Attitude control power system based on carbon dioxide phase change gas storage

Abstract

The invention discloses an attitude control power system based on carbon dioxide phase change gas storage, which belongs to the technical field of attitude control, and comprises a thruster, a phase change energy tube, a storage shunting mechanism and a control assembly. The phase change energy tube comprises a shell and an excitation assembly. A sealing cavity is formed in the shell and filled with liquid carbon dioxide. And excitation powder of the excitation assembly is arranged in the sealed cavity. The shell is provided with a sealed air outlet capable of being opened and closed. The storage and distribution mechanism comprises a storage tank and a distribution channel, and the storage tank communicates with the phase change energy pipe. The storage tank is communicated with the flow dividing channel, and the flow dividing channel is provided with an air supply branch pipe which can be opened and closed and corresponds to each thruster. According to the attitude control power system, the attitude adjustment cost can be reduced as much as possible and the system operation convenience can be improved while the rapid response and high specific impulse of attitude adjustment are ensured, so that the accurate regulation and control of the attitude of the aircraft can be realized.

Description

Technical Field

[0001] This invention belongs to the field of attitude control technology, specifically relating to an attitude control power system based on carbon dioxide phase change gas storage. Background Technology

[0002] In the field of attitude control technology, attitude adjustment methods and systems mainly include air-cooled propulsion systems, chemical propulsion systems, electric propulsion systems, and solid propulsion systems.

[0003] While a cold-air propulsion system can adjust the attitude of an aircraft, it has a low specific impulse during operation. In order to ensure the service life of the cold-air propulsion system, it usually needs to have a large gas tank, which requires a high carrying capacity of the aircraft.

[0004] Chemical propulsion systems have a complex structure. Because they rely on the rapid reaction of chemical substances to generate propellant gases, and these reactions typically require the catalytic action of a catalyst, repeated operation of the system necessitates multiple start-ups and shutdowns of the catalyst, leading to catalyst activity degradation. Furthermore, the fuels used in chemical propulsion systems are mostly toxic, requiring additional protection and handling during production, preparation, and use.

[0005] Electric propulsion systems suffer from high power consumption and low thrust, which makes it impossible to achieve rapid maneuvering of the aircraft during flight.

[0006] Solid propulsion systems are not very stable and do not have the ability to be restarted and stopped multiple times, resulting in low gas utilization.

[0007] Therefore, existing technologies struggle to simultaneously ensure rapid response and high specific impulse in attitude adjustment while minimizing the cost of attitude adjustment and improving the ease of system operation. Summary of the Invention

[0008] In view of one or more of the above-mentioned defects or improvement needs of the prior art, the present invention provides an attitude control propulsion system based on carbon dioxide phase change gas storage, which can reduce the cost of the attitude adjustment system and improve the ease of operation of the system while ensuring rapid response and high specific impulse of attitude adjustment, thereby enabling accurate control of the aircraft attitude.

[0009] To achieve the above objectives, the present invention provides an attitude control propulsion system based on carbon dioxide phase change gas storage, used to drive the motion of an aircraft to adjust its attitude, comprising: A plurality of thrusters, each of which is used to drive the aircraft to adjust its attitude; A plurality of phase change energy tubes, each of which includes a housing and an excitation assembly; The housing has a sealed chamber filled with liquid carbon dioxide. The activating agent of the activating component is disposed in the sealed chamber to activate the liquid carbon dioxide to convert into gaseous carbon dioxide. The housing has an openable and closable sealed gas outlet that communicates with the sealed chamber to discharge the gaseous carbon dioxide from the sealed chamber when the liquid carbon dioxide is converted into gaseous carbon dioxide. The storage and diversion mechanism includes a storage tank and a diversion channel. The inlet of the storage tank is connected to the sealed outlet of each phase change energy tube for receiving and storing gaseous carbon dioxide. The outlet of the storage tank is connected to the diversion channel, and each thruster is provided with an openable and closable air supply branch pipe for providing gaseous carbon dioxide to the corresponding thruster when adjusting the attitude of the aircraft. A control component is electrically connected to the ignition component and the diversion channel, respectively, and is used to control the combustion of the ignition agent and to control the opening and closing of the gas supply branch pipe.

[0010] As a further preferred embodiment of the present invention, the excitation assembly further includes an igniter and an ignition powder; The activating agent is disposed at one end of the sealed chamber away from the gas outlet, and a portion of the outer surface of the activating agent abuts against the ignition agent; The igniter passes through the housing and is electrically connected to the control component for igniting the ignition charge upon receiving an ignition signal.

[0011] As a further preferred embodiment of the present invention, the end of the housing facing away from the activating agent is provided with an opening, and a detachable sealing top cover is provided on the opening, and the air outlet is provided on the sealing top cover.

[0012] As a further preferred embodiment of the present invention, an annular baffle is provided on the side of the sealing top cover facing the sealing chamber, so as to form a circular groove and an annular groove on the inner and outer sides of the annular baffle, respectively. The air outlet is provided on the bottom surface of the circular groove, and a filter unit is provided in the circular groove of the annular baffle.

[0013] As a further preferred embodiment of the present invention, the phase change energy tube further includes an intake valve and a baffle; One end of the air intake valve is located outside the sealing top cover, and the other end of the air intake valve passes through the sealing top cover until it connects to the annular groove; the baffle is an annular baffle with several through holes, and the annular baffle is set at the opening end of the annular groove to reduce the injection impact when the liquid carbon dioxide is filled.

[0014] As a further preferred embodiment of the present invention, the storage distribution mechanism further includes a flow guide tube; The guide pipe is disposed between the outlet of the phase change energy tube and the inlet of the storage tank. The guide pipe is connected to the outlet of each phase change energy tube and to the inlet of the storage tank. It is used to receive gaseous carbon dioxide in the phase change energy tube and then transfer it to the storage tank.

[0015] As a further preferred embodiment of the present invention, the storage tank is provided with a high-pressure safety valve, which is connected to the gas outlet of the storage tank and is used to discharge the gaseous carbon dioxide when the pressure inside the storage tank is too high.

[0016] As a further preferred embodiment of the present invention, a diversion pipe is provided between the gas outlet end of the storage tank and the diversion channel, and a pressure reducing valve is provided between the diversion pipe and the gas outlet end of the storage tank to reduce the pressure of gaseous carbon dioxide flowing from the storage tank into the diversion pipe.

[0017] As a further preferred embodiment of the present invention, a low-pressure safety valve is provided on the diversion pipe, and the low-pressure safety valve is connected to the chamber inside the diversion pipe to prevent the gas supply branch pipe from failing to close due to excessive pressure of gaseous carbon dioxide in the diversion pipe.

[0018] As a further preferred embodiment of the present invention, both the storage tank and the gas supply branch pipe are equipped with gas pressure monitoring sensors, which are used to monitor the pressure of the gaseous carbon dioxide in the storage tank and the gas supply branch pipe, respectively.

[0019] In summary, the beneficial effects of the above-described technical solutions conceived by this invention compared with the prior art include: (1) The attitude control propulsion system based on carbon dioxide phase change gas storage of the present invention includes thrusters, phase change energy tubes, storage and diversion mechanisms, and control components. Each phase change energy tube includes a housing and an excitation component. A sealed chamber is provided inside the housing, and the sealed chamber is filled with liquid carbon dioxide. The excitation agent of the excitation component is placed in the sealed chamber to excite the liquid carbon dioxide to convert into gaseous carbon dioxide. The housing is provided with an openable and closable sealed outlet that communicates with the sealed chamber, so as to discharge the gaseous carbon dioxide from the sealed chamber when the liquid carbon dioxide is converted into gaseous carbon dioxide. The storage and diversion mechanism includes a storage tank and a diversion channel. The inlet end of the storage tank is connected to the sealed outlet of each phase change energy tube, so as to receive and store gaseous carbon dioxide. The outlet end of the storage tank is connected to the diversion channel, and the diversion channel is provided with an openable and closable supply branch pipe for each thruster, so as to provide gaseous carbon dioxide to the corresponding thruster when adjusting the attitude of the aircraft. This attitude control propulsion system can minimize the cost of attitude adjustment and improve the ease of system operation while ensuring rapid response and high specific impulse, thereby enabling accurate control of the aircraft's attitude.

[0020] (2) The attitude control power system based on carbon dioxide phase change gas storage of the present invention, by installing a high-pressure one-way valve on the storage tank or the pipeline between the storage tank and the distribution pipe, allows the gaseous carbon dioxide in the storage tank to be discharged in an appropriate amount when the pressure inside the storage tank is too high, thereby ensuring the operational stability of the storage tank. At the same time, by installing a low-pressure safety valve on the connecting distribution pipe, the failure of the solenoid valve on the gas supply branch pipe caused by the pressure of gaseous carbon dioxide in the distribution pipe exceeding the limit is avoided, further improving the safety and stability of the attitude control power system.

[0021] (3) The attitude control power system based on carbon dioxide phase change gas storage of the present invention has a rapid response and stable power. When the gaseous carbon dioxide pressure in the storage tank is low, it replenishes the storage tank with gaseous carbon dioxide in a timely manner by using a phase change energy tube with built-in liquid carbon dioxide, thereby ensuring that the attitude control system can always maintain a sufficient driving gas source. At the same time, by using the activator in the phase change energy tube, the liquid carbon dioxide in the phase change energy tube is rapidly converted into gaseous carbon dioxide, thereby improving the gas source replenishment efficiency of the entire attitude control power system. Combined with the use of liquid carbon dioxide as the storage gas source, the critical conditions for phase change of carbon dioxide are easier to achieve and overcome compared to other gases. This not only reduces the pressure resistance level of the phase change energy tube, but also allows a relatively small amount of activator to provide energy when all liquid carbon dioxide is converted into gaseous carbon dioxide. This improves the safety of the attitude control power system while reducing its operating cost, and has good promotion value and application prospects. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall structure of the attitude control power system based on carbon dioxide phase change gas storage in an embodiment of the present invention. Figure 2 This is a cross-sectional view of the phase change energy tube of the attitude control power system based on carbon dioxide phase change gas storage in an embodiment of the present invention; In all the accompanying drawings, the same reference numerals denote the same technical features, specifically: 1. Phase change energy tube; 2. Flow guide pipe; 3. Storage tank; 4. Pressure reducing valve; 5. Diverter pipe; 6. Thruster; 7. Control components; 8. High-pressure safety valve; 9. Low-pressure safety valve; 101. Sealed top cover; 102. One-way diaphragm valve; 103. Filter unit; 104. Partition plate; 105. Housing; 106. Liquid carbon dioxide; 107. Igniter; 108. Buffer pad; 109. Ignition charge; 110. Ignition device. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0024] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0025] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0026] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0027] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0028] Example: Please see Figures 1-2 The attitude control propulsion system based on carbon dioxide phase change gas storage in the preferred embodiment of the present invention can reduce the cost of attitude adjustment and improve the convenience of system operation while ensuring rapid response and high specific impulse of attitude adjustment, thereby enabling accurate control of the aircraft attitude.

[0029] Specifically, in a preferred embodiment of this application, the attitude control power system includes several power actuators, several phase change energy tubes 1, a storage and shunt mechanism, and a control component 7.

[0030] Several thrusters are fixedly installed on the aircraft, enabling the thruster 6 to propel the aircraft to move and adjust its attitude.

[0031] Several phase change energy tubes 1 are provided, each including a housing 105 and an excitation assembly. The housing 105 contains a sealed chamber filled with liquid carbon dioxide 106. The excitation assembly includes an activating agent 107 disposed within the sealed chamber, used to excite the liquid carbon dioxide 106 to convert into gaseous carbon dioxide, and to provide energy for the state transition during this conversion. Simultaneously, the housing 105 has an openable and closable sealed outlet communicating with the sealed chamber, used to discharge gaseous carbon dioxide from the sealed chamber during the conversion.

[0032] Furthermore, the storage and distribution mechanism includes a storage tank 3 and a distribution channel. The inlet of the storage tank 3 is connected to the sealed outlet of each phase change energy tube 1, used to receive and store gaseous carbon dioxide discharged from the sealed chamber after the phase change energy tube 1 is excited. Simultaneously, the outlet of the storage tank 3 is connected to the distribution channel, used to supply gaseous carbon dioxide to the distribution channel. Moreover, each thruster 6 in the distribution channel is equipped with an openable and closable air supply branch pipe, used to open the corresponding air supply branch pipe connected to the thruster to be operated according to the needs of aircraft attitude adjustment, allowing gaseous carbon dioxide to be discharged through the thruster 6, thereby enabling the thruster 6 to drive the aircraft in the corresponding direction, and thus flexibly adjust the aircraft's attitude.

[0033] More preferably, the control component 7 is electrically connected to the ignition component and the diversion channel, respectively, and is used to control the combustion of the ignition agent 107 and to control the opening and closing of the gas supply branch pipe.

[0034] Furthermore, such as Figure 2 As shown, in a preferred embodiment of this application, the ignition assembly further includes an igniter 110 and an ignition charge 109. The igniter charge 107 is disposed at the end of the sealed chamber opposite to the gas outlet, and a portion of the outer surface of the igniter charge 107 abuts against the ignition charge 109, so that the combustion of the ignition charge 109 can stably ignite the igniter charge 107. The igniter 110 passes through the housing 105 and is electrically connected to the control assembly 7, enabling the igniter 110 to accurately ignite the ignition charge 109 upon receiving an ignition signal. Preferably, the amount of igniter charge 107 and the filling ratio of liquid carbon dioxide 106 are adjustable to achieve on-demand adjustment of the output gas temperature, with the output gaseous carbon dioxide temperature adjustment range being 100℃~800℃.

[0035] Further preferably, in a preferred embodiment of this application, the igniter 107 is disposed at the end of the receiving chamber opposite to the gas outlet, and correspondingly, the igniter 110 is also disposed at the end of the housing 105 opposite to the gas outlet. Further preferably, a receiving hole is provided in the igniter 107, and the igniter 109 is embedded in the receiving hole, while the portion of the igniter 110 located in the receiving chamber faces the opening end of the receiving hole.

[0036] In actual use, the igniter 110 ignites the ignition powder 109 located in the receiving hole. The ignition powder 109 burns in the receiving hole and quickly ignites the inner wall of the receiving hole. Then the flame spreads along the receiving hole to the side wall of the igniter 107 facing the liquid carbon dioxide 106, and then burns rapidly from the middle and one side of the igniter 107, thus quickly generating high heat in a short time, providing sufficient energy for the vaporization of the liquid carbon dioxide 106.

[0037] More specifically, in a preferred embodiment of this application, a bracket is provided on the side of the receiving hole away from the igniter 110. The bracket is a frame structure and is inserted from the end of the receiving hole away from the igniter 110 to support the ignition powder 109.

[0038] Furthermore, in a preferred embodiment of this application, a buffer pad 108 is provided between the igniter 107 and the inner wall of the receiving chamber to reduce the force exerted by the igniter 107 on the housing 105 during combustion, thereby minimizing damage to the housing 105 caused by the combustion of the igniter 107. Preferably, the buffer pad 108 is adhered to the inner wall of the receiving chamber.

[0039] Further, in a preferred embodiment of this application, an opening is provided at the end of the housing 105 opposite to the activator 107, and a removable sealing cover is provided on the opening. Simultaneously, an outlet is provided on the sealing top cover 101, so that the activator 107 can be easily loaded into the receiving chamber through the opening. Preferably, a one-way diaphragm valve 102 is provided in the outlet, so that the gaseous carbon dioxide 106 can only flow out of the receiving chamber through the one-way diaphragm valve 102 after the rapidly vaporized gaseous carbon dioxide reaches a specified pressure. Preferably, the one-way diaphragm valve 102 has a forward opening pressure of 8 MPa and a reverse bearing pressure of 50 MPa. Preferably, the sealing cover is embedded in the opening, and a sealing assembly is provided between the sealing cover and the opening; preferably, the sealing assembly is an elastic sealing ring.

[0040] Further preferably, in the preferred embodiment of this application, an annular baffle is provided on the side of the sealing top cover 101 facing the sealing chamber, forming a circular groove and an annular groove on the inner and outer sides of the annular baffle, respectively. An air outlet is located on the bottom surface of the circular groove. Simultaneously, a filter unit 103 is provided within the circular groove. Preferably, the filter unit 103 is embedded in the circular groove, forming a blockage of the circular groove, thereby enabling the filter unit 103 to filter the liquid carbon dioxide 106 that is about to flow out of the sealing chamber. Preferably, the filter unit 103 has a filter resolution of 100 μm.

[0041] More specifically, in a preferred embodiment of this application, the phase change energy tube 1 further includes an intake valve and a baffle. One end of the intake valve is located outside the sealing top cover 101, and the other end of the intake valve penetrates through the sealing top cover 101 to the bottom surface of the annular groove. Correspondingly, the baffle is an annular baffle with several through holes, and the annular baffle is disposed at the opening end of the annular groove to absorb the impact generated when the buffered carbon dioxide 106 is injected. Preferably, the inner ring of the baffle is provided with an annular wall that can be embedded in the inner wall of the circular groove, and several locking pins are uniformly arranged circumferentially between the annular wall and the circular groove. The partition 104 is fixed to the annular baffle by the locking pins passing through the locking holes on the annular wall and the side wall of the annular groove.

[0042] Furthermore, such as Figure 1 As shown in the preferred embodiment of this application, the storage diversion mechanism further includes a guide pipe 2. The guide pipe 2 is disposed between the outlet of the phase change energy tube 1 and the inlet of the storage tank 3. The guide pipe 2 is connected to the outlet of each phase change energy tube 1 and to the inlet of the storage tank 3, and is used to transfer the gaseous carbon dioxide in the phase change energy tube 1 to the storage tank 3.

[0043] Further preferably, in a preferred embodiment of this application, a high-pressure safety valve 8 is provided on the storage tank 3. The high-pressure safety valve 8 is connected to the gas outlet of the storage tank 3 and is used to discharge gaseous carbon dioxide when the pressure inside the storage tank 3 is too high. Preferably, the storage tank 3 is made of titanium alloy, has an ellipsoidal end cap, can withstand a maximum pressure of 40 MPa, and has a built-in filter with a filtration accuracy of 10 μm.

[0044] Furthermore, in a preferred embodiment of this application, a diversion pipe 5 is provided between the gas outlet of the storage tank 3 and the diversion channel, and a connecting pipe with a pressure reducing valve 4 is provided between the diversion pipe 5 and the outlet of the storage tank 3 to reduce the pressure of gaseous carbon dioxide flowing from the storage tank 3 into the diversion pipe 5.

[0045] Furthermore, in another preferred embodiment of this application, the high-pressure safety valve 8 may also be installed on the connecting pipe between the outlet end of the storage tank 3 and the inlet end of the diversion pipe 5.

[0046] Further preferably, in the preferred embodiment of this application, a low-pressure safety valve 9 is provided on the diversion pipe 5. The low-pressure safety valve 9 is connected to the chamber inside the diversion pipe 5 to prevent the gas supply branch from failing due to excessive pressure of gaseous carbon dioxide in the diversion pipe 5.

[0047] Furthermore, the high-pressure safety valve 8 opens at a pressure of 35 MPa, and the low-pressure safety valve 9 opens at a pressure of 10 MPa.

[0048] Furthermore, in a preferred embodiment of this application, a pressure monitoring sensor is provided in one or more of the storage tank 3, the diversion pipe 5, and the gas supply branch pipe to monitor the pressure of gaseous carbon dioxide. When the pressure of gaseous carbon dioxide in the storage tank 3 is insufficient, one or more igniters 110 in the phase change energy tube 1 are controlled to operate, thereby replenishing the storage tank 3 with gaseous carbon dioxide.

[0049] More specifically, in a preferred embodiment of this application, the thruster 6 includes a solenoid valve and a nozzle. The nozzle is connected to the air supply branch pipe via the solenoid valve, and the opening and closing of the air supply branch pipe is achieved by opening and closing the solenoid valve. Preferably, the solenoid valve is electrically connected to the control component 7. Preferably, the optimal operating pressure range of the solenoid valve is 0.2~10MPa, and the response time is ≤60ms.

[0050] The attitude control power system based on carbon dioxide phase change gas storage in this invention offers rapid response and stable power. When the gaseous carbon dioxide pressure in the storage tank 3 is low, a phase change energy tube 1 containing built-in liquid carbon dioxide 106 replenishes the storage tank 3 with gaseous carbon dioxide in a timely manner, ensuring that the attitude control system always maintains a sufficient driving gas source. Simultaneously, the activator 107 placed in the phase change energy tube 1 rapidly converts the liquid carbon dioxide 106 into gaseous carbon dioxide, thereby improving the gas supply efficiency of the entire attitude control power system. Furthermore, by using liquid carbon dioxide 106 as the storage gas source, and considering the fact that the critical conditions for carbon dioxide phase change are easier to achieve and overcome compared to other gases, not only can the pressure resistance level of the phase change energy tube 1 be reduced, but a relatively small amount of activator 107 can also provide energy for the conversion of all liquid carbon dioxide 106 into gaseous carbon dioxide. This improves the safety of the attitude control power system while reducing its operating costs, demonstrating significant potential for widespread application.

[0051] Those skilled in the art will readily understand that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An attitude control propulsion system based on carbon dioxide phase change gas storage, used to drive the motion of an aircraft to adjust its attitude, characterized in that, include: A plurality of thrusters, each of which is used to drive the aircraft to adjust its attitude; A plurality of phase change energy tubes, each of which includes a housing and an excitation assembly; The housing has a sealed chamber filled with liquid carbon dioxide. The activating agent of the activating component is disposed in the sealed chamber to activate the liquid carbon dioxide to convert into gaseous carbon dioxide. The housing has an openable and closable sealed gas outlet that communicates with the sealed chamber to discharge the gaseous carbon dioxide from the sealed chamber when the liquid carbon dioxide is converted into gaseous carbon dioxide. The storage and diversion mechanism includes a storage tank and a diversion channel. The inlet of the storage tank is connected to the sealed outlet of each phase change energy tube for receiving and storing gaseous carbon dioxide. The outlet of the storage tank is connected to the diversion channel, and each thruster is provided with an openable and closable air supply branch pipe for providing gaseous carbon dioxide to the corresponding thruster when adjusting the attitude of the aircraft. A control component is electrically connected to the ignition component and the diversion channel, respectively, and is used to control the combustion of the ignition agent and to control the opening and closing of the gas supply branch pipe.

2. The attitude control propulsion system based on carbon dioxide phase change gas storage according to claim 1, wherein, The activation assembly also includes an igniter and an ignition powder; The activating agent is disposed at one end of the sealed chamber away from the gas outlet, and a portion of the outer surface of the activating agent abuts against the ignition agent; The igniter passes through the housing and is electrically connected to the control component for igniting the ignition charge upon receiving an ignition signal.

3. The attitude control propulsion system based on carbon dioxide phase change gas storage according to claim 1, wherein, The end of the housing facing away from the activator is provided with an opening, and a removable sealing top cover is provided on the opening. The vent is provided on the sealing top cover.

4. The attitude control power system based on carbon dioxide phase change gas storage according to claim 3, wherein, An annular baffle is provided on the side of the sealing top cover facing the sealing chamber, forming a circular groove and an annular groove on the inner and outer sides of the annular baffle, respectively. The air outlet is located on the bottom surface of the circular groove, and a filter unit is provided in the circular groove of the annular baffle.

5. The attitude control propulsion system based on carbon dioxide phase change gas storage according to claim 4, wherein, The phase change energy tube also includes an intake valve and a baffle. One end of the air intake valve is located outside the sealing top cover, and the other end of the air intake valve passes through the sealing top cover until it connects to the annular groove; the baffle is an annular baffle with several through holes, and the annular baffle is set at the opening end of the annular groove to reduce the injection impact when the liquid carbon dioxide is filled.

6. The attitude control propulsion system based on carbon dioxide phase change gas storage according to any one of claims 1 to 5, wherein, The storage distribution mechanism also includes a flow guide pipe; The guide pipe is disposed between the outlet of the phase change energy tube and the inlet of the storage tank. The guide pipe is connected to the outlet of each phase change energy tube and to the inlet of the storage tank. It is used to receive gaseous carbon dioxide in the phase change energy tube and then transfer it to the storage tank.

7. The attitude control propulsion system based on carbon dioxide phase change gas storage according to any one of claims 1 to 5, wherein, The storage tank is equipped with a high-pressure safety valve, which is connected to the gas outlet of the storage tank and is used to discharge the gaseous carbon dioxide when the pressure inside the storage tank is too high.

8. The attitude control propulsion system based on carbon dioxide phase change gas storage according to any one of claims 1 to 5, wherein, A diversion pipe is provided between the gas outlet of the storage tank and the diversion channel, and a pressure reducing valve is provided between the diversion pipe and the gas outlet of the storage tank to reduce the pressure of gaseous carbon dioxide flowing from the storage tank into the diversion pipe.

9. The attitude control propulsion system based on carbon dioxide phase change gas storage according to claim 8, wherein, A low-pressure safety valve is installed on the shunt pipe. The low-pressure safety valve is connected to the chamber inside the shunt pipe to prevent the gas supply branch pipe from failing to close due to excessive pressure of gaseous carbon dioxide in the shunt pipe.

10. The attitude control propulsion system based on carbon dioxide phase change gas storage according to any one of claims 1 to 5, wherein, Both the storage tank and the gas supply branch pipe are equipped with gas pressure monitoring sensors, which are used to monitor the pressure of the gaseous carbon dioxide in the storage tank and the gas supply branch pipe, respectively.

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