Air-breathing power system and method for Mars surface aircraft

Abstract

The invention relates to the technical field of aircrafts, in particular to an air-breathing power system and method for a Mars surface aircraft, and the air-breathing power system comprises an air inlet channel, an isolation section, a combustion chamber, a cooling channel, a spray pipe, a heat exchanger and a fuel device, the fuel device comprises a liquid fuel tank, a high-pressure pump, a magnesium powder storage tank, a powder feeder and a gasification nozzle. The air-breathing power system of the aircraft is designed aiming at the fact that gas on the surface of Mars is mainly composed of CO2, the air-breathing power system is provided with magnesium powder capable of reacting with CO2 and methane or hydrogen carrying the magnesium powder to be sprayed into a combustion chamber, CO2 needed by combustion is provided through compressed air in the high-speed flight process, and the combustion efficiency is improved. The air-breathing type power system does not need to carry a large amount of fuel and oxidizing agents like a common rocket engine, and the specific impulse of the engine of the air-breathing type power system is far higher than that of the engine of a common rocket.

Description

Technical Field

[0001] The present invention relates to the field of aircraft technology, and in particular to an air-breathing power system and method for an aircraft on the surface of Mars. Background Art

[0002] The pressure on the surface of Mars is much lower than the standard atmospheric pressure at sea level on Earth. The average surface pressure on Mars is between 0.4 and 0.87 kPa, and on average, it is about 0.6 kPa, which is only about 1% of the value measured at sea level on Earth. Due to the thin atmosphere of Mars, it is difficult for conventional aerodynamic aircraft to obtain sufficient lift, so powerful engines or unique propulsion methods are required.

[0003] The temperature on the surface of Mars changes dramatically between day and night. The temperature can reach -12°C during the day, while it drops to -76°C at night, with an average temperature of -32°C. This drastic temperature change is due to the fact that the atmosphere of Mars is very thin and cannot effectively retain heat, resulting in rapid temperature changes. The huge temperature difference on the surface of Mars also places higher demands on the power of the aircraft. Carbon dioxide (CO2) is the main component of the Martian atmosphere, accounting for 95.32%, followed by nitrogen (N2), accounting for 2.7%, and water vapor accounts for only 0.02%. In addition, there is 1.6% argon (Ar). The power form of aircraft on the surface of Mars needs to adapt to this atmospheric environment that is different from that of the Earth.

[0004] The engines of ordinary rockets need to carry a large amount of fuel and oxidizer to propel the aircraft, which is not suitable for long-term or long-distance flight. Based on this, an air-breathing power system and method for aircraft on the surface of Mars are proposed. Summary of the invention

[0005] In order to address the deficiencies of the prior art, the present invention provides an air-breathing power system and method for a Martian surface aircraft, which uses carbon dioxide in the Martian atmosphere as an oxidant to react with fuel to propel the aircraft. It does not need to carry a large amount of fuel and oxidant like ordinary rocket engines, and has a higher engine specific impulse.

[0006] To achieve the above object, the present invention provides the following technical solution: an air-breathing power system for a vehicle on the surface of Mars, comprising an air intake duct, an isolation section, a combustion chamber, and a cooling channel, a nozzle, a heat exchanger, and a fuel device located downstream of the injection point thereof, wherein the air intake duct, the combustion chamber, and the nozzle are made of ceramic matrix composite materials or C-SiC (carbon-silicon carbide) composite materials.

[0007] Preferably, the fuel device comprises a liquid fuel tank, a high-pressure pump, a magnesium powder storage tank, a powder feeder and a gasification nozzle.

[0008] The present invention also provides a propulsion method for an air-breathing power system of a Mars surface vehicle, comprising:

[0009] (1) Gas from the Martian surface is sucked into the intake duct, generating compressed gas that passes through the isolation section and enters the combustion chamber;

[0010] (2) The liquid fuel in the liquid fuel tank enters the cooling channel through the high-pressure pump, and then enters the heat exchanger to be gasified at high temperature. The gasified fuel flows to the gasification nozzle;

[0011] (3) The powder feeder simultaneously pushes the magnesium powder in the magnesium powder storage tank into the gasification nozzle;

[0012] (4) The gaseous fuel carrying magnesium powder is sprayed into the combustion chamber through the gasification nozzle, mixed with the compressed gas and burned to produce high-temperature and high-pressure gas that is ejected from the nozzle, realizing the propulsion of the aircraft on the surface of Mars.

[0013] Preferably, in step (1), the Martian surface gas components mainly include CO2 95%, N2 2.7%, and Ar 1.6%, measured by volume fraction.

[0014] Preferably, in step (2), the liquid fuel is liquid methane or liquid hydrogen.

[0015] Preferably, in step (2), the working pressure of the high-pressure pump is 2-10 MPa.

[0016] Preferably, in step (4), the computer controls the flow ratio of the gasified fuel (methane or hydrogen) and the magnesium powder according to the obtained flight state. Specifically, the computer calculates the captured carbon dioxide flow rate according to the obtained flight speed, altitude and other states, as well as the capture area of ​​the aircraft inlet, and controls the flow rates of methane or hydrogen and magnesium powder respectively through the high-pressure pump and the feeder, and matches them according to the performance optimization ratio.

[0017] Preferably, in step (2), the heat exchanger is turned on for heating before the combustion chamber is ignited; and in step (4), the heat exchanger is turned off for heating after the combustion chamber is ignited and burned.

[0018] The present invention provides an air-breathing power system and method for a vehicle on the surface of Mars, which has the following beneficial effects compared with the prior art:

[0019] In view of the fact that the gas on the surface of Mars is mainly composed of CO2, the present invention designs an air-breathing power system for the aircraft. The aircraft is equipped with magnesium powder that can react with CO2, as well as methane or hydrogen that is sprayed into the combustion chamber together with the magnesium powder. The CO2 required for combustion is provided by compressed air during high-speed flight, without the need to carry a large amount of fuel and oxidant like ordinary rocket engines. The engine specific impulse of the air-breathing power system is also much higher than that of ordinary rocket engines.

[0020] The present invention uses liquid fuel, which can cool the combustion chamber wall when flowing through the cooling channel, thereby avoiding the problem of combustion chamber ablation due to excessive temperature; at the same time, after heat exchange with the combustion chamber, methane becomes gaseous, which can better carry magnesium powder and spray it evenly into the combustion chamber, solving the problem that magnesium powder is difficult to effectively penetrate into the supersonic airflow inside the ramjet engine, and ensuring the full combustion reaction of fuel and oxidant in the combustion chamber. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0022] Figure 1 A graph showing the relationship between the ratio of methane and magnesium powder and the ratio of oxidant to fuel and engine performance according to the present invention;

[0023] Figure 2 It is a schematic diagram of the air-breathing power system of the present invention;

[0024] Figure 3 It is a schematic diagram of the installation position of the air-breathing power system of the present invention. DETAILED DESCRIPTION

[0025] The following examples are used to explain the implementation methods of the present application in detail, so that the implementation process of how the present application uses technical means to solve technical problems and achieve technical effects can be fully understood and implemented accordingly.

[0026] Example 1

[0027] An air-breathing power system for a vehicle on the surface of Mars includes an air intake, an isolation section, a combustion chamber, a cooling channel located downstream of the injection point, a nozzle, a heat exchanger, and a fuel device; the fuel device includes a liquid fuel tank, a high-pressure pump, a magnesium powder storage tank, a powder feeder, and a gasification nozzle. The air intake, combustion chamber, and nozzle are made of C-SiC composite materials.

[0028] Example 2

[0029] An air-breathing power system for a vehicle on the surface of Mars is basically the same as Example 1, except that the air inlet, combustion chamber and nozzle are made of ceramic-based composite materials.

[0030] Example 3

[0031] A propulsion method for an air-breathing power system of a Mars surface vehicle, comprising:

[0032] (1) Gas from the Martian surface is sucked into the intake duct, generating compressed gas that passes through the isolation section and enters the combustion chamber;

[0033] Table 1 Comparison of the surface gases of Mars and the air 34 km above the Earth

[0034] category Mars surface gases The air 34 km above the earth Atmospheric pressure (bar) 0.4-0.87 0.66 Temperature (K) 241 234 Gas composition (volume fraction%) <![CDATA[95%CO2+2.7%N2+1.6%Ar]]> <![CDATA[21%O2+79%N2]]>

[0035] (2) Before the combustion chamber is ignited, the heat exchanger is turned on for heating. The liquid fuel (liquid methane) in the liquid fuel tank enters the cooling channel through the high-pressure pump and then enters the heat exchanger for high-temperature gasification. The gasified fuel flows to the gasification nozzle;

[0036] (3) The powder feeder simultaneously pushes the magnesium powder in the magnesium powder storage tank into the gasification nozzle;

[0037] (4) The gasified fuel carries magnesium powder and is sprayed into the combustion chamber through the gasification nozzle, where it mixes with the compressed gas and burns to produce high-temperature and high-pressure gas that is ejected from the nozzle to propel the aircraft on the surface of Mars. After the combustion chamber is ignited and burned, the heat exchanger is turned off for heating. When liquid methane flows through the cooling channel, heat exchange on the combustion chamber wall can gasify it, eliminating the need to use a heat exchanger for heating.

[0038] Example 4

[0039] A propulsion method for an air-breathing power system of a Mars surface vehicle is basically the same as Example 3, except that the liquid fuel is replaced by liquid hydrogen from liquid methane. The performance of the engine using a combination of magnesium powder and liquid hydrogen is better, including specific impulse performance and easier cooling of the combustion chamber using liquid hydrogen as a coolant; however, the density of liquid hydrogen is only 1 / 6 of that of liquid methane, which will make the tank volume larger.

[0040] Test Results

[0041] refer to Figure 1 , under the condition of flight Mach number 6, the engine performance at two mass flow ratios of methane and magnesium powder and different mass flow ratios of oxidizer (CO2) and fuel (methane + magnesium powder) can be seen. It can be seen that in the o / f range of 4-8, the engine specific impulse range is 1100-2000s, which is 3-6 times the theoretical vacuum specific impulse (360s) of a commonly used typical liquid oxygen-kerosene rocket, and the engine specific thrust is 1700-2300m / s.

[0042] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An air-breathing power system for a vehicle on the surface of Mars, characterized in that: It includes an air inlet, an isolation section, a combustion chamber, and a cooling channel, a nozzle, a heat exchanger, and a fuel device located downstream of the injection point.

2. An air-breathing power system for a Martian surface vehicle according to claim 1, characterized in that: The fuel device comprises a liquid fuel tank, a high-pressure pump, a magnesium powder storage tank, a powder feeder and a gasification nozzle.

3. The air-breathing power system for a Martian surface vehicle according to claim 1, characterized in that: The air inlet, combustion chamber and nozzle are made of ceramic-based composite materials or C-SiC composite materials.

4. A propulsion method for an air-breathing power system for a Mars surface vehicle according to claim 2, characterized in that: include: (1) Gas from the Martian surface is sucked into the intake duct, generating compressed gas that passes through the isolation section and enters the combustion chamber; (2) The liquid fuel in the liquid fuel tank enters the cooling channel through the high-pressure pump, and then enters the heat exchanger to be gasified at high temperature. The gasified fuel flows to the gasification nozzle; (3) The powder feeder simultaneously pushes the magnesium powder in the magnesium powder storage tank into the gasification nozzle; (4) The gaseous fuel carrying magnesium powder is sprayed into the combustion chamber through the gasification nozzle, mixed with the compressed gas and burned to produce high-temperature and high-pressure gas that is ejected from the nozzle, realizing the propulsion of the aircraft on the surface of Mars.

5. A propulsion method for an air-breathing power system for a Mars surface vehicle according to claim 4, characterized in that: In step (1), the Martian surface gas components mainly include CO2 95%, N2 2.7%, and Ar 1.6%, measured by volume fraction.

6. A propulsion method for an air-breathing power system for a Mars surface vehicle according to claim 4, characterized in that: In step (2), the liquid fuel is liquid methane or liquid hydrogen.

7. A propulsion method for an air-breathing power system for a Mars surface vehicle according to claim 4, characterized in that: In step (2), the working pressure of the high-pressure pump is 2-10 MPa.

8. The propulsion method of an air-breathing power system for a Mars surface vehicle according to claim 4, characterized in that: In step (4), the flow ratio of the gasified fuel and the magnesium powder is controlled by a computer according to the obtained flight status.

9. A propulsion method for an air-breathing power system for a Mars surface vehicle according to claim 4, characterized in that: In step (2), the heat exchanger is turned on for heating before the combustion chamber is ignited; in step (4), the heat exchanger is turned off for heating after the combustion chamber is ignited and burned.

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