A hot ignition method and control device for an ADN-based space engine

Abstract

This invention provides a thermal ignition method for an ADN-based space engine, which relates to the technical field of space engines. The method comprises: sending a temperature control instruction to a temperature control structure, controlling the temperature control structure to drive a heating structure to a preset temperature; and sending a propellant injection instruction to a fuel structure, controlling the fuel structure to spray atomized propellant toward the heating structure, so that the atomized propellant contacts the heating structure to generate a propellant gas. This method can significantly improve ignition efficiency, thereby increasing engine operating time.

Description

Technical Field

[0001] The present invention relates to the technical field of space engines, and in particular to a thermal ignition method and a control device for an ADN-based space engine. Background Art

[0002] Engine ignition is achieved by decomposing the propellant inside the engine to produce high-temperature and high-pressure gas. At present, relevant technologies propose that ADN-based liquid space engines generally adopt catalytic ignition. However, the internal temperature is high during engine operation. The catalytic performance of the catalytic bed decreases in a high-temperature environment, and the ignition efficiency is low, which makes it impossible for the ADN-based liquid space engine to achieve large-flow propellant ignition, thereby reducing the on-orbit operation time of the ADN-based liquid space engine. Summary of the Invention

[0003] In view of this, the purpose of the present invention is to provide a thermal ignition method and control device for an ADN-based space engine. By using a heating structure instead of a catalyst for engine ignition, the ignition efficiency can be significantly improved, thereby increasing the engine running time.

[0004] In the first aspect, an embodiment of the present invention provides a thermal ignition method for an ADN-based space engine, which is applied to the control terminal of the engine. The engine includes a temperature control structure, a heating structure and a fuel structure. The method includes: sending a temperature control instruction to the temperature control structure, controlling the temperature control structure to drive the heating structure to a preset temperature value; sending a propellant injection instruction to the fuel structure, controlling the fuel structure to inject atomized propellant toward the heating structure, so that the atomized propellant contacts the heating structure to generate a propellant gas.

[0005] In one embodiment, the fuel structure includes an atomizing chamber and an injector group, and the heating structure includes a honeycomb-shaped fixed structure and a plurality of electric heating rods, and the electric heating rods are fixed by the fixed structure; the step of controlling the fuel structure to spray atomized propellant toward the heating structure includes: controlling the atomizing chamber to atomize the propellant to obtain atomized propellant, and controlling the injector group to spray the atomized propellant toward each electric heating rod.

[0006] In one embodiment, the injector groups are symmetrically placed on both sides of the fuel structure; the step of controlling the injector groups to spray atomized propellant toward each heating rod includes: controlling the injector groups to spray atomized propellant toward each heating rod according to the injection mode corresponding to the propellant injection instruction, wherein the propellant injection instruction is determined according to a pre-set working sequence, and the injection mode includes a coupled injection mode.

[0007] In one embodiment, the engine further includes a combustion chamber; the step of controlling the fuel structure to spray atomized propellant toward the heating structure so that the atomized propellant contacts the heating structure to generate a propellant gas comprises: controlling the fuel structure to spray atomized propellant toward the heating structure so that after the atomized propellant contacts the heating structure, a reducing gas decomposed from the atomized propellant is obtained; and controlling the combustion chamber to burn the reducing gas to generate a propellant gas.

[0008] In one embodiment, the step of sending a temperature control instruction to the temperature control structure and controlling the temperature control structure to drive the heating structure to a preset temperature value includes: sending a temperature control instruction to the temperature control structure and controlling the temperature control structure to adjust the heating power of the heating structure according to the temperature control instruction so that the heating structure is raised to a preset temperature value.

[0009] In one embodiment, after the step of controlling the fuel structure to spray atomized propellant toward the heating structure so that the atomized propellant contacts the heating structure to generate propellant gas, the step further includes: controlling the temperature control structure to reduce the heating power of the electric heating rod according to a set linear change law so that the power of the electric heating rod is reduced to zero.

[0010] In the second aspect, an embodiment of the present invention also provides a thermal ignition device for an ADN-based space engine, which is applied to the control terminal of the engine. The engine includes a temperature control structure, a heating structure and a fuel structure. The device includes: a heating control module, which sends a temperature control instruction to the temperature control structure, controls the temperature control structure to drive the heating structure to a preset temperature value; a fuel control module, which sends a propellant injection instruction to the fuel structure, controls the fuel structure to inject atomized propellant into the heating structure, so that the atomized propellant contacts the heating structure to generate a propellant gas.

[0011] In one embodiment, an ignition module is further included, which is used to: control the fuel structure to spray the atomized propellant toward the heating structure, so that the atomized propellant contacts the heating structure to obtain reducing gas decomposed from the atomized propellant; and control the combustion chamber to burn the reducing gas to generate propellant gas.

[0012] In a third aspect, an embodiment of the present invention further provides a server, comprising a processor and a memory, wherein the memory stores computer-executable instructions that can be executed by the processor, and the processor executes the computer-executable instructions to implement any one of the methods provided in the first aspect.

[0013] In a fourth aspect, an embodiment of the present invention further provides a computer-readable storage medium, which stores computer-executable instructions. When the computer-executable instructions are called and executed by a processor, the computer-executable instructions prompt the processor to implement any one of the methods provided in the first aspect.

[0014] The embodiments of the present invention bring the following beneficial effects:

[0015] An embodiment of the present invention provides a thermal ignition method and control device for an ADN-based space engine. The method is used in the engine's control terminal. The engine includes a temperature control structure, a heating structure, and a fuel structure. By sending a temperature control instruction to the temperature control structure, the temperature control structure is controlled to drive the heating structure to a predetermined temperature value. Furthermore, by sending a propellant injection instruction to the fuel structure, the fuel structure is controlled to spray atomized propellant toward the heating structure, so that the atomized propellant contacts the heating structure to generate a propellant gas. During engine ignition, this method replaces the catalytic bed with the heating structure, thereby addressing the impact of high temperature on ignition efficiency. Embodiments of the present invention can decompose the atomized propellant through the heating structure, thereby improving the engine's ignition efficiency.

[0016] Other features and advantages of the present invention will be described in the following description, and in part will become apparent from the description, or understood by practicing the present invention. The purposes and other advantages of the present invention are realized and obtained by the structures particularly pointed out in the description, claims and drawings.

[0017] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, preferred embodiments are given below and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0019] Figure 1 A schematic flow chart of a thermal ignition method for an ADN-based space engine provided in an embodiment of the present invention;

[0020] Figure 2 A schematic structural diagram of an arrangement of electric heating rods provided in an embodiment of the present invention;

[0021] Figure 3 A schematic structural diagram of another arrangement of electric heating rods provided in an embodiment of the present invention;

[0022] Figure 4 A schematic flow chart of another thermal ignition method for an ADN-based space engine provided by an embodiment of the present invention;

[0023] Figure 5 A schematic structural diagram of a thermal ignition device for an ADN-based space engine provided by an embodiment of the present invention;

[0024] Figure 6 A schematic structural diagram of an electronic device provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0025] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of them. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0026] Currently, the primary traditional monopropellant is anhydrous hydrazine. However, this has drawbacks such as high toxicity, difficulty in storage, and high operating costs. Consequently, both domestic and international efforts are actively developing new, green, non-toxic propellants. ADN-based liquid propellants, with their high energy density, low freezing point, non-toxicity, good compatibility, and environmental friendliness, are widely recognized as promising alternatives to hydrazine propellants. Traditional ADN-based monopropellant liquid space engines primarily consist of a solenoid valve, injector, catalytic bed, combustion chamber, Laval nozzle, and temperature control structure. They are primarily started through catalytic ignition, with the catalytic bed comprising a front and rear bed. During the operation of the engine, the solenoid valve receives an excitation signal, the valve port opens, and the ADN-based propellant flows into the injector. After being atomized, it is sprayed into the front bed part of the catalytic bed and begins partial pre-evaporation. At the same time, the ADN-based propellant contacts the preheated catalyst and starts a thermal decomposition reaction, releasing chemical energy to produce high-temperature and high-pressure gas. The propellant is fully decomposed in the rear bed part of the catalytic bed. After reaching the combustion chamber, it is further mixed and burned with the fuel methanol contained in the ADN-based propellant. Finally, the high-temperature and high-pressure gas produced by the full reaction is expanded and ejected from the Laval nozzle to generate thrust: the traditional ignition method of the ADN-based liquid space engine can reach an internal temperature of more than 1500K during engine operation. The high temperature environment causes the catalytic performance of the catalytic bed to drop sharply, and may even cause the catalyst to become deactivated. The disadvantage of high-temperature deactivation of the catalytic bed leads to the ADN-based liquid space engine being unable to operate in orbit for a long time, and is not conducive to the space engine carrying out high-thrust space missions. Therefore, traditional catalytic ignition methods suffer from problems such as high-temperature deactivation of the catalyst bed, the need for preheating the catalyst bed prior to ignition, which consumes a lot of energy, and the inability to effectively ignite large propellant flows. This has limited the performance and on-orbit life of space engines. Based on this, the present invention provides a thermal ignition method for an ADN-based space engine, which can decompose the atomized propellant through a heating structure, thereby improving the engine's ignition efficiency.

[0027] To facilitate understanding of this embodiment, firstly, a thermal ignition method of an ADN-based space engine disclosed in an embodiment of the present invention is described in detail. Figure 1 The flowchart of a thermal ignition method of an ADN-based space engine is shown, and the method mainly includes the following steps S102 to S106:

[0028] Step S102: Send a temperature control command to the temperature control structure, controlling the temperature control structure to drive the heating structure to a preset temperature value. The temperature control structure is a temperature control system electrically connected to a control terminal. The temperature control command to the heating structure is an input voltage control signal, and the heating structure comprises one or more electric heating rods. In one embodiment, after the temperature control structure is turned on, the engine begins running and receives the temperature control signal from the control terminal. The temperature control structure adjusts the electrical power input to the heating structure based on the temperature control signal to quickly preheat the heating structure to the preset temperature value.

[0029] In one embodiment, the heating structure includes a high-temperature incandescent object arranged inside the engine for igniting the atomized propellant. The high-temperature incandescent object can be an electric heating rod with a shell material of nickel-chromium alloy. The nickel-chromium alloy material has good high-temperature resistance and corrosion resistance. The electric heating rod can be connected to direct current or alternating current, and the temperature of the electric heating rod can be controlled by adjusting the input voltage by the temperature control structure during the heating process.

[0030] Step S104, sending a propellant injection instruction to the fuel structure, controlling the fuel structure to spray atomized propellant toward the heating structure, so that the atomized propellant contacts the heating structure to generate a propellant gas. The fuel structure includes an atomizing chamber and a plurality of injectors, the atomizing chamber is used to atomize the propellant, and the injectors are used to spray the atomized propellant. In one embodiment, after the electric heating rod is preheated to a set temperature, the injector receives a propellant injection instruction sent by the control terminal and starts working to spray the atomized propellant (such as ADN-based liquid). After the atomized propellant is atomized in the atomizing chamber, it contacts the hot surface of the electric heating rod and evaporates and decomposes under heat, and the decomposition product is a high-temperature and high-pressure propellant gas.

[0031] The thermal ignition method of the above-mentioned ADN-based space engine provided by the embodiment of the present invention decomposes the atomized propellant by heating the structure, thereby improving the ignition efficiency of the engine and thus increasing the engine running time.

[0032] In one embodiment, the engine further comprises a combustion chamber, wherein the fuel structure is controlled to spray atomized propellant toward the heating structure, so that the atomized propellant contacts the heating structure to produce reducing gas decomposed from the atomized propellant, and the combustion chamber is controlled to combust the reducing gas to generate propellant gas. The combustion chamber is used to generate the propellant gas, and the engine further comprises a nozzle. After the atomized propellant is atomized in the atomizing chamber, it contacts the hot surface of the electric heating rod and is heated to evaporate and decompose to produce decomposition products. The decomposition products are transferred to the combustion chamber, where a combustion reaction occurs to produce high-temperature and high-pressure gas. The gas is ejected through the nozzle (such as a Laval nozzle) to generate thrust for the engine.

[0033] The embodiment of the present invention further provides a method for a fuel structure to spray atomized propellant toward a heating structure. For details, see (1) to (2) below:

[0034] (1) The injector groups are symmetrically placed on both sides of the fuel structure, and the injector groups are controlled to spray atomized propellant toward each electric heating rod according to the injection mode corresponding to the propellant injection instruction, wherein the propellant injection instruction is determined according to a pre-set working sequence, and the injection mode includes a coupled injection mode. The propellant injection instruction is used to control the injection sequence and injection time of each injector. In one embodiment, the injector group performs coupled injection according to the propellant injection instruction to maintain a stable operating state of the engine.

[0035] In one embodiment, Figure 2 The structural schematic diagram of a heating rod arrangement shown in the figure adopts a method of arranging the heating rod in the center of the engine. This space engine mainly includes electrode terminals, a metal shell, an injector, a propellant spray, a heating rod, a combustion chamber, a combustion flame and a Laval nozzle. The shell is made of a high-temperature corrosion-resistant nickel-chromium alloy. The heating rod is arranged in the center of the space engine. The heating rod is connected to the temperature control structure through the electrode terminals. The temperature control structure adjusts the temperature of the heating rod by adjusting the electric power input to the heating rod. The injectors are symmetrically arranged on both sides of the engine. This structure is conducive to maintaining stable operation of the engine. The injection port of the injector is at an oblique angle to the heating rod. The oblique angle can be adjusted between 30° and 60° according to the engine working requirements, thereby increasing the contact area between the propellant spray and the heating rod.

[0036] In one embodiment, for Figure 2The arrangement of the heating rods shown in the figure includes the following working processes for the hot ignition of the engine: after the temperature control structure switch is turned on and the electrode terminals are energized, the surface of the heating rod is rapidly heated to a high temperature of several hundred degrees. When the heating rod is heated to a predetermined temperature, the injectors on both sides of the engine receive an excitation signal and start working. The atomizing nozzles of the injectors spray the ADN-based liquid propellant in the form of a spray and at a suitable angle onto the surface of the high-temperature heating rod. The propellant is rapidly evaporated and decomposed by the heat and a combustion reaction occurs in the combustion chamber. The high-temperature and high-pressure combustion flame gas generated by the combustion of the propellant is ejected through the Laval nozzle to form thrust. When the engine is successfully ignited, the temperature control structure automatically reduces the electric power input to the heating rod and adjusts the temperature of the heating rod to a suitable level. When the engine is running stably, the temperature control structure is powered off and the heating rod stops working to reduce power consumption.

[0037] (2) The fuel structure includes an atomizing chamber and an injector group, and the heating structure includes a honeycomb-shaped fixed structure and multiple electric heating rods. The electric heating rods are fixed by the fixed structure, the atomizing chamber is controlled to atomize the propellant to obtain atomized propellant, and the injector group is controlled to spray the atomized propellant toward each electric heating rod. The fixed structure is a honeycomb ceramic, and the multiple electric heating rods are embedded in the honeycomb ceramic of the fixed structure. In one embodiment, the fixed structure can effectively increase the contact area between the propellant and the heating structure, which is beneficial to organizing the combustion of the propellant.

[0038] In one embodiment, Figure 3 The structural schematic diagram of another arrangement of heating rods is shown, which adopts a honeycomb arrangement of heating rods. This space engine includes an injector, an atomization chamber, a propellant spray, a heating rod, a honeycomb ceramic, a shell, a combustion chamber, a combustion flame and a Laval nozzle. The injector is arranged at the front end of the engine, and an atomization chamber part is added between the injector and the combustion chamber to facilitate the full atomization of the propellant. The heating structure is composed of heating rods and honeycomb ceramics. The heating rods are arranged in a honeycomb structure, that is, multiple heating rods are embedded in the honeycomb ceramics. The ceramic wraps the heating rods to prevent the heating rods from contacting the metal shell of the engine, which plays an insulating role. A plurality of honeycomb propellant flow channels are provided inside the honeycomb ceramics. The atomized propellant flows into the honeycomb ceramics through the flow channels and contacts the heating rods and the hot surface of the ceramics. The heating rods are equipped with a temperature control structure, which controls the temperature of the heating rods by adjusting the electric power input to the heating rods.

[0039] In one embodiment, for Figure 3The arrangement of the electric heating rod shown in the figure includes the following working processes for the thermal ignition of the engine: after the electrode terminal is energized, the surface of the electric heating rod is quickly heated to the preheating temperature, and at the same time, the heat dissipated by the electric heating rod can heat the ceramic surface, so that the surface temperature of the ceramic also reaches a temperature that can ignite the atomized propellant. The ADN-based propellant is first sprayed into the atomization chamber through the injector, and the propellant is fully atomized in the atomization chamber. The atomized propellant spray flows into the honeycomb ceramic under the action of the front pressure and then contacts the hot surface of the high-temperature electric heating rod and the honeycomb ceramic, and is quickly heated to evaporate and decompose. The decomposition products undergo a combustion reaction in the combustion chamber, and the high-temperature and high-pressure combustion flame gas generated by the combustion is ejected through the Laval nozzle to form thrust. When the engine is successfully ignited, the temperature control structure automatically reduces the electric power input to the electric heating rod and adjusts the temperature of the electric heating rod to appropriately reduce it. When the engine is running stably, the temperature control structure is powered off, the electric heating rod stops working, and power consumption is reduced.

[0040] In one embodiment, a temperature control instruction is sent to the temperature control structure, which controls the temperature control structure to adjust the heating power of the heating structure according to the temperature control instruction, so that the heating structure is raised to a preset temperature value.

[0041] In one embodiment, the temperature control structure is controlled to reduce the heating power of the electric heating rod according to a predetermined linear variation pattern, until the power of the electric heating rod is reduced to zero. The temperature control structure automatically reduces the input power after the engine is successfully ignited and automatically shuts off after the engine is running steadily, thus avoiding excessive power loss.

[0042] To facilitate understanding of the thermal ignition method of an ADN-based space engine provided in the above embodiment, an embodiment of the present invention provides an application example of the thermal ignition method of an ADN-based space engine, see Figure 4 FIG. 1 is a flow chart of another method for thermal ignition of an ADN-based space engine, which mainly includes the following steps S402 to S412:

[0043] Step S402: When the temperature control structure is powered on, the engine begins running, and the temperature control structure controls the heating structure to rapidly preheat to a set temperature. The temperature control structure is a temperature control system electrically connected to a control terminal. The temperature control command to the heating structure is a voltage control signal input to the heating structure, and the heating structure comprises one or more electric heating rods. In one embodiment, after the temperature control structure is powered on, the engine begins running and receives the temperature control signal from the control terminal. The temperature control structure adjusts the electrical power input to the heating structure based on the temperature control signal to rapidly preheat the heating structure to the set temperature value.

[0044] In one embodiment, the heating structure includes a high-temperature incandescent object arranged inside the engine for igniting the atomized propellant. The high-temperature incandescent object can be an electric heating rod with a shell material of nickel-chromium alloy. The nickel-chromium alloy material has good high-temperature resistance and corrosion resistance. The electric heating rod can be connected to direct current or alternating current, and the temperature of the electric heating rod can be controlled by adjusting the input voltage by the temperature control structure during the heating process.

[0045] Step S404: The fuel structure starts working after receiving the excitation signal, and sprays the atomized propellant into the atomizing chamber, so that the atomized propellant contacts the heating structure. The fuel structure includes an atomizing chamber and a plurality of injectors, the atomizing chamber is used to atomize the propellant, and the injectors are used to spray the atomized propellant. In one embodiment, after the electric heating rod is preheated to a set temperature, the injector receives the propellant injection instruction sent by the control terminal and starts working, spraying the atomized propellant (such as ADN-based liquid). After the atomized propellant is atomized in the atomizing chamber, it contacts the hot surface of the electric heating rod and evaporates and decomposes due to the heat.

[0046] Step S406: After the atomized propellant contacts the heating structure, it evaporates and decomposes to produce redox gas, and the redox gas undergoes a combustion reaction in the combustion chamber to produce high-temperature and high-pressure propellant gas. The engine also includes a combustion chamber and a nozzle. In one embodiment, after the atomized propellant is atomized in the atomizing chamber, it contacts the hot surface of the electric heating rod and evaporates and decomposes to obtain decomposition products. The decomposition products are transferred to the combustion chamber and undergo a combustion reaction in the combustion chamber to produce high-temperature and high-pressure gas. The gas is ejected through the nozzle (such as a Laval nozzle) to generate thrust for the engine.

[0047] Step S408: Upon successful ignition, the propellant gas is ejected through the nozzle to generate thrust for the engine. The temperature control mechanism automatically reduces the input power until the engine stabilizes and then shuts off. The temperature control mechanism automatically reduces the input power after successful engine ignition and automatically shuts off after the engine stabilizes to avoid excessive power loss.

[0048] In summary, the present invention utilizes an ADN-based liquid space engine ignition method based on a thermal ignition method to solve the problem of high-temperature deactivation of the catalyst during the use of the space engine and the inability to ignite a large flow rate of propellant. The corrosion-resistant high-temperature incandescent material arranged inside the engine is used to ignite the ADN-based liquid propellant, thereby realizing catalytic-free combustion of the ADN-based liquid propellant. The catalyst-catalytic ignition method is no longer used, which solves the problem of high-temperature deactivation of the catalyst during engine operation. It is conducive to the green space engine to carry out high-thrust space missions, and the atomized propellant can be decomposed by the heating structure, thereby improving the ignition efficiency of the engine.

[0049] Moreover, the thermal ignition method of an ADN-based space engine provided by the present invention can also utilize a high-temperature corrosion-resistant heating structure arranged inside the engine to ignite the ADN-based liquid propellant, so that the ignition device of the entire engine no longer adopts the traditional catalytic combustion method of the catalytic bed, but uses a high-temperature corrosion-resistant electric heating rod as a direct ignition source, and directly sprays the atomized ADN-based propellant onto the high-temperature electric heating rod to achieve effective ignition of the propellant. In addition, based on the new ignition method of the thermal ignition method, the overall structure of the new space engine is designed, which includes a space engine structure in which the heating rod is arranged in the center of the engine and a space engine structure in which the heating rod is arranged in a honeycomb pattern inside the engine. Among them, if the heating rod is arranged in the center of the engine and the injectors are symmetrically arranged on both sides of the engine, the two can be coupled to realize propellant ignition and maintain stable operation of the engine; if the ceramic inside the engine is designed to be honeycomb-shaped and the ceramic wraps the heating rod, it can prevent the heating rod from contacting the metal shell of the engine to play an insulating role, and can effectively increase the contact area between the propellant and the heating structure to facilitate organized combustion. The engine injector is arranged at the head of the engine, which is conducive to spraying the spray into the honeycomb-shaped ceramic.

[0050] Regarding the thermal ignition method of the ADN-based space engine provided in the above embodiment, an embodiment of the present invention provides a thermal ignition device of an ADN-based space engine, which is applied to the control terminal of the engine. The engine includes a temperature control structure, a heating structure and a fuel structure. Figure 5 The structure diagram of a thermal ignition device of an ADN-based space engine is shown, and the device includes the following parts:

[0051] The heating control module 502 sends a temperature control instruction to the temperature control structure to control the temperature control structure to drive the heating structure to a preset temperature value;

[0052] The fuel control module 504 sends a propellant injection instruction to the fuel structure, controlling the fuel structure to inject atomized propellant toward the heating structure, so that the atomized propellant contacts the heating structure to generate a propellant gas.

[0053] In one embodiment, the thermal ignition device of the ADN-based space engine also includes an ignition module, which is used to: control the fuel structure to spray atomized propellant toward the heating structure, so that after the atomized propellant contacts the heating structure, a reducing gas decomposed from the atomized propellant is obtained; and control the combustion chamber to burn the reducing gas to generate propellant gas.

[0054] The above-mentioned data processing device provided in the embodiment of the present application utilizes an ADN-based liquid space engine ignition method based on a thermal ignition method to solve the problem of high-temperature deactivation of the catalyst during the use of the space engine and the inability to ignite a large flow rate of propellant. The corrosion-resistant high-temperature incandescent material arranged inside the engine is used to ignite the ADN-based liquid propellant, thereby realizing catalytic-free combustion of the ADN-based liquid propellant. The catalyst-catalytic ignition method is no longer used, which solves the problem of high-temperature deactivation of the catalyst during engine operation, is conducive to the green space engine to carry out high-thrust aerospace missions, and can decompose the atomized propellant through the heating structure, thereby improving the ignition efficiency of the engine.

[0055] In one embodiment, the fuel structure includes an atomizing chamber and an injector group, and the heating structure includes a honeycomb-shaped fixed structure and multiple heating rods. The heating rods are fixed by the fixed structure. When controlling the fuel structure to spray atomized propellant toward the heating structure, the fuel control module 504 is also used to: control the atomizing chamber to atomize the propellant to obtain atomized propellant, and control the injector group to spray atomized propellant toward each heating rod.

[0056] In one embodiment, the injector groups are symmetrically placed on both sides of the fuel structure. When controlling the injector groups to spray atomized propellant toward each heating rod, the fuel control module 504 is further used to control the injector groups to spray atomized propellant toward each heating rod according to the injection method corresponding to the propellant injection instruction, wherein the propellant injection instruction is determined according to a pre-set working sequence, and the injection method includes a coupled injection method.

[0057] In one embodiment, the engine further includes a combustion chamber. When performing the step of controlling the fuel structure to spray atomized propellant toward the heating structure so that the atomized propellant contacts the heating structure to generate propellant gas, the fuel control module 504 is further configured to: control the fuel structure to spray atomized propellant toward the heating structure so that the atomized propellant contacts the heating structure to obtain reducing gas decomposed from the atomized propellant; and control the combustion chamber to burn the reducing gas to generate propellant gas.

[0058] In one embodiment, when performing the step of sending a temperature control instruction to the temperature control structure and controlling the temperature control structure to drive the heating structure to a preset temperature value, the heating control module 502 is also used to: send a temperature control instruction to the temperature control structure and control the temperature control structure to adjust the heating power of the heating structure according to the temperature control instruction so that the heating structure is raised to a preset temperature value.

[0059] In one embodiment, after the step of controlling the fuel structure to spray atomized propellant toward the heating structure so that the atomized propellant contacts the heating structure to generate propellant gas, the fuel control module 504 is further used to: control the temperature control structure to reduce the heating power of the electric heating rod according to a set linear change law, so that the power of the electric heating rod is reduced to zero.

[0060] The device provided in the embodiment of the present invention has the same implementation principle and technical effects as those in the aforementioned method embodiment. For the sake of brief description, for matters not mentioned in the device embodiment, reference can be made to the corresponding content in the aforementioned method embodiment.

[0061] An embodiment of the present invention provides an electronic device. Specifically, the electronic device includes a processor and a storage device. The storage device stores a computer program, and when the computer program is executed by the processor, it executes the method described in any one of the above-mentioned embodiments.

[0062] Figure 6 A structural diagram of an electronic device provided in an embodiment of the present invention, the electronic device 100 includes: a processor 60, a memory 61, a bus 62 and a communication interface 63, wherein the processor 60, the communication interface 63 and the memory 61 are connected via the bus 62; the processor 60 is used to execute an executable module stored in the memory 61, such as a computer program.

[0063] The memory 61 may include high-speed random access memory (RAM) and may also include non-volatile memory, such as at least one disk storage. The system network element communicates with at least one other network element via at least one communication interface 63 (which may be wired or wireless), and may utilize the Internet, a wide area network, a local area network, a metropolitan area network, or the like.

[0064] The bus 62 may be an ISA bus, a PCI bus, or an EISA bus. The bus may be divided into an address bus, a data bus, a control bus, and the like. For ease of representation, Figure 6 Only one bidirectional arrow is used in the diagram, but this does not mean that there is only one bus or one type of bus.

[0065] Among them, the memory 61 is used to store programs, and the processor 60 executes the program after receiving the execution instruction. The method executed by the device for flow process definition disclosed in any embodiment of the above-mentioned embodiment of the present invention can be applied to the processor 60 or implemented by the processor 60.

[0066] The processor 60 may be an integrated circuit chip with signal processing capabilities. During implementation, the steps of the above method may be performed by hardware integrated logic circuits or software instructions within the processor 60. The processor 60 may be a general-purpose processor, including a central processing unit (CPU), a network processor (NP), etc.; it may also be a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components. It may implement or execute the methods, steps, and logic block diagrams disclosed in the embodiments of the present invention. The general-purpose processor may be a microprocessor or any conventional processor. The steps of the methods disclosed in the embodiments of the present invention may be directly executed by a hardware decoding processor or by a combination of hardware and software modules within the decoding processor. The software modules may be located in storage media well-known in the art, such as random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, registers, or the like. The storage medium is located in the memory 61 , and the processor 60 reads the information in the memory 61 and completes the steps of the above method in combination with its hardware.

[0067] The computer program product of the readable storage medium provided in the embodiment of the present invention includes a computer-readable storage medium storing program code. The instructions included in the program code can be used to execute the method described in the previous method embodiment. The specific implementation can be referred to the previous method embodiment and will not be repeated here.

[0068] If the functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, or the part that contributes to the prior art, or the part of the technical solution, can be embodied in the form of a software product. The computer software product is stored in a storage medium and includes several instructions for enabling a computer device (which can be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes various media that can store program codes, such as a USB flash drive, a mobile hard disk, a read-only memory (ROM), a random access memory (RAM), a magnetic disk, or an optical disk.

[0069] Finally, it should be noted that the above-described embodiments are only specific implementation methods of the present invention, which are used to illustrate the technical solutions of the present invention, rather than to limit them. The scope of protection of the present invention is not limited thereto. Although the present invention has been described in detail with reference to the above-described embodiments, those skilled in the art should understand that any person skilled in the art can modify or easily conceive of changes to the technical solutions described in the above-described embodiments within the technical scope disclosed by the present invention, or replace some of the technical features therein with equivalents. Such modifications, changes, or replacements do not deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be included in the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be subject to the scope of protection of the claims.

Claims

1. A method for hot ignition of an ADN-based space engine, characterized in that: The method is applied to a control terminal of an engine, wherein the engine includes a temperature control structure, a heating structure, and a fuel structure, and the method includes: Sending a temperature control instruction to the temperature control structure to control the temperature control structure to drive the heating structure to a preset temperature value; sending a propellant injection instruction to the fuel structure to control the fuel structure to inject atomized propellant toward the heating structure, so that the atomized propellant contacts the heating structure to generate a propellant gas; The fuel structure includes an atomizing chamber and an injector group, and the heating structure includes a honeycomb-shaped fixed structure and a plurality of electric heating rods, and the electric heating rods are fixed by the fixed structure; the step of controlling the fuel structure to spray the atomized propellant toward the heating structure includes: controlling the atomizing chamber to atomize the propellant to obtain the atomized propellant, and controlling the injector group to spray the atomized propellant toward each of the electric heating rods, wherein the fixed structure is a honeycomb-shaped ceramic, and the plurality of electric heating rods are embedded in the honeycomb-shaped ceramic of the fixed structure to increase the contact area between the propellant and the heating structure; In which, the injector groups are symmetrically placed on both sides of the fuel structure; the step of controlling the injector group to spray the atomized propellant toward each of the heating rods includes: controlling the injector group to spray the atomized propellant toward each of the heating rods according to the injection mode corresponding to the propellant injection instruction, wherein the propellant injection instruction is determined according to a pre-set working sequence, and the injection mode includes a coupled injection mode.

2. The method according to claim 1, characterized in that The engine also includes a combustion chamber; The step of controlling the fuel structure to spray the atomized propellant toward the heating structure so that the atomized propellant contacts the heating structure to generate the propellant gas comprises: controlling the fuel structure to spray atomized propellant toward the heating structure, so that the atomized propellant contacts the heating structure to obtain reducing gas decomposed from the atomized propellant; The combustion chamber is controlled to burn the reducing gas to generate a propellant gas.

3. The method according to claim 1, characterized in that The step of sending a temperature control instruction to the temperature control structure to control the temperature control structure to drive the heating structure to a preset temperature value includes: A temperature control instruction is sent to the temperature control structure, and the temperature control structure is controlled to adjust the heating power of the heating structure according to the temperature control instruction, so that the heating structure is raised to a preset temperature value.

4. The method according to claim 1, wherein After the step of controlling the fuel structure to spray the atomized propellant toward the heating structure so that the atomized propellant contacts the heating structure to generate a propellant gas, the method further includes: The temperature control structure is controlled to reduce the heating power of the electric heating rod according to a set linear variation rule, so that the power of the electric heating rod is reduced to zero.

5. A thermal ignition device for an ADN-based space engine, characterized in that: The device is applied to the control terminal of an engine, wherein the engine includes a temperature control structure, a heating structure, and a fuel structure. The device includes: A heating control module sends a temperature control instruction to the temperature control structure to control the temperature control structure to drive the heating structure to a preset temperature value; a fuel control module, configured to send a propellant injection instruction to the fuel structure, controlling the fuel structure to inject atomized propellant toward the heating structure, so that the atomized propellant contacts the heating structure to generate a propellant gas; The fuel structure includes an atomizing chamber and an injector group, and the heating structure includes a honeycomb-shaped fixed structure and a plurality of electric heating rods, and the electric heating rods are fixed by the fixed structure; the step of controlling the fuel structure to spray the atomized propellant toward the heating structure includes: controlling the atomizing chamber to atomize the propellant to obtain the atomized propellant, and controlling the injector group to spray the atomized propellant toward each of the electric heating rods, wherein the fixed structure is a honeycomb-shaped ceramic, and the plurality of electric heating rods are embedded in the honeycomb-shaped ceramic of the fixed structure to increase the contact area between the propellant and the heating structure; In which, the injector groups are symmetrically placed on both sides of the fuel structure; the step of controlling the injector group to spray the atomized propellant toward each of the heating rods includes: controlling the injector group to spray the atomized propellant toward each of the heating rods according to the injection mode corresponding to the propellant injection instruction, wherein the propellant injection instruction is determined according to a pre-set working sequence, and the injection mode includes a coupled injection mode.

6. The device according to claim 5, characterized in that Also includes ignition modules for: controlling the fuel structure to spray atomized propellant toward the heating structure, so that the atomized propellant contacts the heating structure to obtain reducing gas decomposed from the atomized propellant; The combustion chamber is controlled to combust the reducing gas to generate a propellant gas.

7. A server, characterized in that: The method comprises a processor and a memory, wherein the memory stores computer-executable instructions that can be executed by the processor, and the processor executes the computer-executable instructions to implement the method according to any one of claims 1 to 4.

8. A computer-readable storage medium, characterized in that The computer-readable storage medium stores computer-executable instructions. When the computer-executable instructions are called and executed by a processor, the computer-executable instructions prompt the processor to implement the method according to any one of claims 1 to 4.

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