A multi-generation power generation system for in-situ resource utilization of Mars and a working method thereof
By utilizing a combined heat and power generation system based on in-situ resources on Mars, and employing components such as a gas jet ice melter and a photocatalytic water splitting unit, the system achieves efficient utilization of multiple energy sources. This solves the problems of energy supply stability and efficiency in Mars exploration, and enhances the mission's endurance and economic efficiency.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- HARBIN INST OF TECH
- Filing Date
- 2026-04-03
- Publication Date
- 2026-07-07
AI Technical Summary
Existing Mars exploration energy supply solutions rely on Earth's resources, resulting in insufficient power supply stability, low energy density, high research and development costs, and significant challenges in radiation protection. Furthermore, existing energy systems lack cascade utilization designs, leading to low efficiency in waste heat recovery and secondary utilization, which limits the mission's endurance.
Design a combined heat and power generation system for in-situ resource generation on Mars. Utilize components such as a gas jet de-icer, a photocatalytic water splitter, and fuel cells to output electricity, heat, and propellant through an open Brayton cycle and combustion chamber, achieving efficient utilization of multiple energy forms, including the combined production of electricity, heat, and propellant.
It reduced the weight of the spacecraft launch payload, lowered launch costs, improved the feasibility and economy of the exploration mission, achieved the synergistic output and efficient utilization of multiple energy forms, met the power supply requirements of the exploration equipment, and provided thermal support and propellant supply, thereby enhancing the overall application value of the system.
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Figure CN122348656A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of space energy technology, specifically to a combined heat and power generation system and its operating method for in-situ resource generation on Mars. Background Technology
[0002] Mars exploration is a core research direction in the field of deep space exploration. The continuous operation of unmanned exploration equipment, the implementation of manned exploration missions, and the construction of Mars bases all place stringent requirements on energy systems, demanding high reliability, long endurance, and multiple resource supplies. Current energy supply solutions for Mars exploration mostly rely on chemical fuels, solar panels, or nuclear power sources carried from Earth. These models all have significant technical shortcomings. Solar panels are susceptible to Martian dust cover and changes in light conditions, resulting in insufficient power supply stability and energy density. Nuclear power sources have high development costs and significant challenges in radiation protection, limiting their engineering applications. Chemical fuels, on the other hand, need to be transported in large quantities from Earth, becoming a major burden on spacecraft launch payloads and severely restricting the endurance and scalability of exploration missions.
[0003] Mars possesses abundant ice resources and an atmosphere primarily composed of carbon dioxide, representing valuable in-situ resources that can be developed and utilized. However, current technologies have not yet achieved efficient conversion and comprehensive utilization of these resources, nor have they established an energy-resource cogeneration system based on Mars' in-situ resources. This means that Mars exploration remains reliant on Earth's resource supply, failing to achieve independent energy supply and resource security in outer space. Furthermore, existing energy systems employ relatively inefficient energy utilization models, lacking tiered energy utilization designs and exhibiting low efficiency in waste heat recovery and secondary utilization, further reducing the overall energy efficiency of the system. Therefore, developing a power generation system that leverages Mars' in-situ resources to achieve multi-energy and multi-resource cogeneration has become a key technological requirement for overcoming the energy bottleneck in Mars exploration. Summary of the Invention
[0004] This invention addresses the challenges of resupplying working fluids in existing space energy systems, as well as the relatively extensive energy utilization models, lack of energy cascade utilization design, and low efficiency in waste heat recovery and secondary utilization, which further reduces the overall energy utilization efficiency of the system. Therefore, this invention proposes a combined heat and power generation system and its operating method based on in-situ resources on Mars. The invention achieves these technical problems through the following technical solutions: Option 1: This invention proposes a combined heat and power generation system for in-situ resource utilization on Mars. The system includes a gas jet de-icing device, a water pump, a photocatalytic water splitting unit, a hydrogen storage tank, an oxygen storage tank, a hydrogen pump, a fuel cell, a filter, a Martian air compressor, a generator, a Martian air turbine, a compressor, a combustion chamber, a turbine, and a cooling channel. The cold-side outlet of the gas jet de-icing device is connected to the inlet of the water pump; the outlet of the water pump is connected to the inlet of the photocatalytic water splitting unit; the hydrogen outlet of the photocatalytic water splitting unit is connected to the inlet of the hydrogen storage tank; the outlet of the hydrogen storage tank is connected to the inlet of the hydrogen pump; the outlet of the hydrogen pump is connected to the anode inlet of the fuel cell; the unreacted hydrogen outlet of the fuel cell is connected to the hydrogen inlet of the combustion chamber; the oxygen outlet of the photocatalytic water splitting unit is connected to the inlet of the oxygen storage tank; the outlet of the oxygen storage tank is connected to the inlet of the compressor; the first outlet of the compressor is connected to the cathode inlet of the fuel cell; the second outlet of the compressor is connected to the oxygen inlet of the combustion chamber; and the outlet of the combustion chamber is connected to the inlet of the turbine. The outlet of the filter is connected to the inlet of the Mars air compressor, the outlet of the Mars air compressor is connected to the inlet of the cooling channel, the outlet of the cooling channel is connected to the inlet of the Mars air turbine, and the Mars air turbine is connected to the hot-side inlet of the gas jet de-icing device.
[0005] Furthermore, a preferred embodiment is provided in which the Mars air compressor, the generator, and the Mars air turbine are arranged coaxially. During operation, the Mars air turbine drives the rotor shaft to rotate, thereby driving the Mars air compressor and the generator to work.
[0006] Furthermore, a preferred embodiment is provided in which the compressor and the turbine are arranged coaxially, and the compressor and the turbine are connected through the rotor shaft. During operation, the turbine drives the rotor shaft to rotate, thereby driving the compressor to work.
[0007] Furthermore, a preferred embodiment is provided in which a filter module is provided at the inlet of the water pump.
[0008] Furthermore, a preferred embodiment is provided in which the Mars air turbine and the turbine are axial flow turbines or radial flow turbines.
[0009] Furthermore, a preferred embodiment is provided, wherein the fuel cell is a solid oxide fuel cell.
[0010] Furthermore, a preferred embodiment is provided in which both the hydrogen storage tank and the oxygen storage tank are equipped with filling valves at their outlets.
[0011] Furthermore, a preferred embodiment is provided in which the filter is used to filter dust impurities contained in the Martian atmosphere.
[0012] Option 2: The operating method of the combined heat and power generation system for in-situ resource utilization on Mars according to any one of Options 1, the method comprising the following steps: The working fluid of the open Brayton cycle and extraterrestrial ice are heated and liquefied by a gas jet de-icing device and then pumped out by a water pump and enter the photocatalytic water splitting unit. During the day, hydrogen and oxygen are generated by photocatalytic water splitting and stored in hydrogen storage tank and oxygen storage tank respectively. Hydrogen is pumped out by a hydrogen pump and enters the anode of the fuel cell. Oxygen is pressurized by a compressor and enters the cathode of the fuel cell to undergo an electrochemical reaction. Unreacted hydrogen in the exhaust gas enters the combustion chamber to participate in combustion. The gas enters the turbine to expand and do work. The turbine drives the compressor to work. Martian air is filtered and then pressurized by a Martian air compressor. The compressed Martian air enters the cooling channel of the fuel cell to absorb the waste heat of the fuel cell. The heated Martian air then enters the Martian air turbine to expand and do work. The turbine drives a generator to generate electricity. The Martian air that has done work then enters a gas jet de-icer to complete the cycle.
[0013] Furthermore, a preferred embodiment is provided in which the open Brayton cycle working fluid is realized using the Martian atmosphere, which is mainly composed of carbon dioxide.
[0014] The advantages of this invention are: The present invention discloses a combined heat and power generation system for in-situ resource generation on Mars, which adopts an in-situ energy production mode from extraterrestrial space. Its open Brayton cycle working medium and extraterrestrial ice can be directly obtained from the surface of Mars without the need to be carried from Earth. This effectively reduces the payload weight before spacecraft launch, thereby significantly reducing launch costs. At the same time, it reduces payload risks during launch and improves the feasibility and economy of extraterrestrial exploration missions.
[0015] The present invention discloses a combined heat and power generation system for in-situ resource generation on Mars, which realizes the synergistic production and efficient utilization of multiple energy forms: power is output through fuel cells and open Brayton cycle system to meet the power supply needs of exploration equipment and related systems; heat is stably output through combustion chamber to provide thermal support for system circulation and operation of related equipment; propellant is prepared through water electrolysis hydrogen production process, which can be directly supplied to the probe, and finally achieves integrated production of heat, electricity and propellant, thereby enhancing the comprehensive application value of the system.
[0016] The in-situ Mars resource-based combined heat and power generation system described in this invention produces pure water and oxygen during the circulation process, both of which are core resources required for astronauts' survival in space. This allows the system to seamlessly integrate and perfectly adapt to space life support systems. This feature expands the system's application scenarios, especially in areas such as manned Mars exploration and the construction of extraterrestrial space bases, where it possesses significant application advantages and broad development prospects.
[0017] The present invention discloses a combined heat and power generation system for in-situ resource utilization on Mars, which constructs a multi-level cascade utilization system for hydrogen energy. Hydrogen directly participates in electrochemical reactions (fuel cell power generation) and combustion reactions (combustion chamber heat generation), while indirectly participating in the open Brayton cycle process. By heating the working fluid of the open Brayton cycle through the waste heat generated by the fuel cell, the expansion and work-making capacity of the working fluid is effectively improved, and the energy utilization efficiency of the entire system is greatly improved.
[0018] This invention is also applicable to the integrated cogeneration of thermal energy, electrical energy, hydrogen-oxygen fuel, and pure water. Attached Figure Description
[0019] Figure 1 This is a schematic diagram of the combined heat and power generation system for in-situ resource utilization on Mars as described in Embodiment 1.
[0020] The components include: a gas jet de-icer 1, a water pump 2, a photocatalytic water splitting unit 3, a hydrogen storage tank 4, an oxygen storage tank 5, a hydrogen pump 6, a fuel cell 7, a filter 8, a Mars air compressor 9, a generator 10, a Mars air turbine 11, a compressor 12, a combustion chamber 13, a turbine 14, and a cooling channel 15. Detailed Implementation
[0021] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them.
[0022] Implementation Method 1, see [link] Figure 1 This embodiment describes a combined heat and power generation system for in-situ resource utilization on Mars. The system utilizes Martian native energy resources for in-situ production, achieving integrated cogeneration of heat, electricity, hydrogen-oxygen fuel, and pure water, thus solving the problem of difficult working fluid replenishment in existing space energy systems. The system includes a gas jet de-icing device 1, a water pump 2, a photocatalytic water splitting unit 3, a hydrogen storage tank 4, an oxygen storage tank 5, a hydrogen pump 6, a fuel cell 7, a filter 8, a Martian air compressor 9, a generator 10, a Martian air turbine 11, a compressor 12, a combustion chamber 13, a turbine 14, and a cooling channel 15. The cold-side outlet of the gas jet de-icing unit 1 is connected to the inlet of the water pump 2. The outlet of the water pump 2 is connected to the inlet of the photocatalytic water splitting unit 3. The hydrogen outlet of the photocatalytic water splitting unit 3 is connected to the inlet of the hydrogen storage tank 4. The outlet of the hydrogen storage tank 4 is connected to the inlet of the hydrogen pump 6. The outlet of the hydrogen pump 6 is connected to the anode inlet of the fuel cell 7. The unreacted hydrogen outlet of the fuel cell 7 is connected to the hydrogen inlet of the combustion chamber 13. The oxygen outlet of the photocatalytic water splitting unit 3 is connected to the inlet of the oxygen storage tank 5. The outlet of the oxygen storage tank 5 is connected to the inlet of the compressor 12. The first outlet of the compressor 12 is connected to the cathode inlet of the fuel cell 7. The second outlet of the compressor 12 is connected to the oxygen inlet of the combustion chamber 13. The outlet of the combustion chamber 13 is connected to the inlet of the turbine 14. The outlet of filter 8 is connected to the inlet of Mars air compressor 9, the outlet of Mars air compressor 9 is connected to the inlet of cooling channel 15, the outlet of cooling channel 15 is connected to the inlet of Mars air turbine 11, and Mars air turbine 11 is connected to the hot side inlet of gas jet de-icing device.
[0023] Implementation Method 2: This implementation method proposes a working method for a Mars in-situ resource-based combined heat and power generation system. The method is based on the Mars in-situ resource-based combined heat and power generation system described in Implementation Method 1. Extraterrestrial ice is heated and liquefied by a gas jet de-icer 1 and then extracted by a water pump 2, entering a photocatalytic water splitting unit 3. During the day, hydrogen and oxygen are generated through photocatalytic water splitting and stored in hydrogen storage tank 4 and oxygen storage tank 5, respectively. Hydrogen is extracted by a hydrogen pump 6 and enters the anode of a fuel cell 7. Oxygen is pressurized by a compressor 12 and enters the cathode of a fuel cell 7 to undergo an electrochemical reaction. Unreacted hydrogen in the exhaust gas enters the combustion chamber 13 to participate in combustion. The combustion gas enters the turbine 14 to expand and do work, and the turbine 14 drives the compressor 12 to work.
[0024] Martian air is filtered by filter 8 and then enters Martian air compressor 9 for pressurization. The compressed Martian air enters the cooling channel 15 of fuel cell 7 to absorb the waste heat of fuel cell. The heated Martian air enters Martian air turbine 11 to expand and do work. The turbine drives generator 10 to generate electricity. The Martian air after doing work enters gas jet de-icing device 1 to complete the cycle.
[0025] In summary, the power generation system described in this embodiment utilizes Martian native energy for in-situ production, achieving integrated co-production of heat, electricity, hydrogen-oxygen fuel, and pure water. This solves the problem of difficult working fluid replenishment in existing space energy systems. Through the coordinated output of power from fuel cells and an open Brayton cycle system, it meets the power supply needs of the exploration equipment and related systems. The combustion chamber stably outputs heat, providing thermal support for system circulation and the operation of related equipment. Propellant is prepared through water electrolysis to directly supply the probe, ultimately achieving integrated co-production of heat, electricity, and propellant, thus enhancing the system's comprehensive application value.
[0026] Those skilled in the art will understand that the above description is merely a preferred embodiment of the present invention, and the features described in the various embodiments and / or claims of this disclosure can be combined or combined in various ways, even if such combinations or combinations are not explicitly described in this disclosure. This is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.
[0027] Although preferred embodiments of the invention have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the invention. Clearly, those skilled in the art can make various alterations and modifications to the invention without departing from its spirit and scope. Thus, if these modifications and modifications of the invention fall within the scope of the claims and their equivalents, the invention is also intended to include these modifications and modifications.
Claims
1. A combined heat and power generation system for in-situ resource utilization on Mars, characterized in that, The system includes a gas jet de-icing device (1), a water pump (2), a photocatalytic water splitting unit (3), a hydrogen storage tank (4), an oxygen storage tank (5), a hydrogen pump (6), a fuel cell (7), a filter (8), a Mars air compressor (9), a generator (10), a Mars air turbine (11), a compressor (12), a combustion chamber (13), a turbine (14), and a cooling channel (15); The cold side outlet of the gas jet de-icing device (1) is connected to the inlet of the water pump (2), the outlet of the water pump (2) is connected to the inlet of the photocatalytic water splitting unit (3), the hydrogen outlet of the photocatalytic water splitting unit (3) is connected to the inlet of the hydrogen storage tank (4), the outlet of the hydrogen storage tank (4) is connected to the inlet of the hydrogen pump (6), the outlet of the hydrogen pump (6) is connected to the anode inlet of the fuel cell (7), the unreacted hydrogen outlet of the fuel cell (7) is connected to the hydrogen inlet of the combustion chamber (13); the oxygen outlet of the photocatalytic water splitting unit (3) is connected to the inlet of the oxygen storage tank (5), the outlet of the oxygen storage tank (5) is connected to the inlet of the compressor (12), the first outlet of the compressor (12) is connected to the cathode inlet of the fuel cell (7), the second outlet of the compressor (12) is connected to the oxygen inlet of the combustion chamber (13), and the outlet of the combustion chamber (13) is connected to the inlet of the turbine (14); The outlet of the filter (8) is connected to the inlet of the Mars air compressor (9), the outlet of the Mars air compressor (9) is connected to the inlet of the cooling channel (15), the outlet of the cooling channel (15) is connected to the inlet of the Mars air turbine (11), and the Mars air turbine (11) is connected to the hot side inlet of the gas jet de-icer (1).
2. The combined heat and power generation system for in-situ resource utilization on Mars according to claim 1, characterized in that, The Mars air compressor (9), the generator (10) and the Mars air turbine (11) are arranged coaxially. When working, the Mars air turbine (9) drives the rotor shaft to rotate, thereby driving the Mars air compressor (9) and the generator (10) to work.
3. The combined heat and power generation system for in-situ resource utilization on Mars according to claim 1, characterized in that, The compressor (12) and the turbine (14) are arranged coaxially, and the compressor (12) and the turbine (14) are connected through the rotor shaft. When working, the turbine (14) drives the rotor shaft to rotate, thereby driving the compressor (12) to work.
4. The combined heat and power generation system for in-situ resource utilization on Mars according to claim 1, characterized in that, The water pump (2) is equipped with a filter module at its inlet.
5. The combined heat and power generation system for in-situ resource utilization on Mars according to claim 1, characterized in that, The Mars air turbine (11) and turbine (14) are axial flow turbines or radial flow turbines.
6. The combined heat and power generation system for in-situ resource utilization on Mars according to claim 1, characterized in that, The fuel cell (7) is a solid oxide fuel cell.
7. The combined heat and power generation system for in-situ resource utilization on Mars according to claim 1, characterized in that, Both the hydrogen storage tank (4) and the oxygen storage tank (5) are equipped with filling valves at their outlets.
8. The combined heat and power generation system for in-situ resource utilization on Mars according to claim 1, characterized in that, The filter (8) is used to filter out dust and impurities contained in the Martian atmosphere.
9. The operating method of the combined heat and power generation system for in-situ resource utilization on Mars according to any one of claims 1-8, characterized in that, The method includes the following steps: The working fluid of the open Brayton cycle and the extraterrestrial ice are heated and liquefied by the gas jet de-icer (1) and then pumped out by the water pump (2) and enter the photocatalytic water splitting unit (3). During the day, hydrogen and oxygen are generated by photocatalytic water splitting and stored in the hydrogen storage tank (4) and oxygen storage tank (5) respectively. The hydrogen is pumped out by the hydrogen pump (6) and enters the anode of the fuel cell (7). The oxygen is pressurized by the compressor (12) and enters the cathode of the fuel cell (7) to undergo an electrochemical reaction. The unreacted hydrogen in the exhaust gas enters the combustion chamber (13) to participate in combustion. The gas enters the turbine (14) to expand and do work. The turbine (14) drives the compressor (12) to work. After being filtered by filter (8), Martian air enters Martian air compressor (9) for pressurization. The compressed Martian air enters the cooling channel (15) of fuel cell (7) to absorb the waste heat of fuel cell. The heated Martian air enters Martian air turbine (11) to expand and do work. The turbine drives generator (10) to generate electricity. The Martian air after doing work enters gas jet de-icing device (1) to complete the cycle.
10. The operating method of the combined heat and power generation system for in-situ resource utilization on Mars according to claim 9, characterized in that, The working fluid for the open Brayton cycle is the Martian atmosphere, which is mainly composed of carbon dioxide.