A chemical-arc combined power thruster for space use and its application method

Abstract

The present invention discloses a chemical-arc combined power thruster for space and its application method, including an injector, a cathode, a combustion chamber, an anode, a power supply and a propellant supply system; the injector is coaxially sealed and arranged at the upstream section of the combustion chamber, and the injector is respectively connected to the chemical oxidant supply assembly and the chemical fuel supply assembly, and can inject oxidant and fuel into the combustion chamber; the anode is coaxially arranged at the tail end of the combustion chamber and has a Laval spray cavity; the anode is connected to the positive electrode of the power supply; the cathode is coaxially inserted in the center of the injector and connected to the negative electrode of the power supply; the power supply has a low voltage mode and a high voltage mode. The present invention effectively integrates chemical propulsion and arc propulsion, so that the same thruster can realize the alternating work of chemical propulsion and arc propulsion, and can meet the needs of spacecraft to complete rapid maneuvering tasks such as avoiding space debris and orbit transfer, and can also complete orbit maintenance, attitude fine-tuning, and deep space exploration tasks while simplifying the structure.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft space propulsion technology, in particular to a space chemical-arc combined power thruster and an application method thereof. Background Art

[0002] With the continuous expansion of space mission scenarios, in order to meet the growing demand for efficient use of space missions, future spacecraft propulsion systems need to have capabilities such as variable specific impulse, adjustable thrust, and green and non-toxic. At present, most spacecraft use traditional chemical propulsion, but its specific impulse is low, resulting in a large amount of propellant required, reducing the payload ratio, and it is difficult to achieve precise control of thruster performance. In comparison, arc propulsion, as a typical representative of electric propulsion technology, has a simple structure and has greater advantages in specific impulse and thrust control. However, due to its relatively small thrust compared to chemical propulsion, it is difficult to support rapid maneuvers and other attitude and orbit control tasks.

[0003] It can be seen that the two propulsion methods have different characteristics and scope of application. When performing tasks alone, there are certain limitations and they cannot meet the established requirements of complex space missions. At the same time, carrying multiple different types of thrusters will complicate the system structure. Therefore, spacecraft urgently need a propulsion device that can realize the integration of chemical and electric propulsion. Summary of the invention

[0004] The technical problem to be solved by the present invention is to address the deficiencies of the above-mentioned prior art and to provide a space chemical-arc combined power thruster and an application method thereof. The space chemical-arc combined power thruster and an application method thereof effectively integrate chemical propulsion and arc propulsion, so that the same thruster can realize alternating operation of chemical propulsion and arc propulsion, and while simplifying the structure, it can better meet the different mission requirements of space propulsion.

[0005] In order to solve the above technical problems, the technical solution adopted by the present invention is:

[0006] A chemical-arc combined power thruster for space use comprises an injector, a cathode, a combustion chamber, an anode, a power supply, a chemical oxidant supply component, a chemical fuel supply component and an electric propulsion working fluid working component.

[0007] The injector is coaxially sealed and arranged at the upstream section of the combustion chamber. The injector is respectively connected to the chemical oxidant supply assembly and the chemical fuel supply assembly and can inject the oxidant and the fuel into the combustion chamber.

[0008] The anode is coaxially arranged at the rear end of the combustion chamber and has a Laval spray cavity; the anode is connected to the positive electrode of the power supply.

[0009] The cathode is coaxially inserted in the center of the injector, and the cathode has a tip pointing toward the throat of the Laval nozzle chamber.

[0010] The cathode is connected to the negative pole of the power supply; the power supply has a low voltage mode and a high voltage mode.

[0011] The electric propulsion working fluid working component can supply electric propulsion working fluid to the combustion chamber.

[0012] Also included is a cathode support and an insulating shell.

[0013] The upstream end of the cathode extends out from the outer side of the injector and is coaxially mounted in the cathode support.

[0014] The insulating shell is coaxially sleeved on the outer periphery of the cathode support.

[0015] The invention also comprises a cover shell which is coaxially sleeved on the insulating shell, the combustion chamber and the outer periphery of the anode.

[0016] The electric propulsion working fluid is the oxidant in the chemical oxidant supply assembly or the fuel in the chemical fuel supply assembly.

[0017] The electric propulsion working fluid working component includes a rotating air intake pipe, which is spirally wound around the outer periphery of the cathode; the air intake end of the rotating air intake pipe is connected to a chemical oxidant supply component or a chemical fuel supply component.

[0018] The cathode material is cerium tungsten which is resistant to high temperature and arc erosion; the anode material is stainless steel, molybdenum or tungsten which is resistant to high temperature and arc erosion.

[0019] A method for operating a chemical-arc combined propulsion thruster for space use has two working modes: a chemical propulsion mode and an electric propulsion mode. By controlling the start-up timing of an oxidizer, a fuel and an electric propulsion working fluid, and the selection of a power supply working mode, the combined propulsion thruster can switch between the two working modes.

[0020] When a spacecraft with a combined power thruster needs to complete a rapid maneuvering mission, the chemical propulsion mode is used to provide large thrust for the spacecraft; when the spacecraft needs to maintain and adjust its orbital attitude, the electric propulsion mode is used to precisely control the thrust of the spacecraft.

[0021] The working process of chemical propulsion mode includes the following steps:

[0022] Step A1, injecting chemical propellant: the chemical oxidant supply assembly supplies the oxidant with a set pressure P1 to the injector, and the chemical fuel supply assembly supplies the fuel with a set pressure P2 to the injector; the injector atomizes and mixes the oxidant and the fuel through the spray hole and injects them into the combustion chamber; wherein the set pressures P1 and P2 are not less than 8.0 MPa.

[0023] Step A2, ignition: when the mixture of fuel and oxidant fills the entire combustion chamber, the power supply working mode is selected as the low voltage mode, so that a low pulse voltage of the set voltage U1 is formed between the anode and the cathode connected to the positive and negative poles of the power supply. The low pulse voltage will cause the chemical propellant mixed evenly in the combustion chamber to ignite and burn in the combustion chamber adjacent to the contraction section, thereby achieving chemical propulsion with a set thrust; wherein, the voltage range of the set voltage U1 is 80 to 100V.

[0024] The working process of the electric propulsion mode includes the following steps:

[0025] Step B1, supplying electric propulsion working fluid: the electric propulsion working fluid working component should be able to supply electric propulsion working fluid into the combustion chamber in a swirling manner.

[0026] Step B2, long arc discharge: while the electric propulsion working fluid is supplied, the power supply working mode is selected as the high voltage mode, so that a high voltage of set voltage U2 is present between the anode and cathode connected to the positive and negative poles of the power supply, and a discharge arc is generated at the cathode tip. Under the pressure impact of the electric propulsion working fluid, the discharge arc forms a long discharge arc; on the one hand, the long arc can ionize a part of the electric propulsion working fluid to form plasma to maintain the long arc, and on the other hand, it can heat the remaining electric propulsion working fluid, so that it expands due to heat and is ejected from the anode at an accelerated speed to form a reaction thrust.

[0027] The present invention has the following beneficial effects:

[0028] 1. The present invention integrates the injector, combustion chamber, cathode and anode required for arc propulsion on the same thruster, sharing the combustion chamber, nozzle and other structures. The integrated thruster can work in two thrust modes, chemical and arc, respectively, taking into account the advantages of high thrust and high specific impulse of the two propulsion modes, and meeting the established requirements of complex aerospace missions.

[0029] 2. The present invention is similar to the original arc thruster in structure, easy to implement, and has mature processing technology; the present invention makes full use of the internal space of the arc thruster, and combines its simple structure to achieve a clever combination with the chemical thruster. That is, the present invention combines chemical propulsion and arc propulsion together by utilizing the characteristics of the two discharge modes of the arc thruster without affecting the structure of the arc thruster itself, and proposes a specific implementation method for the chemical thrust mode and the electric thrust mode to work separately in the chemical-arc combined power space thruster.

[0030] 3. The present invention enables the thruster to operate in two thrust modes by adjusting the flow supply of the propellant and the input power of the inter-pole power supply device.

[0031] 4. The chemical thrust mode and electric thrust mode of the present invention can share propellants such as methane, hydrogen, and hydrogen peroxide, saving space for propellant tanks and pipelines, and facilitating optimization of thruster quality and structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 The schematic diagram of the structure of a chemical-arc combined power thruster for space use according to the present invention is shown.

[0033] Figure 2 The schematic diagram of the structure of the injector in the present invention is shown.

[0034] Figure 3 A schematic diagram of a propellant supply system in the present invention is shown.

[0035] Figure 4 A schematic diagram showing the working principle of the chemical propulsion mode in the present invention.

[0036] Figure 5 A schematic diagram showing the working principle of the electric propulsion mode in the present invention is shown.

[0037] Among them are:

[0038] 1. Cathode support; 2. Insulating shell; 3. Rotating air intake pipe; 4. Cathode; 5. Fuel input pipeline; 6. Axial air intake pipe; 7. Combustion chamber; 8. Injector; 9. Upper nozzle; 10. Throat; 11. Anode; 12. Lower nozzle; 13. Cover. DETAILED DESCRIPTION

[0039] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific preferred embodiments.

[0040] In the description of the present invention, it should be understood that the terms "left side", "right side", "upper part", "lower part" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. "First", "second" and the like do not indicate the importance of the components, and therefore cannot be understood as limiting the present invention. The specific dimensions used in this embodiment are only for illustrating the technical solution, and do not limit the scope of protection of the present invention.

[0041] like Figure 1 As shown, a chemical-arc combined power thruster for space use includes an injector 8, a cathode 4, a combustion chamber 7, an anode 11, a power supply, a propellant supply system, a cathode support 1, an insulating shell 2 and a cover 13.

[0042] The injector coaxial seal is arranged in the upstream section of the combustion chamber. The structure of the injector is roughly the same as the plane injector commonly used in liquid rocket engines. Figure 2 As shown, it is a planar annular structure having a fuel input pipeline 5 and an oxidant input pipeline.

[0043] Furthermore, the injector base is provided with a plurality of mixing zones arranged along the direction of the flame spray after atomization, and each mixing zone is connected to the oxidant input pipeline and the fuel input pipeline respectively, so that the oxidant and the fuel are sprayed into the mixing zone at an angle under high pressure to achieve atomization and full mixing. In the injector, the fuel and the oxidant are respectively sealed in the flow channels of different propellants, which can also avoid the dangers of fire and explosion of the liquid engine to a certain extent.

[0044] like Figure 3 As shown, the propellant supply system includes a chemical oxidizer supply component, a chemical fuel supply component and an electric propulsion working fluid working component.

[0045] The chemical fuel supply assembly includes a fuel filling device, a high-pressure gas cylinder and a fuel tank; wherein the fuel filling device is used to fill the fuel tank with fuel, and the fuel is preferably kerosene, methane or oxygen; the high-pressure gas cylinder is used to pressurize the fuel tank; and the fuel tank is used to supply fuel with a set pressure P2 to the injector. Since high-pressure nitrogen is selected as the pressurized gas and stored in the high-pressure gas cylinder, the pressure P2 supplied to the orifice plate inlet is generally set to be no less than 8.0Mpa to achieve a better atomization effect.

[0046] The chemical oxidant supply assembly comprises an oxidant filling device, a high-pressure gas cylinder and an oxidant tank. The oxidant filling device is used to fill the oxidant tank with oxidant, preferably oxygen or hydrogen peroxide, and the high-pressure gas cylinder is used to pressurize the oxidant tank.

[0047] The above-mentioned electric propulsion working fluid working component can supply electric propulsion working fluid into the combustion chamber. Further, the electric propulsion working fluid is preferably an oxidant in the chemical oxidant supply component or a fuel in the chemical fuel supply component. In this embodiment, the electric propulsion working fluid is preferably an oxidant in the chemical oxidant supply component.

[0048] Therefore, the electric propulsion working fluid component of the present invention can share the oxidant filling device, high-pressure gas cylinder and oxidant tank in the chemical oxidant supply component. That is, the oxidant tank has two oxidant input pipelines, wherein the oxidant input pipeline located in the injector is called the axial air inlet pipe 6, and the other oxidant input pipeline is the rotary air inlet pipe 3, which is spirally wound around the cathode; the air inlet ends of the axial air inlet pipe and the rotary air inlet pipe are both connected to the oxidant tank, that is, the oxidant tank can provide the axial air inlet pipe (injector) and the rotary air inlet pipe with a set pressure P1, respectively, and realize the automatic switching of the two oxidant input pipelines through the flow control valve. Since high-pressure nitrogen is selected as the boost gas and stored in a high-pressure gas cylinder, the pressure P1 supplied to the orifice plate inlet is generally set to be not less than 8.0Mpa to achieve a better atomization effect.

[0049] The configuration of the propellant supply system of the present invention has the following two advantages:

[0050] On the one hand, most current spacecraft use hydrazine substances that can spontaneously combust as chemical propellant working fluids, but hydrazine propellants cannot meet the green and non-toxic requirements of future spacecraft propulsion systems, and green and non-toxic propellant combinations represented by oxygen-oxygen, oxygen-methane, oxygen-kerosene, etc. have the problem of not being able to spontaneously combust, and need to be equipped with additional igniters, and generally need to install multiple gunpowder igniters to achieve multiple starts, which increases the complexity of the propulsion device structure. The present invention can just solve this problem well: in the context of the future development of space chemical propellants towards non-toxic and green, the device realizes ignition through the arc formed between the cathode and the anode, solves the ignition problem of two propellants that cannot react spontaneously, and does not need to be equipped with an ignition device, so that the combination of the two working modes increases the degree of structural reuse, and also enables the thruster to be ignited multiple times according to mission requirements.

[0051] On the other hand, for the existing toxic hypergolic propellants, mainly hydrazine propellants, it can be used as a fuel in the chemical propulsion mode and as a working fluid in the arc propulsion mode to form hydrazine arc propulsion, thereby realizing propellant reuse and significantly simplifying the propellant supply system.

[0052] The anode is coaxially arranged at the rear end of the combustion chamber and has a Laval nozzle cavity; the Laval nozzle cavity has an upper nozzle 9 (i.e., a contraction section), a throat 10 and a lower nozzle 12 (i.e., an expansion section) in sequence along the axial direction.

[0053] The anode material is preferably stainless steel, molybdenum or tungsten which is resistant to high temperature and arc erosion.

[0054] The cathode is preferably coaxially inserted in the center of the injector through a cathode support 1, and the cathode has a tip pointing to the throat of the Laval injection chamber. Further, an insulating shell 2 is provided on the periphery of the cathode support, preferably made of stainless steel.

[0055] The cathode material is preferably cerium tungsten with strong electron emission capability, good high temperature resistance and arc ablation resistance. Therefore, it has good plasma discharge performance in the electric propulsion mode and will not affect the combustion reaction in the chemical propulsion mode.

[0056] In the electric propulsion mode, since the arc center temperature can reach over 20,000K, which is much higher than the operating temperature inside the combustion chamber in the chemical propulsion mode, the anode and cathode materials selected above have sufficient high temperature resistance, so they can work well in both working modes with very little ablation.

[0057] The total axial length of the cylindrical cathode with a tip in the center of the device is L, and the throat diameter of the anode nozzle constraint channel is d t (generally 0.4 to 0.6 mm), constrained channel length l con (generally 1 to 10 cm), nozzle area ratio ε = nozzle outlet cross-sectional area / nozzle throat area, generally 130 to 450.

[0058] The above-mentioned power supply is also called a power conditioning unit, the positive pole of the power supply is connected to the anode, the negative pole of the power supply is connected to the cathode, and the power supply has a low voltage mode and a high voltage mode.

[0059] Furthermore, the insulating shell, the combustion chamber and the outer periphery of the anode are coaxially sleeved with a cover shell, and the cover shell and the insulating shell are both made of insulating materials, preferably mica ceramics or boron nitride ceramics.

[0060] A method for operating a chemical-arc combined propulsion thruster for space use has two working modes: a chemical propulsion mode and an electric propulsion mode. By controlling the start-up timing of an oxidizer, a fuel and an electric propulsion working fluid, and the selection of a power supply working mode, the combined propulsion thruster can switch between the two working modes.

[0061] The present invention better combines the advantages of high thrust of chemical engines and high specific impulse and adjustable thrust of arc thrusters, thereby improving their comprehensive performance and covering a wider range of mission types.

[0062] When a spacecraft with a combined power thruster needs to complete rapid maneuvering tasks such as avoiding space debris and orbit transfer, the chemical propulsion mode is used to provide large thrust for the spacecraft. When the spacecraft needs to maintain orbit, fine-tune attitude, and complete deep space exploration, the electric propulsion mode is used to precisely control the thrust of the spacecraft.

[0063] 1. The working process of chemical propulsion mode includes the following steps:

[0064] Step A1, injecting chemical propellant: the chemical oxidant supply assembly supplies the oxidant with a set pressure P1 to the injector, and the chemical fuel supply assembly supplies the fuel with a set pressure P2 to the injector; the injector atomizes and mixes the oxidant and fuel through the spray hole and injects them into the combustion chamber.

[0065] Step A2, ignition: When the mixture of fuel and oxidant fills the entire combustion chamber, the power supply working mode is selected as the low voltage mode, so that a low pulse voltage of a set voltage U1 is formed between the anode and the cathode connected to the positive and negative electrodes of the power supply. The low pulse voltage will make the chemical propellant in the combustion chamber mixed evenly, and form a combustion chamber near the contraction section as shown in FIG. Figure 4 As shown, the unstable short arc, the high temperature at the short arc ignites the atomized and fully mixed fuel in the combustion chamber, so that the combustion chamber is filled with high-temperature and high-pressure combustion gas, which is accelerated at the contraction section and discharged from the lower nozzle at high speed to form thrust, thereby achieving chemical propulsion of the set thrust.

[0066] The voltage range of the set voltage U1 is preferably 80 to 100 V. At this time, it is sufficient to generate an arc and achieve ignition, and the arc stability is not required, thereby saving energy.

[0067] 2. The working process of the electric propulsion mode includes the following steps:

[0068] Step B1, supplying electric propulsion working fluid: the electric propulsion working fluid working component should be able to supply electric propulsion working fluid into the combustion chamber in a swirling manner.

[0069] Step B2, long arc discharge: while the electric propulsion medium is supplied, the power supply working mode is selected as the high voltage mode, so that the anode and cathode connected to the positive and negative electrodes of the power supply have a high voltage of set voltage U2, and a discharge arc is generated at the cathode tip. Under the appropriate pressure impact of the electric propulsion medium at room temperature, the discharge arc forms a long and thin discharge arc, and gradually spreads at the outlet of the contraction nozzle and adheres to the surface of the anode. The above-mentioned long arc can ionize a part of the electric propulsion medium to form plasma to maintain the long arc, and on the other hand, it can heat the remaining electric propulsion medium, so that it is heated and expanded and then ejected from the anode at an accelerated speed to form a reaction thrust.

[0070] In order to make the thruster have better specific impulse and propulsion efficiency in the arc working mode, the propellant needs to form a slender arc at an appropriate flow rate (too much flow rate will break the arc, and too little flow rate will make the arc unstable. Different propellants have different corresponding flow rates, generally in the range of 0.001 to 0.6 g / s). At this time, the voltage U2 varies according to the type of working fluid and flow rate, generally between 120 and 200 V.

[0071] The present invention ingeniously realizes the sharing of the structural gap between the chemical propulsion combustion chamber and the two poles of the arc, transforms the disadvantage of arc instability in the low-voltage mode into the ignition mode during chemical propulsion, solves the problem that green non-toxic propellants cannot spontaneously ignite in the future, avoids the cumbersome and complex ignition device, and enables the two thrusters to achieve a high degree of structural reuse with lower complexity. When the chemical propulsion mode works alone, it only needs to input a low-voltage pulse with a small power to ignite the arc formed between the two poles after the fuel is mixed in the combustion chamber; when the electric propulsion mode works, a slender arc is formed at an appropriate flow rate and higher input power, so that the arc thruster can achieve better performance.

[0072] The present invention can combine chemical propulsion and arc propulsion without affecting the structure of the arc thruster itself, utilizing the characteristics of the two discharge modes of the arc thruster. The arc ignition method replaces the traditional ignition device, simplifies the structure of the igniter under chemical propulsion, improves the miniaturization and integration of the combined thruster, and improves the flat injector into a ring shape in the invention, so that its structure is better compatible with the cathode.

[0073] The preferred embodiments of the present invention are described in detail above; however, the present invention is not limited to the specific details in the above embodiments. Within the technical concept of the present invention, various equivalent transformations can be made to the technical solutions of the present invention, and these equivalent transformations all belong to the protection scope of the present invention.

Claims

1. A method for operating a chemical-arc combined power thruster for space, characterized in that: On the basis of not affecting the structure of the arc thruster itself, the characteristics of the two discharge modes of the arc thruster are utilized to combine chemical propulsion and arc propulsion together, and the combined power thruster has two working modes: chemical propulsion mode and electric propulsion mode. By controlling the start-up timing of the oxidant, fuel and electric propulsion working fluid, as well as the selection of the power supply working mode, the combined power thruster can realize the switching of the two working modes. The working process of chemical propulsion mode includes the following steps: Step A1, injecting chemical propellant: the chemical oxidant supply assembly supplies the oxidant with a set pressure P1 to the injector, and the chemical fuel supply assembly supplies the fuel with a set pressure P2 to the injector; the injector atomizes and mixes the oxidant and the fuel through the spray hole and injects them into the combustion chamber; wherein the set pressures P1 and P2 are not less than 8.0 MPa; Step A2, ignition: When the mixture of fuel and oxidant fills the entire combustion chamber, the power supply working mode is selected as the low voltage mode, so that a low pulse voltage of the set voltage U1 is formed between the anode and the cathode connected to the positive and negative electrodes of the power supply. The low pulse voltage will cause the chemical propellant mixed evenly in the combustion chamber to ignite and burn in the combustion chamber adjacent to the contraction section, thereby achieving chemical propulsion with the set thrust; wherein the voltage range of the set voltage U1 is 80~100V; The ignition of chemical propellants is achieved through the electric arc formed between the cathode and the anode, which solves the problem that the oxidizer and fuel cannot spontaneously react and ignite. There is no need to equip an ignition device, and multiple ignitions can be performed according to mission requirements. The working process of the electric propulsion mode includes the following steps: Step B1, supplying electric propulsion working fluid: the electric propulsion working fluid working component can supply electric propulsion working fluid into the combustion chamber in a swirling manner; Step B2, long arc discharge: while the electric propulsion working fluid is supplied, the power supply working mode is selected as the high voltage mode, so that a high voltage of set voltage U2 is present between the anode and cathode connected to the positive and negative poles of the power supply, and a discharge arc is generated at the cathode tip. Under the pressure impact of the electric propulsion working fluid, the discharge arc forms a long discharge arc; on the one hand, the long arc can ionize a part of the electric propulsion working fluid to form plasma to maintain the long arc, and on the other hand, it can heat the remaining electric propulsion working fluid, causing it to expand due to heat and then be ejected from the anode at an accelerated speed, thereby forming a reaction thrust.

2. The method for operating a chemical-arc combined power thruster for space use according to claim 1, characterized in that: When a spacecraft with a combined power thruster needs to complete a rapid maneuvering mission, the chemical propulsion mode is used to provide large thrust for the spacecraft; when the spacecraft needs to maintain and adjust its orbital attitude, the electric propulsion mode is used to precisely control the thrust of the spacecraft.

3. A chemical-arc combined power thruster for space use, based on the operation method of the chemical-arc combined power thruster for space use according to any one of claims 1 to 2, characterized in that: It includes an injector, a cathode, a combustion chamber, an anode, a power source, a chemical oxidant supply assembly, a chemical fuel supply assembly and an electric propulsion fluid working assembly; The injector is coaxially sealed and arranged at the upstream section of the combustion chamber. The injector is connected to the chemical oxidant supply assembly and the chemical fuel supply assembly respectively, and can inject the oxidant and the fuel into the combustion chamber. The anode is coaxially arranged at the rear end of the combustion chamber and has a Laval spray cavity; the anode is connected to the positive electrode of the power supply; The cathode is coaxially inserted in the center of the injector, and the cathode has a tip pointing to the throat of the Laval nozzle chamber; The cathode is connected to the negative pole of the power supply; the power supply has a low voltage mode and a high voltage mode; The electric propulsion working fluid working component can supply electric propulsion working fluid to the combustion chamber.

4. The chemical-arc combined power thruster for space use according to claim 1, characterized in that: Also included are a cathode support and an insulating shell; The upstream end of the cathode extends out from the outer side of the injector and is coaxially mounted in the cathode support; The insulating shell is coaxially sleeved on the outer periphery of the cathode support.

5. The chemical-arc combined power thruster for space use according to claim 4 is characterized in that: The invention also comprises a cover shell which is coaxially sleeved on the insulating shell, the combustion chamber and the outer periphery of the anode.

6. The chemical-arc combined power thruster for space use according to claim 3, characterized in that: The electric propulsion working fluid is the oxidant in the chemical oxidant supply assembly or the fuel in the chemical fuel supply assembly.

7. The chemical-arc combined power thruster for space use according to claim 4, characterized in that: The electric propulsion working fluid working component includes a rotating air intake pipe, which is spirally wound around the outer periphery of the cathode; the air intake end of the rotating air intake pipe is connected to a chemical oxidant supply component or a chemical fuel supply component.

8. The chemical-arc combined power thruster for space use according to claim 3 is characterized in that: The cathode material is cerium tungsten which is resistant to high temperature and arc erosion; the anode material is stainless steel, molybdenum or tungsten which is resistant to high temperature and arc erosion.

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