Ground fire back-and-forth powder metal fuel rotary detonation rocket ramjet combined cycle engine

Abstract

The invention discloses an earth Mars back-and-forth powder metal fuel rotary detonation rocket ramjet combined cycle engine, and belongs to the technical field of aerospace engines, the combined engine comprises a rocket type rotary detonation engine and a ramjet type rotary detonation engine, and the whole engine system adopts powder metal as main fuel. Combustion is organized by the rocket type rotary detonation engine and the ram type rotary detonation engine respectively, and thrust is generated jointly. The advantages of a rocket engine, a ramjet engine and a rotary detonation combustion mode can be fully played, and the advantages that the powdered metal fuel is good in stability, high in energy density and capable of being subjected to combustion reaction with multiple oxidants are utilized; and the combined power propulsion requirements of an aerospace aircraft, an earth Mars back-and-forth interplanetary aircraft and the like which can be repeatedly used in the future can be met.

Description

Technical Field

[0001] The present invention belongs to the technical field of aerospace engines, and more specifically, relates to a powdered metal fuel rotating detonation rocket ramjet combined cycle engine that travels back and forth between Earth and Mars. Background Art

[0002] Over the past half century, with the increase of human space exploration activities in outer space, people are eager to explore deep space, and Mars is one of them. Many countries have launched spacecraft to Mars to survey its surface environment. The atmosphere of Mars is very thin, including 96% carbon dioxide, 1.93% argon and 1.89% nitrogen, with trace amounts of oxygen and water. For traditional launch vehicles, reaching the surface of Mars and completing the exploration of the surface of Mars requires a lot of fuel, and powder detonation engines such as Mg / CO2 can solve this problem well.

[0003] The spacecraft taking off from the Earth carries powdered metal fuels such as magnesium powder and flies to Mars. During the flight, the O2 in the oxidizer tank is continuously consumed until it is exhausted. After landing on Mars, the spacecraft uses the temperature difference between day and night on Mars to collect CO2 in the Martian atmosphere and store it in the empty oxidizer tank in the form of liquid, realizing the in-situ resource utilization of propellant materials and tank reuse, and using Mg / CO2 and other propulsion systems as the power for Mars surface exploration and return orbit to complete the Mars exploration mission. In addition, powdered metal propellants are stored in the form of solid particles, have strong adaptability to environmental temperature, and do not have problems such as low-temperature vitrification and low-temperature condensation. Powdered metal transportation and ignition do not require preheating, which enables the propulsion system to achieve long-term storage and timely response in high-cold environments such as near-Earth space and outer space. In addition, powdered metals generally have a higher energy density than traditional fossil fuels and can produce more powerful thrust, so engines using this fuel are very promising.

[0004] The rotating detonation engine refers to a new concept engine based on the detonation combustion method. It has the advantages of one-time detonation, fast combustion speed, high thermal efficiency, and compact structure. It is expected to bring about a leapfrog development in aerospace propulsion technology. It uses the high-temperature and high-pressure combustion gas generated by the continuously rotating detonation wave to generate thrust. In recent years, it has received great attention from countries around the world and has become a research hotspot for domestic and foreign scholars and industrial sectors in the field. It can be used as a commercial space rocket power, high-speed UAV power, and gas turbine power, and can be used in various rockets and missiles, near-space vehicles, military aircraft, UAVs and other fields, and has very good development prospects.

[0005] Future aerospace engines will have compact structure, high thermal efficiency and reusability. Powdered metal detonation engines are a good choice. The detonation problem of powdered metal fuels has been studied for a long time, and in the early days, it mainly involved the fields of explosive explosion, fuel-air bombs and safety explosion prevention. The fuels currently used in detonation engines are mostly gases (such as hydrogen, methane, etc.) and liquids (such as gasoline, kerosene, etc.), but the volume calorific value of these fuels is generally low. The development of detonation technology, computer simulation technology, and experimental measurement technology for condensed phase energetic materials such as liquid fuels has made great progress in detonation engine technology. Powdered metal fuels have attracted people's attention due to their advantages such as high mass calorific value, high storage and use safety, and no need to consider atomization. The engine generates large thrust and can meet the requirements of aerospace vehicles for power devices such as free shuttle across the atmosphere, long-term work in the atmosphere and space, reusability, and low cost. It represents the development direction of new aerospace power technology and is a strategic competitive highland in the future aerospace field.

[0006] The key to the problem is how to combine the advantages of various engines, fuels and combustion modes to design a combined engine that is compact, reusable and has high efficiency. Summary of the invention

[0007] In response to the defects of the prior art or the need for improvement, the present invention provides a powdered metal fuel rotating detonation rocket-ramjet combined cycle engine that travels back and forth between Earth and Mars. Its purpose is to arrange an annular ramjet rotating detonation combustion chamber outside the rocket rotating detonation combustion chamber so that the thrust of the combined cycle engine is jointly generated by the rocket rotating detonation engine and the ramjet rotating detonation engine and the thrust is provided by the rotating detonation combustion method, thereby solving the technical problem of low performance of the engine combustion method in the prior art.

[0008] To achieve the above-mentioned object, according to one aspect of the present invention, there is provided a ground-fire round-trip powder metal fuel rotating detonation rocket-ramjet combined cycle engine, comprising an engine casing, wherein a ramjet engine central cone, a ramjet rotating detonation combustion chamber, a rocket rotating detonation combustion chamber, an engine tail cone, an oxidant tank and a fuel tank are arranged in the engine casing;

[0009] The outer wall surface of the ramjet engine center cone and the inner wall surface of the engine housing form an adjustable air inlet; the ramjet rotating detonation combustion chamber is annularly arranged outside the rocket type rotating detonation combustion chamber, and the ramjet rotating detonation combustion chamber is connected to the adjustable air inlet;

[0010] The fuel tank is arranged in the middle part of the engine, and is used to supply metal powder fuel to the ramjet rotating detonation combustion chamber and the rocket rotating detonation combustion chamber respectively;

[0011] The oxidant tank is arranged at the periphery of the middle part of the engine and is used to provide oxidant to the rocket-type rotating detonation combustion chamber;

[0012] The engine tail cone is arranged at one end of the rocket-type rotating detonation combustion chamber, and adjustable tail nozzle blades are arranged around the outside of the engine tail cone. The inner wall surface of the adjustable tail nozzle blades and the outer wall surface of the engine tail cone form a rocket-type rotating detonation combustion chamber nozzle, and the outer wall surface of the adjustable tail nozzle blades and the inner wall surface of the engine casing form a ramjet rotating detonation combustion chamber nozzle.

[0013] Preferably, the air inlet is an axisymmetric structure.

[0014] Preferably, the air flow rate is adjusted by adjusting the relative position between the ramjet engine central cone and the casing.

[0015] Preferably, the rocket-type rotating detonation combustion chamber nozzle and the ramjet rotating detonation combustion chamber nozzle are simultaneously regulated by adjustable tail nozzle blades, and the adjustable tail nozzle blades are umbrella-shaped structures, and electromagnetic drive is utilized to expand and contract the adjustable tail nozzle blades, thereby adjusting the flow paths of the rocket-type rotating detonation combustion chamber nozzle and the ramjet rotating detonation combustion chamber nozzle.

[0016] Preferably, powdered metal fuel such as magnesium powder is stored in the fuel storage tank, and powdered metal fuel such as magnesium powder is provided to the ramjet rotating detonation combustion chamber and the rocket rotating detonation combustion chamber through the fuel nozzle of the ramjet rotating detonation combustion chamber and the fuel nozzle of the rocket rotating detonation combustion chamber, respectively.

[0017] Preferably, the fuel nozzles of the ramjet rotating detonation combustion chamber are evenly distributed on the wall surface of the ramjet rotating detonation combustion chamber, and the fuel nozzles of the rocket rotating detonation combustion chamber are evenly distributed on the wall surface of the rocket rotating detonation combustion chamber.

[0018] Preferably, the oxidant tank stores different oxidants in the two stages of the round trip between Earth and Mars, carrying oxygen when departing from Earth and collecting carbon dioxide in the Martian atmosphere after arriving at Mars.

[0019] Preferably, it also includes a fixed support plate, which is used to connect the engine housing and the internal structure of the engine.

[0020] In general, the above technical solutions conceived by the present invention can achieve the following beneficial effects compared with the prior art:

[0021] 1. The earth-fire round-trip powder metal fuel rotary detonation rocket-ramjet combined cycle engine proposed in the present invention comprises a rocket rotary detonation engine and a ramjet rotary detonation engine. The annular ramjet rotary detonation combustion chamber is arranged outside the rocket rotary detonation combustion chamber. The thrust of the combined cycle engine is jointly generated by the rocket rotary detonation engine and the ramjet rotary detonation engine and the thrust is provided by the rotary detonation combustion method. In terms of combustion energy conversion and thermodynamic cycle performance, compared with the traditional isobaric combustion propulsion method, the detonation combustion has the advantages of fast energy release rate and self-pressurization. It is expected to simplify the combustion chamber structure, improve the thermal cycle efficiency, and reduce the engine fuel consumption. It is expected to have a revolutionary impact on the existing combustion propulsion method. Theoretically, it can adapt to the air-breathing working mode in the Mach number range of 0-12+, providing a new possible approach for the research and development of new aerospace combined cycle power solutions.

[0022] 2. The earth-to-Mars round-trip powder metal fuel rotating detonation rocket-ramjet combined cycle engine proposed in the present invention cleverly utilizes the control system to adjust the matching and coordinated working mechanism of the two rotating detonation engines in the full speed range to meet the flexibility and high efficiency requirements of the rocket-ramjet-detonation combined cycle in different working stages and working modes. It can not only improve the average acceleration and effective specific impulse performance of the Ma0-2 rocket in the ejection mode stage and reduce fuel consumption, but also improve the thrust and efficiency of orbit insertion, and effectively alleviate the mutual constraints of the integrated design of the flow path of the traditional RBCC engine on the embedded rocket structure and working parameters for the earth-to-Mars round-trip interplanetary flight mission. It can effectively give play to the advantages of the air-breathing combined cycle and the performance of the high-thrust rocket engine, making aerospace flight missions more free, flexible and convenient, and realizing horizontal take-off and landing and earth-to-Mars round-trip interplanetary flight missions.

[0023] 3. The earth-to-Mars round-trip powdered metal fuel rotating detonation rocket ramjet combined cycle engine proposed in the present invention adopts a scheme in which metal powder is used as the main fuel, can adapt to different temperature conditions, and the energy density of metal powder is generally higher than that of traditional fossil fuels, and can generate more powerful thrust. This scheme can save space and optimize the tank structure to the greatest extent, and maximize the full-speed propulsion performance of the combined engine.

[0024] 4. The round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine proposed in the present invention cleverly utilizes the fact that the surface of Mars is rich in CO2, and uses powder metals such as Mg powder as the main fuel, which helps the aircraft to save oxidant to a great extent during flight in the Martian atmosphere, laying a better foundation for the Mars exploration program. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic diagram of the structure of the earth-fire round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine of the present invention;

[0026] Figure 2 Schematic diagram of a rocket-type rotating detonation engine operating alone when Ma=0-2 and above 10 until entering orbit in an embodiment of the present invention;

[0027] Figure 3 Schematic diagram of a rocket rotating detonation engine and a ramjet rotating detonation engine working together when Ma=2-4 in an embodiment of the present invention;

[0028] Figure 4 Schematic diagram of a ramjet rotating detonation engine operating alone when Ma=4-10 in an embodiment of the present invention;

[0029] Figure 5 is a schematic diagram of an engine of an aircraft in an embodiment of the present invention when it is flying without power in outer space;

[0030] Figure 6 is a schematic diagram of the orbit of an aircraft flying from the Earth to Mars in an embodiment of the present invention;

[0031] Figure 7 It is a schematic diagram of the orbit of the spacecraft returning to the Earth from Mars in an embodiment of the present invention.

[0032] In all the drawings, the same figure numbers are used to represent the same elements or structures, among which: 1-ramjet engine center cone; 2-engine casing; 3-fixed support plate; 4-ramjet rotating detonation combustion chamber; 5-rocket rotating detonation combustion chamber; 6-engine tail cone; 7-inlet duct; 8-oxidizer tank; 9-fuel tank; 10-ramjet rotating detonation combustion chamber fuel nozzle; 11-rocket rotating detonation combustion chamber fuel nozzle; 12-adjustable tail nozzle blades; 13-rocket rotating detonation combustion chamber nozzle; 14-ramjet rotating detonation combustion chamber nozzle. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0034] like Figure 1As shown, the present invention proposes a combined cycle engine of powdered metal fuel rotating detonation rocket ramjet for round trip between Earth and Mars, the engine comprising a rocket rotating detonation engine and a ramjet rotating detonation engine, and adopts a rotating detonation combustion mode to provide thrust. Specifically, an annular ramjet rotating detonation combustion chamber is arranged outside the rocket rotating detonation combustion chamber, and the thrust of the combined engine is jointly generated by the rocket rotating detonation engine and the ramjet rotating detonation engine.

[0035] To further explain, the engine includes a ramjet engine central cone 1, an oxidizer tank 8, a fuel tank 9, an engine casing 2, a rocket-type rotating detonation combustion chamber 5, a ramjet rotating detonation combustion chamber 4, a tail nozzle, and an engine tail cone 6, which are connected in sequence. The ramjet engine central cone 1 and the inner wall of the engine casing 2 form an adjustable air inlet 7, the rocket-type rotating detonation combustion chamber 5 is annularly surrounded by an annular ramjet rotating detonation combustion chamber 4 on the outside, the tail nozzle is connected to the rocket-type rotating detonation engine, and the internal channel formed by the inner wall of the adjustable tail nozzle blade 12 of the tail nozzle and the wall of the engine tail cone 6 is the nozzle of the rocket-type rotating detonation engine, and the outer ring channel formed by the outer wall of the adjustable tail nozzle blade 12 of the tail nozzle and the inner wall of the engine casing 2 is the nozzle of the ramjet rotating detonation engine, and the adjustable air inlet 7, the ramjet rotating detonation combustion chamber 4 and the ramjet rotating detonation combustion chamber nozzle 14 are connected in sequence.

[0036] To further explain, the engine housing 2 and the ramjet engine center cone 1 located inside the engine housing 2 constitute an adjustable air inlet 7. The air inlet 7 is an axisymmetric structure. The ramjet engine center cone 1 is hydraulically driven to move forward and backward to change the inlet cross-sectional area, thereby adjusting the air flow.

[0037] To further explain, the fuel nozzles 11 of the rocket-type rotating detonation combustion chamber and the fuel nozzles 10 of the ramjet-type rotating detonation combustion chamber are uniformly arranged in the circumferential direction.

[0038] To further explain, the rocket-type rotating detonation combustion chamber nozzle 13 and the ramjet rotating detonation combustion chamber nozzle 14 are simultaneously regulated by the adjustable tail nozzle blades 12. The adjustable tail nozzle blades 12 are umbrella-shaped structures, which are expanded and contracted by electromagnetic drive to thereby adjust the flow paths of the rocket-type rotating detonation combustion chamber nozzle 13 and the ramjet rotating detonation combustion chamber nozzle 14.

[0039] To further explain, the rocket rotating detonation combustion chamber 5 and the ramjet rotating detonation combustion chamber 4 of the combined cycle engine both use powdered metals such as magnesium powder as fuel. The rocket rotating detonation combustion chamber 5 uses O2 and CO2 as oxidants during the departure from the Earth and the return to Mars stages, respectively, and the ramjet rotating detonation combustion chamber 4 uses the Earth's atmosphere and the Martian atmosphere as oxidants, respectively.

[0040] To explain further, the oxidant tank 8 stores different oxidants in the two stages of the round trip from Earth to Mars. It carries O2 when departing from Earth, and after arriving at Mars, uses the empty oxidant tank 8 to collect CO2 from the Martian atmosphere for return propulsion.

[0041] The technical solution of the present invention is further illustrated by specific embodiments below. Figure 1-7 As shown:

[0042] The earth-fire round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine proposed by the present invention is applied to an interplanetary spacecraft. During the earth-fire round-trip flight, the working mode of the combined cycle engine is divided into the following stages:

[0043] Phase 1: The aircraft takes off from the earth, with a flight Mach number of 0-2, the central cone of the ramjet engine is at the top, the adjustable air inlet is closed to the maximum extent, the tail nozzle is at a set opening, the solid fuel nozzle is opened, and powdered metals such as magnesium powder are injected into the rocket combustion chamber. The liquid oxidizer tank injects oxygen into the rocket rotating detonation combustion chamber, and the rocket rotating detonation engine works;

[0044] Stage 2: The flight Mach number is 2-4. The center cone of the ramjet engine moves backward, the opening degree of the adjustable air inlet is increased, the solid fuel nozzle injects fuel into the ramjet rotating detonation combustion chamber, and the ramjet rotating detonation engine mode works;

[0045] Stage 3: The flight Mach number is 4-10, the central cone of the ramjet engine moves back to the bottom, the adjustable air inlet is fully opened, the ramjet rotating detonation combustion chamber is working, the tail nozzle blades are retracted, the detonation ramjet nozzle is at the maximum opening, the liquid oxidizer tank nozzle is closed, and the rocket rotating detonation engine is shut down;

[0046] Stage 4: The flight Mach number is above 10 until it enters the Earth's parking orbit. The central cone of the ramjet engine moves forward to the top, the adjustable air inlet is closed, the liquid oxidizer tank nozzle is opened, the tail nozzle blades are expanded, the detonation rocket nozzle is at the maximum opening, the detonation ramjet nozzle is closed, the rocket-type rotating detonation engine works, and the detonation ramjet combustion chamber is closed.

[0047] Phase 5: The spacecraft makes orbital adjustments, the detonation rocket engine continues to work, the spacecraft accelerates to the second cosmic speed to escape the Earth's gravity, and then enters the Earth-Mars double-tangent orbit, which is the most energy-saving flight path for interplanetary spacecraft;

[0048] Stage 6: The spacecraft uses the heliocentric gravity to fly toward Mars in a double-tangent orbit, the tail nozzle is retracted, the detonation rocket nozzle opening is reduced, the rocket-type rotating detonation engine is shut down, and the spacecraft is in unpowered flight;

[0049] Phase 7: The spacecraft approaches Mars, the liquid oxidizer tank nozzle opens, the solid fuel nozzle injects fuel into the rocket-type rotating detonation combustion chamber, the detonation rocket engine starts, and the spacecraft accelerates into the Mars stationary orbit;

[0050] In Phase 8, the spacecraft lands on Mars and uses jet thrusters to flip its flight direction so that one end of the engine faces the Earth. The detonation rocket combustion chamber works, the engine performs reverse thrust to decelerate, and the spacecraft flaps open for attitude control to achieve a vertical landing on the surface of Mars.

[0051] Phase 9: The spacecraft stops on the surface of Mars. The oxygen in the liquid oxidizer tank is basically exhausted. After it is emptied, the temperature difference between day and night on Mars is used to collect carbon dioxide and store it in liquid form, preparing for the next step of the spacecraft returning to Earth.

[0052] Stage 10: The spacecraft takes off from Mars, with a flight Mach number of 0-2, the adjustable air inlet is closed, the detonation rocket nozzle is at a set opening, the solid fuel nozzle is opened, and magnesium powder and other powdered metals are injected into the rocket-type rotating detonation combustion chamber, the liquid oxidizer tank nozzle is opened, and carbon dioxide is injected into the detonation rocket combustion chamber, and the rocket-type rotating detonation engine is working;

[0053] Stage 11, the flight Mach number is 2-4, the central cone of the ramjet engine moves backward, the adjustable air inlet gradually opens, the air inlet intakes the Martian atmospheric carbon dioxide to supply the detonation ramjet combustion chamber, the solid fuel nozzle injects fuel into the detonation ramjet combustion chamber, and the ramjet rotating detonation engine mode works;

[0054] Stage 12, the flight Mach number is 4-10, the center cone moves back to the bottom, the adjustable air inlet is fully opened, the detonation ramjet combustion chamber works at full capacity, the tail nozzle blades are retracted, the detonation ramjet nozzle is at the maximum opening, the liquid oxidizer tank nozzle is closed, the detonation rocket combustion chamber fuel nozzle is closed, and the rocket-type rotating detonation engine is closed;

[0055] Stage 13: The spacecraft continues to accelerate until it enters the Mars stationing orbit. The center cone of the ramjet engine moves forward to the top, the adjustable air inlet is closed, the liquid oxidizer tank nozzle is opened, the tail nozzle blades are expanded, the detonation rocket nozzle is at the maximum opening, the rocket-type rotating detonation engine works, and the detonation ramjet engine stops running.

[0056] Stage 14: The rocket-type rotating detonation engine continues to work, the spacecraft accelerates until it escapes the gravity of Mars, enters the Earth-Mars double-intersection orbit, and then decelerates to reach the set speed. The detonation rocket engine is shut down, and the spacecraft performs unpowered flight.

[0057] Phase 15: The spacecraft approaches the Earth, uses jet propulsion to slow down to the first cosmic speed, and enters the Earth's stationary orbit;

[0058] In Phase 16, the spacecraft descends to the Earth, undergoing two stages: unpowered gliding deceleration and powered controlled landing, to achieve a horizontal landing on the Earth's surface.

[0059] It will be easily understood by those skilled in the art that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A combined cycle engine of rotating detonation rocket ramjet and powdered metal fuel for round trip between Earth and Mars, comprising an engine casing (2), characterized in that: The engine casing (2) is provided with a ramjet engine central cone (1), a ramjet type rotating detonation combustion chamber (4), a rocket type rotating detonation combustion chamber (5), an engine tail cone (6), an oxidant tank (8) and a fuel tank (9); The outer wall surface of the ramjet engine center cone (1) and the inner wall surface of the engine housing (2) form an adjustable air inlet (7); the ramjet type rotating detonation combustion chamber (4) is annularly arranged outside the rocket type rotating detonation combustion chamber (5), and the ramjet type rotating detonation combustion chamber (4) is in communication with the air inlet (7); The fuel storage tank (9) is arranged in the middle of the engine and is used to provide powdered metal fuel to the ramjet rotating detonation combustion chamber (4) and the rocket rotating detonation combustion chamber (5) respectively; The oxidant tank (8) is arranged in the middle of the engine and is used to provide oxidant to the rocket-type rotating detonation combustion chamber (5); The engine tail cone (6) is arranged at one end of the rocket-type rotating detonation combustion chamber (5), and an adjustable tail nozzle blade (12) is arranged around the outside of the engine tail cone (6). The inner wall surface of the adjustable tail nozzle blade (12) and the outer wall surface of the engine tail cone (6) form a rocket-type rotating detonation combustion chamber nozzle (13), and the outer wall surface of the adjustable tail nozzle blade (12) and the inner wall surface of the engine casing (2) form a ramjet rotating detonation combustion chamber nozzle (14).

2. The earth-fire round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine according to claim 1, characterized in that: The air inlet (7) is an axisymmetric structure.

3. The earth-to-fire round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine according to claim 2, characterized in that: The air flow rate is adjusted by adjusting the relative position between the ramjet engine central cone (1) and the casing (2).

4. The earth-fire round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine according to claim 1, characterized in that: The rocket-type rotating detonation combustion chamber nozzle (13) and the ramjet-type rotating detonation combustion chamber nozzle (14) are simultaneously regulated by an adjustable tail nozzle blade (12). The adjustable tail nozzle blade (12) is an umbrella-shaped structure, and electromagnetic drive is used to expand and contract the adjustable tail nozzle blade (12), thereby regulating the flow channels of the rocket-type rotating detonation combustion chamber nozzle (13) and the ramjet-type rotating detonation combustion chamber nozzle (14).

5. The earth-fire round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine according to claim 1, characterized in that: The fuel storage tank (9) stores powdered metal fuel such as magnesium powder, and the powdered metal fuel is provided to the ramjet rotating detonation combustion chamber (4) and the rocket rotating detonation combustion chamber (5) through the fuel nozzle (10) of the ramjet rotating detonation combustion chamber and the fuel nozzle (11) of the rocket rotating detonation combustion chamber, respectively.

6. The earth-to-fire round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine according to claim 1, characterized in that: The fuel nozzles (10) of the ramjet rotating detonation combustion chamber are evenly distributed around the wall of the ramjet rotating detonation combustion chamber (4), and the fuel nozzles (11) of the rocket rotating detonation combustion chamber are evenly distributed around the head of the rocket rotating detonation combustion chamber (5).

7. The earth-to-fire round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine according to claim 1, characterized in that: The oxidant storage tank (8) stores different oxidants in the two stages of the round trip from Earth to Mars, carrying oxygen when departing from Earth and collecting carbon dioxide in the Martian atmosphere after arriving at Mars.

8. The earth-to-fire round-trip powder metal fuel rotating detonation rocket ramjet combined cycle engine according to claim 1, characterized in that: It also comprises a fixed support plate (3), wherein the fixed support plate (3) is used to connect the engine housing (2) and the internal structure of the engine.

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