Combined multi-unit electrically controlled solid thruster and electrically controlled thrust method

Abstract

The present invention relates to the technical field of arrangement or configuration of a propulsion system, and discloses a combined multi-unit electrically controlled solid thruster and an electrically controlled thrust method, wherein a shell, an anode assembly and an integrated nozzle are connected and fixed into an integral structure through an anode assembly, and the anode terminal of the anode assembly is exposed; a porous area is provided in the area between the inner cavity of the shell and the inner cavity of the integrated nozzle on the anode assembly, and the porous area is used to form a flow channel for the propellant gas; at least one end thruster unit and at least one coaxial thruster unit are also arranged on the shell, and the end thruster unit and the coaxial thruster unit are arranged at intervals along the circumference of the shell, and the cathode terminal of the end thruster unit and the three-axis cathode of the coaxial thruster unit are respectively exposed from the end surface of the shell. It can realize repeatable ignition and flameout, and is suitable for use in applications where frequent starting and stopping of thrust is required.

Description

Technical Field

[0001] The present invention relates to the technical field of arrangement or configuration of a propulsion system, and in particular to a combined multi-unit electrically controlled solid thruster and an electrically controlled thrust method. Background Art

[0002] In recent years, commercial aerospace has developed rapidly, and they are actively promoting their own Starlink plans. It is expected that a large number of satellites will be launched for networking. These large numbers of satellites are basically microsatellites, which have the advantages of short development cycle, low development and launch costs, and fast launch and networking speed. Microsatellites are developing in the direction of stronger on-orbit execution capabilities, more powerful functions, and better performance. However, the size and mass of microsatellites limit the design of thrusters, and they usually do not have good maneuverability, which also limits their mission application scenarios.

[0003] The electrically controlled solid microthruster utilizes the combustion of propellant to generate greater power, and at the same time can control its combustion intensity through electric current. Therefore, compared with electric thrusters, it has the advantages of large thrust and simple structure, and can be used as a thrust source for rapid maneuvering missions of microsatellites.

[0004] At present, the performance of electronically controlled solid thrusters is not perfect enough. For example, the electronically controlled solid thrusters recorded in "The Current Development Status of Vacuum Arc Thruster Configuration Design (Li Xiaotian et al., "Vacuum and Cryogenics", Vol. 24, No. 1, February 2018)" have problems such as low thrust and unstable repeated ignition performance. In addition, the number of repeated ignitions of a single-engine thruster is limited, and it does not have the ability to complete multiple tasks. Summary of the invention

[0005] The present invention provides a combined multi-unit electric-controlled solid thruster and an electric-controlled thrust method, which can flexibly combine a coaxial structure thruster and an end-face structure thruster. Each unit can work independently, and can also share a combustion chamber and a nozzle to work. After all thruster units complete their tasks, the replacement and assembly of the thruster units can be easily completed, and the thruster can be reused, further reducing the cost of the propulsion system; it can achieve repeatable ignition and flameout on the basis of directly applying voltage for ignition, thereby improving the reliability and adaptability of the thruster, and is particularly suitable for use in applications that require frequent starting and stopping of thrust. The technical problems of low thrust and unstable repeated ignition performance of existing electric-controlled solid thrusters are solved.

[0006] According to one aspect of the present invention, there is provided a combined multi-unit electrically controlled solid thruster, comprising a shell, an anode assembly and an integrated nozzle arranged in sequence along the axial direction, the shell, the anode assembly and the integrated nozzle are connected and fixed into an integral structure through the anode assembly, and the anode terminal of the anode assembly is exposed; a porous area is provided in an area between the inner cavity of the shell and the inner cavity of the integrated nozzle on the anode assembly, and the porous area is used to form a flow channel for propellant fuel gas; at least one end thruster unit and at least one coaxial thruster unit are also arranged on the shell, the end thruster unit and the coaxial thruster unit are arranged at intervals along the circumference of the shell, and the cathode terminal of the end thruster unit and the three-axis cathode of the coaxial thruster unit are respectively exposed from the end surface of the shell.

[0007] Furthermore, a first flange for connecting to the anode assembly and the integrated nozzle is provided at the first end of the shell, and an end plate is provided at the second end of the shell; an assembly cavity is provided at the first end of the shell in an axial direction toward the second end, and a plurality of assembly cavities are arranged at intervals along the circumference of the shell, and the cathode terminal post and the coaxial thruster unit are respectively assembled in the corresponding assembly cavities, and the cathode terminal post of the end face thruster unit and the three-axis cathode of the coaxial thruster unit are respectively exposed through the end plate of the shell.

[0008] Furthermore, a water cooling channel is provided at the first end of the shell in an axial direction toward the second end; a plurality of water cooling channels are arranged at intervals along the circumference of the shell, and the water cooling channels are distributed around the periphery of the assembly cavity.

[0009] Furthermore, an air guide channel arranged along the axial direction is opened on the inner wall surface of the assembly cavity, and a plurality of air guide channels are arranged at intervals along the circumference of the assembly cavity.

[0010] Furthermore, the end-type thruster unit includes a quartz shell, a spring, a cathode plate and a first electrically-controlled solid propellant; the quartz shell is assembled in the assembly cavity, and the cathode terminal, the spring, the cathode plate and the first electrically-controlled solid propellant are arranged in sequence in the quartz shell, and the cathode terminal is arranged toward the second end of the shell and simultaneously passes through the end face of the quartz shell and the end plate of the shell, and the spring is arranged in a pre-stressed state between the cathode terminal and the cathode plate; during the combustion of the first electrically-controlled solid propellant, the spring compresses the cathode plate to achieve a stable supply of the first electrically-controlled solid propellant.

[0011] Furthermore, a plurality of exhaust holes are provided on the cathode plate and / or the quartz shell; the combustion gas generated during the combustion of the first electronically controlled solid propellant enters the gas guide channel of the shell through the exhaust holes and is transported to the integrated nozzle via the gas guide channel.

[0012] Furthermore, the coaxial thruster unit includes a metal shell, an insulating base and a second electronically controlled solid propellant. The metal shell is assembled in the assembly cavity, and the three-axis cathode is connected to the insulating base to achieve insulation from the metal shell. A plurality of exhaust holes are opened on the metal shell, and the combustion gas generated during the combustion of the second electronically controlled solid propellant enters the air guide channel of the shell through the exhaust holes and is transported to the integrated nozzle via the air guide channel.

[0013] Furthermore, the three-axis cathode includes an outrigger column, an adapter plate and an inrigger column, the outrigger column and the inrigger column are respectively arranged at both ends of the adapter plate, the outrigger column passes through the end plate at the second end of the shell to be exposed; three inrigger columns are arranged and spaced apart along the circumference of the adapter plate, the inrigger column passes through the insulating base and is inserted into the second electrically-controlled solid propellant, the portion of the inrigger column in contact with the second electrically-controlled solid propellant is coated with an insulating thin layer, and the end face height of the inrigger column is lower than the propellant combustion surface of the second electrically-controlled solid propellant to achieve gradual combustion of the second electrically-controlled solid propellant.

[0014] Furthermore, the integrated nozzle includes a combustion chamber section arranged close to the shell and a nozzle section arranged away from the shell, the combustion chamber section and the nozzle section are an integral structure formed as one piece, and a second flange is provided at the end of the combustion chamber section; the anode assembly includes a porous anode plate and connecting bolts, the porous anode plate is arranged between the shell and the integrated nozzle, and a concave-convex structure is used for positioning and matching between the porous anode plate and the shell and / or between the porous anode plate and the integrated nozzle; the connecting bolts simultaneously penetrate the first flange, the porous anode plate and the second flange and connect and fix the shell, the porous anode plate and the integrated nozzle, and the connecting bolts serve as anode terminals of the anode assembly; a plurality of porous areas are arranged on the porous anode plate, the porous areas are arranged one-to-one with the assembly cavity, and the radial dimension of the porous area is larger than the radial dimension of the assembly cavity.

[0015] According to another aspect of the present invention, there is also provided an electric control thrust method, which adopts the above-mentioned combined multi-unit electric control solid thruster, wherein the positive electrode of the power supply is connected to the anode terminal of the anode assembly through an electric wire, so that the anode assembly is positively charged, and the negative electrode of the power supply is connected to the cathode terminal of the end thruster unit and / or the three-axis cathode of the coaxial thruster unit through an electric wire; according to the thrust requirement of the mission, the cathode terminal of the end thruster unit and / or the three-axis cathode of the coaxial thruster unit are controlled by a switch to change the type and number of working thrusters; when the thrust requirement is relatively small, only a single coaxial thruster unit needs to be turned on, when the thrust requirement is medium, a single end thruster unit is turned on, and when the thrust requirement is relatively large, all thruster units are turned on at the same time; during the working process, cooling water is circulated and cooled in the water cooling channel to prevent the end thruster unit and / or the coaxial thruster unit from thermal runaway during the power-on working process, so as to ensure that the combined multi-unit electric control solid thruster can be stably and repeatedly ignited multiple times.

[0016] The present invention has the following beneficial effects:

[0017] The combined multi-unit electrically controlled solid thruster of the present invention realizes a modular design of the thruster by sequentially arranging a shell, an anode assembly and an integrated nozzle along the axial direction, which is convenient for maintenance and replacement, and is also convenient for modular assembly. Such modular design can also increase the thrust output range of the thruster, and because multiple units can work in parallel, the thruster can also provide a greater total thrust; the anode assembly not only connects and fixes the shell, the anode assembly and the integrated nozzle into an integral structure, but also exposes the anode terminal, which is convenient for electrical connection and control, and helps to improve the ignition and control efficiency of the thruster; the porous area on the anode assembly is used to form a flow channel for the propellant gas, which helps the propellant gas Uniform distribution and efficient combustion improve the performance and thrust of the thruster; the end thruster units and coaxial thruster units arranged on the shell are arranged at intervals along the circumferential direction. This combination provides different types and numbers of thrusters at the same time, which can enhance the performance of the thruster and form a synergistic and complementary effect; the cathode terminal of the end thruster unit and the three-axis cathode of the coaxial thruster unit are respectively exposed from the end surface of the shell, which is convenient for electrical connection and control, and helps to improve the repeated ignition performance of the thruster; it can achieve repeatable ignition and flameout on the basis of directly applying voltage for ignition, thereby improving the reliability and adaptability of the thruster, and is particularly suitable for use in applications that require frequent starting and stopping of thrust. The combined multi-unit electrically-controlled solid thruster and the electrically-controlled thrust method can flexibly combine the multi-unit electrically-controlled solid thruster of the coaxial structure thruster and the end structure thruster. Each unit can work independently, and can also share the combustion chamber and the nozzle to work. After all the thruster units complete the task, the thruster units can be easily replaced and assembled, so that the thrusters can be reused, further reducing the cost of the propulsion system, and effectively solving the technical problems of low thrust and unstable repeated ignition performance faced by the existing electrically-controlled solid thrusters.

[0018] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0020] Figure 1 It is a schematic diagram of the appearance structure of a combined multi-unit electrically controlled solid thruster according to a preferred embodiment of the present invention;

[0021] Figure 2is a schematic cross-sectional structure diagram of a combined multi-unit electrically controlled solid thruster according to a preferred embodiment of the present invention;

[0022] Figure 3 is a schematic structural diagram of a housing in a preferred embodiment of the present invention;

[0023] Figure 4 is a schematic structural diagram of an air guide channel and a water cooling channel of a housing in a preferred embodiment of the present invention;

[0024] Figure 5 is a schematic structural diagram of a porous anode plate in a preferred embodiment of the present invention;

[0025] Figure 6 is a structural schematic diagram of an end-type thruster unit according to a preferred embodiment of the present invention;

[0026] Figure 7 is a structural schematic diagram of a coaxial thruster unit according to a preferred embodiment of the present invention;

[0027] Figure 8 Schematic diagram of the structure of a three-axis cathode according to a preferred embodiment of the present invention.

[0028] Legend:

[0029] 100, shell; 101, first flange; 102, end plate; 103, assembly cavity; 104, water cooling channel; 105, air guide channel; 200, anode assembly; 201, anode terminal; 202, porous area; 203, porous anode plate; 204, connecting bolt; 300, integrated nozzle; 301, second flange; 400, end thruster unit; 401, cathode terminal; 402, Quartz shell; 403, spring; 404, cathode plate; 405, first electrically controlled solid propellant; 500, coaxial thruster unit; 501, three-axis cathode; 5011, outrigger column; 5012, adapter plate; 5013, internal column; 502, metal shell; 503, insulating base; 504, second electrically controlled solid propellant; 600, fastening nut; 700, sealing gasket; 800, concave-convex structure. DETAILED DESCRIPTION

[0030] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0031] Figure 1 It is a schematic diagram of the appearance structure of a combined multi-unit electrically controlled solid thruster according to a preferred embodiment of the present invention; Figure 2 is a schematic cross-sectional structure diagram of a combined multi-unit electrically controlled solid thruster according to a preferred embodiment of the present invention; Figure 3 is a schematic structural diagram of a housing in a preferred embodiment of the present invention; Figure 4is a schematic structural diagram of an air guide channel and a water cooling channel of a housing in a preferred embodiment of the present invention; Figure 5 is a schematic structural diagram of a porous anode plate in a preferred embodiment of the present invention; Figure 6 is a structural schematic diagram of an end-type thruster unit according to a preferred embodiment of the present invention; Figure 7 is a structural schematic diagram of a coaxial thruster unit according to a preferred embodiment of the present invention; Figure 8 Schematic diagram of the structure of a three-axis cathode according to a preferred embodiment of the present invention.

[0032] like Figure 1 and Figure 2As shown, the combined multi-unit electrically controlled solid thruster of this embodiment comprises a shell 100, an anode assembly 200 and an integrated nozzle 300 arranged in sequence along the axial direction, the shell 100, the anode assembly 200 and the integrated nozzle 300 are connected and fixed into an integral structure through the anode assembly 200, and the anode terminal 201 of the anode assembly 200 is exposed; the area on the anode assembly 200 between the inner cavity of the shell 100 and the inner cavity of the integrated nozzle 300 is provided with a porous area 2 02, the porous area 202 is used to form a flow channel for the propellant fuel gas; at least one end thruster unit 400 and at least one coaxial thruster unit 500 are also arranged on the shell 100, and the end thruster unit 400 and the coaxial thruster unit 500 are arranged at intervals along the circumference of the shell 100, and the cathode terminal 401 of the end thruster unit 400 and the three-axis cathode 501 of the coaxial thruster unit 500 are respectively exposed from the end surface of the shell 100. The combined multi-unit electrically controlled solid thruster of the present invention realizes a modular design of the thruster by sequentially arranging the shell 100, the anode assembly 200 and the integrated nozzle 300 in the axial direction, which is convenient for maintenance and replacement, and also convenient for modular assembly. Such modular design can also increase the thrust output range of the thruster, and because multiple units can work in parallel, the thruster can also provide a greater total thrust; the anode assembly 200 not only connects and fixes the shell 100, the anode assembly 200 and the integrated nozzle 300 into an integral structure, but also exposes the anode terminal 201, which is convenient for electrical connection and control, and helps to improve the ignition and control efficiency of the thruster; the porous area 202 on the anode assembly 200 is used to form a flow channel for the propellant gas, which helps the propellant The gas is evenly distributed and burned efficiently, thereby improving the performance and thrust of the thruster; the end thruster unit 400 and the coaxial thruster unit 500 arranged on the shell 100 are arranged at intervals along the circumferential direction. This combination provides thrusters of different types and numbers at the same time, which can enhance the performance of the thruster and form a synergistic and complementary effect; the cathode terminal 401 of the end thruster unit 400 and the three-axis cathode 501 of the coaxial thruster unit 500 are respectively exposed from the end surface of the shell 100, which is convenient for electrical connection and control, and helps to improve the repeated ignition performance of the thruster; it can achieve repeatable ignition and flameout on the basis of directly applying voltage for ignition, thereby improving the reliability and adaptability of the thruster, and is particularly suitable for use in applications where frequent starting and stopping of thrust is required.The combined multi-unit electrically-controlled solid thruster and the electrically-controlled thrust method can flexibly combine the multi-unit electrically-controlled solid thruster of the coaxial structure thruster and the end structure thruster. Each unit can work independently, and can also share the combustion chamber and the nozzle to work. After all the thruster units complete the task, the thruster units can be easily replaced and assembled, so that the thrusters can be reused, further reducing the cost of the propulsion system, and effectively solving the technical problems of low thrust and unstable repeated ignition performance faced by the existing electrically-controlled solid thrusters.

[0033] like Figure 1 , Figure 2 and Figure 3 As shown, in this embodiment, the first end of the shell 100 is provided with a first flange 101 for connecting with the anode assembly 200 and the integrated nozzle 300, and the second end of the shell 100 is provided with an end plate 102; the first end of the shell 100 is provided with an assembly cavity 103 along the axial direction toward the second end, and a plurality of assembly cavities 103 are arranged at intervals along the circumference of the shell 100, and the cathode terminal 401 and the coaxial thruster unit 500 are respectively assembled in the corresponding assembly cavity 103, and the cathode terminal 401 of the end thruster unit 400 and the three-axis cathode 501 of the coaxial thruster unit 500 are respectively exposed through the end plate 102 of the shell 100. The first flange 101 is provided to realize the connection and fixation between the shell 100, the anode assembly 200 and the integrated nozzle 300, thereby improving the modularization and integration of the thruster, and facilitating assembly and maintenance; the assembly cavities 103 are arranged at intervals along the circumference of the shell 100, so that the cathode terminal 401 and the coaxial thruster unit 500 can be assembled in the corresponding assembly cavities 103. This modular combination design is helpful to optimize the assembly process and maintenance of the thruster; the end thruster unit 400 and the coaxial thruster unit 500 are arranged along the shell The circumferentially spaced arrangement of the shell 100 can improve the thrust output and combustion efficiency of the thruster, while increasing the flexibility and adaptability of the thruster; the cathode terminal 401 of the end-face thruster unit 400 and the three-axis cathode 501 of the coaxial thruster unit 500 are respectively exposed through the end plate 102 of the shell 100, which enhances the reliability of the electrical connection of the thruster and facilitates electrical control and signal transmission; by changing the electrode structure of the original electrically controlled solid thruster, the propellant combustion stability is improved, and the controllability of the thruster operation is improved. Optionally, the cathode terminal 401 of the end thruster unit 400 and the three-axis cathode 501 of the coaxial thruster unit 500 are respectively exposed through the end plate 102 of the shell 100, and the exposed cathode terminal 401 and the exposed three-axis cathode 501 both have external threads. The exposed cathode terminal 401 and the exposed three-axis cathode 501 are respectively sealed by a sealing gasket 700, and are locked and fixed by a fastening nut 600 to ensure the sealing effect.

[0034] like Figure 1 , Figure 2 and Figure 4 As shown, in this embodiment, a water cooling channel 104 is provided at the first end of the shell 100 in the axial direction toward the second end; a plurality of water cooling channels 104 are arranged at intervals along the circumference of the shell 100, and the water cooling channels 104 are distributed around the periphery of the assembly cavity 103. The water cooling channels 104 are arranged at intervals along the circumference of the shell 100, which helps to disperse the heat more evenly and improve the heat dissipation efficiency. Through the circulation of the coolant in the water cooling channels 104, the heat generated by the thruster during operation can be effectively absorbed and taken away, so as to prevent overheating and maintain the optimal operating temperature of the thruster; the water cooling channels 104 are distributed around the periphery of the assembly cavity 103, so as to protect sensitive components such as the thruster unit and the terminal inside, and prevent them from being damaged by high temperature, thereby improving the reliability and service life of the thruster; through effective cooling, the performance stability of the thruster under various working conditions can be ensured, and the performance degradation or failure caused by temperature fluctuation can be avoided.

[0035] like Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, in this embodiment, an axially arranged air guide channel 105 is provided on the inner wall surface of the assembly cavity 103, and a plurality of air guide channels 105 are arranged at intervals along the circumference of the assembly cavity 103. The air guide channel 105 helps the propellant gas to flow evenly and guide it into the integrated nozzle 300, which can improve the response speed of the thruster, and is particularly important for occasions where the thrust needs to be adjusted quickly, thereby improving the combustion efficiency and the performance of the thruster; the air guide channels 105 arranged at intervals along the circumference can ensure that the gas flows evenly in the combustion chamber, which helps to optimize the combustion process and reduce local overheating or incomplete combustion; the air guide channel 105 can be used as a part of the structure of the shell 100 to help disperse the internal pressure and ensure the structural stability of the shell 100 to a certain extent.

[0036] like Figure 1 , Figure 2 and Figure 6As shown, in this embodiment, the end-type thruster unit 400 includes a quartz shell 402, a spring 403, a cathode plate 404 and a first electrically controlled solid propellant 405; the quartz shell 402 is assembled in the assembly cavity 103, and the cathode terminal 401, the spring 403, the cathode plate 404 and the first electrically controlled solid propellant 405 are arranged in sequence in the quartz shell 402, and the cathode terminal 401 is arranged toward the second end direction of the shell 100 and simultaneously penetrates the end surface of the quartz shell 402 and the end plate 102 of the shell 100, and the spring 403 is arranged between the cathode terminal 401 and the cathode plate 404 in a pre-stressed state; during the combustion process of the first electrically controlled solid propellant 405, the spring 403 squeezes the cathode plate 404 to achieve a stable supply of the first electrically controlled solid propellant 405. The quartz shell 402 provides a relatively closed environment to protect and constrain the cathode terminal 401, spring 403, cathode plate 404 and first electrically controlled solid propellant 405 inside; the spring 403 is arranged between the cathode terminal 401 and the cathode plate 404 in a pre-stressed state, which can provide stable mechanical support to ensure that the cathode plate 404 maintains appropriate pressure during the operation of the thruster, thereby maintaining a stable supply of the first electrically controlled solid propellant 405; during the combustion of the first electrically controlled solid propellant 405, the spring 403 squeezes the cathode plate 404 to ensure a continuous and stable supply of propellant to maintain the thruster continuous operation; the cathode terminal 401 penetrates the end surface of the quartz shell 402 and the end plate 102 of the shell 100, which helps to improve the ignition efficiency and combustion efficiency of the thruster, because the cathode plate 404 is in direct contact with the propellant, which can more effectively initiate and maintain combustion; since the cathode terminal 401 is directly connected to the cathode plate 404, this direct electrical connection can improve the response speed of the thruster to the electrical signal, thereby achieving rapid ignition and combustion control; the durability of the quartz shell 402 and the pre-stress design of the spring 403 work together to improve the structural stability and working reliability of the thruster and extend the service life of the thruster.

[0037] like Figure 1 , Figure 2 and Figure 6As shown, in this embodiment, a plurality of exhaust holes are provided on the cathode plate 404 and / or the quartz housing 402; the gas generated during the combustion of the first electrically controlled solid propellant 405 enters the gas guide channel 105 of the housing 100 through the exhaust holes and is transported to the integrated nozzle 300 through the gas guide channel 105. The design of the exhaust holes allows the gas generated by the combustion to be output in time to avoid accumulation inside the thruster, thereby reducing pressure accumulation and possible damage; through the reasonable layout of the gas guide channel 105, the gas can be effectively guided and transported, optimizing the gas flow path, and improving the combustion efficiency and thrust output of the thruster; the gas is transported to the integrated nozzle 300 through the gas guide channel 105, which helps to form a more uniform and controllable gas flow, and enhances the performance and thrust control capability of the thruster; the design of the exhaust holes and the gas guide channel 105 helps to reduce the pressure inside the thruster and reduce the safety risks caused by excessive pressure.

[0038] like Figure 1 , Figure 2 and Figure 7 As shown, in this embodiment, the coaxial thruster unit 500 includes a metal shell 502, an insulating base 503 and a second electrically controlled solid propellant 504. The metal shell 502 is assembled in the assembly cavity 103, and the three-axis cathode 501 is connected to the insulating base 503 to achieve insulation from the metal shell 502; a plurality of exhaust holes are opened on the metal shell 502, and the combustion gas generated during the combustion of the second electrically controlled solid propellant 504 enters the gas guide channel 105 of the shell 100 through the exhaust holes and is transported to the integrated nozzle 300 via the gas guide channel 105. The three-axis cathode 501 is connected to the insulating base 503 to achieve insulation from the metal shell 502, which can prevent current leakage and ensure the electrical safety and reliability of the thruster; the multiple exhaust holes opened on the metal shell 502 allow the gas generated during the combustion of the second electronically controlled solid propellant 504 to be smoothly output, reducing the internal pressure of the thruster and avoiding overpressure and possible damage; the gas enters the gas guide channel 105 of the shell 100 through the exhaust holes; the gas is transported to the integrated nozzle 300 through the gas guide channel 105 to form a more uniform and controllable gas flow, enhance the thrust and specific impulse of the thruster, and improve the performance of the thruster; by reasonably designing the exhaust holes and the gas guide channel 105, the pollution caused by the plasma plume backflow to the thruster can be reduced, the thruster can be protected from damage, and the impact on the surrounding environment can be reduced; the design of the coaxial thruster unit 500 improves the performance and reliability of the thruster by optimizing gas exhaust, enhancing cooling effect, improving thrust and specific impulse, and reducing plume pollution.

[0039] like Figure 1 , Figure 2 , Figure 7 and Figure 8As shown, in this embodiment, the three-axis cathode 501 includes an outrigger 5011, an adapter plate 5012, and an inner-connected column 5013. The outrigger 5011 and the inner-connected column 5013 are respectively arranged at the two ends of the adapter plate 5012, and the outrigger 5011 passes through the end plate 102 at the second end of the shell 100 and is exposed. There are three inner-connected columns 5013 arranged at intervals along the circumference of the adapter plate 5012. The inner-connected columns 5013 penetrate the insulating base 503 and are plugged into the second electrically controlled solid propellant 504. The portion of the inner-connected column 5013 that contacts the second electrically controlled solid propellant 504 is coated with an insulating thin layer, and the end surface height of the inner-connected column 5013 is lower than the propellant combustion surface of the second electrically controlled solid propellant 504, so as to realize the gradual combustion of the second electrically controlled solid propellant 504. The three-axis cathode 501 is connected to the insulating base 503 through the adapter plate 5012, thereby achieving insulation from the metal shell 502 and improving the electrical safety and structural stability of the thruster; three inner columns 5013 are arranged at intervals along the circumference of the adapter plate 5012, which helps to achieve uniform combustion of the second electrically controlled solid propellant 504; the portion of the inner column 5013 in contact with the second electrically controlled solid propellant 504 is coated with an insulating thin layer to prevent the occurrence of short circuits and ensure the normal operation of the thruster; the end face height of the inner column 5013 is lower than the propellant burning surface of the second electrically controlled solid propellant 504, so that the propellant can be gradually burned, thereby accurately controlling the thrust output and combustion time of the thruster; the combustion gas generated during the combustion of the second electrically controlled solid propellant 504 enters the gas guide channel 105 of the shell 100 through the exhaust holes on the metal shell 502, and is transported to the integrated nozzle 300 via the gas guide channel 105, thereby optimizing the gas flow and improving the combustion efficiency and thrust output of the thruster. The three-axis cathode 501 design improves thruster performance and safety through insulation, progressive combustion control and optimized gas flow.

[0040] like Figure 1 , Figure 2 and Figure 5As shown, in this embodiment, the integrated nozzle 300 includes a combustion chamber section arranged near the shell 100 and a nozzle section arranged away from the shell 100. The combustion chamber section and the nozzle section are an integral structure formed in one piece, and a second flange 301 is provided at the end of the combustion chamber section. The anode assembly 200 includes a porous anode plate 203 and a connecting bolt 204. The porous anode plate 203 is arranged between the shell 100 and the integrated nozzle 300, and the porous anode plate 203 and the shell 100 and / or the porous anode plate 203 and the integrated nozzle 300 are positioned and matched by a concave-convex structure 800. The connecting bolt 204 simultaneously penetrates the first flange 101, the porous anode plate 203 and the second flange 301, and connects and fixes the shell 100, the porous anode plate 203 and the integrated nozzle 300, and the connecting bolt 204 serves as the anode terminal 201 of the anode assembly 200. A plurality of porous regions 202 are arranged on the porous anode plate 203, and the porous regions 202 are arranged one-to-one with the assembly cavity 103, and the radial dimension of the porous regions 202 is greater than the radial dimension of the assembly cavity 103. The integrated nozzle 300 is composed of a combustion chamber section and a nozzle section, and is an integral structure formed in one piece, making the nozzle structure more compact and strong; the integrated design of the combustion chamber section and the nozzle section helps to more effectively manage the high-temperature combustion gas generated by the thruster, reduce heat loss, and maintain the performance of the thruster; the porous anode plate 203 is arranged between the shell 100 and the integrated nozzle 300, and the porous regions 202 are arranged one-to-one with the assembly cavity 103, which helps to accurately control the flow direction and distribution of the combustion gas and improve the combustion efficiency. The connecting bolt 204 simultaneously penetrates the first flange 101, the porous anode plate 203 and the second flange 301, and connects and fixes the shell 100, the porous anode plate 203 and the integrated nozzle 300, and the connecting bolt 204 acts as the anode terminal 201 of the anode assembly 200, which simplifies the electrical connection and improves the electrical stability and reliability of the thruster. The porous anode plate 203 and the shell 100 and / or the porous anode plate 203 and the integrated nozzle 300 are positioned and matched using a concave-convex structure 800, which improves the matching accuracy and structural stability between the components, especially ensures a one-to-one correspondence between the porous area 202 and the assembly cavity 103, which helps to accurately control the flow direction and distribution of the gas and improve the combustion efficiency. The radial dimension of the porous area 202 is larger than the radial dimension of the assembly cavity 103, which improves the efficiency of the gas flow and the combustion efficiency of the thruster.

[0041] The electric control thrust method of this embodiment adopts the above-mentioned combined multi-unit electric control solid thruster, the positive electrode of the power supply is connected to the anode terminal 201 of the anode assembly 200 through an electric wire, so that the anode assembly 200 is positively charged, and the negative electrode of the power supply is connected to the cathode terminal 401 of the end thruster unit 400 and / or the three-axis cathode 501 of the coaxial thruster unit 500 through an electric wire; according to the thrust demand of the mission, the cathode terminal 401 of the end thruster unit 400 and / or the three-axis cathode 501 of the coaxial thruster unit 500 is controlled by a switch to be turned on and off, thereby changing the type of working thruster type and quantity; when the thrust requirement is relatively small, only a single coaxial thruster unit 500 needs to be turned on; when the thrust requirement is medium, a single end thruster unit 400 is turned on; when the thrust requirement is relatively large, all thruster units are turned on at the same time, that is, all end thruster units 400 and all coaxial thruster units 500 are turned on; during operation, cooling water is circulated and cooled in the water-cooling channel 104 to prevent thermal runaway of the end thruster unit 400 and / or the coaxial thruster unit 500 during power-on operation, thereby ensuring that the combined multi-unit electronically controlled solid thruster can be stably and repeatedly ignited for multiple times. By controlling the on and off of the cathode terminal 401 of the end thruster unit 400 and / or the three-axis cathode 501 of the coaxial thruster unit 500 through switches, the type and number of working thrusters can be flexibly changed according to the thrust requirements of the mission, so that the thrusters can adapt to different thrust requirements, from small thrust to large thrust application scenarios; when the thrust requirement is relatively small, only a single coaxial thruster unit 500 needs to be turned on; when the thrust requirement is medium, a single end thruster unit 400 is turned on; when the thrust requirement is relatively large, all thruster units are turned on at the same time, so that the thruster has a wide range of applications and high adaptability; During operation, cooling water is circulated and cooled in the water cooling channel 104 to prevent thermal runaway of the end thruster unit 400 and / or the coaxial thruster unit 500 during power-on operation. The design of this cooling system ensures that the combined multi-unit electrically controlled solid thruster can be stably and repeatedly ignited multiple times, thereby improving the reliability and service life of the thruster. The controller controls the input voltage to realize controllable start and stop of the thruster and adjust the thrust. On this basis, the controller can control the propellant combustion of one or more units, which can greatly increase the adjustment range of the thruster thrust. This precise thrust control capability is crucial for aerospace missions that require delicate operations. In summary, the electrically controlled thrust method of the present invention enables the combined multi-unit electrically controlled solid thruster to play an important role in a variety of aerospace missions through flexible thrust adjustment, improved adaptability of the thruster, stable and repeated ignition capability, and precise thrust control.

[0042] During implementation, a reusable combined multi-unit electrically controlled solid thruster is provided, which can flexibly combine the coaxial micro-thruster and the end-face micro-thruster to achieve wide-range adjustment and stable operation of the thruster thrust. After all units have finished working, new thruster units can be conveniently replaced to achieve reuse of the thruster main structure and further reduce the cost of the thruster. It has the advantages of a wide thrust adjustment range, a large number of power-on and ignition times, simple assembly and reusability.

[0043] A reusable combined multi-unit electrically controlled solid thruster comprises: a shell 100, a porous anode plate 203, and an integrated nozzle 300. The shell 100 is equipped with a plurality of end thruster units 400 and a coaxial thruster unit 500 (a plurality of coaxial thruster units 500 may also be installed). The shell 100 is connected with the porous anode plate 203 and the integrated nozzle 300 by fastening screws and nuts, and the fastening screws can serve as anode terminals 201. After the end thruster unit 400 and the coaxial thruster unit 500 are assembled in the shell 100, the cathode terminals of the thruster units are sealed and fixed by sealing gaskets 700 and fastening nuts 600. The shell 100 is an insulator, and one or more end thruster units 400 and / or one or more coaxial thruster units 500 can be flexibly placed in the middle. The thruster units can work independently, and are isolated from each other by insulators so as not to affect each other. The inner wall of the loading chamber (assembly chamber 103) of the shell 100 is designed with a gas guide channel 105, which allows the combustion gas generated by the propellant at the cathode to reach the combustion chamber (inside the integrated nozzle 300) smoothly. The shell 100 is designed with a water cooling channel 104. The cooling water is circulated and cooled in the cooling layer through the water inlet and outlet, which can take away the residual heat of the propellant after it is powered on, thereby enhancing the repeated ignition stability of the thruster. A plurality of porous areas 202 are distributed on the porous anode plate 203. The porous area 202 is a flow channel for the propellant combustion gas. The combustion gas generated by the combustion of the propellant at the anode enters the combustion chamber through the hole. The integrated nozzle 300 integrates the combustion chamber and the nozzle, simplifies the engine structure, and can increase the structural reliability of the engine. The end thruster unit 400 is composed of a quartz shell 402, a cathode terminal 401, a spring 403, a cathode plate 404 and a first electrically controlled solid propellant 405. During the combustion of the first electrically controlled solid propellant 405, the spring 403 squeezes the cathode plate 404 to achieve a stable supply of propellant. The wall of the quartz shell 402 is perforated to allow the combustion gas of the cathode propellant to enter the gas guide channel 105 of the shell 100 through the exhaust hole. The coaxial thruster unit 500 is composed of a metal shell 502, a three-axis cathode 501, an insulating base 503 and a second electrically controlled solid propellant 504. The three-axis cathode 501 is connected to the insulating base 503 to achieve insulation from the metal shell 502. The part of the three-axis cathode 501 that contacts the second electrically controlled solid propellant 504 is coated with an insulating thin layer, the height of which is slightly lower than the propellant combustion surface, thereby achieving gradual combustion of the propellant. The shell 100 is made of PTFE, which has good electrical insulation properties and high temperature stability, is easy to process and has low cost. The porous anode plate 203 and the integrated nozzle 300 are made of stainless steel, and aluminum alloy can also be used to reduce the mass of the thruster. Three loading bays (assembly chambers 103) are designed in the shell 100, which can flexibly combine multiple end thruster units 400 and coaxial thruster units 500. More loading bay units can also be designed to achieve more ignition times and greater thrust.The shell of the end thruster unit 400 is made of quartz, which has good insulation and high temperature resistance. The cathode terminal 401, spring 403 and cathode plate 404 are made of stainless steel, which has the advantages of easy processing and low cost. The metal shell 502 and the three-axis cathode 501 of the coaxial thruster unit 500 are made of stainless steel, and the insulating base 503 is made of PTFE, which has the advantages of easy processing and low cost. The cathode terminal 401 and the tail of the three-axis cathode 501 have connecting threads, and the sealing gasket 700 and the fastening nut 600 seal the thruster unit with the shell 100 through the threads. The main components of the electric-controlled solid propellant (the first electric-controlled solid propellant 405 and the second electric-controlled solid propellant 504) are hydroxylamine nitrate, polyvinyl alcohol and boric acid. A certain amount of aluminum powder or boric acid can be added to improve the ignition and combustion performance.

[0044] Working process: The positive pole of the power supply is connected to the fastening screw through an electric wire, so that the porous anode plate 203 is positively charged, and the negative pole of the power supply is connected to the cathode terminal of the thruster unit through an electric wire. At the same time, the cathode terminal is sealed by the fastening nut 600 and the sealing gasket 700. According to the thrust requirements of the mission, the on and off of the cathode of the thruster unit is controlled by the switch, so as to change the type and number of working thrusters. When the thrust requirement is very small, only a single coaxial thruster unit 500 needs to be turned on. When the thrust requirement is medium, a single end thruster unit 400 can be turned on. When the thrust requirement is very large, all thruster units can be turned on at the same time. During the working process, the cooling water is continuously circulated and cooled in the water cooling channel 104 to prevent the thruster from thermal runaway during the power-on working process and ensure that the thruster can be stably and repeatedly ignited.

[0045] The reusable combined multi-unit electrically controlled solid thruster can flexibly combine the end thruster unit 400 and the coaxial thruster unit 500. A single thruster unit (a single end thruster unit 400 or a single coaxial thruster unit 500) uses an electrically controlled solid working fluid as a propellant, can be used multiple times, and the thrust of the thrust unit can be controlled by adjusting the power supply voltage. The thrust can be adjusted by controlling the type and number of working thrust units. The housing 100 realizes heat insulation and insulation between the thruster units, and is designed with an air guide channel 105 and a water cooling channel 104 to realize multiple stable and repeated ignition of the thruster unit. A plurality of thruster units (end thruster unit 400 and coaxial thruster unit 500) share the same porous anode plate 203. The porous region 202 of the porous anode plate 203 is a passage for the fuel gas. Meanwhile, the porous anode plate 203 isolates the combustion area of ​​the fuel gas from the combustion surface of the propellant, thereby preventing the propellant combustion surface from experiencing high-temperature thermal runaway and improving the working stability of the thruster.

[0046] A plurality of thruster units (end thruster unit 400 and coaxial thruster unit 500) share the same integrated nozzle 300. The integrated nozzle 300 integrates the combustion chamber and the nozzle channel, thereby reducing the structural complexity and cost of the thruster and improving the working reliability of the thruster.

[0047] The end thruster unit 400 and the coaxial thruster unit 500 are of universal design and can be efficiently assembled and circuit-connected in the same manner, thereby enabling flexible replacement and integrated use of the thrusters.

[0048] The present invention has the following advantages:

[0049] 1. Combining the advantages of multi-unit thruster structure and various electronically controlled solid thruster units, the working type and quantity of thrusters can be flexibly adjusted according to mission requirements, thereby achieving a wide range of thrust adjustment and multiple ignition operations.

[0050] 2. Various electronically controlled solid thruster units can be flexibly matched, and the assembly method with the thruster housing is simple, which can easily realize the replacement of thruster units and the reuse of thruster structures.

[0051] 3. The thruster housing can achieve insulation and heat insulation between multiple thruster units. At the same time, the designed air guide channel 105 and water cooling channel 104 can further improve the working stability of the thruster ignition and combustion process.

[0052] 4. The porous anode serves as a conductive electrode and a gas channel for multiple thruster units. It can also isolate the combustion area of ​​the gas and the propellant combustion surface to prevent high-temperature thermal runaway behavior on the propellant combustion surface. The integrated nozzle 300 integrates the combustion chamber and the nozzle, further reducing the structural complexity and cost and improving the thruster's operating reliability.

[0053] Matters not covered by the present invention are known technologies.

[0054] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0055] The above-mentioned embodiments only express several implementation modes of the present invention, and the description thereof is relatively specific and detailed, but it cannot be understood as limiting the scope of the invention. It should be pointed out that, for a person of ordinary skill in the art, several modifications and improvements can be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the attached claims.

[0056] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A combined multi-unit electrically controlled solid thruster, characterized in that: The invention comprises a shell (100), an anode assembly (200) and an integrated nozzle (300) which are sequentially arranged along the axial direction, wherein the shell (100), the anode assembly (200) and the integrated nozzle (300) are connected and fixed into an integral structure through the anode assembly (200) and the anode terminal (201) of the anode assembly (200) is exposed; A porous region (202) is provided in an area of ​​the anode assembly (200) between the inner cavity of the shell (100) and the inner cavity of the integrated nozzle (300), and the porous region (202) is used to form a flow channel for the propellant fuel gas; At least one end thruster unit (400) and at least one coaxial thruster unit (500) are also arranged on the shell (100); the end thruster unit (400) and the coaxial thruster unit (500) are arranged at intervals along the circumference of the shell (100); and the cathode terminal (401) of the end thruster unit (400) and the three-axis cathode (501) of the coaxial thruster unit (500) are respectively exposed from the end surface of the shell (100).

2. The combined multi-unit electrically controlled solid thruster according to claim 1, characterized in that: The first end of the shell (100) is provided with a first flange (101) for connecting to the anode assembly (200) and the integrated nozzle (300), and the second end of the shell (100) is provided with an end plate (102); An assembly cavity (103) is provided at the first end of the shell (100) in an axial direction toward the second end, and a plurality of assembly cavities (103) are arranged at intervals along the circumference of the shell (100); the cathode terminal post (401) and the coaxial thruster unit (500) are respectively assembled in the corresponding assembly cavities (103), and the cathode terminal post (401) of the end-face thruster unit (400) and the three-axis cathode (501) of the coaxial thruster unit (500) are respectively exposed through the end plate (102) of the shell (100).

3. The combined multi-unit electrically controlled solid thruster according to claim 2, characterized in that: A water cooling channel (104) is provided at the first end of the shell (100) in an axial direction toward the second end; A plurality of water cooling channels (104) are arranged at intervals along the circumference of the shell (100), and the water cooling channels (104) are distributed around the periphery of the assembly cavity (103).

4. The combined multi-unit electrically controlled solid thruster according to claim 2 or 3, characterized in that: An air guide channel (105) arranged along the axial direction is provided on the inner wall surface of the assembly cavity (103), and a plurality of air guide channels (105) are arranged at intervals along the circumference of the assembly cavity (103).

5. The combined multi-unit electrically controlled solid thruster according to claim 4, characterized in that: The end-type thruster unit (400) comprises a quartz housing (402), a spring (403), a cathode plate (404), and a first electrically controlled solid propellant (405); The quartz housing (402) is assembled in the assembly cavity (103); the cathode terminal (401), the spring (403), the cathode plate (404), and the first electrically controlled solid propellant (405) are arranged in sequence in the quartz housing (402); the cathode terminal (401) is arranged toward the second end of the housing (100) and simultaneously penetrates the end surface of the quartz housing (402) and the end plate (102) of the housing (100); and the spring (403) is arranged in a pre-stressed state between the cathode terminal (401) and the cathode plate (404); During the combustion of the first electrically controlled solid propellant (405), the spring (403) presses the cathode plate (404) to achieve a stable supply of the first electrically controlled solid propellant (405).

6. The combined multi-unit electrically controlled solid thruster according to claim 5, characterized in that: A plurality of exhaust holes are provided on the cathode plate (404) and / or the quartz housing (402); The combustion gas generated during the combustion of the first electrically controlled solid propellant (405) enters the gas guide channel (105) of the shell (100) through the exhaust hole and is transported to the integrated nozzle (300) via the gas guide channel (105).

7. The combined multi-unit electrically controlled solid thruster according to claim 2 or 3, characterized in that: The coaxial thruster unit (500) comprises a metal shell (502), an insulating base (503) and a second electrically controlled solid propellant (504); the metal shell (502) is assembled in an assembly cavity (103); and the three-axis cathode (501) is connected to the insulating base (503) to achieve insulation from the metal shell (502); The metal shell (502) is provided with a plurality of exhaust holes, and the combustion gas generated during the combustion of the second electrically controlled solid propellant (504) enters the gas guide channel (105) of the shell (100) through the exhaust holes and is transported to the integrated nozzle (300) via the gas guide channel (105).

8. The combined multi-unit electrically controlled solid thruster according to claim 7, characterized in that: The triaxial cathode (501) comprises an outrigger column (5011), an adapter plate (5012) and an inrigger column (5013), wherein the outrigger column (5011) and the inrigger column (5013) are respectively arranged at two ends of the adapter plate (5012), and the outrigger column (5011) passes through an end plate (102) at the second end of the shell (100) to be exposed. Three internal columns (5013) are provided and arranged at intervals along the circumference of the adapter plate (5012); the internal columns (5013) penetrate the insulating base (503) and are inserted into the second electrically controlled solid propellant (504); the portion of the internal columns (5013) in contact with the second electrically controlled solid propellant (504) is coated with an insulating thin layer, and the end surface height of the internal columns (5013) is lower than the propellant combustion surface of the second electrically controlled solid propellant (504), so as to achieve gradual combustion of the second electrically controlled solid propellant (504).

9. The combined multi-unit electrically controlled solid thruster according to claim 2 or 3, characterized in that: The integrated nozzle (300) comprises a combustion chamber section arranged close to the housing (100) and a nozzle section arranged away from the housing (100); the combustion chamber section and the nozzle section are an integral structure formed in one piece, and a second flange (301) is provided at the end of the combustion chamber section; The anode assembly (200) comprises a porous anode plate (203) and a connecting bolt (204); the porous anode plate (203) is arranged between the shell (100) and the integrated nozzle (300); and the porous anode plate (203) and the shell (100) and / or the porous anode plate (203) and the integrated nozzle (300) are positioned and matched using a concave-convex structure; The connecting bolts (204) simultaneously penetrate the first flange (101), the porous anode plate (203) and the second flange (301) and connect and fix the shell (100), the porous anode plate (203) and the integrated nozzle (300), and the connecting bolts (204) serve as anode terminals (201) of the anode assembly (200); A plurality of porous regions (202) are arranged on the porous anode plate (203), the porous regions (202) and the assembly cavities (103) are arranged in one-to-one correspondence, and the radial dimensions of the porous regions (202) are greater than the radial dimensions of the assembly cavities (103).

10. An electric thrust control method, using the combined multi-unit electric thruster according to any one of claims 1 to 9, characterized in that: The positive electrode of the power supply is connected to the anode terminal (201) of the anode assembly (200) through an electric wire, so that the anode assembly (200) is positively charged, and the negative electrode of the power supply is connected to the cathode terminal (401) of the end thruster unit (400) and / or the three-axis cathode (501) of the coaxial thruster unit (500) through an electric wire; According to the thrust demand of the mission, the cathode terminal (401) of the end thruster unit (400) and / or the three-axis cathode (501) of the coaxial thruster unit (500) are controlled by switches to switch on and off, thereby changing the type and quantity of the working thrusters; When the thrust requirement is relatively small, only a single coaxial thruster unit (500) needs to be turned on; when the thrust requirement is medium, a single end thruster unit (400) needs to be turned on; when the thrust requirement is relatively large, all thrusters are turned on at the same time; During operation, cooling water is circulated in the water cooling channel (104) for cooling, thereby preventing the end thruster unit (400) and / or the coaxial thruster unit (500) from experiencing thermal runaway during power-on operation, thereby ensuring that the combined multi-unit electronically controlled solid thruster can be stably and repeatedly ignited multiple times.

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