Anhydrous hydrazine propulsion system and satellite

Abstract

This invention discloses an anhydrous hydrazine propulsion system and satellite, relating to the field of satellite propulsion control. In this system, when the system is operational, the control module controls the catalyst temperature to a preset reaction temperature via a first temperature control module. Then, it controls the flow of anhydrous hydrazine to a solenoid valve. The solenoid valve is opened and closed according to the target thrust to regulate the flow rate and volume of the anhydrous hydrazine. This allows the anhydrous hydrazine to flow into a second storage module and react with the catalyst to generate fuel gas. An acceleration module then accelerates the fuel gas before ejecting it, so that the ejected gas generates thrust to achieve the target thrust. In this design, catalyst temperature control ensures a sufficient and efficient reaction between the catalyst and anhydrous hydrazine. Controlling the opening and closing of the solenoid valve according to the target thrust meets the thrust requirements of different operating conditions. The fuel gas generated by the reaction between the catalyst and anhydrous hydrazine is essentially high-temperature, high-pressure fuel gas. After being processed by the acceleration module before being ejected, this doubly ensures sufficient thrust to flexibly adapt to various operating conditions.

Description

Technical Field

[0001] This invention relates to the field of satellite propulsion and control technology, and in particular to an anhydrous hydrazine propulsion system and a satellite. Background Technology

[0002] The propulsion system is a crucial power source for satellites. The thrust generated by the propulsion system enables orbital transfers, orbital maintenance, and attitude control. Currently, the main propulsion system used in satellites is electric propulsion, which generates thrust by ionizing propellants such as xenon, producing ions that are then ejected at high speeds. However, in practical applications, this method generates relatively little thrust and is unsuitable for missions requiring high thrust, such as rapid orbital transfers. Therefore, developing an effective propulsion system to provide the necessary thrust for satellite operation is a pressing issue that needs to be addressed. Summary of the Invention

[0003] In view of this, the present invention provides an anhydrous hydrazine propulsion system and satellite, which can ensure the generation of sufficient thrust to meet the thrust requirements under different operating conditions and is beneficial for practical applications.

[0004] To solve the above-mentioned technical problems, this application provides an anhydrous hydrazine propulsion system, including a first storage module, a solenoid valve, a second storage module, a first temperature control module, an acceleration module, and a control module;

[0005] The first storage module, the solenoid valve, the second storage module, and the acceleration module are connected in sequence. The first temperature control module is connected to the control module and the second storage module respectively. The control module is also connected to the first storage module, the solenoid valve, and the acceleration module.

[0006] The control module is used to control the temperature of the catalyst stored in the second storage module to reach the preset reaction temperature through the first temperature control module when the anhydrous hydrazine propulsion system is in operation. Then, it controls the anhydrous hydrazine stored in the first storage module as a propellant to flow to the solenoid valve. The control module controls the opening and closing of the solenoid valve according to the target thrust to adjust the flow rate and flow of the anhydrous hydrazine. This allows the anhydrous hydrazine to flow through the solenoid valve to the second storage module and react with the catalyst to generate fuel gas. The control module then controls the acceleration module to accelerate the fuel gas before ejecting it. The thrust generated by the ejected gas is the same as the target thrust.

[0007] The anhydrous hydrazine propulsion system further includes a second temperature control module that is connected to both the first storage module and the control module.

[0008] The control module is also used to control the temperature of the anhydrous hydrazine stored in the first storage module to be no less than the preset minimum storage temperature when the anhydrous hydrazine propulsion system is in standby mode, through the second temperature control module.

[0009] The anhydrous hydrazine propulsion system also includes a third temperature control module that is connected to both the acceleration module and the control module.

[0010] The control module is also used to preheat the acceleration module via the third temperature control module before the anhydrous hydrazine stored in the first storage module flows to the solenoid valve, so that the temperature of each component in the acceleration module reaches the preset start-up temperature.

[0011] Furthermore, it also includes an injection module;

[0012] The input end of the injection module is connected to the output end of the solenoid valve through a first pipe, and the injection end extends into the second storage module through an opening on the second storage module. The control end is connected to the control module and is used to inject anhydrous hydrazine input through the first pipe into the second storage module according to the injection rule corresponding to the first control signal sent by the control module, so that the anhydrous hydrazine reacts with the catalyst to generate fuel gas.

[0013] Furthermore, the first storage module includes a self-locking switch module and a storage component for storing the anhydrous hydrazine;

[0014] The input end of the self-locking switch module is connected to the liquid outlet end of the storage component, the output end is connected to the input end of the solenoid valve through the second pipe, and the control end is connected to the control module for turning on and off according to the second control signal sent by the control module; wherein, the first air pressure in the storage component is greater than the second air pressure in the second pipe.

[0015] Furthermore, the first storage module also includes a filtering module;

[0016] The input end of the filtration module is connected to the liquid outlet end of the storage component, and the output end is connected to the input end of the self-locking switch module, for filtering impurities in the anhydrous hydrazine.

[0017] Furthermore, it also includes a first pressure detection module and a second pressure detection module;

[0018] The first pressure detection module is connected to the storage component and the control module respectively, and is used to detect the first air pressure in the storage component;

[0019] The second pressure detection module is connected to the second pipeline and the control module respectively, and is used to detect the second air pressure in the second pipeline;

[0020] The control module is also used to determine whether the anhydrous hydrazine is being supplied normally based on the first gas pressure and the second gas pressure.

[0021] Furthermore, it also includes gas supply and exhaust switches connected to the control module and the storage component respectively;

[0022] The gas filling and emptying switch is used to turn on and off according to the third control signal sent by the control module, so that when it is turned on, compressed gas is injected into the storage component or the air in the storage component is emptied.

[0023] Furthermore, it also includes liquid filling and draining switches connected to the control module and the storage component respectively;

[0024] The liquid filling and draining switch is used to turn on and off according to the fourth control signal sent by the control module, so that when it is turned on, anhydrous hydrazine for propellant replenishment is injected into the storage component or the remaining anhydrous hydrazine in the storage component is drained.

[0025] To address the aforementioned technical problems, the present invention also provides a satellite, including the anhydrous hydrazine propulsion system as described above.

[0026] This application provides an anhydrous hydrazine propulsion system and a satellite. The system includes a first storage module, a solenoid valve, a second storage module, a first temperature control module, an acceleration module, and a control module. When the anhydrous hydrazine propulsion system is in operation, the control module controls the temperature of the catalyst stored in the second storage module to reach a preset reaction temperature through the first temperature control module. Then, it controls the flow of anhydrous hydrazine, which serves as a propellant, stored in the first storage module to the solenoid valve. The control module controls the opening and closing of the solenoid valve according to the target thrust to adjust the flow rate and volume of the anhydrous hydrazine, so that the anhydrous hydrazine flows through the solenoid valve to the second storage module to react with the catalyst and generate fuel gas. Subsequently, the acceleration module is controlled to accelerate the fuel gas before it is ejected, so that the ejected gas generates thrust to achieve the required target thrust. It is evident that this scheme, by controlling the catalyst temperature, ensures a full and efficient reaction between the catalyst and anhydrous hydrazine. The opening and closing of the solenoid valve is controlled according to the target thrust to adjust the flow rate and volume of the anhydrous hydrazine. Furthermore, the control of the acceleration module ensures that the final ejected gas matches the target thrust, thus meeting the thrust requirements under different operating conditions. Moreover, the gas produced by the reaction between the catalyst and anhydrous hydrazine is essentially a high-temperature, high-pressure gas, which, after being processed by the acceleration module, is ejected, thus doubly ensuring sufficient thrust to flexibly adapt to various operating conditions and facilitate practical applications.

[0027] The above description is only an overview of the technical solution of this application. In order to better understand the technical means of this application, it can be implemented according to the contents of the specification. In order to make the above and other objects, features and advantages of this application more obvious and understandable, the following are specific embodiments of this application. Attached Figure Description

[0028] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments of this application and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0029] Figure 1 This is a schematic diagram of the structure of an anhydrous hydrazine propulsion system provided by the present invention;

[0030] Figure 2 This is a schematic diagram of another anhydrous hydrazine propulsion system provided by the present invention. Detailed Implementation

[0031] The core of this invention is to provide an anhydrous hydrazine propulsion system and satellite that can ensure sufficient thrust to meet the thrust requirements under different operating conditions and facilitate practical applications.

[0032] The technical solutions of the embodiments of this application will be clearly described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application are within the scope of protection of this application.

[0033] The terms "first," "second," etc., used in the specification and claims of this application are used to distinguish similar objects and not to describe a specific order or sequence. It should be understood that such use of data can be interchanged where appropriate so that embodiments of this application can be implemented in orders other than those illustrated or described herein, and the objects distinguished by "first," "second," etc., are generally of the same class and the number of objects is not limited; for example, a first object can be one or more. Furthermore, in the specification and claims, "and / or" indicates at least one of the connected objects, and the character " / " generally indicates that the preceding and following objects are in an "or" relationship.

[0034] Please refer to Figure 1 , Figure 1 This is a schematic diagram of the structure of an anhydrous hydrazine propulsion system provided by the present invention.

[0035] The anhydrous hydrazine propulsion system includes a first storage module 1, a solenoid valve 2, a second storage module 3, a first temperature control module 5, an acceleration module 4, and a control module 6.

[0036] The first storage module 1, the solenoid valve 2, the second storage module 3 and the acceleration module 4 are connected in sequence. The first temperature control module 5 is connected to the control module 6 and the second storage module 3 respectively. The control module 6 is also connected to the first storage module 1, the solenoid valve 2 and the acceleration module 4.

[0037] When the anhydrous hydrazine propulsion system is in operation, the control module 6 controls the temperature of the catalyst stored in the second storage module 3 to reach the preset reaction temperature through the first temperature control module 5. Then, it controls the anhydrous hydrazine stored in the first storage module 1 as a propellant to flow to the solenoid valve 2. The control module 6 controls the opening and closing of the solenoid valve 2 according to the target thrust to adjust the flow rate and flow of the anhydrous hydrazine. This allows the anhydrous hydrazine to flow through the solenoid valve 2 to the second storage module 3 to react with the catalyst and generate fuel gas. The control module 6 then controls the acceleration module 4 to accelerate the fuel gas before it is ejected. The thrust generated by the ejected gas is the same as the target thrust.

[0038] In this embodiment, it should first be noted that the second storage module 3 can be a storage component 12 storing catalyst, such as a catalyst bed; the first temperature control module 5 can include a first temperature acquisition module and a first heater. The first temperature acquisition module is used to acquire the temperature of the catalyst and feed it back to the control module 6. The first heater is used to heat the second storage module 3 according to the fifth control signal sent by the control module 6, so as to raise the temperature of the catalyst stored therein. Thus, when the system is in working state and waiting to generate the required thrust, the temperature of the catalyst is first raised to the preset reaction temperature, and then the solenoid valve 2 is controlled to open, thereby ensuring that the catalyst has good activity, which is conducive to ensuring that the catalyst and anhydrous hydrazine can react fully, rapidly and efficiently, and ensuring the reaction effect. It should be noted that the reaction between anhydrous hydrazine and the catalyst is a strongly exothermic reaction, which can generate high-temperature and high-pressure gas. More specifically, the preset reaction temperature can be 160 degrees Celsius, which is not particularly limited here, and can be set according to the temperature range for maintaining the optimal activity of the catalyst; the first temperature acquisition module can be a temperature sensor or a temperature detection circuit designed based on a thermistor, which is not particularly limited here.

[0039] Specifically, the target thrust is determined based on the satellite's thrust requirements under current operating conditions. The opening and closing of solenoid valve 2 is then controlled according to the target thrust to regulate the flow rate and volume of anhydrous hydrazine. More specifically, the control of solenoid valve 2 includes controlling its opening and closing frequency, as well as the valve opening degree, thereby reliably regulating the flow rate and volume of anhydrous hydrazine. This ensures that the flow of anhydrous hydrazine meets the target thrust requirements while also guaranteeing the safety and reliability of the entire system. Anhydrous hydrazine flows through solenoid valve 2 to the second storage module 3, where it reacts with the high-temperature catalyst. This reaction produces high-temperature, high-pressure gas, which then enters the acceleration module 4.

[0040] Furthermore, the acceleration module 4 may include a thrust chamber and a nozzle. After the high-temperature, high-pressure gas enters the thrust chamber, it expands within it. The control module 6 controls the nozzle according to the target thrust to accelerate the gas ejection (specifically, it can control the flow rate of the gas entering the nozzle, or adjust the size of the opening at the nozzle throat for gas passage, i.e., adjust the size of the narrowest part of the opening in a convergent-then-divergent nozzle). The ejected gas will generate a reaction force equal in magnitude and opposite in direction on the satellite. This reaction force is the thrust that propels the satellite for orbital control, and this thrust is the same as the target thrust. In addition, the direction of the nozzle orifice can be adjusted to change the direction of the generated thrust; no specific limitations are made here.

[0041] It is understandable that there are no special restrictions on the specific placement of the modules in the satellite. As long as the above structural settings are met, adjustments can be made flexibly according to actual needs. Figure 1 To limit the focus of the image display and to avoid confusing the wiring, the control modules are illustrated with circles and attached labels.

[0042] In summary, this application provides an anhydrous hydrazine propulsion system. By controlling the catalyst temperature, it ensures that the catalyst and anhydrous hydrazine can react fully and efficiently. The opening degree of the solenoid valve 2 is controlled according to the target thrust to adjust the flow rate and volume of the anhydrous hydrazine. Furthermore, the control of the acceleration module 4 ensures that the final ejected gas is the same as the target thrust, which helps to meet the thrust requirements under different operating conditions. Moreover, the gas produced by the reaction between the catalyst and anhydrous hydrazine is essentially a high-temperature and high-pressure gas. After being processed by the acceleration module 4, it is ejected, which can doubly ensure that sufficient thrust is generated to flexibly adapt to various operating conditions and facilitate practical applications.

[0043] Based on the above embodiments:

[0044] In some embodiments, a second temperature control module is also included, which is connected to the first storage module 1 and the control module 6 respectively;

[0045] The control module 6 is also used to control the temperature of the anhydrous hydrazine stored in the first storage module 1 to be no less than the preset minimum storage temperature when the anhydrous hydrazine propulsion system is in standby mode, through the second temperature control module.

[0046] In this embodiment, considering that in space, especially in certain low-temperature environments during satellite operation, the propellant may freeze due to reaching its freezing point, in order to ensure the long-term on-orbit operation of the anhydrous hydrazine propulsion system, the above method can ensure that even when the system is in standby mode, the anhydrous hydrazine will not freeze and affect subsequent normal operation.

[0047] Specifically, the second temperature control module here may include a second temperature acquisition module and a second heater. The second temperature acquisition module is used to acquire the temperature of the stored anhydrous hydrazine and feed it back to the control module 6. The acquisition method can be real-time acquisition or acquisition according to a preset sampling period, which is not particularly limited here. The second heater is used to heat the stored anhydrous hydrazine according to the sixth control signal sent by the control module 6 to ensure that the temperature of the stored anhydrous hydrazine is not lower than the preset minimum storage temperature, thereby facilitating the normal flow of anhydrous hydrazine and the normal start-up and operation of the entire system when it is required to work. In addition, the preset minimum storage temperature here includes, but is not limited to, 5 degrees Celsius, and can be determined according to the freezing point of anhydrous hydrazine.

[0048] Please refer to Figure 2 , Figure 2 This is a schematic diagram of another anhydrous hydrazine propulsion system provided by the present invention. In this diagram, the control module is shown in circles with reference to the attached figures to avoid confusion. The connection between the second storage module 3, the first temperature control module 5, and the acceleration module 4 is temporarily omitted.

[0049] In some embodiments, the injection module 7 is also included;

[0050] The input end of the injection module 7 is connected to the output end of the solenoid valve 2 through the first pipe. The injection end extends into the second storage module 3 through the opening on the second storage module 3. The control end is connected to the control module 6 and is used to inject anhydrous hydrazine input through the first pipe into the second storage module 3 according to the injection rule corresponding to the first control signal sent by the control module 6, so that the anhydrous hydrazine reacts with the catalyst to generate gas.

[0051] In this embodiment, the injection module 7 can be an injector. The design of the injection module 7 allows anhydrous hydrazine to be injected into the second storage module 3 according to a preset injection rule. Specifically, the injection rule includes, but is not limited to, uniform injection, so that the anhydrous hydrazine and the catalyst can be fully mixed and contacted, which is conducive to the reaction between the two and improves the reaction efficiency.

[0052] In some embodiments, a third temperature control module is also included, which is connected to the acceleration module 4 and the control module 6 respectively.

[0053] The control module 6 is also used to preheat the acceleration module 4 via the third temperature control module before the anhydrous hydrazine stored in the first storage module 1 flows to the solenoid valve 2, so that the temperature of each device in the acceleration module 4 reaches the preset start-up temperature.

[0054] In this embodiment, considering that the gas produced by the reaction is a high-temperature and high-pressure gas, in order to avoid damage to the components in the acceleration module 4 due to excessive temperature difference at the beginning of operation, the acceleration module 4 can be preheated by the third temperature control module. Specifically, the preset start-up temperature can be set according to the actual application requirements. The components in the acceleration module 4 that participate in the preheating can include the thrust chamber and the nozzle.

[0055] More specifically, the third temperature control module may include a third temperature acquisition module and a third heater. The third temperature acquisition module is used to acquire the temperature of each device in the acceleration module 4 and feed it back to the control module 6. The third heater is used to heat each device according to the seventh control signal sent by the control module 6 to achieve preheating and avoid damage to the device due to excessive temperature difference.

[0056] In some embodiments, the first storage module 1 includes a self-locking switch module 11 and a storage component 12 for storing anhydrous hydrazine;

[0057] The input end of the self-locking switch module 11 is connected to the liquid outlet end of the storage component 12, the output end is connected to the input end of the solenoid valve 2 through the second pipe, and the control end is connected to the control module 6 for turning on and off according to the second control signal sent by the control module 6; wherein, the first air pressure in the storage component 12 is greater than the second air pressure in the second pipe.

[0058] In this embodiment, the self-locking switch module 11 can prevent anhydrous hydrazine from flowing out when it is turned off, thus preventing anhydrous hydrazine from accidentally flowing into the pipeline and damaging the components in each module of the system. Since the first gas pressure in the storage component 12 is greater than the second gas pressure in the second pipeline, the pressure difference allows the anhydrous hydrazine to flow smoothly through the second pipeline to the solenoid valve 2 when the self-locking switch module 11 is turned on. More specifically, the self-locking switch module 11 can be a self-locking valve, and the control module 6 can more precisely control the flow rate and volume of anhydrous hydrazine by controlling the opening degree of the self-locking valve and the frequency of opening and closing.

[0059] It should also be noted that the first and second pipes can be preheated to ensure that anhydrous hydrazine flows smoothly through the pipes at the initial stage of system operation, without affecting the flow due to the coldness of the pipes. Additionally, the storage component 12 here can be a storage tank.

[0060] In some embodiments, the first storage module 1 further includes a filter module 13;

[0061] The input end of the filter module 13 is connected to the liquid outlet end of the storage component 12, and the output end is connected to the input end of the self-locking switch module 11, for filtering impurities in anhydrous hydrazine.

[0062] In this embodiment, considering that anhydrous hydrazine may contain some impurities, a filter module 13 is provided to filter out these impurities, ensuring that only pure anhydrous hydrazine is output to the self-locking switch module 11. This prevents impurities from damaging the self-locking switch module 11 and other precision components such as the solenoid valve 2, thus affecting control accuracy. More specifically, the filter module 13 can be a filter.

[0063] In some embodiments, the system further includes a first pressure detection module and a second pressure detection module;

[0064] The first pressure detection module is connected to the storage component 12 and the control module 6 respectively, and is used to detect the first air pressure in the storage component 12.

[0065] The second pressure detection module is connected to the second pipeline and the control module 6 respectively, and is used to detect the second air pressure in the second pipeline.

[0066] Control module 6 is also used to determine whether anhydrous hydrazine is being supplied normally based on the first and second gas pressures.

[0067] In this embodiment, the first pressure detection module can be a first pressure sensor, and the second pressure detection module can be a second pressure sensor. The anhydrous hydrazine is supplied normally based on the first and second air pressures. For example, when the first air pressure is within the first preset allowable fluctuation range and the second air pressure is within the second preset allowable fluctuation range, it is determined that the anhydrous hydrazine is supplied normally. Otherwise, there may be abnormal situations such as leakage or insufficient pressure difference that prevents the anhydrous hydrazine from flowing smoothly.

[0068] As can be seen, the above settings facilitate reliable pressure monitoring, enabling timely detection of pressure runaway and preventing damage to pipes or components in various modules, thus benefiting practical applications.

[0069] In some embodiments, a gas supply / discharge switch is also included, which is connected to the control module 6 and the storage component 12 respectively.

[0070] The gas filling and emptying switch is used to turn on and off according to the third control signal sent by the control module 6, so that when it is turned on, compressed gas is injected into the storage component 12 or the air in the storage component 12 is emptied.

[0071] In this embodiment, the gas filling and venting switch allows for sealing of the storage component 12 when closed, ensuring its internal pressure and preventing gas leakage. When open, it allows compressed gas to be injected into the storage component 12 to raise its internal pressure to a preset value. Alternatively, during satellite assembly, maintenance, or repair, it can vent the air from the storage component 12 to ensure safe operation. Specifically, the gas filling and venting switch can be a gas filling and venting valve.

[0072] In some embodiments, a liquid filling / draining switch is also included, which is connected to the control module 6 and the storage component 12 respectively;

[0073] The liquid filler / drain switch is used to turn on and off according to the fourth control signal sent by the control module 6, so that when turned on, anhydrous hydrazine for propellant replenishment is injected into the storage unit 12 or the remaining anhydrous hydrazine in the storage unit 12 is emptied.

[0074] In this embodiment, the liquid filling and draining switch can be turned on when the remaining anhydrous hydrazine is insufficient and needs to be replenished, so that new anhydrous hydrazine is injected into the storage component 12, and turned off after replenishment is completed; or, during satellite assembly, maintenance, repair, etc., the remaining anhydrous hydrazine in the storage component 12 can be drained into the corresponding storage container by turning on the liquid filling and draining switch, and turned off after the draining is completed.

[0075] The present invention also provides a satellite comprising the anhydrous hydrazine propulsion system as described above.

[0076] For a description of the satellite provided in this application, please refer to the above-described embodiments of the anhydrous hydrazine propulsion system; further details will not be repeated here.

[0077] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since it corresponds to the method disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to in the method section. Relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus 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 apparatus. Without further limitations, an element defined by the phrase "comprising one" does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0078] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A propulsion system using anhydrous hydrazine, characterized in that, It includes a first storage module, a solenoid valve, a second storage module, a first temperature control module, an acceleration module, and a control module; The first storage module, the solenoid valve, the second storage module, and the acceleration module are connected in sequence. The first temperature control module is connected to the control module and the second storage module respectively. The control module is also connected to the first storage module, the solenoid valve, and the acceleration module. The control module is used to control the temperature of the catalyst stored in the second storage module to reach the preset reaction temperature through the first temperature control module when the anhydrous hydrazine propulsion system is in operation. Then, it controls the anhydrous hydrazine stored in the first storage module as a propellant to flow to the solenoid valve. The control module controls the opening and closing of the solenoid valve according to the target thrust to adjust the flow rate and flow of the anhydrous hydrazine. This allows the anhydrous hydrazine to flow through the solenoid valve to the second storage module and react with the catalyst to generate fuel gas. The control module then controls the acceleration module to accelerate the fuel gas before ejecting it. The thrust generated by the ejected gas is the same as the target thrust. The anhydrous hydrazine propulsion system further includes a second temperature control module that is connected to both the first storage module and the control module. The control module is also used to control the temperature of the anhydrous hydrazine stored in the first storage module to be no less than the preset minimum storage temperature when the anhydrous hydrazine propulsion system is in standby mode, through the second temperature control module. The anhydrous hydrazine propulsion system also includes a third temperature control module that is connected to both the acceleration module and the control module. The control module is also used to preheat the acceleration module via the third temperature control module before the anhydrous hydrazine stored in the first storage module flows to the solenoid valve, so that the temperature of each component in the acceleration module reaches the preset start-up temperature.

2. The anhydrous hydrazine propulsion system as described in claim 1, characterized in that, It also includes an injection module; The input end of the injection module is connected to the output end of the solenoid valve through a first pipe, and the injection end extends into the second storage module through an opening on the second storage module. The control end is connected to the control module and is used to inject anhydrous hydrazine input through the first pipe into the second storage module according to the injection rule corresponding to the first control signal sent by the control module, so that the anhydrous hydrazine reacts with the catalyst to generate fuel gas.

3. The anhydrous hydrazine propulsion system as described in claim 1 or 2, characterized in that, The first storage module includes a self-locking switch module and a storage component for storing the anhydrous hydrazine; The input end of the self-locking switch module is connected to the liquid outlet end of the storage component, the output end is connected to the input end of the solenoid valve through the second pipe, and the control end is connected to the control module for turning on and off according to the second control signal sent by the control module; wherein, the first air pressure in the storage component is greater than the second air pressure in the second pipe.

4. The anhydrous hydrazine propulsion system as described in claim 3, characterized in that, The first storage module also includes a filtering module; The input end of the filtration module is connected to the liquid outlet end of the storage component, and the output end is connected to the input end of the self-locking switch module, for filtering impurities in the anhydrous hydrazine.

5. The anhydrous hydrazine propulsion system as described in claim 3, characterized in that, It also includes a first pressure detection module and a second pressure detection module; The first pressure detection module is connected to the storage component and the control module respectively, and is used to detect the first air pressure in the storage component; The second pressure detection module is connected to the second pipeline and the control module respectively, and is used to detect the second air pressure in the second pipeline; The control module is also used to determine whether the anhydrous hydrazine is being supplied normally based on the first gas pressure and the second gas pressure.

6. The anhydrous hydrazine propulsion system as described in claim 3, characterized in that, It also includes gas supply and exhaust switches that are connected to the control module and the storage component, respectively; The gas filling and emptying switch is used to turn on and off according to the third control signal sent by the control module, so that when it is turned on, compressed gas is injected into the storage component or the air in the storage component is emptied.

7. The anhydrous hydrazine propulsion system as described in claim 3, characterized in that, It also includes liquid filling and draining switches that are connected to the control module and the storage component, respectively; The liquid filling and draining switch is used to turn on and off according to the fourth control signal sent by the control module, so that when it is turned on, anhydrous hydrazine for propellant replenishment is injected into the storage component or the remaining anhydrous hydrazine in the storage component is drained.

8. A satellite, characterized in that, Including the anhydrous hydrazine propulsion system as described in any one of claims 1 to 7.

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