Space station structure capable of reconstructing air brake cabin

Abstract

The space station configuration of the reconfigurable air brake cabin comprises a core cabin, a second spacecraft and a third spacecraft, the core cabin comprises a node cabin and a first living cabin, and the core cabin further comprises the reconfigurable air brake cabin; the reconfigurable air brake cabin is provided with two docking ports, one docking port is docked with the node cabin, and the other docking port can be used as a docking port of other spacecrafts for expansion; and after the core cabin operates in orbit, the reconfigurable air brake cabin is transferred to the ground interface of the node cabin from the forward docking port of the node cabin, so that the forward docking port of the node cabin is released. The reconfigurable air brake cabin serves as the main air brake cabin or the backup air brake cabin to replace the backup air brake cabin function of the node cabin, the vital communication line function of the node cabin is normally released, and the potential risk and defect that the node cabin serves as the backup air brake cabin in an existing space station are overcome; and the number and direction of docking ports of the space station are not influenced.

Description

Technical Field

[0001] The present invention relates to the field of overall aerospace design, and in particular to a space station configuration with a reconfigurable airlock. Background Art

[0002] Currently, the space station mainly includes the core module, experimental module a, and experimental module b. In addition to the experimental module a which has an airlock for astronauts to exit the vehicle, the core module has a node module as a backup airlock for astronauts to exit the vehicle.

[0003] When the node cabin is used as an airlock cabin, it is in a vacuum exposed state. If at this time a malfunction or accident occurs in the cabin section where the astronauts are not in the cabin, such as air leakage in the cabin wall caused by impact of space debris, fire, etc., it will take a long time to close the cabin door to restore the pressure in the node cabin and then restore the connection between the three cabins. The astronauts in the cabin will not be able to reach the faulty cabin for repairs in time through the node cabin, which is a major traffic artery, thus losing the most precious opportunity to deal with the accident, which will lead to further development and expansion of the impact scope of the accident and the level of dangerous damage. Summary of the invention

[0004] In order to solve the above problems, the present invention provides a space station configuration with a reconfigurable airlock. The reconfigurable airlock is used as the main airlock or backup airlock to replace the backup airlock function of the node cabin, and the traffic artery function of the node cabin is normally released. At the same time, the reconfigurable airlock has two docking ports, which does not affect the number and direction of the docking ports of the space station.

[0005] The specific technical solutions of the present invention are as follows:

[0006] A space station configuration with a reconfigurable airlock, comprising a core module, a second spacecraft, and a third spacecraft, wherein the core module comprises a node module and a first living module, and the core module further comprises a reconfigurable airlock;

[0007] The reconfigurable airlock cabin is provided with two docking ports, one of which is docked with the node cabin, and the other can be used as an expansion docking port for other spacecraft;

[0008] The node module is connected to the first living module, and the node module takes the flight direction after entering orbit as the front and the direction facing the ground as the bottom, and includes five docking mechanisms, namely, upper, lower, left, right, and front, and can provide five docking ports;

[0009] When the core module is launched, from top to bottom, it consists of a reconfigurable airlock module, a node module and a first living module. The three modules are connected in series, and the axis of the module coincides with the axis of the launch vehicle to adapt to the limited carrying envelope. After the core module enters orbit, with the flight direction as the front, from front to back, it consists of a reconfigurable airlock module, a node module, and a first living module.

[0010] Preferably, after the core module is in orbit, the reconfigurable airlock module can be transferred from the forward docking port of the node module to the ground interface of the node module, and the forward docking port of the node module is released and can serve as the main docking port of the second spacecraft and the third spacecraft to be launched subsequently;

[0011] Furthermore, after one docking port of the reconfigurable airlock is transferred to the ground interface of the node module, another docking port of the reconfigurable airlock can continue to be used as an expansion docking port for other spacecraft;

[0012] Preferably, the second spacecraft includes a second airlock and a second living cabin, and the second airlock and the reconfigurable airlock of the core cabin serve as backup airlocks for each other.

[0013] The beneficial effects achieved by the present invention are as follows:

[0014] The present invention uses a reconfigurable airlock as the main airlock or backup airlock to replace the backup airlock function of the node cabin, thereby normally releasing the traffic artery function of the node cabin, thereby optimizing and compensating for the potential risks and shortcomings of the current space station using the node cabin as a backup airlock.

[0015] With the space station configuration of the reconfigurable airlock provided by the present invention, when astronauts enter and exit the sealed environment inside the cabin and the vacuum environment outside the cabin, unless there is a fault or accident in the cabin section where the astronauts are located, such as air leakage in the cabin wall caused by collision with space debris, fire, etc., the function of the main traffic artery of the node cabin is no longer affected. The astronauts in the cabin can still reach the faulty cabin for maintenance in time through the node cabin as a main traffic artery, thereby seizing the most precious opportunity to handle and eliminate the accident, thereby controlling the scope of the accident and the level of dangerous damage.

[0016] At the same time, the reconfigurable airlock provided by the present invention has two docking ports, which does not affect the number and direction of the docking ports of the space station. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions disclosed in the present invention, the following briefly introduces the drawings required to be used in some embodiments disclosed in the present invention. Obviously, the drawings described below are only drawings of some embodiments disclosed in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings. In addition, the drawings described below can be regarded as schematic diagrams, and are not limitations on the actual size of the products involved in the embodiments disclosed in the present invention, the actual process of the method, etc.

[0018] Figure 1 A schematic diagram of the launch status of the core module provided by the present invention.

[0019] Figure 2This is a schematic diagram of the on-orbit operation status of the core module provided by the present invention.

[0020] Figure 3 A schematic diagram of the in-orbit operation of a space station with a reconfigurable airlock provided by the present invention.

[0021] The accompanying drawings are marked as follows: 1. core module; 2. second spacecraft; 3. third spacecraft; 4. fourth spacecraft; 5. fifth spacecraft; 6. sixth spacecraft; 7. reconfigurable airlock; 8. node module; 9. first living module; 10. second airlock; 11. second living module. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0023] like Figure 1 As shown, the core module 1 includes a reconfigurable airlock module 7, a node module 8 and a first living module 9; the reconfigurable airlock module 7 is provided with two docking ports, one of which is docked with the node module, and the other can be used as an expansion of the docking port for other spacecraft; the node module 8 is connected to the first living module 9, and the node module 8 takes the flight direction after entering orbit as the front and the direction facing the earth as the bottom, including five docking mechanisms of upper, lower, left, right and front, and can provide five docking ports; when the core module 1 is launched, from top to bottom, it is the reconfigurable airlock module 7, the node module 8 and the first living module 9, and the three modules are connected in series, and the axis of the module body coincides with the axis of the carrier rocket to adapt to the limited carrying envelope. After the core module 1 enters orbit, with the flight direction as the front, from front to back, it is the reconfigurable airlock module 7, the node module 8, and the first living module 9.

[0024] like Figure 2 As shown, after the core module 1 is in orbit, the reconfigurable airlock module 7 can be transferred from the forward docking port of the node module 8 to the ground interface of the node module 8, and at the same time, the forward docking port of the node module 8 is released and can be used as the main docking port for other spacecraft launched subsequently; further, after one docking port of the reconfigurable airlock module 7 is transferred to the ground interface of the node module 8, the other docking port of the reconfigurable airlock module 7 can continue to be used as an expansion of the docking port for other spacecraft.

[0025] like Figure 3As shown, a space station with a reconfigurable airlock provided by the present invention comprises a core module 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 10 and a second living module 11, and the second airlock 10 and the reconfigurable airlock 7 of the core module 1 are backup airlocks for each other.

[0026] The present invention uses a reconfigurable airlock as the main airlock or backup airlock to replace the backup airlock function of the node cabin, thereby normally releasing the traffic artery function of the node cabin, thereby optimizing and compensating for the potential risks and shortcomings of the current space station using the node cabin as a backup airlock.

[0027] With the space station configuration of the reconfigurable airlock provided by the present invention, when astronauts enter and exit the sealed environment inside the cabin and the vacuum environment outside the cabin, unless there is a malfunction or accident in the cabin section where the astronauts are located, such as air leakage in the cabin wall caused by collision with space debris, fire, etc., the function of the main traffic artery of the node cabin is no longer affected. The astronauts in the cabin can still reach the faulty cabin in time for maintenance through the node cabin, which is a main traffic artery, to seize the most precious opportunity to handle and eliminate the accident, thereby controlling the scope of the accident and the level of dangerous damage.

[0028] At the same time, the reconfigurable airlock provided by the present invention has two docking ports, which does not affect the number and direction of the docking ports of the space station.

[0029] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention using the above disclosed contents without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the contents of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

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) comprises a node module (8) and a first living module (9), and is characterized in that: The core module (1) further comprises a reconfigurable airlock module (7); The reconfigurable airlock cabin (7) is provided with two docking ports, one of which is docked with the node cabin, and the other can be used as an expansion docking port for other spacecraft; The node cabin (8) is connected to the first living cabin (9), and the node cabin (8) has the flight direction after entering orbit as the front and the direction facing the ground as the bottom, and includes five docking mechanisms, namely, upper, lower, left, right and front, and can provide five docking ports; When the core module (1) is launched, from top to bottom, it is composed 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 axis of the module body coincides with the axis of the launch vehicle to adapt to the limited carrying envelope. After the core module (1) enters orbit, with the flight direction as the front, from front to back, it is composed of the reconfigurable airlock module (7), the node module (8) and the first living module (9).

2. A space station configuration of a reconfigurable airlock according to claim 1, characterized in that: After the core module (1) is in orbit, the reconfigurable airlock module (7) can be transferred from the forward docking port of the node module (8) to the ground interface of the node module (8). At the same time, the forward docking port of the node module (8) is released and can serve as the main docking port for other spacecraft launched subsequently.

3. A space station configuration of a reconfigurable airlock according to claim 1, characterized in that: The second spacecraft (2) comprises a second airlock cabin (10) and a second living cabin (11).

4. A space station configuration of a reconfigurable airlock according to claim 3, characterized in that: The second airlock (10) and the reconfigurable airlock (7) of the core module (1) serve as backup airlocks for each other.

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