High-frequency induction heating space propulsion system and propulsion method

Abstract

This invention relates to the field of aerospace propulsion technology, specifically disclosing a high-frequency induction heating space propulsion system and method. The system includes a Laval nozzle, a high-frequency induction heating chamber, a flange joint, and a working propellant delivery pipeline. The high-frequency induction heating chamber includes an induction coil, a heating chamber shell, and a metal workpiece to be heated. The induction coil is wound around the outside of the heating chamber shell. The induction coil generates a high-frequency alternating magnetic field powered by a high-frequency AC power supply. This magnetic field induces eddy currents in the metal workpiece, thereby heating the heating chamber shell. The working propellant delivery pipeline injects propellant from the propellant tank into the high-frequency induction heating chamber for heating. The resulting high-temperature, high-pressure gas is ejected from the Laval nozzle, generating thrust. Utilizing the principle of electromagnetic induction, eddy currents are generated inside the thruster shell, directly heating the propellant, offering advantages such as high heating efficiency and fast response speed.

Description

Technical Field

[0001] This invention relates to the field of aerospace propulsion technology, and in particular to a high-frequency induction heating space propulsion system and propulsion method. Background Technology

[0002] Resistance-heated thrusters are a type of electrothermal jet engine that uses resistance-heated propellant to generate thrust through aerodynamic acceleration during ejection from a nozzle. Due to the increased propellant temperature, their specific impulse is higher than that of cold-gas thrusters. They utilize electrical energy (Joule heat generated by current flowing through resistance wires) to heat the propellant to a high temperature, which is then accelerated by aerodynamic heat, converting electrical energy into the kinetic energy of a directional jet to generate a reaction force.

[0003] Traditional resistance-heated thrusters have heating resistors located inside the heating chamber. Heating temperatures are limited by the resistance material, and heat loss is significant, resulting in low energy efficiency. Furthermore, the power supply must be routed into the thrust chamber, which is technically demanding and carries the risk of air leakage, leading to a high failure rate. To prevent leakage, a complex airtight structure is required, increasing costs.

[0004] The above content is only used to help understand the technical solution of the present invention and does not represent an admission that the above content is prior art. Summary of the Invention

[0005] The main objective of this invention is to provide a high-frequency induction heating space propulsion system and propulsion method, aiming to solve the technical problems of large heat loss and low propulsion energy efficiency in existing space thrusters.

[0006] To achieve the above objectives, the present invention provides a high-frequency induction heating space propulsion system, which includes: a Laval nozzle, a high-frequency induction heating chamber, a flange joint, and a working fluid delivery pipeline; One end of the working fluid delivery pipeline is connected to the propellant storage tank, and the other end of the working fluid delivery pipeline is sealed to one end of the high-frequency induction heating chamber through the flange joint. The other end of the high-frequency induction heating chamber is connected to the Laval nozzle. The high-frequency induction heating chamber includes: an induction coil, a heating chamber shell, and a metal workpiece to be heated; The induction coil is wound around the outside of the heating chamber shell, and the induction coil is electrically connected to a high-frequency AC power supply; The induction coil is used to generate a high-frequency alternating magnetic field based on the high-frequency AC power supply, and to induce eddy currents on the metal workpiece using the high-frequency alternating magnetic field, so as to raise the temperature of the heating chamber shell. The working fluid delivery pipeline is used to inject the propellant in the propellant storage tank into the high-frequency induction heating chamber for heating. The high-temperature and high-pressure gas formed after heating is ejected from the Laval nozzle to generate thrust.

[0007] In one embodiment, the high-frequency induction heating chamber is provided with: a first working fluid channel, a heat insulation sheet, and a first bolt hole; The first working fluid flow channel consists of a main pipe along the shell of the heating chamber and a fine hole for injecting into the high-frequency induction heating chamber. The heat insulation sheet is disposed at the inlet where the high-frequency induction heating chamber connects to the working fluid delivery pipeline. The first working fluid flow channel extends from the flange joint through the inner wall of the heating chamber housing; The heat insulation sheet is used to prevent the heat from the high-frequency induction heating chamber from spreading to the flange joint and the working fluid delivery pipeline. The first bolt hole is used to connect the high-frequency induction heating chamber, the flange joint, and the working fluid delivery pipeline in sequence by fixing bolts.

[0008] In one embodiment, the heating chamber shell is made of a high-temperature resistant ceramic material; The heat insulation sheet is made of graphite material; The propellant is a gaseous or liquid working fluid.

[0009] In one embodiment, the metal heating workpiece is made of high-temperature resistant metal and is constructed with a metal rod in the middle and sheet-like edges. The Laval nozzle is provided with a contraction section and an expansion section, wherein the cross-sectional radius of the contraction section is smaller than the cross-sectional radius of the expansion section.

[0010] In one embodiment, the induction coil is made of high-conductivity copper and employs a multi-layer coil design, with the outside wrapped with a high-temperature resistant insulating material.

[0011] In one embodiment, the flange joint has a second working fluid flow channel inside; The second working fluid channel introduces the working fluid into the high-frequency induction heating chamber through the first working fluid channel; The second working fluid channel is connected to the first working fluid channel inside the high-frequency induction heating chamber.

[0012] In one embodiment, both the flange joint and the working fluid delivery pipeline are made of high-temperature resistant and corrosion-resistant metal materials.

[0013] In one embodiment, the flange joint has second bolt holes distributed at equal intervals; The second bolt hole corresponds to the position of the first bolt hole in the high-frequency induction heating chamber; The second bolt hole is used to connect the high-frequency induction heating chamber, the flange joint, and the working fluid delivery pipeline in sequence via fixing bolts, in conjunction with the first bolt hole.

[0014] Furthermore, to achieve the above objectives, the present invention also proposes a high-frequency induction heating propulsion method, which is applied to the high-frequency induction heating space propulsion system described above, and the method includes: A high-frequency alternating magnetic field is generated by a high-frequency AC power supply. Eddy currents are induced in the metal workpiece inside the high-frequency induction heating chamber using the high-frequency alternating magnetic field to heat and raise the temperature. The working medium is injected into the high-frequency induction heating chamber through the working medium delivery pipeline and flange joint to heat and form a high-temperature and high-pressure gas. The high-temperature, high-pressure gas is accelerated and ejected through the Laval nozzle to generate thrust.

[0015] In one embodiment, the step of injecting the working medium into the high-frequency induction heating chamber through a working medium delivery pipeline and flange joint to heat and form a high-temperature, high-pressure gas includes: The working medium is injected into the first working medium flow channel inside the high-frequency induction heating chamber through the working medium delivery pipeline and flange joint, and is heated and vaporized into gas by the heating chamber shell. The vaporized gas is heated to a high temperature and high pressure state by the metal workpiece to form a high temperature and high pressure gas.

[0016] This invention provides a high-frequency induction heating space propulsion system and method. The high-frequency induction heating space propulsion system includes a Laval nozzle, a high-frequency induction heating chamber, a flange joint, and a working propellant delivery pipeline. One end of the working propellant delivery pipeline is connected to a propellant storage tank, and the other end of the working propellant delivery pipeline is sealed to one end of the high-frequency induction heating chamber via the flange joint. The other end of the high-frequency induction heating chamber is connected to the Laval nozzle. The high-frequency induction heating chamber includes an induction coil, a heating chamber shell, and a metal workpiece to be heated. The induction coil is wound around the outside of the heating chamber shell and is electrically connected to a high-frequency AC power supply. The induction coil generates a high-frequency alternating magnetic field based on the high-frequency AC power supply, and uses this high-frequency alternating magnetic field to induce eddy currents in the metal workpiece to heat the heating chamber shell. The working propellant delivery pipeline injects propellant from the propellant storage tank into the high-frequency induction heating chamber for heating. The resulting high-temperature, high-pressure gas is ejected from the Laval nozzle to generate thrust. Utilizing the principle of electromagnetic induction, eddy currents are generated inside the thruster casing to directly heat the propellant, offering advantages such as high heating efficiency and fast response speed. Meanwhile, the induction coil is wound around the outside of the thruster casing, resulting in a simple structure that is easy to manufacture and assemble. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of the first embodiment of the high-frequency induction heating space propulsion system proposed in this invention; Figure 2 This is a cross-sectional view of the thruster body in the second embodiment of the high-frequency induction heating space propulsion system proposed in this invention; Figure 3 This is a cross-sectional view of the working propellant loading structure in the third embodiment of the high-frequency induction heating space propulsion system proposed in this invention; Figure 4 This is a schematic diagram of the working propellant loading structure in the third embodiment of the high-frequency induction heating space propulsion system proposed in this invention; Figure 5 This is a flowchart illustrating the first embodiment of the high-frequency induction heating propulsion method proposed in this invention. Figure 6 This is a schematic flowchart of the second embodiment of the high-frequency induction heating propulsion method proposed in this invention.

[0018] Explanation of reference numerals in the attached drawings: 1. Laval nozzle; 2. High-frequency induction heating chamber; 3. Flange joint; 4. Working fluid delivery pipeline; 21. First working fluid flow channel; 22. Heat insulation sheet; 23. Metal heating workpiece; 24. First bolt hole; 25. Induction coil; 31. Second working fluid flow channel; 32. Second bolt hole; 33. Fixing bolt.

[0019] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0020] It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0021] The technical solutions of the embodiments of the present invention 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 the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0022] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0023] Furthermore, the use of terms such as "first" and "second" in this invention is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature. Additionally, the technical solutions of the various embodiments can be combined with each other, but only on the basis of being achievable by those skilled in the art. When the combination of technical solutions is contradictory or impossible to implement, such a combination of technical solutions should be considered non-existent and not within the scope of protection claimed by this invention.

[0024] Reference Figure 1 , Figure 1 This is a schematic diagram of the first embodiment of the high-frequency induction heating space propulsion system proposed in this invention. Based on Figure 1 The first embodiment of the high-frequency induction heating space propulsion system of the present invention is presented.

[0025] In this embodiment, the high-frequency induction heating space propulsion system includes: a Laval nozzle 1, a high-frequency induction heating chamber 2, a flange joint 3, and a working propellant delivery pipeline 4; one end of the working propellant delivery pipeline 4 is connected to a propellant storage tank (not shown in the figure), the other end of the working propellant delivery pipeline 4 is sealed to one end of the high-frequency induction heating chamber 2 through the flange joint 3, and the other end of the high-frequency induction heating chamber 2 is connected to the Laval nozzle 1.

[0026] Furthermore, the high-frequency induction heating chamber 2 includes: an induction coil 25, a heating chamber shell, and a metal heating workpiece 23; the induction coil 25 is wound around the outside of the heating chamber shell, and the induction coil 25 is electrically connected to a high-frequency AC power supply (not shown in the figure).

[0027] It should be noted that the induction coil can be used to generate a high-frequency alternating magnetic field based on the high-frequency AC power supply, inducing eddy currents on the metal workpiece to raise the temperature of the heating chamber shell. The working fluid delivery pipeline is used to inject the propellant from the propellant storage tank into the high-frequency induction heating chamber for heating. The high-temperature, high-pressure gas formed after heating is ejected from the Laval nozzle to generate thrust.

[0028] It should be understood that the thruster body includes a Laval nozzle 1 and a high-frequency induction heating chamber 2. The heating chamber shell can be made of a high-temperature resistant and corrosion-resistant ceramic material, which has virtually no impact on the magnetic field generated by the induction coil. The induction coil 25 is wound around the outside of the high-frequency induction heating chamber 2 of the thruster and is made of high-conductivity copper, wrapped with a high-temperature resistant insulating material (such as ceramic fiber). The induction coil 25 is powered by a high-frequency AC power supply, generating a high-frequency alternating magnetic field. The coil adopts a multi-layer coil design to effectively improve the magnetic field strength, thereby enhancing the heating effect. The frequency of the high-frequency AC power is adjustable between 10 kHz and 1 MHz, depending on the heating requirements of the propellant and the material properties of the thruster shell. A metal heating element 23 can be installed inside the heating chamber shell. The metal heating workpiece 23 is placed in the heating chamber. The heating workpiece is made of high-temperature resistant metals such as tungsten and is made into a shape with a metal rod in the middle and a spiral blade surface around the periphery (or other shapes that are easy to generate high-frequency heating and heat transfer). This effectively increases the heating area of ​​the propellant in the heating chamber, so that the propellant heats up rapidly in a short time and is ejected after passing through the contraction section and expansion section of the Laval nozzle 1 in sequence. The cross-sectional radius of the contraction section of the Laval nozzle 1 is smaller than the cross-sectional radius of the expansion section.

[0029] Furthermore, the propellant loading structure can pump propellant from the propellant storage tank into the high-frequency induction heating chamber of the thruster. The propellant loading structure includes a flange joint 3 and a propellant delivery pipeline 4. A control component such as a solenoid valve (not shown in the figure) can be installed between the propellant delivery pipeline 4 and the propellant storage tank. The solenoid valve is switched on and off based on the received thrust command, thereby controlling the propellant supply.

[0030] Specifically, copper can be used to make the induction coil, and tungsten (or other high-temperature resistant metals) can be used as the metal heating workpiece, with the heating temperature maintained at 2000K-3000K; the thruster housing is made of silicon carbide (or other high-temperature resistant ceramic materials), and the propellant is injected into the thruster heating chamber along the housing wall. Gas or liquid working fluid is used as the propellant, and the propellant delivery pipeline is sealed to the thruster housing through a flange joint, which is convenient to disassemble and effectively ensures airtightness.

[0031] In this embodiment, the high-frequency induction heating space propulsion system includes: a Laval nozzle, a high-frequency induction heating chamber, a flange joint, and a working propellant delivery pipeline; one end of the working propellant delivery pipeline is connected to the propellant storage tank, and the other end of the working propellant delivery pipeline is sealed to one end of the high-frequency induction heating chamber through the flange joint. The other end of the high-frequency induction heating chamber is connected to the Laval nozzle; the high-frequency induction heating chamber includes: an induction coil, a heating chamber shell, and a metal heating workpiece; the induction coil is wound around the outside of the heating chamber shell, and the induction coil is electrically connected to a high-frequency AC power supply. The induction coil is used to generate a high-frequency alternating magnetic field based on the high-frequency AC power supply, and uses the high-frequency alternating magnetic field to induce eddy currents on the metal heating workpiece, thereby heating the heating chamber shell; the working propellant delivery pipeline is used to inject the propellant from the propellant storage tank into the high-frequency induction heating chamber for heating, and the high-temperature, high-pressure gas formed after heating is ejected from the Laval nozzle to generate thrust. Utilizing the principle of electromagnetic induction, eddy currents are generated inside the thruster shell, thereby directly heating the propellant, which has the advantages of high heating efficiency and fast response speed. Meanwhile, the induction coil is wound around the outside of the thruster housing, which is simple in structure and easy to process and assemble.

[0032] Reference Figure 2 , Figure 2 This is a cross-sectional view of the thruster body in the second embodiment of the high-frequency induction heating space propulsion system proposed in this invention. Based on the first embodiment of the high-frequency induction heating space propulsion system described above, a second embodiment of the high-frequency induction heating space propulsion system of this invention is proposed.

[0033] In this embodiment, the thruster body includes a Laval nozzle 1 and a high-frequency induction heating chamber 2. The high-frequency induction heating chamber 2 contains a first working fluid channel 21, a heat insulation plate 22, and a first bolt hole 24. The first working fluid channel 21 consists of a main pipe along the heating chamber shell and a fine hole for injecting into the high-frequency induction heating chamber 2. The heat insulation plate 22 is located at the inlet where the high-frequency induction heating chamber 2 connects to the working fluid delivery pipeline 4.

[0034] It should be noted that the first working fluid flow channel 21 can extend through the heating chamber shell from the flange joint 3 along the inner wall of the shell to extend the flow path of the propellant in the heating chamber shell. On the one hand, the heat of the shell can be used to preheat the propellant and improve the energy utilization rate; on the other hand, the propellant flowing through the interior of the heating chamber shell can effectively carry away some heat, play a heat dissipation role, and prevent the heating chamber shell from overheating.

[0035] It is understood that the heat insulation sheet 22 can be made of graphite material, which has a high melting point, excellent thermal stability and mechanical strength. This component is placed at the entrance of the heating chamber to effectively prevent the heat from the heating chamber from spreading to the flange joint 3 and the working fluid conveying pipeline 4, thereby further ensuring airtightness.

[0036] It should be understood that the first bolt hole can be used to sequentially connect the high-frequency induction heating chamber, the flange joint, and the working fluid delivery pipeline via fixing bolts.

[0037] In this embodiment, the high-frequency induction heating chamber is provided with: a first working fluid channel, a heat insulation plate, and a first bolt hole; the first working fluid channel consists of a main pipe along the heating chamber shell and a fine hole for injecting into the high-frequency induction heating chamber; the heat insulation plate is disposed at the inlet where the high-frequency induction heating chamber connects to the working fluid delivery pipeline; the first working fluid channel extends through the heating chamber shell from the flange joint along the inner wall of the shell; the heat insulation plate is used to prevent the heat from the high-frequency induction heating chamber from diffusing to the flange joint and the working fluid delivery pipeline; the first bolt hole is used to sequentially connect the high-frequency induction heating chamber, the flange joint, and the working fluid delivery pipeline with fixing bolts. The working fluid is injected from the heating chamber shell wall channel: the working fluid passes through the delivery pipeline and the flange joint, and is injected from the high-frequency induction heating chamber shell wall channel. On the one hand, the residual heat of the thruster shell can be used to preheat the propellant, improving energy utilization; on the other hand, the working fluid flowing through the heating chamber shell can effectively carry away some heat, playing a heat dissipation role and preventing the thruster from overheating.

[0038] Reference Figure 3 and Figure 4 , Figure 3 This is a cross-sectional view of the working propellant loading structure in the third embodiment of the high-frequency induction heating space propulsion system proposed in this invention; Figure 4 This is a schematic diagram of the propellant loading structure in the third embodiment of the high-frequency induction heating space propulsion system proposed in this invention. Based on the above embodiments of the high-frequency induction heating space propulsion system, the third embodiment of the high-frequency induction heating space propulsion system of this invention is proposed.

[0039] In this embodiment, the propellant loading structure includes a flange joint 3 and a propellant delivery pipeline 4 in sequence. The flange joint 3 has a second working fluid channel 31 inside. The second working fluid channel 31 is connected to the first working fluid channel 21 inside the high-frequency induction heating chamber 2.

[0040] It should be noted that the second working fluid flow channel 31 inside the flange joint 3 is connected to the first working fluid flow channel 21 inside the thruster body. The second working fluid flow channel introduces the working fluid into the high-frequency induction heating chamber through the first working fluid flow channel. The working fluid delivery pipeline 4 is connected to subsequent components such as solenoid valves and storage tanks (not shown in the figure) and is used to inject propellant into the thruster. The walls of all working fluid flow pipelines are smooth and free of burrs to reduce propellant flow resistance. Both the flange joint 3 and the working fluid delivery pipeline 4 are made of high-temperature and corrosion-resistant metal materials to ensure reliability under high-temperature and high-pressure environments.

[0041] Understandably, the flange joint 3 and the thruster body also have equally spaced second bolt holes 32, which correspond to the positions of the first bolt holes 24 on the high-frequency induction heating chamber 2. The working fluid delivery pipeline 4, flange joint 3, and high-frequency induction heating chamber 2 are sequentially connected by fixing bolts 33 to ensure airtightness and facilitate disassembly and maintenance. After the bolts are fixed, a sealed contact is formed between the flange plates, maintaining good sealing performance even under high temperature and high pressure environments. Once the working fluid delivery pipeline 4, flange joint 3, and high-frequency induction heating chamber 2 are connected and fixed, the thruster can be installed, disassembled, and maintained by tightening the fixing bolts 33.

[0042] In this embodiment, the flange joint has a second working fluid channel inside; the second working fluid channel is connected to the first working fluid channel inside the high-frequency induction heating chamber; the first and second working fluid channels have the same cross-sectional size; the flange joint has second bolt holes evenly spaced on it; the second bolt holes correspond to the positions of the first bolt holes in the high-frequency induction heating chamber; the second bolt holes are used to connect the high-frequency induction heating chamber, the flange joint, and the working fluid delivery pipeline sequentially via fixing bolts, in conjunction with the first bolt holes. This effectively ensures the airtightness between the thruster and the propellant loading pipeline, preventing propellant leakage, and also facilitates disassembly and maintenance.

[0043] Furthermore, this invention also proposes a high-frequency induction heating propulsion method. (Refer to...) Figure 5 , Figure 5 This is a schematic flowchart of the first embodiment of the high-frequency induction heating propulsion method proposed in this invention. The high-frequency induction heating propulsion method includes: Step S10: A high-frequency alternating magnetic field is generated based on a high-frequency AC power supply. Eddy currents are induced on the metal workpiece inside the high-frequency induction heating chamber using the high-frequency alternating magnetic field to heat and raise the temperature.

[0044] It should be noted that the executing entity in this embodiment can be a computing service device with data processing, network communication, and program execution functions, or an electronic device capable of performing the above functions. For example, the high-frequency induction heating space propulsion system described above. The following description uses the high-frequency induction heating space propulsion system as an example to illustrate this embodiment and the following embodiments.

[0045] It should be understood that a high-frequency alternating current is used to power the induction coil, generating a high-frequency alternating magnetic field. This magnetic field induces eddy currents in the metal workpiece inside the high-frequency induction heating chamber, causing the casing to heat up rapidly. The frequency of the high-frequency alternating current is adjustable between 10 kHz and 1 MHz, depending on the propellant heating requirements and the material properties of the thruster casing.

[0046] Step S20: The working medium is injected into the high-frequency induction heating chamber through the working medium delivery pipeline and flange joint to heat and form a high-temperature and high-pressure gas.

[0047] It should be noted that the working fluid passes through the working fluid delivery pipeline 4 and the flange joint 3 in sequence, is heated by the shell and then by the metal heating workpiece 23 to a high temperature and high pressure state, forming a high temperature and high pressure gas.

[0048] Step S30: The high-temperature and high-pressure gas is accelerated and ejected through the Laval nozzle to generate thrust.

[0049] It should be noted that the high-temperature and high-pressure gas is ejected after passing through the contraction section and the expansion section of the Laval nozzle in sequence. The cross-sectional radius of the contraction section is smaller than that of the expansion section, which accelerates the gas injection and generates a reaction force (thrust).

[0050] This embodiment achieves efficient, rapid, and reliable propulsion performance by employing high-frequency induction heating, injecting the working propellant along the wall of the heating chamber, and a sealed joint structure. Its simple structure, high heating efficiency, and fast response make it suitable for propulsion systems of spacecraft such as small satellites and deep space probes.

[0051] Reference Figure 6 , Figure 6 This is a schematic flowchart of the second embodiment of the high-frequency induction heating propulsion method proposed in this invention. Step S20 includes: Step S201: The working medium is injected into the first working medium flow channel in the high-frequency induction heating chamber through the working medium delivery pipeline and flange joint, and is heated and vaporized into gas by the heating chamber shell.

[0052] Step S202: The vaporized gas is heated to a high temperature and high pressure state by the metal heating workpiece to form a high temperature and high pressure gas.

[0053] It should be noted that the working propellant is injected into the first working propellant channel 21 inside the high-frequency induction heating chamber 2. During the flow of the working propellant through the first working propellant channel 21, it absorbs heat from the shell, thus dissipating heat and preventing overheating of the shell. Simultaneously, the propellant is preheated during injection, improving energy utilization efficiency.

[0054] Understandably, the propellant can be either gaseous or liquid. Liquid propellants are heated and vaporized into gas (e.g., ammonia) within the flow channel, and then heated to a high-temperature, high-pressure state by the metal heating element in the heating chamber, forming a high-temperature, high-pressure gas. This high-temperature, high-pressure gas is accelerated and ejected through the Laval nozzle at the tail of the thruster, generating a reaction force (thrust). The propellant is injected along the heating chamber shell, effectively carrying away some heat and preventing the thruster from overheating.

[0055] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or system that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or system. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or system that includes that element.

[0056] The above are merely preferred embodiments of the present invention and do not limit the scope of the patent. Any equivalent structural or procedural transformations made based on the description and drawings of the present invention, or direct or indirect applications in other related technical fields, are similarly included within the scope of patent protection of the present invention.

Claims

1. A high-frequency induction heating space propulsion system, characterized in that, The high-frequency induction heating space propulsion system includes: a Laval nozzle, a high-frequency induction heating chamber, a flange joint, and a working fluid delivery pipeline; One end of the working fluid delivery pipeline is connected to the propellant storage tank, and the other end of the working fluid delivery pipeline is sealed to one end of the high-frequency induction heating chamber through the flange joint. The other end of the high-frequency induction heating chamber is connected to the Laval nozzle. The high-frequency induction heating chamber includes: an induction coil, a heating chamber shell, and a metal workpiece to be heated; The induction coil is wound around the outside of the heating chamber shell, and the induction coil is electrically connected to a high-frequency AC power supply; The induction coil is used to generate a high-frequency alternating magnetic field based on the high-frequency AC power supply, and to induce eddy currents on the metal workpiece using the high-frequency alternating magnetic field, so as to raise the temperature of the heating chamber shell. The working fluid delivery pipeline is used to inject the propellant in the propellant storage tank into the high-frequency induction heating chamber for heating. The high-temperature and high-pressure gas formed after heating is ejected from the Laval nozzle to generate thrust.

2. The high-frequency induction heating space propulsion system as described in claim 1, characterized in that, The high-frequency induction heating chamber is provided with: a first working fluid channel, a heat insulation sheet and a first bolt hole; The first working fluid flow channel consists of a main pipe along the shell of the heating chamber and a fine hole for injecting into the high-frequency induction heating chamber. The heat insulation sheet is disposed at the inlet where the high-frequency induction heating chamber connects to the working fluid delivery pipeline. The first working fluid flow channel extends from the flange joint through the inner wall of the heating chamber housing; The heat insulation sheet is used to prevent the heat from the high-frequency induction heating chamber from spreading to the flange joint and the working fluid delivery pipeline. The first bolt hole is used to connect the high-frequency induction heating chamber, the flange joint, and the working fluid delivery pipeline in sequence by fixing bolts.

3. The high-frequency induction heating space propulsion system as described in claim 2, characterized in that, The heating chamber shell is made of high-temperature resistant ceramic material; The heat insulation sheet is made of graphite material; The propellant is a gaseous or liquid working fluid.

4. The high-frequency induction heating space propulsion system as described in claim 3, characterized in that, The metal heating workpiece is made of high-temperature resistant metal and is constructed with a metal rod in the middle and sheet-like edges. The Laval nozzle is provided with a contraction section and an expansion section, wherein the cross-sectional radius of the contraction section is smaller than the cross-sectional radius of the expansion section.

5. The high-frequency induction heating space propulsion system as described in claim 1, characterized in that, The induction coil is made of high-conductivity copper and features a multi-layer coil design, with the outside wrapped in high-temperature resistant insulating material.

6. The high-frequency induction heating space propulsion system as described in claim 2, characterized in that, The flange joint is internally provided with a second working fluid flow channel; The second working fluid channel introduces the working fluid into the high-frequency induction heating chamber through the first working fluid channel; The second working fluid channel is connected to the first working fluid channel inside the high-frequency induction heating chamber.

7. The high-frequency induction heating space propulsion system as described in claim 6, characterized in that, Both the flange joint and the working fluid delivery pipeline are made of high-temperature resistant and corrosion-resistant metal materials.

8. The high-frequency induction heating space propulsion system as described in claim 7, characterized in that, The flange joint has second bolt holes distributed at equal intervals; The second bolt hole corresponds to the position of the first bolt hole in the high-frequency induction heating chamber; The second bolt hole is used to connect the high-frequency induction heating chamber, the flange joint, and the working fluid delivery pipeline in sequence via fixing bolts, in conjunction with the first bolt hole.

9. A high-frequency induction heating propulsion method, characterized in that, The propulsion method is applied to the high-frequency induction heating space propulsion system as described in any one of claims 1 to 8; the propulsion method includes: A high-frequency alternating magnetic field is generated by a high-frequency AC power supply. Eddy currents are induced in the metal workpiece inside the high-frequency induction heating chamber using the high-frequency alternating magnetic field to heat and raise the temperature. The working medium is injected into the high-frequency induction heating chamber through the working medium delivery pipeline and flange joint to heat and form a high-temperature and high-pressure gas. The high-temperature, high-pressure gas is accelerated and ejected through the Laval nozzle to generate thrust.

10. The high-frequency induction heating propulsion method as described in claim 9, characterized in that, The step of injecting the working medium into the high-frequency induction heating chamber through a working medium delivery pipeline and flange joint to heat and form a high-temperature, high-pressure gas includes: The working medium is injected into the first working medium flow channel inside the high-frequency induction heating chamber through the working medium delivery pipeline and flange joint, and is heated and vaporized into gas by the heating chamber shell. The vaporized gas is heated to a high temperature and high pressure state by the metal workpiece to form a high temperature and high pressure gas.

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