Nitrous oxide based oxidized cold composite high maneuverability star-burst propulsion system

Abstract

The application belongs to the technical field of spacecraft propulsion, and specifically discloses a nitrogen monoxide-based cold composite high-mobility honeycomb star propulsion system, which comprises at least one nitrogen monoxide gas cylinder and at least one propane gas cylinder, the outlet of the nitrogen monoxide gas cylinder is connected to the nitrogen monoxide inlets of a single-element thruster, a cold gas thruster and a premixing cavity through a first pressure-reducing valve, the outlet of the propane gas cylinder is connected to the propane inlet of the premixing cavity through a second pressure-reducing valve, the outlets of the first pressure-reducing valve and the second pressure-reducing valve are connected to the premixing cavity, the outlet of the premixing cavity is connected to a double-element thruster, and the double-element thruster is provided with only one air inlet pipe. The application connects three kinds of thrusters in parallel through the same pressure-reducing gas source, supplies the double-element thruster with premixed single-pipe, and cooperates with nitrogen monoxide self-pressurized gas supply, so that the system structure is compact, the power consumption is low, high-precision attitude control and large-thrust orbit control are considered, and the mobility of the honeycomb star is improved.

Description

Technical Field

[0001] This invention relates to the field of spacecraft propulsion technology, and in particular to a nitrous oxide-based cold composite high-mobility bee-star propulsion system. Background Technology

[0002] Nitrous oxide (N₂O) is stored as a liquefied gas at room temperature. It decomposes into nitrogen and oxygen at approximately 800°C, releasing a significant amount of heat; the temperature of the completely decomposed gas can reach 2200°C. Utilizing this property, heating and decomposing nitrous oxide before expanding it through a nozzle can yield thrust with a high specific impulse. Therefore, nitrous oxide monocomponent thrusters offer advantages such as simple structure, non-toxicity, and environmental friendliness, making them suitable for satellite attitude control and orbit maintenance.

[0003] However, nitrous oxide has a lower storage density than conventional hydrazine fuel (0.62 kg / L vs 1.1 kg / L), and its decomposition temperature is much higher than that of hydrazine (2200℃ vs 800℃), requiring extremely high temperature resistance from the catalyst, which can easily lead to rapid catalyst deactivation. Simultaneously, its high preheating temperature and high power consumption severely restrict its engineering application. Currently, domestic institutions such as Beijing University of Aeronautics and Astronautics, Northwestern Polytechnical University, and Tsinghua University have conducted relevant ground-based experimental research. A Swedish company achieved the first in-orbit flight of a nitrous oxide monocomponent thruster around 2015, and the Shanghai Aerospace Control Technology Research Institute in China achieved the first flight verification of a 0.2N nitrous oxide monocomponent thruster in May 2024.

[0004] Beestars are miniaturized spacecraft weighing between 5 kg and 20 kg, possessing velocity increments exceeding 100 m / s and strong maneuverability, and typically equipped with multiple chemical and cold gas propulsion systems. Constrained by strict size and weight limitations, the propulsion system of a beestar must achieve high miniaturization and low power consumption, while simultaneously meeting significant thrust and total impulse requirements.

[0005] In existing propulsion schemes, conventional hydrazine monopropellant thrusters require pressurization structures and struggle to achieve precise low-thrust control. Furthermore, hydrazine fuel is toxic and expensive. While liquid ammonia-cooled propulsion offers self-pressurization and precise thrust control, its high heat of vaporization, high heating power consumption, and low specific impulse make it unsuitable for high-speed incremental orbit control missions. Nitrogen-cooled propulsion, while requiring no heating and consuming little power, suffers from low specific impulse and storage density, similarly unsuitable for the high-maneuverability requirements of the Beacon. Green liquid propellants, such as ADN and HAN-based propellants, are non-toxic, but still require pressurization structures and face similar challenges in low-thrust output control as hydrazine monopropellant thrusters.

[0006] In summary, existing bee-planet propulsion systems have significant shortcomings in terms of miniaturization, low power consumption, large speed increments, high-precision attitude control, and low cost. There is an urgent need for a new propulsion system configuration to systematically solve these problems. Summary of the Invention

[0007] The purpose of this invention is to provide a nitrous oxide-based cold composite high-mobility bee star propulsion system to solve the above-mentioned technical problems existing in the prior art.

[0008] To achieve the above objectives, the present invention provides the following solution: a nitrous oxide-based cold composite high-mobility bee-planet propulsion system, comprising: at least one nitrous oxide cylinder and at least one propane cylinder; a pressure reduction and premixing module, comprising a first pressure reducing valve, a second pressure reducing valve, and a premixing chamber, wherein the outlet of the nitrous oxide cylinder is connected to the first pressure reducing valve, the outlet of the propane cylinder is connected to the second pressure reducing valve, and the outlets of the first and second pressure reducing valves are respectively connected to the premixing chamber; at least one single-component thruster, the air supply port of which is connected to the outlet of the first pressure reducing valve; at least one cold gas thruster, the air supply port of which is connected to the outlet of the first pressure reducing valve; and at least one dual-component thruster, the air inlet of which is connected to the outlet of the premixing chamber.

[0009] Optionally, the bicomponent thruster is provided with only a single intake pipe. The premixed gas from the premixing chamber outlet passes through the backfire prevention valve and the high-frequency response solenoid valve of the bicomponent thruster and then enters the combustion chamber of the bicomponent thruster through the single intake pipe.

[0010] Optionally, the number of nitrous oxide cylinders is four, and the four nitrous oxide cylinders are distributed and installed on the four long sides of the bee star. Each nitrous oxide cylinder is provided with a first shut-off valve on its outlet branch pipe, and the branch pipes are connected to the first filling valve after being combined.

[0011] Optionally, the nitrous oxide cylinder is made of lightweight, high-strength composite material and serves as a propellant storage and main load-bearing component of the satellite.

[0012] Optionally, the first pressure reducing valve is connected to a first buffer chamber, which is used to fully vaporize liquefied nitrous oxide after pressure reduction. The outlet of the first buffer chamber is connected to the nitrous oxide inlet of the single-component thruster, the cold gas thruster, and the premixing chamber, respectively.

[0013] Optionally, the nitrous oxide inlet pipe of the premixing chamber is provided with a first throttle and a first flow control valve, and the propane inlet pipe of the premixing chamber is provided with a second throttle and a second flow control valve. The ratio of the throttle orifice area of ​​the first throttle and the second throttle is equal to the mass flow rate ratio of nitrous oxide to propane, which is 8:1.

[0014] Optionally, the first flow control valve and the second flow control valve, together with the first pressure sensor, the second pressure sensor, and the third pressure sensor disposed on the premixing chamber, respectively form a closed-loop flow control system. The control unit adjusts the opening of the first flow control valve and the second flow control valve in real time according to the pressure signals fed back by the first pressure sensor, the second pressure sensor, and the third pressure sensor through a PID control algorithm to maintain the mixing ratio of nitrous oxide and propane within a set range.

[0015] Optionally, the single-component thruster includes a heater, a high-frequency response solenoid valve, a low-temperature decomposition catalyst bed, and a thruster body. The heater is used to preheat the catalyst bed to 300°C to 400°C, and the catalyst bed is filled with ZSM-5 molecular sieve supported low-temperature decomposition catalyst.

[0016] Optionally, the heater adopts an embedded heating element or an externally wrapped armored heating wire structure. During normal operation, the heater adopts an intermittent working mode and only performs supplementary heating when the catalyst bed temperature is lower than a set threshold.

[0017] Optionally, the premixing chamber is equipped with a safety valve and a backfire prevention valve. The safety valve is used to prevent abnormal pressure rise in the premixing chamber, and the backfire prevention valve is installed on the pipeline between the premixing chamber and the bicomponent thruster to prevent high-temperature combustion gas from the combustion chamber of the bicomponent thruster from flowing back into the premixing chamber.

[0018] Optionally, the number of the bi-component thrusters is four, and the combustion chamber head of the bi-component thrusters is equipped with spark plugs. The ignition power supply converts 12V DC voltage into 5000V high-frequency AC pulses, with a single pulse energy of 20mJ to 50mJ. Ignition is achieved by breaking down the gas through the spark plugs.

[0019] Optionally, the ignition power supply is a dual-channel micro ignition power supply module, with each channel simultaneously igniting two bi-component thrusters on the same side.

[0020] Optionally, the number of the cold air thrusters is four, and the four cold air thrusters are arranged in an X-shaped layout in the central rolling direction of the star. Each of the cold air thrusters is provided with an independent high-frequency response solenoid valve on its air supply pipeline.

[0021] Optionally, the number of the single-component thrusters is four, and the four single-component thrusters are arranged in the ±X direction of the star to realize pitch, yaw and X-direction position adjustment.

[0022] Optionally, a first filter is provided on the outlet pipe of the nitrous oxide cylinder to remove particulate impurities entrained in the propellant; a second filter is provided on the outlet pipe of the propane cylinder to remove particulate impurities entrained in the propane.

[0023] Optionally, the nitrous oxide cylinder is equipped with a gas-liquid separation device to increase the proportion of extracted gas.

[0024] Optionally, the number of the bicomponent thrusters is four, and the four bicomponent thrusters are used to achieve high-thrust orbit control.

[0025] Optionally, the outlet pipeline of the propane cylinder is provided with a second filling valve, a second filter, and a second shut-off valve in sequence, and the outlet of the propane cylinder is connected to the second pressure reducing valve.

[0026] Compared with the prior art, the present invention discloses at least the following beneficial effects: This invention constructs a composite propulsion architecture using nitrous oxide and propane as working fluids, and connects a monocomponent thruster, a cold gas thruster, and a premixed bicomponent thruster in parallel under the same decompression source. This allows the system to selectively output cold gas micro-impulse, monocomponent medium specific impulse, and bicomponent high thrust based on the same working fluid source, thus achieving both high-precision attitude control and high-maneuverability orbit control requirements within a single propulsion system. Specifically, the nitrous oxide cylinder directly supplies gas using its self-pressurization characteristics, and a stable vaporization supply is achieved with a pressure reducing valve and a buffer chamber, eliminating the need for external pressurization and complex phase change control structures, significantly reducing system size and power consumption. At the same time, nitrous oxide serves as both cold gas and monocomponent propulsion working fluid, and is also mixed with propane in the premixing chamber at a fixed throttling area ratio before being supplied to the bicomponent thruster via a single pipeline. This eliminates the need for separate supply channels for oxidizer and fuel in the bicomponent thruster, greatly simplifying the propellant delivery pipeline and thruster head structure, and meeting the stringent requirements of the Bee Planet propulsion system for high miniaturization. In addition, the distributed installation of nitrous oxide cylinders along the long side of the satellite and their function as main load-bearing components further saves structural mass and installation space. This enables the entire propulsion system to achieve full-condition coverage from extremely precise attitude adjustment to high-speed incremental orbital maneuvers under limited weight and volume constraints, effectively improving the satellite's mission adaptability and maneuverability. Attached Figure Description

[0027] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0028] Figure 1A schematic diagram of the structural connection of the nitrous oxide-based cold composite high-mobility bee star propulsion system provided by the present invention; Figure 2 This is a schematic diagram of the integrated installation of the nitrous oxide cylinder and the honeycomb structure in this invention; Figure 3 A schematic diagram illustrating the working principle of the nitrous oxide-based cold composite high-mobility bee-planet propulsion system provided by this invention; Reference numerals in the attached diagram: 1. Nitrous oxide cylinder; 2. First filling valve; 3. First filter; 4. First shut-off valve; 5. First pressure reducing valve; 6. First buffer chamber; 7. First pressure sensor; 8. First flow control valve; 9. Safety valve; 10. Premixing chamber; 11. Propane cylinder; 12. Second filling valve; 13. Second filter; 14. Second shut-off valve; 15. Second pressure reducing valve; 16. Second buffer chamber; 17. Second pressure sensor; 18. Second flow control valve; 19. Third pressure sensor; 20. Backfire preventer; 21. Two-component thruster; 22. Spark plug; 23. Ignition power supply; 24. Cold air thruster; 25. Throttling device; 26. High-frequency response solenoid valve; 27. Single-component thruster. Detailed Implementation

[0029] 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 some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0030] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0031] Reference Figures 1 to 3 As shown, this embodiment provides a nitrous oxide-based cold composite high-mobility bee star propulsion system, comprising:

[0032] Reference Figures 1 to 3 As shown, this embodiment provides a nitrous oxide-based cold composite high-maneuverability satellite propulsion system, including a propellant storage device, a decompression and premixing module, a single-component thruster group, a cold gas thruster group, a dual-component thruster group, and an ignition power supply. The system has a total of 12 thrusters, including 4 single-component thrusters 27, 4 cold gas thrusters 24, and 4 dual-component thrusters 21, achieving comprehensive coverage of orbit control and attitude control. Figure 1 The connection relationships of each component and the flow path of the working fluid are shown. Figure 2 This diagram illustrates an integrated propulsion structure design where nitrous oxide cylinders are distributed along the four long sides of a bee-shaped propulsion system, serving as the main load-bearing structure. Figure 3 This is a schematic diagram of the system's working principle.

[0033] like Figure 1 As shown, the propellant storage device consists of four nitrous oxide cylinders 1 and one propane cylinder 11, distributed and installed on the honeycomb structure. The four nitrous oxide cylinders 1 are respectively installed on the four long sides of the honeycomb structure. The cylinders are made of lightweight, high-strength composite materials, serving as both propellant storage and main load-bearing structures, achieving an integrated design of propulsion and structure. Nitrous oxide is stored in the cylinders as liquefied gas at room temperature. Utilizing its self-pressurization characteristics, a stable propellant supply can be achieved without external pressurizing gas. The four nitrous oxide cylinders 1 are connected in parallel, and each nitrous oxide cylinder 1 has a first shut-off valve 4 on its outlet branch pipe for independent isolation and management of individual cylinders. All branch pipes are connected to a first filling valve 2, which is located on the main pipeline upstream of the first filter 3. During filling, the propellant enters each cylinder through the first filling valve 2. During operation, the propellant flows out of each cylinder and, after being collected, passes through the first filter 3 for filtration to remove any particulate impurities that may be entrained in the propellant.

[0034] Based on the above embodiments, a gas-liquid separation device is further provided inside the nitrous oxide cylinder 1 to increase the proportion of extracted gas. The installation position and fixing method of each nitrous oxide cylinder 1 are optimized according to the structural dynamics requirements of the satellite, so that the cylinder has sufficient safety margin when bearing the mechanical load of the launch phase and the attitude and orbit control maneuver load of the flight phase.

[0035] Furthermore, the working fluid, after being expelled from the gas cylinder nozzle under its own vaporization pressure, enters the depressurization and premixing module. The nitrous oxide pipeline is depressurized to a set value (initially 0.5 MPa) through the first depressurization valve 5. The first depressurization valve 5 is connected to the first buffer chamber 6. After depressurization, the liquefied nitrous oxide is fully vaporized in the first buffer chamber 6 to ensure the stability of subsequent flow control and combustion reaction.

[0036] Furthermore, a first pressure sensor 7 is installed on the outlet pipeline of the first pressure reducing valve 5 to monitor the pressure of nitrous oxide gas after pressure reduction in real time and feed the pressure signal back to the system control unit to monitor the working status of the first pressure reducing valve 5 and provide an alarm for any abnormalities.

[0037] Furthermore, the outlet of the first buffer chamber 6 is divided into multiple paths: one path is connected to each cold air thruster 24 and each unit thruster 27 via a high-frequency response solenoid valve 26; the other path is connected to the nitrous oxide inlet of the premixing chamber 10 via a high-frequency response solenoid valve 26 and the first throttle 25.

[0038] Based on the above embodiments, the outlet pipeline of the propane cylinder 11 is further equipped with a second filling valve 12, a second filter 13, and a second shut-off valve 14 in sequence. Propane, under its own vaporization pressure, is squeezed out of the cylinder opening and then depressurized to the same pressure level (initially 0.5 MPa) by a second pressure reducing valve 15. The second pressure reducing valve 15 is connected to a second buffer chamber 16, and a second pressure sensor 17 is installed on the outlet pipeline of the second pressure reducing valve 15 to monitor the pressure state of the propane after pressure reduction. The outlet of the second buffer chamber 16 is connected to the propane inlet of the premixing chamber 10 via a high-frequency response solenoid valve 26 and a second throttle valve 25.

[0039] Based on the above embodiments, the nitrous oxide inlet pipe of the premixing chamber 10 is further provided with a first throttle 25 and a first flow control valve 8, and the propane inlet pipe of the premixing chamber 10 is provided with a second throttle 25 and a second flow control valve 18. The ratio of the throttling orifice area of ​​the first throttle 25 and the second throttle 25 is equal to the mass flow rate ratio of nitrous oxide to propane, which is 8:1. The throttle 25 can basically ensure that the two gases meet the preset mass flow rate ratio.

[0040] The first flow control valve 8 and the second flow control valve 18, together with the first pressure sensor 7, the second pressure sensor 17, and the third pressure sensor 19 disposed on the premixing chamber 10, form a closed-loop flow control system. The control unit adjusts the opening of the first flow control valve 8 and the second flow control valve 18 in real time through a PID control algorithm based on the nitrous oxide pipeline pressure signal fed back by the first pressure sensor 7, the propane pipeline pressure signal fed back by the second pressure sensor 17, and the pressure parameters in the premixing chamber 10 fed back by the third pressure sensor 19, so as to compensate for the flow deviation caused by pressure fluctuations and maintain the mixing ratio of nitrous oxide and propane within the set range (mass flow ratio 8:1).

[0041] Furthermore, the premixing chamber 10 is equipped with a safety valve 9 and a backfire prevention valve 20. The safety valve 9 is used to prevent abnormal pressure increases within the premixing chamber 10, and the backfire prevention valve 20 is located on the pipeline between the premixing chamber 10 and the bicomponent thruster 21 to prevent high-temperature combustion gases from the combustion chamber of the bicomponent thruster 21 from flowing back into the premixing chamber 10 under abnormal operating conditions. A turbulence-prone structure can also be installed within the premixing chamber 10 to promote thorough mixing of the two gases.

[0042] In one specific embodiment, the first flow control valve 8 and the second flow control valve 18 can be electrically operated regulating valves or piezoelectric micro-flow control valves. For applications requiring further reduction in system power consumption, the flow control valves can be selected based on different valve body types with varying response speeds and adjustment accuracies, depending on the system operating conditions.

[0043] In one specific embodiment, the system is equipped with four single-component thrusters 27. The single-component thrusters 27 adopt an electrothermal enhanced structure and are arranged in the ±X direction of the satellite according to the thrust vector requirements. They are responsible for the precise position adjustment of the satellite's pitch, yaw and X direction.

[0044] Based on the above embodiment, the gas supply port of the single-component thruster 27 is directly connected to the outlet of the first pressure reducing valve 5 (i.e., the first buffer chamber 6), and its on / off control is achieved through its own independent high-frequency response solenoid valve 26. The single-component thruster 27 includes a heater, a high-frequency response solenoid valve 26, a cryogenic decomposition catalyst bed, and a thruster body.

[0045] Based on the above embodiments, the heater further employs an embedded heating element or an externally wrapped armored heating wire structure to preheat the catalyst bed to 300℃~400℃. The catalyst bed is filled with a ZSM-5 molecular sieve supported low-temperature decomposition catalyst, which exhibits high catalytic decomposition activity for nitrous oxide within a temperature window of 300℃~400℃, effectively reducing the activation energy of the nitrous oxide decomposition reaction and enabling the decomposition reaction to start and be maintained at a lower temperature.

[0046] Based on the above embodiments, the working process of the monocomponent thruster 27 is further as follows: First, the heater is started to preheat the catalyst bed to the set temperature. Then, the high-frequency solenoid valve 26 is opened, and nitrous oxide gas enters the catalyst bed, where an exothermic decomposition reaction occurs under the action of the catalyst (N2O→N2+½O2+heat). The heat released by the decomposition reaction can further increase the temperature of the catalyst bed. Under the combined action of the auxiliary heating of the heater and the exothermic reaction, a high-precision pulse thrust of approximately 90 seconds specific impulse can be obtained. During normal operation, the heater adopts an intermittent working mode, supplementing heating only when the catalyst bed temperature is lower than the set threshold to reduce system power consumption. The thruster can operate in pulse mode or in short-term continuous operation. When nitrous oxide is used as a monocomponent propellant, the decomposition temperature can reach approximately 1640°C, requiring the selection of high-temperature resistant catalyst materials to ensure the catalyst's service life.

[0047] In one specific embodiment, the system is equipped with four cold gas thrusters 24. These four cold gas thrusters 24 are high-frequency response cold gas thrusters, arranged in an X-shaped layout in the roll direction of the satellite's center according to thrust vector requirements. They are responsible for the precise adjustment of the satellite's roll and YZ-direction positions. The air supply ports of the cold gas thrusters 24 are also directly connected to the outlet of the first pressure reducing valve 5 (i.e., the first buffer chamber 6), and their on / off control is achieved via independent high-frequency response solenoid valves 26. Compared to the single-component thruster 27, the cold gas thrusters 24 eliminate the built-in heater and catalyst bed, resulting in a more compact structure and higher thrust control precision.

[0048] During operation, the high-frequency response solenoid valve 26 opens, and nitrous oxide gas, in a cold state, is directly expanded and accelerated through the thruster nozzle before being ejected to generate thrust. Although the specific impulse of the cold gas operating mode is lower than that of the single-component mode, it has advantages such as fast response speed, high thrust resolution, and no preheating waiting time, making it particularly suitable for applications requiring high-precision attitude control and extremely small impulse output.

[0049] In one specific embodiment, the system is equipped with four bicomponent thrusters 21, which can be flexibly arranged according to thrust vector requirements. Unlike conventional bicomponent thrusters, this bicomponent thruster 21 has only a single intake pipe, whose inlet is connected to the outlet of the premixing chamber 10. The premixed gas from the outlet of the premixing chamber 10 passes through the backfire preventer 20 and the high-frequency response solenoid valve 26 of the bicomponent thruster 21, and then enters the combustion chamber of the bicomponent thruster 21 through the single intake pipe. The single intake pipe reduces the piping layout by half to meet the requirements of the BeeStar for the extreme miniaturization of the propulsion system.

[0050] It should be noted that the dual-component thruster 21 in this embodiment adopts a premixed gas feeding method, but only a single air inlet pipe is provided instead of the two independent air inlet pipes of a conventional dual-component thruster. In terms of structure, it is similar to a premixed burner. In fact, the gas has been premixed in the premixing chamber 10 and then introduced into the thruster through a single pipe.

[0051] After being drawn from the premixing chamber 10, the premixed gas passes through the backfire prevention valve 20 and enters the intake high-frequency response solenoid valve 26 of each bicomponent thruster 21, before entering the thruster combustion chamber. A spark plug 22 is installed at the head of the combustion chamber of the bicomponent thruster 21, and the ignition of the gas mixture is controlled by the ignition power supply 23. The bicomponent thruster 21 can operate in pulse mode or continuously for extended periods. When precise position control with a very small impulse is required, it can operate directly in cold gas pulse jet mode, i.e., by opening the high-frequency response solenoid valve 26 but not activating the spark plug 22, allowing the premixed gas to be directly ejected through the nozzle to generate a very small impulse.

[0052] The mixture of nitrous oxide and propane exhibits a high energy release rate and a combustion temperature exceeding 3000℃, achieving a specific impulse performance far superior to that of the single-component operating mode. Due to the premixing of nitrous oxide and propane, rapid ignition can be achieved using spark plug 22, avoiding the need for catalysts and their associated lifespan and preheating delay issues.

[0053] The ignition power supply 23 is a dual-channel miniature ignition power supply module. Each channel simultaneously ignites two bi-component thrusters 21 on the same side, thereby reducing the number of channels and lightening the weight. Each spark plug 22 is connected to the corresponding output channel of the ignition power supply 23 via a high-voltage wire. When the ignition power supply 23 receives the ignition command from the control unit, the corresponding channel outputs a high-voltage pulse. The ignition power supply 23 converts the 12V DC voltage into a 5000V high-frequency AC pulse, which releases energy through the breakdown of the gas by the spark plug 22 to complete the ignition. Based on the combustion threshold of the nitrous oxide / propane mixture, the single pulse energy is set to 20mJ~50mJ. The ignition power supply 23 has internal short-circuit protection and overcurrent protection functions, meeting the requirements of reliability and safety while achieving miniaturization.

[0054] Reference Figure 3 The diagram illustrates the working principle of the system. The working process of the nitrous oxide-based cold composite high-mobility bee-planet propulsion system provided in this embodiment is as follows: Nitrous oxide and propane are extruded from the gas cylinder nozzle under their own vaporization pressure. Nitrous oxide is depressurized to a set value through the first pressure reducing valve 5 and vaporized in the first buffer chamber 6. Propane is depressurized to the same pressure level through the second pressure reducing valve 15. The pressure of the depressurized gas is monitored in real time by the first pressure sensor 7 and the second pressure sensor 17. The pressure signal is sent to the control unit. The control unit determines whether the current pressure state is normal based on the preset pressure value. If the pressure exceeds the set threshold, an alarm signal is issued or corresponding protective actions are performed. The nitrous oxide gas in the first buffer chamber 6 enters each cold gas thruster 24 and each unit thruster 27 under the control of their respective high-frequency solenoid valves 26. Before operation, the single-component thruster 27 is preheated to a set temperature. After nitrous oxide is introduced, it is partially decomposed into oxygen and nitrogen under the action of a low-temperature catalyst, releasing heat and thus obtaining a high specific impulse. After the high-frequency response solenoid valve 26 of the cold gas thruster 24 is opened, nitrous oxide is directly ejected through the nozzle to generate thrust. The structure is simple and does not require preheating.

[0055] The system control unit automatically selects the appropriate operating mode based on the magnitude and accuracy requirements of the thrust command, thereby achieving an optimal match between propulsion efficiency and thrust accuracy. When high-precision position control with minimal impulse is required, the cold gas operating mode is selected; when medium thrust is required for attitude control and precise orbit control, the single-component operating mode is selected; and when high-thrust main propulsion is required, the dual-component operating mode is selected.

[0056] When high-thrust orbit control is required, the high-frequency response solenoid valve 26 in parallel with the premixing pipeline is opened. The two gases enter the premixing chamber 10 from the first buffer chamber 6 and the second buffer chamber 16 through the throttle valve 25 and the flow control valves (first flow control valve 8 and second flow control valve 18) respectively, and are fully mixed. Before the mixed gas enters the premixing chamber 10, the flow control valve adjusts the gas flow rate of each pipeline in real time according to the pressure signals of each pipeline fed back by the pressure sensor and the pressure parameters in the premixing chamber 10, so as to ensure that the two gases meet a mass flow ratio of approximately 8:1. During the initial stage of system startup or the transition process when the operating conditions change, the flow control valve can adjust its opening to compensate for the flow deviation caused by pressure fluctuations, ensuring the accuracy of the mixing ratio. The high-frequency response solenoid valve 26 of the bicomponent thruster 21 is opened, and the premixed gas enters the thruster combustion chamber. The spark plug 22 is controlled by the ignition power supply 23 to ignite the mixed gas. After successful ignition, the ignition power supply 23 is turned off, and the thruster achieves self-sustaining combustion until the high-frequency response solenoid valve 26 is closed. After the high-frequency response solenoid valve 26 closes, the backfire prevention valve 20 prevents high-temperature combustion gas from entering the premixing chamber 10. Through the above-described workflow and the flexible combination and switching of the three working modes—cooled gas, single-component, and dual-component—various mission requirements such as main propulsion, attitude control, and precise small-range orbit control of the satellite can be achieved.

[0057] Based on the above embodiments, for application scenarios that require further reduction of system power consumption, an optimized heating control strategy can be adopted: preheating is performed when the single-component thruster 27 is started for the first time, and the temperature of the catalyst bed is maintained by the exothermic reaction of the decomposition reaction during subsequent pulse operation, with supplementary heating only performed when the temperature is lower than the set threshold.

[0058] It should be understood that, in practical applications, the number and volume ratio of nitrous oxide cylinder 1 and propane cylinder 11, as well as the number and layout of various types of thrusters, can be adjusted according to the specific mission requirements and platform resources of the satellite. The first pressure sensor 7, the second pressure sensor 17, and the third pressure sensor 19 can all utilize MEMS miniature pressure sensor chips to further reduce size and weight. The first flow control valve 8 and the second flow control valve 18 can be selected with different valve body types for different response speeds and adjustment accuracies according to specific flow control accuracy requirements.

[0059] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0060] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A nitrous oxide-based cold composite high-mobility starburst propulsion system, characterized in that, include: It includes at least one nitrous oxide cylinder (1) and at least one propane cylinder (11); The pressure reduction and premixing module includes a first pressure reducing valve (5), a second pressure reducing valve (15), and a premixing chamber (10). The outlet of the nitrous oxide cylinder (1) is connected to the first pressure reducing valve (5), the outlet of the propane cylinder (11) is connected to the second pressure reducing valve (15), and the outlets of the first pressure reducing valve (5) and the second pressure reducing valve (15) are respectively connected to the premixing chamber (10). At least one single-unit thruster (27) has its air supply port connected to the outlet of the first pressure reducing valve (5); At least one cold air thruster (24) has its air supply port connected to the outlet of the first pressure reducing valve (5); At least one bicomponent thruster (21) has its inlet connected to the outlet of the premix chamber (10).

2. The nitrous oxide-based cold composite high-mobility starburst propulsion system according to claim 1, characterized in that, The bicomponent thruster (21) is equipped with only a single intake pipe. The premixed gas from the outlet of the premix chamber (10) enters the combustion chamber of the bicomponent thruster (21) through the single intake pipe after passing through the anti-backfire valve (20) and the high-frequency response solenoid valve (26) of the bicomponent thruster (21).

3. The nitrous oxide-based cold composite high-mobility starburst propulsion system according to claim 1, characterized in that, The number of nitrous oxide cylinders (1) is four. The four nitrous oxide cylinders (1) are distributed and installed on the four long sides of the bee star. Each nitrous oxide cylinder (1) has a first shut-off valve (4) on its outlet branch pipe. The branch pipes are connected to the first filling valve (2) after being combined.

4. The nitrous oxide-based cold composite high-mobility starburst propulsion system according to claim 3, characterized in that, The nitrous oxide cylinder (1) is made of lightweight and high-strength composite material and is used as a propellant storage and main load-bearing component of the pyroplanet.

5. The nitrous oxide-based cold composite high-mobility starburst propulsion system according to claim 1, characterized in that, The first pressure reducing valve (5) is connected to the first buffer chamber (6), which allows the liquefied nitrous oxide to be fully vaporized after pressure reduction. The outlet of the first buffer chamber (6) is connected to the nitrous oxide inlet of the single-component thruster (27), the cold gas thruster (24), and the premixing chamber (10), respectively.

6. The nitrous oxide-based cold composite high-mobility starburst propulsion system according to claim 1 or 5, characterized in that, The nitrous oxide inlet pipe of the premixing chamber (10) is provided with a first throttle (25) and a first flow control valve (8), and the propane inlet pipe of the premixing chamber (10) is provided with a second throttle (25) and a second flow control valve (18). The ratio of the throttling orifice area of ​​the first throttle (25) and the second throttle (25) is equal to the mass flow rate ratio of nitrous oxide to propane, which is 8:

1.

7. The nitrous oxide-based cold composite high-mobility starburst propulsion system according to claim 6, characterized in that, The first flow control valve (8) and the second flow control valve (18) together with the first pressure sensor (7), the second pressure sensor (17) and the third pressure sensor (19) disposed on the premixing chamber (10) form a closed-loop flow control system. The control unit adjusts the opening of the first flow control valve (8) and the second flow control valve (18) in real time according to the pressure signals fed back by the first pressure sensor (7), the second pressure sensor (17) and the third pressure sensor (19) through the PID control algorithm, so as to maintain the mixing ratio of nitrous oxide and propane within the set range.

8. The nitrous oxide-based cold composite high-mobility starburst propulsion system according to claim 1, characterized in that, The single-component thruster (27) includes a heater, a high-frequency response solenoid valve (26), a low-temperature decomposition catalyst bed and a thruster body, wherein the catalyst bed is filled with a ZSM-5 molecular sieve supported low-temperature decomposition catalyst.

9. The nitrous oxide-based cold composite high-mobility starburst propulsion system according to claim 1 or 3, characterized in that, The number of the two-component thrusters (21) is four, and the combustion chamber head of the two-component thrusters (21) is provided with spark plugs (22).

10. The nitrous oxide-based cold composite high-mobility starburst propulsion system according to claim 1, characterized in that, The premixing chamber (10) is equipped with a safety valve (9) and a backfire prevention valve (20), and the backfire prevention valve (20) is located on the pipeline between the premixing chamber (10) and the bicomponent thruster (21).

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