Flexible cable membrane structure and deployment method, mars outpost structure and deployment method
Patent Information
- Application Number
- CN202611209406.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-08-10
- Publication Date
- 2026-09-25
Smart Images
Figure CN122808994A_ABST
Abstract
Description
Technical Field
[0001] Embodiments of this disclosure relate to a flexible cable-membrane structure and deployment method, and a Mars outpost structure and deployment method. Background Technology
[0002] Extraterrestrial habitats are engineering systems designed to support long-term human survival beyond Earth, while extraterrestrial outposts are indispensable precursor projects before the capability for in-situ extraterrestrial construction is achieved. Mars, as Earth's close neighbor, possesses a thin atmosphere and water ice, making it the most promising potentially habitable planet in the solar system besides Earth. Constructing a Mars outpost is a core component of Mars exploration and development missions, enabling further glimpses into Martian geological and climate evolution, the search for signs of extraterrestrial life, the conduct of unique scientific experiments, the verification of in-situ resource utilization technologies, and the development of extraterrestrial survival capabilities, thus preparing for astronauts to land on Mars and remain there long-term. Summary of the Invention
[0003] At least one embodiment of this disclosure provides a flexible cable-membrane structure, which includes a first surface layer and a second surface layer; the first surface layer includes an opening and has a first spherical radius, and the second surface layer has a second spherical radius, wherein the second surface layer is circumferentially sealed to the first surface layer in the circumferential direction, and the first spherical radius is larger than the second spherical radius, so that a first accommodating space can be formed between the first surface layer and the second surface layer.
[0004] For example, in the flexible cable membrane structure provided in at least one embodiment of this disclosure, the second surface layer includes a first portion and a second portion; the first portion is configured to form the first accommodating space with the first surface layer, and the second portion extends beyond the first accommodating space to form a second accommodating space, wherein the second accommodating space communicates with the first accommodating space through the opening.
[0005] For example, in at least one embodiment of the flexible cable-membrane structure provided in this disclosure, a connector is provided at the edge of the second portion away from the first portion, the connector being configured to connect to a lander so that the flexible cable-membrane structure can achieve a deceleration parachute configuration before the lander lands.
[0006] For example, in at least one embodiment of the flexible cable membrane structure provided in this disclosure, the first part includes an openable or closable hatch configured to adapt to the airlock of a lander so that the flexible cable membrane structure can be deployed after the lander lands.
[0007] For example, in at least one embodiment of the flexible cable membrane structure provided in this disclosure, the opening is located in the middle of the first surface layer and is configured to connect to the cabin of the lander.
[0008] At least one embodiment of this disclosure provides a Mars outpost structure, which includes a flexible cable membrane structure and a lander provided in the embodiments of this disclosure. The lander includes a combined cabin and an airlock cabin arranged in axial tandem. The combined cabin includes a first cabin portion with a first outer diameter smaller than the diameter of the opening, so that the first cabin portion can enter the first accommodating space through the opening and be sealed to the opening.
[0009] For example, in a Mars outpost structure provided in at least one embodiment of this disclosure, the combined module includes a core module and a propulsion module arranged in axial tandem, the airlock is located on the side of the core module away from the propulsion module, and the first module portion includes the core module.
[0010] At least one embodiment of this disclosure provides a deployment method for a flexible cable-membrane structure, comprising: connecting the edge of the second surface layer of the flexible cable-membrane structure to a lander, so that the flexible cable-membrane structure achieves a deceleration parachute configuration before the lander lands; and after the lander lands, placing at least a portion of the lander in a first receiving space through an opening in the first surface layer, and sealing the lander to the opening to form a closed space in the first receiving space, thereby enabling the flexible cable-membrane structure to achieve a deployment configuration after the lander lands.
[0011] For example, in a deployment method provided in at least one embodiment of this disclosure, the lander includes a combined cabin and an airlock, wherein connecting the edge of the second surface layer of the flexible cable membrane structure to the lander includes: connecting the edge of the second surface layer of the flexible cable membrane structure to the airlock.
[0012] For example, in a deployment method provided in at least one embodiment of this disclosure, the combined cabin includes a core cabin connected to the airlock and a propulsion cabin disposed on the side of the core cabin away from the airlock. The method of placing at least a portion of the lander in the first accommodating space through the opening includes: placing at least a portion of the core cabin in the first accommodating space through the opening.
[0013] For example, at least one embodiment of the deployment method provided in this disclosure further includes: fixing the end of the core module away from the propulsion module to the second surface layer.
[0014] For example, at least one embodiment of the deployment method provided in this disclosure further includes: after the lander lands, disconnecting the edge of the second surface layer from the airlock and fixing the edge of the second surface layer to the ground.
[0015] For example, in a deployment method provided in at least one embodiment of this disclosure, the second surface layer includes a first portion forming the first accommodating space with the first surface layer, the first portion including an openable or closable hatch, and the deployment method further includes: installing the airlock onto the hatch and inflating the first accommodating space.
[0016] At least one embodiment of this disclosure also provides a method for deploying a Mars outpost structure, comprising: deploying the flexible cable-membrane structure on Mars using the above-described method for deploying a flexible cable-membrane structure. Attached Figure Description
[0017] To more clearly illustrate the technical solutions of the embodiments of this disclosure, the accompanying drawings of the embodiments will be briefly described below. Obviously, the drawings described below only relate to some embodiments of this disclosure and are not intended to limit this disclosure.
[0018] Figure 1 This is a schematic diagram of the flexible cable-membrane structure provided in at least one embodiment of the present disclosure when realizing a deceleration parachute configuration; Figure 2 A schematic diagram of the flexible cable-membrane structure provided in at least one embodiment of this disclosure when implementing a deployment configuration; and Figure 3 This is a schematic diagram of the structure of a launcher provided in at least one embodiment of the present disclosure. Detailed Implementation
[0019] To make the objectives, technical solutions, and advantages of the embodiments of this disclosure clearer, the technical solutions of the embodiments of this disclosure will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this disclosure. All other embodiments obtained by those skilled in the art based on the described embodiments of this disclosure without creative effort are within the scope of protection of this disclosure.
[0020] Unless otherwise defined, the technical or scientific terms used in this disclosure shall have the ordinary meaning understood by one of ordinary skill in the art to which this disclosure pertains. The terms “first,” “second,” and similar terms used in this disclosure do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Terms such as “comprising” or “including” mean that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, without excluding other elements or objects. Terms such as “connected” or “linked” are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. Terms such as “upper,” “lower,” “left,” and “right” are used only to indicate relative positional relationships, and these relative positional relationships may change accordingly when the absolute position of the described objects changes.
[0021] Inflatable cable-membrane structures are a novel type of space structure composed of high-performance fiber membrane materials and a high-strength cable net system. They primarily utilize internal inflation to generate pressure, tensioning the flexible material and imparting stiffness, thereby forming a predetermined geometry and load-bearing capacity. During spacecraft launch, this flexible structure can be compactly folded, and after landing, it can be inflated and deployed, significantly saving spacecraft payload volume. Furthermore, while providing the same effective habitation volume, the structure's weight is far lower than traditional rigid cabins, significantly reducing the transport load for the launch system. Therefore, inflatable cable-membrane structures are a core solution for constructing Martian outposts and large-scale infrastructure: in the early stages of a Mars landing without in-situ structure construction capabilities, inflatable cable-membrane structures are suitable as the first modular habitation modules, airlocks, or transfer warehouses to arrive on Mars, enabling rapid deployment; even after establishing a permanent Martian base, the enormous internal volume provided by this structure makes it an ideal choice for constructing large-area greenhouses on the Martian surface.
[0022] To further save the spacecraft's carrying capacity and the launch system's transport payload, at least one embodiment of this disclosure provides a flexible cable-membrane structure and its deployment method, as well as a Mars outpost structure and its deployment method. The flexible cable-membrane structure includes a first surface layer and a second surface layer. The first surface layer includes an opening and has a first spherical radius, while the second surface layer has a second spherical radius. The second surface layer is circumferentially sealed to the first surface layer, and the first spherical radius is larger than the second spherical radius, so that a first accommodating space can be formed between the first surface layer and the second surface layer.
[0023] The flexible cable-membrane structure provided in this embodiment has a double-layer structure. This double-layer structure can be configured as a drag chute during the landing process to perform the function of a drag chute (or parachute), and can be configured as a deployment structure after the lander lands to perform the function of a surface base. Thus, the flexible cable-membrane structure can realize the dual functions of a drag chute and a surface base, thereby saving space and load for the landing mission.
[0024] Specifically, during the lander's descent phase, the double-layer structure undergoes a parachute deployment process. During deployment, the first layer initially bears the load. Due to its larger first spherical radius, the first layer has a lower aerodynamic drag coefficient, and its central opening prevents excessive dynamic load during deployment, ensuring stability. As descent continues, airflow fills the first accommodating space between the first and second layers through the opening, gradually shaping and bearing the load on the second layer. As the descent speed decreases, the "inflation" is complete, and the second layer primarily bears the load on the deceleration parachute, gradually reducing the descent speed to a stable value, thus assisting the lander in a smooth landing. After landing, the lander's hull can be positioned within the first accommodating space through the opening, providing a rigid support structure for the double-layer structure. Together with the double-layer structure, it forms the base surface. The first accommodating space between the first and second layers becomes a closed space, where modules such as power supply and communication components can be installed, functioning as an outpost. Alternatively, the first accommodating space can form a greenhouse for cultivation, experimentation, or other scientific research activities.
[0025] The following describes the flexible cable-membrane structure and its deployment method, as well as the Mars outpost structure and its deployment method, provided in this disclosure through several specific embodiments.
[0026] This disclosure provides at least one embodiment of a flexible cable-membrane structure. Figure 1 This diagram illustrates the structure of the flexible cable-membrane structure when realizing the deceleration parachute configuration. Figure 2 A schematic diagram of the flexible cable-membrane structure in its deployment configuration is shown, as follows. Figure 1 and Figure 2 As shown, the flexible cable membrane structure includes a first surface layer 10 and a second surface layer 20; the first surface layer 10 includes an opening 11 and has a first spherical radius; the second surface layer 20 has a second spherical radius and is circumferentially sealed to the first surface layer 10. The first spherical radius is larger than the second spherical radius, so that the first surface layer 10 is flatter than the second surface layer 20, so that a first accommodating space S1 can be formed between the first surface layer 10 and the second surface layer 20.
[0027] Therefore, this flexible cable-membrane structure has a double-layer structure, which can be used in conjunction with the lander to achieve the deceleration parachute configuration during the lander's descent. The double-layer structure assists the lander in a smooth landing and achieves the deployment configuration after the lander lands. Thus, this flexible cable-membrane structure can realize the dual functions of deceleration parachute and ground base, and can also be called a "dual-purpose flexible cable-membrane structure for deceleration parachute and deployment", so as to save space and load for landing missions.
[0028] Specifically, in combination Figure 1 During the lander's descent phase, the double-layer structure undergoes a parachute deployment process. During deployment, the first layer 10 initially bears the load. Due to its larger first spherical radius, the first layer 10 has a lower aerodynamic drag coefficient, and its central opening 11 prevents excessive dynamic load during deployment, ensuring stability. As descent continues, airflow fills the first accommodating space S1 between the first and second layers 10 through the opening 11, causing the second layer 20 to gradually form (bulge) and bear the load. As the lander's descent speed gradually decreases, the "inflation" is complete, and the second layer 20 becomes the primary load-bearing component of the deceleration parachute, gradually reducing the descent speed to a stable value, thus assisting the lander in a smooth landing. Combined with... Figure 2 After the lander lands, the lander's hull can be positioned in the first accommodating space S1 through the opening 11, thereby utilizing the lander's hull to achieve a rigid support structure for the double-layer structure, forming a base surface together with the double-layer structure. The first accommodating space S1 between the first layer 10 and the second layer 20 forms a closed space, where modules such as power supply components and communication components can be built to realize the function of an outpost; or, the first accommodating space S1 can form a greenhouse (such as a flexible dome greenhouse) for scientific research activities such as grain cultivation or experiments.
[0029] For example, in some embodiments, the edge of the first surface layer 10 is rounded, the edge of the second surface layer 20 is also rounded, and the second surface layer 20 is circumferentially sealed to the circumferential edge of the first surface layer 10.
[0030] For example, such as Figure 1 and Figure 2As shown, the second surface layer 20 includes a first portion 21 and a second portion 22. The first portion 21 is configured to form a first receiving space S1 with the first surface layer 10, and the second portion 22 extends beyond the first receiving space S1 to form a second receiving space S2. The second receiving space S2 is connected to the first receiving space S1 through an opening 11. The second receiving space S2 is an open space. Therefore, during the opening process of the double-layer structure, the first surface layer 10 is subjected to force first and gradually bulges up. The second receiving space S2 gradually increases in size. The opening 11 at the center of the first surface layer 10 can connect the first receiving space S1 and the second receiving space S2, thereby allowing airflow to gradually enter the first receiving space S1, so that the dynamic load of the opening is not too large and the opening stability is guaranteed.
[0031] For example, in some embodiments, the second portion 22 of the second surface layer 20 may be provided with serrated slits (not shown), which extend circumferentially along the second portion 22 to achieve the effects of exhaust and regulating air pressure, making the umbrella opening process smoother.
[0032] For example, such as Figure 1 and Figure 2 As shown, the edge of the second part 22 away from the first part 21 is provided with connectors 23, such as multiple connectors 23. The connectors 23 are configured to connect with the lander so that the flexible cable membrane structure can achieve a deceleration parachute configuration before the lander lands. For example, the connectors 23 can be implemented as any form of connection structure such as connecting holes, connecting rings, or snap-fit pieces. They can connect parachute lines 24, which can be fixed to the lander, for example, to the airlock 31 of the lander, to achieve the deceleration parachute configuration.
[0033] For example, in some embodiments, reference Figure 2 The first part 21 includes an openable or closable hatch 25. The hatch 25 can be a pre-reserved connection port on the first part 21. The connection port is closed when the double-layer structure is in the deceleration parachute configuration. The hatch 25 is configured to be adapted to the airlock 31 of the lander so that the flexible cable membrane structure is sealed to the airlock 31 through the hatch 25 after the lander lands, so that the flexible cable membrane structure can achieve the deployment configuration. At this time, the airlock 31 forms the "door" of the surface base.
[0034] For example, in some embodiments, reference Figure 2 The opening 11 is located in the middle of the first surface layer 10 and is configured to connect (e.g., seal) the lander's body, such as the core module 32 or propulsion module 33 of the lander (detailed in detail later), so that the lander's body can be reused as a rigid support structure for the surface base. At this time, the rigid support structure is located in the middle of the double-layer structure, thereby improving the stability of the surface base.
[0035] For example, in other embodiments, the opening 11 can also be connected to other support materials, such as high-elasticity glass fiber rods, elastic memory materials, etc., for rigid support; or, the opening 11 can be directly closed, and then the first accommodating space S1 can be inflated, so that the flexible cable membrane structure can realize the deployment function independently.
[0036] For example, the flexible cable membrane structure can be made of various flexible materials such as polyester fiber, ultra-high molecular weight polyethylene, poly(p-phenylenebenzobisoxazole), ethylene-vinyl alcohol copolymer, and high-strength woven fabric, such as aramid woven fabric. The embodiments disclosed herein do not specifically limit the use of such materials.
[0037] For example, the flexible cable-membrane structure provided in this disclosure can be used on extraterrestrial landers such as those for Mars, to realize functions such as extraterrestrial outposts. For example, the flexible cable-membrane structure can be used to realize a Mars landing outpost system, such as a Mars deceleration parachute, a Mars outpost, or a Mars greenhouse, to save space and payload for landing missions. For example, the flexible cable-membrane structure provided in this disclosure can also be used in extreme sports, wilderness exploration, and other fields to assist participants in a smooth landing and to build outdoor campsites, for example, by using high-elastic fiberglass poles, elastic memory materials, and other structures to achieve the deployment and support of the membrane material, thus enabling the construction of outdoor campsites.
[0038] At least one embodiment of this disclosure provides a Mars outpost structure, which includes a flexible cable-membrane structure and a lander as provided in the embodiments of this disclosure. Figure 3 A schematic diagram of the lander's structure is shown, as follows: Figure 3 As shown, the lander includes a combined cabin 30 and an airlock cabin 31 arranged axially in tandem. The combined cabin includes a first hull section (e.g., Figure 2 (The portion located within the first accommodating space S1), see reference. Figure 3 The first cabin portion has a first outer diameter D1, which is smaller than the diameter of the opening 11, so that the first cabin portion can enter the first accommodating space S1 through the opening 11 and be sealed to the opening 11. Thus, after landing, the lander's combined cabin can form a rigid support structure with a flexible cable membrane structure. By sealing the lander's cabin to the opening 11, the first accommodating space S1 can become a closed space, which can be filled with the required gas to achieve functions such as a greenhouse or outpost.
[0039] As can be seen, the Mars outpost structure provided in this embodiment employs a double-layer flexible cable-membrane structure to combine the flexible dome outpost and the deceleration parachute. During the descent phase, the double-layer flexible cable-membrane structure functions as a deceleration parachute. This deceleration parachute is a centrally radiating cable-membrane structure. Its main circular structure features two layers: the first layer has a large spherical radius and a central opening, while the second layer has a small spherical radius and no opening. Due to the difference in spherical radii, a certain space exists between the first and second layers, forming a first accommodating space. After the lander lands, the deceleration parachute can directly serve as the main structure of the dome outpost, saving space and payload for the landing mission.
[0040] For example, such as Figure 3 As shown, the combined module 30 includes a core module 32 and a propulsion module 33 arranged axially in series. An airlock 31 is located on the side of the core module 32 away from the propulsion module 33. The aforementioned first module portion includes the core module 32. For example, the propulsion module 33 of the lander is sealed to the opening 11. Thus, the lander's modules are arranged axially so that after landing, the combined module 30 and the airlock 31 separate. The combined module 30 can function as a rigid support structure for the flexible cable membrane structure, while the airlock 31 functions as a "door."
[0041] For example, such as Figure 3 As shown, the lander is cylindrical in shape, for example, nearly cylindrical, with the airlock 31, core module 32, and propulsion module 33 arranged along the axial direction of the column. The shape of the opening 11 is adapted to the shape of the lander, for example, it is circular. For example, in other embodiments, the lander may adopt other shapes as needed, and the embodiments disclosed herein are not specifically limited in this regard.
[0042] For example, the sealing connection between the airlock 31 and the hatch 25, and the sealing connection between the lander's body and the opening 11, can be achieved in various ways. For instance, a metal flange can provide clamping force to sandwich the flexible material of the flexible cable-membrane structure in the middle, and special rubber (such as fluoropolymer or silicone rubber) can be used to achieve airtightness. In this case, a ring-shaped metal flange can be reserved on the side wall of the propulsion compartment 33 and the airlock 31. The outer diameter of the ring-shaped metal flange can be larger than the diameter of the opening 11 so as to cover the opening 11. The flexible material of the flexible cable-membrane structure is clamped and compressed by the metal flange to achieve a sealing connection. Alternatively, the sealing connection between the airlock 31 and the hatch 25, and the sealing connection between the lander's body and the opening 11, can also adopt other sealing connection methods such as chemical bonding or heat fusion / heat sealing. The embodiments disclosed herein do not specifically limit this method.
[0043] At least one embodiment of this disclosure provides a method for deploying a flexible cable-membrane structure, the method comprising: referring to Figure 1The edge of the second surface layer 20 of the flexible cable membrane structure is connected to the lander so that the flexible cable membrane structure can achieve the deceleration parachute configuration before the lander lands; after the lander lands, at least a part of the lander is placed in the first receiving space S1 through the opening 11 of the first surface layer 10, and the lander is sealed to the opening 11 to form a closed space in the first receiving space S1, so that the flexible cable membrane structure can achieve the deployment configuration after the lander lands.
[0044] For example, the lander includes a combined compartment 30 and an airlock compartment 31. Connecting the edge of the second surface layer 20 of the flexible cable membrane structure to the lander includes connecting the edge of the second surface layer 20 of the flexible cable membrane structure to the airlock compartment 31. For example, the edge of the second surface layer 20 of the flexible cable membrane structure is connected to the airlock compartment 31 of the lander via a connector 23 and parachute ropes 24.
[0045] For example, the combined module 30 includes a core module 32 connected to the airlock module 31 and a propulsion module 33 disposed on the side of the core module 32 away from the airlock module 31. The process of placing at least a portion of the lander in the first receiving space S1 through the opening 11 includes: placing at least a portion (e.g., all) of the core module 32 in the first receiving space S1 through the opening 11; the process of sealing the lander to the opening 11 includes: sealing the body of the propulsion module 33 of the lander to the opening 11.
[0046] For example, in some embodiments, to improve the stability of the surface substrate formed by the flexible cable-membrane structure, the deployment method further includes: positioning the end of the core module 32 furthest from the propulsion module 33 (i.e., Figure 2 The upper end of the middle layer is fixedly connected to the second surface layer 20. For example, refer to Figure 2 The top of the core module 32 is fixedly connected to the top of the second surface layer 20, for example, by means of hooks, snap-fit structures or any other means. This allows the combined module 30 to achieve better rigid support as a whole and improves the stability of the ground base.
[0047] For example, in some embodiments, the deployment method further includes: after the lander lands, separating the airlock 31 from the combined module 30, disconnecting the edge of the second surface layer 20 from the airlock 31, and fixing the edge of the second surface layer 20 to the ground; for example, disconnecting the connector 23 and parachute ropes 24 from the airlock 31 and fixing it to the ground via the connector 23 and parachute ropes 24, or fixing it to the ground via the connector 23 and other rope structures 26. Thus, the connector 23 can be used to connect to the airlock 31 when the double-layer structure is in the deceleration parachute configuration, and to connect to the alien ground after the lander lands.
[0048] For example, in some embodiments, reference Figure 2The deployment method also includes: installing the airlock 31 at the hatch 25 and inflating the first containment space S1. For example, installing the airlock 31 at the hatch 25 can function as a "door". Furthermore, the required gas can be injected into the first containment space S1 through the airlock 31 to make the first containment space S1 more suitable for biological living, experimental operations, or other functions.
[0049] At least one embodiment of this disclosure also provides a method for deploying a Mars outpost structure, the method comprising: deploying the flexible cable-membrane structure on Mars using the above-described method for deploying flexible cable-membrane structures.
[0050] The deployment method provided in this disclosure will be described in detail below through a specific example of a lander landing on Mars and a flexible cable-membrane structure forming a Mars outpost.
[0051] First, the edge of the second layer 20 of the flexible cable membrane structure is fixed to the airlock 31 of the lander by the connector 23 and the parachute rope 24, and the flexible cable membrane structure is tightened and folded for use.
[0052] After the lander ascends and reaches the designated position, and begins its descent to a certain altitude, it deploys its deceleration parachute. During the deployment process, the first layer 10 of the double-layer structure is initially subjected to force. Due to the larger radius of the first spherical surface of the first layer 10, it has a smaller aerodynamic drag coefficient, and the opening 11 in the center prevents the dynamic load of the parachute from becoming too large, ensuring the stability of the parachute deployment. As the descent continues, airflow "inflates" the first accommodating space S1 between the first layer 10 and the second layer 20 through the opening 11 of the first layer 10. The second layer 20 gradually takes shape (bulges) and is subjected to force. As the descent speed of the lander gradually decreases, the "inflation" is completed, and the deceleration parachute is mainly supported by the second layer 20. The descent speed gradually decreases to a stable value, thereby assisting the lander in a smooth landing.
[0053] As the lander approaches the ground, the airlock 31 separates from the core module 32, the propulsion module 33's engines start up, and it descends vertically together with the core module 32. At the same time, the drag chute carries the airlock 31 to the ground nearby.
[0054] Next, the deployment of the Mars outpost will proceed. For example, astronauts will land nearby in a separate landing spacecraft, or retrieve the deceleration parachute and airlock 31 using a Mars rover; the combined module 30 (rigid core) will be secured to the ground, and the surrounding ground will be leveled; the parachute ropes 24 will be removed, and the opening 11 of the first layer 10 of the double-layer structure will be fitted into the combined module 30, with the second layer 20 connected and secured to the top of the combined module 30, and the opening 11 sealed to the bottom of the combined module 30; at this point, with the combined module 30, i.e., the rigid core, as the center and the diameter of the deceleration parachute as the diameter, a Mars outpost of a certain size will be formed. The outpost is secured to the ground by connecting parts 23 at the edge of the second surface layer 20. The hatch 25 reserved on the side of the second surface layer 20 is opened and connected to the airlock 31 and sealed. Then, gas is supplied through the airlock 31 using a gas generator and other gas supply devices, thus completing the deployment of the main structure of the Mars outpost. Power supply components, communication components and other modules are taken out from the core module 32 and assembled, finally completing the deployment of the entire Mars outpost.
[0055] For example, astronauts can return to Mars aboard their original spacecraft after completing a certain period of stay, while the Mars outpost can remain and operate continuously indefinitely. In some embodiments, the second surface layer 20 can be a light-transmitting structure, such as being made of light-transmitting materials like ultra-high molecular weight polyethylene. In this case, the Mars outpost can serve as a Martian greenhouse for food cultivation, as well as an energy supply station and communication station, providing energy and commands for in-situ construction robots.
[0056] The deployment method provided in this disclosure is simple and easy to operate. Furthermore, the flexible cable membrane structure provided in this disclosure can realize multiple functions such as deceleration parachute, outpost, and greenhouse, which can save space and load for landing missions and make the configuration more flexible.
[0057] The following points also need to be explained: (1) The accompanying drawings of the embodiments of this disclosure only involve the structures involved in the embodiments of this disclosure. Other structures can be referred to the general design.
[0058] (2) For clarity, the thickness of layers or regions in the drawings used to describe embodiments of the present disclosure is enlarged or reduced, i.e., these drawings are not drawn to actual scale.
[0059] (3) Where there is no conflict, the embodiments of this disclosure and the features in the embodiments can be combined with each other to obtain new embodiments.
[0060] The above are merely specific embodiments of this disclosure, but the scope of protection of this disclosure is not limited thereto. The scope of protection of this disclosure shall be determined by the scope of the claims.
Claims
1. A flexible cable-membrane structure, comprising: The first surface layer includes an opening having a first spherical radius, and The second surface layer has a second spherical radius, wherein the second surface layer is circumferentially sealed to the first surface layer in the circumferential direction. The radius of the first sphere is greater than the radius of the second sphere, so that a first accommodating space can be formed between the first surface layer and the second surface layer.
2. The flexible cable-membrane structure according to claim 1, wherein, The second surface layer includes: The first part is configured to form the first receiving space with the first surface layer. The second part extends beyond the first accommodating space to form a second accommodating space, wherein the second accommodating space is connected to the first accommodating space through the opening.
3. The flexible cable-membrane structure according to claim 2, wherein, The second part has a connector at its edge away from the first part, the connector being configured to connect to the lander so that the flexible cable membrane structure can achieve a deceleration parachute configuration before the lander lands.
4. The flexible cable-membrane structure according to claim 2 or 3, wherein, The first part includes an openable or closable hatch configured to adapt to the airlock of the lander so that the flexible cable membrane structure can be deployed after the lander lands.
5. The flexible cable-membrane structure according to any one of claims 1-3, wherein, The opening is located in the middle of the first surface layer and is configured to connect to the landing vehicle's cabin.
6. A Mars outpost structure, comprising: The flexible cable-membrane structure according to any one of claims 1-5, and The lander comprises a combined compartment and an airlock arranged in axial tandem. The combined cabin includes a first cabin portion having a first outer diameter smaller than the diameter of the opening, so that the first cabin portion can enter the first accommodating space through the opening and be sealed to the opening.
7. The Mars outpost structure according to claim 6, wherein, The combined module includes a core module and a propulsion module arranged in tandem along an axis, with the airlock located on the side of the core module away from the propulsion module. The first cabin section includes the core cabin.
8. A method for deploying the flexible cable-membrane structure according to claim 1, comprising: The edge of the second surface layer of the flexible cable-membrane structure is connected to the lander, so that the flexible cable-membrane structure achieves a deceleration parachute configuration before the lander lands. After the lander lands, at least a portion of the lander is placed in the first receiving space through the opening in the first surface layer, and the lander is sealed to the opening to form a closed space in the first receiving space, thereby enabling the flexible cable membrane structure to be deployed after the lander lands.
9. The deployment method according to claim 8, wherein, The lander includes a combined module and an airlock. The connection of the edge of the second surface layer of the flexible cable membrane structure to the lander includes: The edge of the second surface layer of the flexible cable membrane structure is connected to the airlock.
10. The deployment method according to claim 9, wherein, The combined compartment includes a core compartment connected to the airlock and a propulsion compartment located on the side of the core compartment away from the airlock. Wherein, at least a portion of the landing device is disposed in the first receiving space through the opening, including: At least a portion of the core compartment is disposed in the first accommodating space through the opening.
11. The deployment method according to claim 10, further comprising: The end of the core module furthest from the propulsion module is fixedly connected to the second surface layer.
12. The deployment method according to claim 9, further comprising: After the lander lands, disconnect the edge of the second surface layer from the airlock and fix the edge of the second surface layer to the ground.
13. The deployment method according to claim 12, wherein, The second surface layer includes a first portion forming the first accommodating space with the first surface layer, the first portion including an openable or closable hatch. The deployment method also includes: The airlock is installed at the hatch and inflated into the first containment space.
14. A method for deploying a Mars outpost structure, comprising: The flexible cable-membrane structure is deployed on Mars using the deployment method of the flexible cable-membrane structure as described in claim 8.