[0028] Meanwhile, the reconfigurable airlock cabin provided by the application has two docking interfaces, which does not affect the number and direction of the docking interfaces of the space station.

[0029] Although the above-mentioned preferred embodiments of the application have been disclosed, the application is not limited to the above-mentioned embodiments, and any person skilled in the art can make possible changes and modifications to the technical solutions of the application according to the above-mentioned disclosure without departing from the spirit and scope of the application. Therefore, any simple modification, equivalent change and modification made to the above-mentioned embodiments according to the technical essence of the application, which does not depart from the technical solutions of the application, belongs to the protection scope of the technical solutions of the application.

Claims

1. A space station configuration with a reconfigurable airlock, comprising a core module (1), a second spacecraft (2), and a third spacecraft (3), wherein the core module (1) includes a node module (8) and a first living quarters module (9), characterized in that: The core module (1) also includes a reconfigurable airlock module (7). The reconfigurable airlock (7) is provided with two docking interfaces, one of which is docked with the node module, and the other is used as an extension of the docking interface for other spacecraft; The node module (8) is connected to the first living module (9), and the node module (8) has five docking mechanisms (up, down, left, right, and front) with the flight direction after entering orbit as the front and the direction to the ground as the bottom, providing five docking interfaces; When the core module (1) is launched, from top to bottom, it consists of a reconfigurable airlock module (7), a node module (8), and a first living module (9). The three modules are connected in series, and the module axis coincides with the launch vehicle axis to accommodate the limited launch envelope. After the core module (1) enters orbit, with the flight direction as the front, from front to back, it consists of a reconfigurable airlock module (7), a node module (8), and a first living module (9). After the core module (1) is in orbit, it can transfer the reconfigurable airlock (7) from the forward docking port of the node module (8) to the ground docking port of the node module (8). At the same time, the forward docking port of the node module (8) is released to serve as the main docking port for other spacecraft launched subsequently. The second spacecraft (2) includes a second airlock (10) and a second living compartment (11), with the second airlock (10) and the reconfigurable airlock (7) of the core compartment (1) serving as backup airlocks for each other.

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