An integrated pressure-reducing flow control module for a satellite hall electric propulsion system

Abstract

The application provides an integrated pressure-reducing flow control module for a satellite Hall electric propulsion system, which comprises a primary pressure-reducing valve and a secondary pressure-reducing valve installed on a valve block body, the secondary pressure-reducing valve comprises a valve body, a first valve core and a diaphragm partition plate installed in the valve body, and a compression nut, the diaphragm partition plate is compressed towards the first valve core by the compression nut, the compression nut is connected with a first adjusting nut, an elastic component is arranged between the first adjusting nut and the diaphragm partition plate, and rolling bodies are arranged between the two ends of the elastic component and the first adjusting nut and the diaphragm partition plate respectively. On one hand, the functional elements are integrated and installed in one body through the valve block body, external connecting pipelines are saved, the system integration is greatly improved, the volume and weight of the module are reduced, and the leakage risk is lowered; on the other hand, the pressure is reduced through the two-stage pressure-reducing valve, the single-stage pressure-reducing ratio is lowered, the elastic component does not produce circumferential torsional deformation in the adjusting process through the rolling bodies, the outlet pressure fluctuation caused by the torsional stress release of the elastic component is effectively eliminated, and the high-precision stable output of the outlet pressure under the large pressure-reducing ratio working condition is realized.

Description

Technical Field

[0001] This invention relates to the field of flow control technology, and more particularly to an integrated decompression flow control module for a satellite Hall thruster system. Background Technology

[0002] Hall effect electric propulsion systems, due to their advantages such as simple structure, high specific impulse, and high thrust-to-power ratio, have been widely used in spacecraft orbit maintenance, orbit transfer, attitude control, and deep space exploration missions. The propellant storage and supply system is one of the three core modules of a Hall effect electric propulsion system. It plays a crucial role in depressurizing the high-pressure stored propellant (xenon or krypton) to the pressure required by the thruster and precisely controlling the flow rate. Its performance directly determines the reliability of satellite orbit maintenance and attitude control, as well as its full life-cycle service capability.

[0003] Currently, the storage and supply unit of a satellite Hall thruster system typically consists of a storage module, a pressure regulation module, and a flow regulation module, with these modules connected sequentially via stainless steel pipes and standard compression fittings. This discrete piping connection architecture, inherited from chemical propulsion systems, has the following shortcomings in practical engineering applications:

[0004] 1. Excessive system weight and size: Traditional storage and supply systems employ a layout of discrete, interconnected units via pipelines. Components such as valves, sensors, and pressure reducing valves are scattered and require numerous pipes and connectors for connection. Due to the variety and large number of components, miniaturization is difficult, which not only occupies the satellite's extremely limited payload space but also significantly increases launch costs.

[0005] 2. High risk of leakage and low reliability: Discrete piping connections involve a large number of pipe joints and welded interfaces, with a single system typically having more than 20 leakage points. The welding and assembly process also carries the risk of high temperatures causing valve core deformation or even melting. Each interface is a potential on-orbit leak hazard, and since maintenance cannot be performed while the satellite is in orbit, any leak could lead to premature propellant depletion and mission failure.

[0006] 3. Insufficient pressure control accuracy: Traditional mechanical storage and supply systems typically use a single-stage mechanical pressure reducing valve as the pressure reducing element, setting the outlet pressure by adjusting the spring pre-compression. However, under high pressure reduction ratio conditions, the outlet pressure of a single-stage pressure reducing valve is easily affected by inlet pressure fluctuations and spring characteristics, resulting in limited control accuracy. Existing solutions often require additional buffer cylinders or electronic feedback control to stabilize the pressure, further increasing system complexity and weight.

[0007] 4. Limited lifespan of solenoid valves: Solenoid valves in storage and supply systems require high-frequency operation in orbit, with their armature assemblies undergoing high-frequency reciprocating motion. In traditional designs, the radial limiting of the armature assembly is directly achieved by the coil frame. Stainless steel materials lack sufficient wear resistance during long-term reciprocating motion, easily leading to increased clearance and seal failure. Furthermore, the impact generated by the valve core and seat during each closure accelerates valve core wear, limiting the on-orbit service life of the solenoid valve. Summary of the Invention

[0008] To address the aforementioned technical problems, this invention proposes an integrated depressurization flow control module for satellite Hall thruster systems. This module solves the problem in existing Hall thruster systems where, under high depressurization ratio conditions, the outlet pressure is easily affected by inlet pressure fluctuations and the torsional stress of the elastic element itself, resulting in poor outlet pressure stability and insufficient control accuracy.

[0009] To achieve the above objectives, the technical solution of the present invention is implemented as follows:

[0010] An integrated pressure-reducing flow control module for a satellite Hall thruster system includes a valve block body, a primary pressure-reducing valve and a secondary pressure-reducing valve mounted on and connected to the valve block body. The secondary pressure-reducing valve includes a valve body, a first valve core and a diaphragm partition mounted in the valve body, and a clamping nut. The clamping nut presses the diaphragm partition against the end face of the first valve core. A first adjusting nut is connected to the end of the clamping nut away from the first valve core. An elastic component is provided between the first adjusting nut and the diaphragm partition. Rolling elements are provided at both ends of the elastic component between the first adjusting nut and the diaphragm partition, so that the elastic component does not rotate when the first adjusting nut is rotated. This invention employs the aforementioned structure. On one hand, it integrates functional components into a single unit via the valve block body, eliminating the need for external connecting pipelines, significantly improving system integration, reducing module size and weight, and lowering leakage risk. On the other hand, it achieves two-stage pressure reduction by connecting a second-stage pressure reducing valve in series with the first-stage pressure reducing valve, reducing the single-stage pressure reduction ratio and improving pressure reduction stability. Simultaneously, a rolling element is installed in the second-stage pressure reducing valve to isolate the rotational movement of the first adjusting nut from the elastic component, ensuring that the elastic component undergoes only axial compression deformation without circumferential torsional deformation during adjustment. This effectively eliminates outlet pressure fluctuations caused by the release of torsional stress in the elastic component, achieving high-precision and stable outlet pressure output under high pressure reduction ratio conditions without the need for a gas chamber or electronic feedback control.

[0011] Furthermore, in order to refine the specific composition of the elastic component and the number and positional relationship of the rolling elements, the first adjusting nut and the diaphragm partition are in point contact with the corresponding rolling elements; the rolling elements include a first rolling element and a second rolling element, and the elastic component includes a first spring seat, a pressure adjusting spring and a second spring seat. One end of the pressure adjusting spring abuts against the first rolling element through the first spring seat, and the other end of the pressure adjusting spring abuts against the second rolling element through the second spring seat.

[0012] Furthermore, in order to further define the specific type of the rolling element and ensure the installation stability of the rolling element during the adjustment process, the first rolling element is a first steel ball, the second rolling element is a second steel ball, the first spring seat is provided with a limiting groove for installing the first steel ball, and the second spring seat is provided with a limiting groove for installing the second steel ball.

[0013] Furthermore, in order to ensure the reliability of the installation of the first valve core on the valve body, the first valve core is fixed to the valve body by the second adjusting nut.

[0014] Furthermore, to clarify the complete composition of the entire pressure-reducing flow control module and its connection relationship in the system, it also includes an inflation valve, a self-locking valve, a solenoid valve, a high-pressure sensor, and a low-pressure sensor installed on the valve block body. The valve block body is located between the gas cylinder and the gas supply outlet. The outlet of the gas cylinder is connected to the gas supply outlet in sequence via the high-pressure sensor, the self-locking valve, the first-stage pressure-reducing valve, the second-stage pressure-reducing valve, the solenoid valve, and the low-pressure sensor. A branch is provided on the pipeline between the gas cylinder and the self-locking valve, and an inflation valve is provided on the branch. The inflation valve is used to connect to the gas source. The inflation valve, the self-locking valve, the first-stage pressure-reducing valve, the second-stage pressure-reducing valve, and the solenoid valve are all installed on the valve block body with a cartridge structure. A sealing structure is provided between each valve and the mounting hole of the valve block body.

[0015] Furthermore, in order to extend the service life of the solenoid valve and reduce the impact of the valve core, the solenoid valve includes a coil frame, a magnetic drive component movably disposed within the coil frame, and an interface assembly connected to the end of the coil frame. One end of the magnetic drive component abuts against the coil frame via a spring, and the other end is connected to a second valve core. The second valve core cooperates with the valve port of the interface assembly. The magnetic drive component is used to drive the movement of the second valve core by electromagnetic force to control the flow of fluid within the interface assembly. A buffer component is sleeved on the magnetic drive component to absorb impact energy when the magnetic drive component resets.

[0016] Furthermore, in order to ensure the sensitivity of the solenoid valve's operation and avoid obstruction due to excessive pressure difference between the two ends during movement, the coil frame includes a first section and a second section arranged sequentially along the axial direction. The inner diameter of the first section is smaller than the inner diameter of the second section. The magnetic drive component is embedded in the first section and fits with the first section with a gap. The magnetic drive component is provided with a transverse through hole and an axial through hole. One end of the axial through hole is connected to the transverse through hole, and the other end is connected to the cavity where the spring is located. The transverse through hole is connected to the gap.

[0017] Furthermore, in order to refine the assembly position relationship of each part inside the solenoid valve and to achieve a wear reduction effect, the magnetic drive component includes a large-diameter section partially embedded in the first section and a small-diameter section located in the second section; the solenoid valve also includes a pressure block, which is sleeved on the small-diameter section, and a buffer is clamped between the end face of the pressure block and the large-diameter section. The second valve core is pressed and fixed inside the pressure block by a pressure ring; a wear-resistant part is sleeved on the outer periphery of the pressure ring, and a sleeve is provided between the outer periphery of the wear-resistant part and the inner wall of the second section of the coil frame.

[0018] Furthermore, to ensure the reliable fixation of the second valve core within the pressure block, the second valve core is T-shaped, and an annular platform is provided on the inner side of the pressure block to limit one end of the second valve core. A pressure ring is fitted onto the other end of the second valve core to press the second valve core against the driving component.

[0019] Furthermore, in order to further define the specific types of the magnetic drive component, buffer component, and wear-resistant component and ensure the friction reduction effect, the magnetic drive component is an armature, the buffer component is a spring, and the wear-resistant component is a polyimide friction-reducing ring. When the drive component moves, it only contacts and rubs against the friction-reducing ring.

[0020] The beneficial effects of this invention are:

[0021] 1. This invention incorporates an elastic component in a two-stage pressure reducing valve, with rolling elements positioned between the elastic component and the first adjusting nut and diaphragm partition at both ends. This ensures point contact between the first adjusting nut and diaphragm partition and the corresponding rolling elements. When the first adjusting nut rotates, the rolling elements isolate the rotational motion on one side of the first adjusting nut, preventing the elastic component from rotating. The pressure regulating spring undergoes only axial compression deformation without circumferential torsional deformation, eliminating outlet pressure fluctuations caused by the release of spring torsional stress. This achieves a high-precision, stable outlet pressure of 50±2.5 kPa without the need for a gas chamber or electronic feedback control.

[0022] 2. This invention integrates the inflation valve, self-locking valve, primary pressure reducing valve, secondary pressure reducing valve, and solenoid valve into the valve block body using a cartridge-type structure. The functional components are fluidly connected through the internal flow channels inside the valve block body, eliminating the need for external connecting pipelines and significantly improving system integration. Compared to the traditional discrete pipeline connection architecture, the volume is reduced by approximately 60%, the weight is reduced by approximately 45%, and the installation efficiency is increased by approximately 80%, effectively saving satellite payload space and launch costs.

[0023] 3. This invention integrates and installs various functional components in the valve block body and achieves fluid communication through internal flow channels, replacing a large number of external pipes and pipe joints in the traditional solution. The number of leakage points is reduced from more than 20 in the traditional solution to no more than 8, which significantly reduces the risk of on-orbit leakage and improves the reliability and safety of the satellite storage and supply system.

[0024] 4. This invention incorporates wear-resistant components within the solenoid valve, ensuring that the magnetic drive component only contacts and rubs against these components during movement, preventing direct contact wear between the magnetic drive component and the coil frame. The wear-resistant components are made of polyimide material, which possesses excellent wear resistance and self-lubricating properties, effectively improving the wear resistance and service life of the moving parts.

[0025] 5. This invention provides a buffer component that is fitted over the magnetic drive component of the solenoid valve. The buffer component is sandwiched between the pressure block and the end face of the large-diameter section of the magnetic drive component. During the reset process of the magnetic drive component, the buffer component absorbs the impact energy, effectively reducing the impact between the second valve core and the valve port of the interface assembly. This avoids premature failure of the valve core due to frequent impacts. In synergy with the wear-resistant component, the lifespan of the solenoid valve can reach 10 million cycles.

[0026] 6. This invention sets a first section with a smaller inner diameter and a second section with a larger inner diameter in the coil frame. The magnetic drive component is embedded in the first section and fits with the gap in the first section. A transverse through hole and an axial through hole are set on the magnetic drive component. One end of the axial through hole is connected to the transverse through hole and the other end is connected to the cavity where the spring is located. The transverse through hole is connected to the gap, so that gas can enter the gap through the transverse through hole and the axial through hole, which plays a role in pressure balance. This avoids the magnetic drive component from being blocked due to excessive pressure difference at both ends when it moves, and ensures the sensitivity and reliability of the solenoid valve.

[0027] 7. This invention employs a purely mechanical two-stage pressure reduction scheme using a primary pressure reducing valve and a secondary pressure reducing valve connected in series. The primary pressure reducing valve reduces the inlet 10MPa high-pressure gas to 0.5MPa, and the secondary pressure reducing valve further reduces the 0.5MPa gas to 50KPa. It requires no external pipeline connection, no gas chamber, and no electronic feedback control, making it simple and reliable in structure and suitable for the long-term unattended use of satellites in orbit. Attached Figure Description

[0028] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0029] Figure 1 This is a schematic diagram illustrating the principle of the present invention.

[0030] Figure 2 This is a schematic diagram of the structure of the present invention.

[0031] Figure 3 This is a schematic diagram of the structure of the two-stage pressure reducing valve of the present invention.

[0032] Figure 4This is a schematic diagram of the structure of the solenoid valve of the present invention.

[0033] Figure 5 This is a partial structural schematic diagram of the solenoid valve of the present invention. Detailed Implementation

[0034] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0035] The integrated pressure-reducing flow control module for a satellite Hall thruster system, as described in Embodiment 1 of the present invention, includes a valve block body 1, a primary pressure-reducing valve 4 and a secondary pressure-reducing valve 7 mounted on the valve block body 1. The outlet of the primary pressure-reducing valve 4 is connected to the inlet of the secondary pressure-reducing valve 7.

[0036] like Figure 3 As shown, the valve body 79 of the two-stage pressure reducing valve 7 has two internal cavities. A first valve core 710 is installed in the first cavity of the valve body 79. Specifically, this cavity of the valve body 79 has an internally threaded hole, into which the first valve core 710 is threaded and secured by a second adjusting nut 711. The first valve core 710 extends axially along the valve body 79, and its end face passes through a partition between the two cavities, with a clearance fit between the end face of the first valve core 710 and the partition. The second cavity of the valve body 79 also has internal threads, and a clamping nut 78 is threaded into the second cavity of the valve body 79. During installation, first, place the diaphragm partition 77 from the second cavity into the valve body 79, close to the partition. Then, screw in the clamping nut 78. The end face of the clamping nut 78 presses the diaphragm partition 77 tightly, forming a sealing fit between the diaphragm partition 77 and the end face of the first valve core 710. The diaphragm partition 77 can undergo axial elastic deformation under gas pressure. At the same time, the clamping nut 78 seals the second cavity of the valve body 79.

[0037] like Figure 3 As shown, the end of the clamping nut 78 away from the first valve core 710 has an internal threaded hole, and the first adjusting nut 71 is threaded into this internal threaded hole. The first adjusting nut 71 is a cylindrical structure with a closed top, and its outer wall mates with the internal thread of the clamping nut 78, while its inner cavity accommodates part of the elastic component. Furthermore, the top of the first adjusting nut 71 is provided with a hexagonal blind hole to facilitate the rotation and adjustment of the first adjusting nut 71.

[0038] like Figure 3As shown, an elastic component is disposed inside the clamping nut 78, within the space between the first adjusting nut 71 and the diaphragm partition 77. In this embodiment, the elastic component includes a first spring seat 73, a pressure adjusting spring 74, and a second spring seat 75, arranged sequentially along the axial direction. A limiting groove is machined on the end face of the first spring seat 73 facing the first adjusting nut 71 to accommodate a first steel ball 72. The first steel ball 72 is disposed between the first adjusting nut 71 and the limiting groove of the first spring seat 73, making point contact with the first adjusting nut 71. A limiting groove is also machined on the end face of the second spring seat 75 facing the diaphragm partition 77 to accommodate a second steel ball 76. The second steel ball 76 is disposed between the spherical groove of the second spring seat 75 and the diaphragm partition 77, making point contact with the diaphragm partition 77. The pressure adjusting spring 74 is a helical compression spring, with its two ends abutting against the inner end faces of the first spring seat 73 and the second spring seat 75, respectively, changing the compression amount through the axial displacement of the first spring seat 73 and the second spring seat 75.

[0039] When adjusting the outlet pressure, the first adjusting nut 71 is rotated. The internal thread of the first adjusting nut 71 engages with the external thread of the clamping nut 78, converting the rotational motion into axial feed motion. The end face of the first adjusting nut 71 pushes the first steel ball 72, which in turn pushes the first spring seat 73. Since the first steel ball 72 has point contact with both the first adjusting nut 71 and the first spring seat 73, the frictional resistance is extremely small. When the first adjusting nut 71 rotates, the first steel ball 72 only rolls or slides slightly, and the first spring seat 73 is only subjected to axial thrust and not circumferential torsional torque, therefore it does not rotate with the first adjusting nut 71. Similarly, the diaphragm diaphragm 77 only undergoes axial displacement during operation, and it also has point contact with the second spring seat 75 via the second steel ball 76. The second spring seat 75 is only subjected to axial force and not circumferential torsional torque. The two ends of the pressure adjusting spring 74 are fixedly in contact with the first spring seat 73 and the second spring seat 75, respectively. Since neither spring seat rotates, the pressure adjusting spring 74 only undergoes axial deformation during compression and rebound, without circumferential torsional deformation. In this embodiment, as... Figure 3As shown, the first valve core 710 has an axial inlet at its center and an outlet off-center on the valve body. A portion of the first valve core 710 near the partition has a gap between its outer periphery and the first cavity section. A radial through-hole is located near the partition of the first valve core 710, allowing the medium entering through the inlet to enter the gap between the first valve core 710 and the first cavity section. The front end of the first valve core 710 passes through a through-hole in the partition via a smaller head. The front end of the head is convex, and when it mates with the diaphragm partition 77, a certain gap exists between the diaphragm partition 77 and the partition, and this gap communicates with the outlet. A sealing ring is located on the shoulder of the first valve core 710 at the outer periphery of the head; an annular protrusion extending towards the shoulder is located near the through-hole, and this annular protrusion, in conjunction with the sealing ring on the shoulder, forms an air passage, allowing gas in the gap between the first valve core 710 and the first cavity section to enter the gap between the first valve core head and the partition through the air passage, and then enter the outlet from the gap between the diaphragm partition 77 and the partition. The opening size of the air passage can be changed by adjusting the axial position of the first valve core 710 through the pressure adjusting spring 74.

[0040] In this embodiment, the diaphragm partition 77 adopts a composite structure of pressure-resistant rubber and metal skeleton. Its central area can generate elastic displacement under gas pressure. Through the second steel ball 76, it acts on the second spring seat 75, forming a force balance with the elastic force of the pressure regulating spring 74. When the outlet pressure of the secondary pressure reducing valve 7 increases, the diaphragm partition 77 protrudes towards the first adjusting nut 71, pushing the second steel ball 76 and the second spring seat 75 to compress the pressure regulating spring 74, thereby reducing the airflow passage at the shoulder of the first valve core 710 and causing the outlet pressure to drop. Conversely, when the outlet pressure decreases, the pressure regulating spring 74 pushes the second spring seat 75, the second steel ball 76, and the diaphragm partition 77 towards the first valve core 710, increasing the ventilation cross-sectional area and causing the outlet pressure to rise again.

[0041] Tests have verified that the two-stage pressure reducing valve 7 with the structure of this embodiment can stably control the outlet pressure within the range of 50±2.5KPa under the conditions of inlet pressure of 0.5MPa and outlet flow rate of 3~4ml / min, without the need to set up a gas chamber and electronic feedback control.

[0042] As an alternative, the limiting grooves on the end face of the first adjusting nut 71 and the end face of the first spring seat 73 can also be replaced with spherical grooves.

[0043] Example 2 differs from Example 1 in that, as Figure 1 As shown, the valve block body 1 is located between the gas cylinder 9 and the gas supply outlet. The valve block body 1 is made of high-strength aluminum alloy, and its interior is machined with several internal flow channels for fluid communication. Figure 2As shown, the inflation valve 6, the self-locking valve 3, the first-stage pressure reducing valve 4, the second-stage pressure reducing valve 7, the solenoid valve 8, the high-pressure sensor 2, and the low-pressure sensor 5 are all installed on the valve block body 1.

[0044] like Figure 1 As shown, the outlet of gas cylinder 9 is connected to the gas supply outlet via a series of interconnected components: high-pressure sensor 2, self-locking valve 3, primary pressure reducing valve 4, secondary pressure reducing valve 7, solenoid valve 8, and low-pressure sensor 5. The high-pressure sensor 2 is located on the pipeline between gas cylinder 9 and self-locking valve 3 to detect the output pressure of gas cylinder 9. The low-pressure sensor 5 is located on the pipeline between secondary pressure reducing valve 7 and solenoid valve 8 to detect the pressure of the gas after pressure reduction.

[0045] like Figure 1 As shown, a branch line is also provided on the pipeline between the gas cylinder 9 and the self-locking valve 3. The branch line is equipped with an inflation valve 6, which is used to connect to an external gas source. During inflation, the external gas source injects high-pressure propellant into the gas cylinder 9 through the inflation valve 6, and the high-pressure sensor 2 monitors the pressure value inside the gas cylinder 9 in real time.

[0046] The various functional components are fluidly connected through internal flow channels within the valve block body 1, eliminating the need for external piping. The internal flow channels on the valve block body 1 are machined using deep-hole drilling, with rounded transitions at bends to reduce fluid resistance. Each valve on the valve block body 1 has a locally raised boss at its mounting position, and each valve is secured to its corresponding raised boss with screws.

[0047] The self-locking valve 3 is a normally closed self-holding valve. It remains open when energized and closed when de-energized. Its function is to isolate the high-pressure gas in the gas cylinder 9 without consuming electrical energy, preventing the high-pressure gas from directly affecting the downstream components when the pressure reducing valve malfunctions.

[0048] In this embodiment, the primary pressure reducing valve 4 reduces the high-pressure gas output from the gas cylinder 9 from 10 MPa to 0.5 MPa, and the secondary pressure reducing valve 7 further reduces the 0.5 MPa gas to 50 kPa. The solenoid valve 8 is used to control the on / off state of the reduced gas, thereby achieving fine regulation of the gas supply.

[0049] Compared to traditional discrete piping connection architecture, this module is about 60% smaller in size, about 45% lighter, and the number of leakage points is reduced from more than 20 in the traditional solution to no more than 8.

[0050] Example 3 differs from Example 1 in that the inflation valve 6, self-locking valve 3, primary pressure reducing valve 4, secondary pressure reducing valve 7, and solenoid valve 8 are all mounted on the valve block body 1 using a cartridge-type structure. Specifically, the valve block body 1 has mounting holes corresponding to each valve, and each valve housing has a cartridge part that mates with the mounting hole. The cartridge part is inserted into the corresponding mounting hole and fixedly connected to the valve block body 1 by screws.

[0051] Each valve is provided with a sealing structure between its mounting hole and the valve body 1. The sealing structure uses an O-ring seal, which is embedded in the sealing groove on the outer circumference of the valve body. When the valve is inserted into the mounting hole, the O-ring seal is pressed between the valve body and the inner wall of the mounting hole to achieve radial sealing.

[0052] The cartridge-type structure allows for quick removal and installation of each valve from the valve block body 1 without disassembling other components on the valve block body 1. Furthermore, the mounting holes for each valve are machined from the same or opposite sides of the valve block body 1, facilitating mass production and assembly.

[0053] Example 4 differs from Example 2 in that, as Figure 4 , Figure 5 As shown, the solenoid valve 8 includes a coil frame 81, a magnetic drive 82 movably disposed within the coil frame 81, and an interface assembly 85 connected to the end of the coil frame 81. One end of the magnetic drive 82 abuts against the coil frame 81 via a spring 89, and the other end is connected to a second valve core 86. The second valve core 86 engages with the valve port of the interface assembly 85, and the magnetic drive 82 is used to drive the second valve core 86 to move under electromagnetic force to control the flow of fluid within the interface assembly 85. In this embodiment, the interface assembly 85 has an axially extending outlet at its center and an inlet parallel to the axial direction at a position off-center; a cone-shaped part that engages with the end of the second valve core 86 and a groove surrounding the center are located at the center of the end face of the interface assembly 85 near the second valve core 86. The groove communicates with the inlet; the cone-shaped part has an axially narrow flow channel that communicates with the outlet. When there is a gap between the second valve core 86 and the valve port of the interface assembly 85, fluid can enter the narrow flow channel from the groove and then enter the outlet.

[0054] like Figure 4 As shown, the coil frame 81 has a stepped hole structure, comprising a first section and a second section arranged sequentially along the axial direction, with the inner diameter of the first section being smaller than that of the second section. The magnetic drive component 82 is embedded in the first section and has a clearance fit with it. The magnetic drive component 82 has a transverse through hole and an axial through hole. One end of the axial through hole communicates with the transverse through hole, and the other end communicates with the cavity where the spring 89 is located. The transverse through hole communicates with the clearance.

[0055] Furthermore, the magnetic drive component 82 includes a large-diameter section partially embedded in the first segment and a small-diameter section located in the second segment. The clearance fit between the large-diameter section and the first segment of the coil frame 81 is a small-clearance fit, ensuring that the magnetic drive component 82 moves smoothly along the axial direction without radial movement. A positioning groove for mounting the spring 89 is also machined on the large-diameter section.

[0056] like Figure 4 and Figure 5 As shown, the solenoid valve 8 also includes a pressure block 87, which is fitted onto the small-diameter section of the magnetic drive member 82. A portion of the inner side of the pressure block 87 precisely fits the small-diameter section of the magnetic drive member 82, while another portion has an enlarged inner cavity for accommodating the second valve core 86. The second valve core 86 is pressed and fixed inside the pressure block 87 by a pressure ring 810. A buffer member 88 is clamped between the pressure block 87 and the end face of the large-diameter section of the magnetic drive member 82.

[0057] A wear-resistant part 84 is fitted around the outer periphery of the pressure block 87. A sleeve 83 is provided between the outer periphery of the wear-resistant part 84 and the inner wall of the second section of the coil frame 81. The sleeve 83 is a cylindrical thin-walled part. Its inner wall fits against the outer periphery of the wear-resistant part 84, and its outer wall fits against the inner wall of the second section of the coil frame 81, fixing the wear-resistant part 84 between the pressure block 87 and the coil frame 81, ensuring that the wear-resistant part 84 does not move axially during the operation of the solenoid valve 8.

[0058] Among them, the outer periphery of the wear-resistant part 84 is provided with a small groove, which allows the fluid in the groove of the interface component end face to enter the stepped hole, and enter the gap between the magnetic drive part 82 and the first section through the transverse through hole and the axial through hole, so as to play a pressure balancing role and prevent the magnetic drive part 82 from being blocked due to the excessive pressure difference between the two ends when it moves.

[0059] Preferably, the magnetic drive component 82 is an armature. The buffer component 88 is a spring. The wear-resistant component 84 is a polyimide friction-reducing ring. A fitting gap is provided between the magnetic drive component 82 and the coil frame 81 to ensure that they do not come into contact during movement. Friction and wear during movement are completely transferred between the magnetic drive component 82 and the friction-reducing ring. Polyimide material has excellent wear resistance and self-lubricating properties, and the fitting gap between the magnetic drive component 82 and the friction-reducing ring is precisely controlled through the matching process, effectively improving the wear resistance and service life of the moving pair.

[0060] Furthermore, the second valve core 86 is T-shaped. The annular platform at the end of the expanded inner cavity of the pressure block 87 is used to limit one end of the second valve core 86. The pressure ring 810 is sleeved on the other end of the second valve core 86 to press the second valve core 86 against the magnetic drive member 82.

[0061] The working process of solenoid valve 8 is as follows:

[0062] In the initial state, the solenoid valve 8 is not energized, the spring 89 pushes the magnetic drive 82 to move towards the interface assembly 85, the magnetic drive 82 pushes the second valve core 86 to press against the valve port of the interface assembly 85, and the valve is in the closed state.

[0063] When the coil is energized, an electromagnetic force is generated that attracts the magnetic drive 82 to move into the coil frame 81, that is, to move towards the spring 89. The magnetic drive 82 compresses the spring 89, and the second valve core 86 moves away from the valve port as the magnetic drive 82 moves, the valve opens, and the gas flows out through the interface assembly 85.

[0064] When the coil is de-energized, the electromagnetic force disappears, the spring 89 pushes the magnetic drive 82 to reset, the second valve core 86 re-tightens against the valve port of the interface assembly 85, and the valve closes.

[0065] During the high-frequency operation of the solenoid valve 8, there is relative movement between the magnetic drive component 82 and the inner wall of the coil frame 81. The anti-friction ring radially limits the magnetic drive component 82, preventing direct contact and friction between it and the inner wall of the coil frame 81. Simultaneously, the second valve core 86 is fixed to the small-diameter section of the magnetic drive component 82 by the pressure block 87 and the pressure ring 810, while the buffer component 88 is clamped between the pressure block 87 and the end face of the large-diameter section of the magnetic drive component 82. During the reset process of the magnetic drive component 82, the buffer component 88 absorbs impact energy, effectively reducing the impact between the second valve core 86 and the valve port of the interface assembly 85, thereby extending the service life of the valve core.

[0066] Example 5, as a parallel solution to Example 4, also shows that the wear-resistant part 84 can be made of polytetrafluoroethylene (PTFE) or polyetheretherketone (PEEK). PTFE has a lower coefficient of friction, making it suitable for low-power solenoid valve applications; PEEK has higher temperature resistance and mechanical strength, making it suitable for high-temperature or high-frequency applications.

[0067] As another alternative embodiment 4, the buffer 88 is not limited to using a reed; it can also be a wave spring or a disc spring. Wave springs and disc springs have the advantage of smaller axial dimensions, making them suitable for solenoid valve structures with limited axial installation space.

[0068] Example 6, as a parallel solution to Example 1, shows that the elastic component is not limited to a combination of a helical compression spring and a spring seat; a disc spring or a wave spring can also be used to achieve the elastic force application function. When a disc spring is used, its two ends also make point contact with the first adjusting nut 71 and the diaphragm partition 77 respectively through rolling elements to prevent spring torsion. Disc springs have the advantages of small axial dimensions, high stiffness, and wide adjustment range, making them suitable for applications with limited installation space.

[0069] Example 7 differs from Example 1 in that the valve block body 1 is made of a high thermal conductivity aluminum alloy, and a closed cavity is machined inside the valve block body 1 near the pressure regulating spring 74 of the secondary pressure reducing valve 7. This closed cavity is filled with a phase change material. The phase change material can be paraffin wax, with a phase change temperature range of 20°C to 40°C. When the satellite experiences alternating high and low temperatures in orbit, the phase change material, through the process of melting and absorbing heat and solidifying and releasing heat, slows down the rate of temperature change of the valve block body 1. This allows the pressure regulating spring 74 and the diaphragm diaphragm 77 of the secondary pressure reducing valve 7 to operate in a relatively stable temperature environment, further reducing the temperature drift of the outlet pressure.

[0070] The pressure regulating spring 74 is made of a constant elasticity alloy material, such as 3J53 alloy, which has a modulus of elasticity change rate of less than 5% over a temperature range of -40°C to 80°C. The constant elasticity alloy spring, in conjunction with phase change thermal storage measures, ensures the stability of the outlet pressure over a wide temperature range.

[0071] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that any modifications to the technical solutions described in the foregoing embodiments, or equivalent substitutions of some or all of the technical features thereof, within the spirit and principles of the present invention, do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention, and should all be included within the protection scope of the present invention.

Claims

1. An integrated decompression flow control module for a satellite Hall thruster system, characterized in that, It includes a valve block body (1), a primary pressure reducing valve (4) and a secondary pressure reducing valve (7) installed on and connected to the valve block body (1). The secondary pressure reducing valve (7) includes a valve body (79), a first valve core (710) and a diaphragm partition (77) installed in the valve body (79), and a clamping nut (78). The clamping nut (78) presses the diaphragm partition (77) against the end face of the first valve core (710). A first adjusting nut (71) is connected to one end of the clamping nut (78) away from the first valve core (710). An elastic component is provided between the first adjusting nut (71) and the diaphragm partition (77). Rolling elements are provided between the two ends of the elastic component and the first adjusting nut (71) and the diaphragm partition (77), so that the elastic component does not rotate when the first adjusting nut (71) is rotated.

2. The integrated depressurization flow control module for a satellite Hall thruster system according to claim 1, characterized in that, The first adjusting nut (71) and the diaphragm partition (77) are in point contact with the corresponding rolling element; the rolling element includes a first rolling element and a second rolling element, and the elastic component includes a first spring seat (73), a pressure adjusting spring (74) and a second spring seat (75). One end of the pressure adjusting spring (74) abuts against the first rolling element through the first spring seat (73), and the other end of the pressure adjusting spring (74) abuts against the second rolling element through the second spring seat (75).

3. The integrated decompression flow control module for a satellite Hall thruster system according to claim 2, characterized in that, The first rolling element is a first steel ball (72), and the second rolling element is a second steel ball (76); the first spring seat (73) is provided with a limiting groove for installing the first steel ball (72), and the second spring seat (75) is provided with a limiting groove for installing the second steel ball (76).

4. The integrated depressurization flow control module for a satellite Hall thruster system according to claim 2 or 3, characterized in that, The first valve core (710) is fixed to the valve body (79) by the second adjusting nut (711).

5. The integrated decompression flow control module for a satellite Hall thruster system according to any one of claims 1 to 3, characterized in that, It also includes an inflation valve (6), a self-locking valve (3), a solenoid valve (8), a high-pressure sensor (2), and a low-pressure sensor (5) installed on the valve block body (1); the valve block body (1) is located between the gas cylinder (9) and the gas supply outlet, and the outlet of the gas cylinder (9) is connected to the gas supply outlet in sequence via the high-pressure sensor (2), the self-locking valve (3), the first-stage pressure reducing valve (4), the second-stage pressure reducing valve (7), the solenoid valve (8), and the low-pressure sensor (5); a branch is provided on the pipeline between the gas cylinder (9) and the self-locking valve (3), and the inflation valve (6) is provided on the branch. The inflation valve (6) is used to connect to the gas source; the inflation valve (6), the self-locking valve (3), the first-stage pressure reducing valve (4), the second-stage pressure reducing valve (7), and the solenoid valve (8) are all installed on the valve block body (1) with a cartridge structure, and a sealing structure is provided between each valve and the mounting hole of the valve block body (1).

6. The integrated decompression flow control module for a satellite Hall thruster system according to claim 5, characterized in that, The solenoid valve (8) includes a coil frame (81), a magnetic drive (82) movably disposed within the coil frame (81), and an interface assembly (85) connected to the end of the coil frame (81). One end of the magnetic drive (82) abuts against the coil frame (81) via a spring (89), and the other end is connected to a second valve core (86). The second valve core (86) cooperates with the valve port of the interface assembly (85). The magnetic drive (82) is used to drive the movement of the second valve core (86) by electromagnetic force to control the flow of fluid in the interface assembly (85). A buffer (88) is sleeved on the magnetic drive (82) to absorb impact energy when the magnetic drive (82) is reset.

7. The integrated depressurization flow control module for a satellite Hall thruster system according to claim 6, characterized in that, The coil frame (81) includes a first section and a second section arranged sequentially along the axial direction. The inner diameter of the first section is smaller than that of the second section. The magnetic drive (82) is embedded in the first section and fits with the gap of the first section. The magnetic drive (82) is provided with a transverse through hole and an axial through hole. One end of the axial through hole is connected to the transverse through hole and the other end is connected to the cavity where the spring (89) is located. The transverse through hole is connected to the gap.

8. The integrated decompression flow control module for a satellite Hall thruster system according to claim 7, characterized in that, The magnetic drive component (82) includes a large-diameter section partially embedded in the first section and a small-diameter section located in the second section; the solenoid valve (8) also includes a pressure block (87), the pressure block (87) is sleeved on the small-diameter section, the buffer (88) is clamped between the pressure block (87) and the end face of the large-diameter section, and the second valve core (86) is pressed and fixed inside the pressure block (87) by a pressure ring (810); a wear-resistant component (84) is sleeved on the outer periphery of the pressure ring (810), and a sleeve (83) is provided between the outer periphery of the wear-resistant component (84) and the inner wall of the second section of the coil frame (81).

9. The integrated decompression flow control module for a satellite Hall thruster system according to claim 8, characterized in that, The second valve core (86) is T-shaped. The inner side of the pressure block (87) is provided with a ring platform for limiting one end of the second valve core (86). The pressure ring (810) is sleeved on the other end of the second valve core (86) to press the second valve core (86) against the drive member (82).

10. The integrated decompression flow control module for a satellite Hall thruster system according to claim 8 or 9, characterized in that, The magnetic drive component (82) is an armature; the buffer component (88) is a spring; the wear-resistant component (84) is a polyimide friction-reducing ring; and the drive component (82) only contacts and rubs against the friction-reducing ring when it moves.

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