Propellant filling device

Abstract

The application belongs to the field of spacecraft and provides a propellant filling device, which comprises a containing device provided with a movement cavity, a containing cavity and a limiting cavity which are sequentially communicated, a valve core penetrating through the movement cavity, the containing cavity and the limiting cavity, a main body section of the valve core comprising a blind hole at one end towards the limiting cavity, a plurality of through holes at the middle part, a boss at the other end, an extension section connected with the boss at one end and provided with an end head at the other end, a valve seat movably sleeved on the valve core and movable in the movement cavity, one end of the valve seat towards the limiting cavity and abutting against the boss, the other end of the valve seat sealably matched with the end head, an elastic member fixed at one end of the containing cavity and connected with one end of the valve seat, and the end head and the valve seat sealing the outlet of the movement cavity together when the elastic member is in the stretched state. When filling, only an external force is needed to be applied to the valve seat to make the valve seat and the valve core sealably matched; when the filling is finished, only the external force is needed to be removed to seal the containing device, so that the rapid filling is realized and exposure to the toxic environment is avoided.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft, and particularly relates to a propellant loading device. Background Technology

[0002] Attitude and orbit control propulsion systems are an important component of various spacecraft. Among them, liquid attitude and orbit control propulsion systems use liquid propellants as energy, and the refueling of propellants usually needs to be carried out on the ground.

[0003] Because propellants are toxic and hazardous substances with explosive properties, posing an extremely high risk, strict measures must be taken to prevent leaks during propellant loading. Furthermore, many propellants are stored and loaded at cryogenic temperatures, and the loading volume is typically large, necessitating rapid loading to prevent temperature fluctuations.

[0004] Therefore, there is an urgent need to develop a refueling device that is fast and leak-proof in order to solve the above-mentioned technical problems. Summary of the Invention

[0005] This invention provides a propellant loading device for a liquid orbital attitude control propulsion system, aiming to solve the problems of slow loading speed and easy leakage in existing propellant loading devices.

[0006] In a first aspect, the present invention provides a propellant loading device for a liquid orbital attitude control propulsion system, comprising:

[0007] A container is provided with a motion cavity, a receiving cavity, and a limiting cavity connected in sequence;

[0008] A valve core that runs through the motion cavity, the receiving cavity, and the limiting cavity. The valve core includes a main body section with one end facing the limiting cavity and having a blind hole, a plurality of flow holes in the middle, and a boss at the other end; and an extension section with one end connected to the boss and the other end facing the motion cavity and having an end head.

[0009] A valve seat is movably fitted onto the valve core and can move within the moving cavity. One end of the valve seat faces the limiting cavity and can abut against the boss, while the other end can be sealed to the end head.

[0010] An elastic element with one end fixed to the accommodating cavity and the other end connected to one end of the valve seat;

[0011] When the elastic element is in the extended state, the end of the elastic element and the other end of the valve seat together seal the outlet of the motion chamber.

[0012] Optionally, the valve seat is provided with a stepped hole, one end of the stepped hole connected to the elastic element is provided with a first step, and the other end that is sealed with the end head is provided with a second step;

[0013] Wherein, the first step abuts against the side of the boss facing the limiting cavity, and its inner diameter is smaller than the diameter of the boss;

[0014] The inner diameter of the second step is equal to the diameter of the end.

[0015] Optionally, at least one sealing element is provided around the periphery of the end;

[0016] At least one seal is provided around the outer perimeter of the second step.

[0017] Optionally, the seal is elastic;

[0018] In the compressed state, the compression of the seal ranges from 8% to 15%.

[0019] Optionally, a limiting ring is sleeved around one end of the valve core;

[0020] A limiting platform is provided between the accommodating cavity and the limiting cavity;

[0021] The limiting ring abuts against the limiting platform.

[0022] Optionally, an adapter plug is also connected to the entrance of the limiting cavity.

[0023] Optionally, a retaining ring is provided at the entrance of the limiting cavity, and the inner diameter of the retaining ring is smaller than the outer diameter of one end of the valve core.

[0024] Optionally, a filter element is also provided at the connection between the adapter plug and the limiting cavity.

[0025] Optionally, the mesh size of the filter element is in the range of 80 to 100.

[0026] Optionally, at least one pressure relief hole is also provided in the middle of the valve core.

[0027] The propellant loading device provided by this invention is used for ground loading of liquid orbital attitude control power systems. During loading, only an external force needs to be applied to the valve seat to disengage the valve seat and valve core from their sealing fit, allowing them to be pushed into the container together, thus enabling the entire loading device to conduct and achieve loading. When loading is finished, only the external force applied to the valve seat needs to be removed. Under the action of the elastic element, the valve seat rebounds and drives the valve core to move together, allowing the valve seat and valve core to return to their mating state and seal the container. The operation is simple, takes little time, and achieves rapid loading. Operators can avoid prolonged exposure to toxic and harmful environments, thus improving safety. Attached Figure Description

[0028] Figure 1 This is a cross-sectional schematic diagram of the propellant loading device provided by the present invention with the elastic element in an extended state;

[0029] Figure 2 This is a cross-sectional schematic diagram of the propellant loading device provided by the present invention when the elastic element is in a compressed state;

[0030] Figure 3 yes Figure 1 A magnified view of a portion of point III;

[0031] Figure 4 yes Figure 2 A magnified view of a portion of point IV in the middle;

[0032] Figure 5 This is a three-dimensional schematic diagram of the valve core provided by the present invention;

[0033] Figure 6 This is a cross-sectional schematic diagram of the valve core provided by the present invention;

[0034] Figure 7 This is a cross-sectional schematic diagram of the valve seat provided by the present invention.

[0035] Explanation of key component symbols:

[0036] 100. Container; 120. Limiting cavity; 140. Receiving cavity; 160. Moving cavity; 180. Limiting platform; 200. Valve core; 220. Main body section; 222. Blind hole; 224. Flow hole; 226. Boss; 228. Large pressure relief hole; 229. Small pressure relief hole; 240. Extension section; 242. End; 300. Valve seat; 320. First step; 340. Second step; 400. Elastic element; 500. Sealing element; 600. Limiting ring; 700. Adapter plug; 720. Retaining ring; 740. Filter element. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the invention, and should not be construed as limiting the invention. Furthermore, it should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0038] In the description of this invention, it should be understood that the terms "length", "width", "upper", "lower", "left", "right", "horizontal", "top", "bottom", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0039] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0040] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection, an electrical connection, or a connection that allows for communication; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0041] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0042] The following disclosure provides numerous different embodiments or examples for implementing various structures of the invention. To simplify the disclosure, specific examples of components and arrangements are described below. These are merely examples and are not intended to limit the invention. Furthermore, reference numerals and / or letters may be repeated in different examples; such repetition is for simplification and clarity and does not in itself indicate a relationship between the various embodiments and / or arrangements discussed. In addition, examples of various specific processes and materials are provided in this invention, but those skilled in the art will recognize the application of other processes and / or the use of other materials.

[0043] The propellant loading device provided by this invention is used for ground loading of liquid orbital attitude control power systems. During loading, only an external force needs to be applied to the valve seat to disengage the valve seat and valve core from their sealing fit, allowing them to be pushed into the container together, thus enabling the entire loading device to conduct and achieve loading. When loading is finished, only the external force applied to the valve seat needs to be removed. Under the action of the elastic element, the valve seat rebounds and drives the valve core to move together, allowing the valve seat and valve core to return to their mating state and seal the container. The operation is simple, takes little time, and achieves rapid loading. Operators can avoid prolonged exposure to toxic and harmful environments, thus improving safety.

[0044] Example 1

[0045] Please see Figures 1 to 7 This embodiment provides a propellant loading device for a liquid orbital attitude control propulsion system, comprising:

[0046] A container 100 is provided with a motion cavity 160, a receiving cavity 140 and a limiting cavity 120 connected in sequence;

[0047] A valve core 200 passes through the motion cavity 160, the receiving cavity 140 and the limiting cavity 120. The valve core 200 includes a main body section 220 with one end facing the limiting cavity 120 and having a blind hole 222, a plurality of flow holes 224 in the middle, and a boss 226 at the other end, and an extension section 240 with one end connected to the boss 226 and the other end facing the motion cavity 160 and having an end 242.

[0048] A valve seat 300 is movably sleeved on the valve core 200 and can move within the moving cavity 160. One end of the valve seat 300 faces the limiting cavity 120 and can abut against the boss 226, while the other end can be sealed with the end head 242.

[0049] An elastic element 400, one end of which is fixed to the accommodating cavity 140 and the other end of which is connected to one end of the valve seat 300;

[0050] When the elastic element 400 is in the extended state, the end 242 and the other end of the valve seat 300 together seal the outlet of the motion chamber 160.

[0051] The propellant loading device provided in this embodiment is used for ground-based loading of a liquid orbital attitude control propulsion system. Specifically, the propellant is typically stored in a container in a liquid state. The liquid orbital attitude control propulsion system includes a storage tank for receiving the propellant. The loading device simultaneously connects to both the propellant container and the storage tank, enabling them to communicate and allowing the propellant to flow from the container through the loading device into the storage tank.

[0052] In this embodiment, the propellant filling device can be regarded as a valve core 200, valve seat 300 and container 100 being sequentially connected from the inside to the outside, and the three can move relative to each other.

[0053] The container 100 can be configured as a cylindrical structure, including an outer wall of a certain thickness to provide sufficient strength and insulation. Inside the cylindrical structure, a motion chamber 160, a receiving chamber 140, and a limiting chamber 120 are sequentially formed, and these three chambers are interconnected, allowing propellant liquid to pass through the loading device during refueling. During refueling, the limiting chamber 120 is located at the propellant inflow end; therefore, the free end of the limiting chamber 120 not connected to the receiving chamber 140 can be considered its own inlet, which is also the inlet of the container 100. Similarly, during refueling, the motion chamber 160 is located at the propellant outflow end; therefore, the free end of the motion chamber 160 not connected to the receiving chamber 140 can be considered its own outlet, which is also the outlet of the container 100.

[0054] Understandably, to provide sufficient movement space for the valve seat 300 and valve core 200, the length of the moving cavity 160 can be significantly greater than the lengths of the receiving cavity 140 and the limiting cavity 120. In this embodiment, the length of the moving cavity 160 is set to be approximately half the overall length of the receiving cavity. Furthermore, the inner diameter of the moving cavity 160 is slightly larger than the width of the receiving cavity 140 and the limiting cavity 120, facilitating the simultaneous reception of the valve seat 300 and the valve core 200. The valve core 200 can be configured as a stepped cylindrical structure, specifically, it can be composed of a main body segment 220 and an extension segment 240. A boss 226 is provided at the end where the main body segment 220 connects to the extension segment 240, and the boss 226 is connected to the extension segment 240. The main body section 220 has a blind hole 222 inside. Several flow holes 224 are also provided at the junction of the main body section 220 and the boss 226. These flow holes 224 connect the blind hole 222 to the outside, meaning they are mainly used to transfer fluid media between the blind hole 222 and the outside of the blind hole 222. The extension section 240 can be a solid cylinder with an end 242 at the end not connected to the boss 226.

[0055] The diameters and lengths of the main body section 220, boss 226, extension section 240, and end 242 are all different, resulting in the valve core 200 appearing as a stepped cylinder. Specifically, the diameter and length of the main body section 220 are both larger than those of the extension section 240, resulting in a larger volume of the blind hole 222, thereby increasing the propellant flow rate during filling. Since the extension section 240 is a solid structure with a smaller diameter and length, it provides sufficient strength while reducing weight, improving smoothness during movement, and reducing material usage, thus saving costs. The boss 226 can be formed at the junction of the main body section 220 and the extension section 240, and its diameter is slightly larger than that of the main body section 220. End 242 is located at the free end of extension 240 that is not connected to boss 226. The diameter of end 242 can be set slightly smaller than that of boss 226, making the overall shape of valve core 200 more regular and facilitating its adaptation to valve seat 300 and receiving cavity. It is easy to understand that the diameter of end 242 is significantly larger than that of extension 240. When valve core 200 moves within receiver 100, the end with blind hole 222 is restricted by limiting cavity 120, thus preventing it from exceeding the inlet of limiting cavity 120.

[0056] The valve seat 300 can be configured as a cylindrical structure with an inner bore, the inner diameter of which is larger than the outer diameter of the valve core 200, so that it can be fitted around the periphery of the valve core 200 and can move relative to the valve core 200. The inner diameters at both ends of the valve seat 300 are tightened, so that the boss 226 is completely contained in the inner bore of the valve seat 300. The inner diameter of the end of the valve seat 300 near the boss 226 is slightly smaller than that of the boss 226, so that it can abut against the boss 226. Specifically, the abutment point is located on the end face of the boss 226 facing the main body section 220. The inner diameter of the end of the valve seat 300 near the end 242 is approximately equal to that of the end 242, so that the valve seat 300 and the end 242 can fit well and achieve a sealing fit.

[0057] It is understandable that, since the diameter of end 242 is slightly smaller than that of boss 226, the inner diameter of the end of valve seat 300 near end 242 is also slightly smaller than the outer diameter of boss 226. Furthermore, the length of valve seat 300 is approximately equal to the total length of boss 226, extension 240, and end 242 combined, ensuring that when one end of valve seat 300 is in contact with boss 226, the other end is positioned just around the periphery of end 242. The diameter of valve seat 300 is approximately equal to that of moving cavity 160 and larger than that of receiving cavity 140, thus restricting the displacement of the end of valve seat 300 near boss 226 when it moves within receiver 100, preventing the main body of valve seat 300 from entering receiving cavity 140.

[0058] In this embodiment, the portion of the valve seat 300 that is fitted with the valve core 200 is always located within the moving cavity 160, while the portion of the valve core 200 not fitted with the valve seat 300 penetrates the receiving cavity 140 and the limiting cavity 120. One end of the elastic member 400 is fixed to the receiving cavity 140, and the other end is connected to the end of the valve seat 300 near the boss 226. When the elastic member 400 is in the extended state, the total length of the elastic member 400 and the valve seat 300 is approximately equal to the total length of the receiving cavity 140 and the moving cavity 160, such that in this state, the end of the valve seat 300 near the end 242 is located exactly at the outlet of the moving cavity 160. At the same time, the other end of the valve seat 300 is positioned just around the periphery of the end 242, thereby sealing with the end 242. At this time, the end 242 and the other end of the valve seat 300 together can seal the outlet of the moving cavity 160. The elastic member 400 can be a spring.

[0059] In this embodiment, when the valve seat 300 is driven by the elastic element 400, it will move a considerable distance within the motion chamber 160 before driving the valve core 200 to move. This arrangement enables cooperation with the filling liquid receiving device in the storage and transportation tank, ensuring that the filling device will not be blown open under high pressure conditions.

[0060] It should be noted that the description of the relative positions of the components is based on the condition that the elastic element 400 is in the extended state, that is, the end 242 of the valve core 200 and the valve seat 300 together seal the outlet of the moving chamber 160. For example, "the end of the valve seat 300 near the boss 226" refers to the end of the valve seat 300 near the boss 226 when the elastic element 400 is in the extended state.

[0061] The working principle of the propellant loading device provided by this invention is as follows: During loading, the inlet of the container 100 is connected to the container storing the propellant, and the outlet is connected to the storage tank of the liquid orbital attitude control power system. An external force is applied to the end of the valve seat 300 near the end 242, pushing the valve seat 300 into the container 100 and further moving within the motion chamber 160. At the same time, the elastic element 400 is compressed and accumulates elastic force. After the valve seat 300 moves a certain distance, the end subjected to the external force approaches the boss 226 until it hooks the boss 226. As the valve seat 300 is pushed in, the valve core 200 is driven into the container 100, opening the outlet of the motion chamber 160. At this time, the blind hole 222 of the valve core 200 is connected to the outlet of the motion chamber 160 through the flow hole 224. The propellant can enter from the inlet of the limiting cavity 120, flow through the blind hole 222 and the flow hole 224 into the motion chamber 160, and finally flow out from the outlet of the motion chamber 160, thus achieving refueling. When refueling is finished, the external force applied to the valve seat 300 is removed. The elastic element 400 releases the stored elastic force, causing the valve seat 300 to rebound. The end of the valve seat 300 connected to the elastic element 400 approaches the boss 226 until it abuts against the boss 226. The valve seat 300 continues to rebound, causing the valve core 200 to move in the opposite direction until the end 242 reaches the outlet of the motion chamber 160. At this time, the elastic element 400 returns to its extended state, and the end of the valve seat 300 near the end 242 is just located at the outlet of the motion chamber 160 and seals with the end 242. At this time, the end 242 and the valve seat 300 together seal the outlet of the motion chamber 160, and the flow hole 224 of the valve core 200 is isolated from the outside, and the propellant in the container cannot flow out.

[0062] The propellant loading device provided by this invention is used for ground loading of liquid orbital attitude control power systems. During loading, only an external force needs to be applied to the valve seat 300 to disengage the valve seat 300 from the valve core 200, allowing them to be pushed into the container 100 together, thus enabling the entire loading device to conduct and achieve loading. When loading is finished, only the external force applied to the valve seat 300 needs to be removed. Under the action of the elastic element 400, the valve seat 300 rebounds and drives the valve core 200 to move together, so that the valve seat 300 and the valve core 200 return to the mating state to seal the container 100. The operation is simple, takes little time, and achieves rapid loading. Operators can avoid prolonged exposure to toxic and harmful environments, thus improving safety.

[0063] Example 2

[0064] Please see Figures 3 to 4 In this embodiment, the valve seat 300 is provided with a stepped hole. One end of the stepped hole connected to the elastic member 400 is provided with a first step 320, and the other end that is sealed to the end 242 is provided with a second step 340.

[0065] The first step 320 abuts against the side of the boss 226 facing the limiting cavity 120, and its inner diameter is smaller than the diameter of the boss 226.

[0066] The inner diameter of the second step 340 is equal to the diameter of the end 242.

[0067] In this embodiment, the stepped hole may include three sections with different inner diameters. Specifically, the middle section has a larger inner diameter and a longer length, occupying most of the stepped hole. The inner diameter of the end connected to the elastic member 400 is tightened to form a first step 320, the length of which is much smaller than that of the middle section. Similarly, the inner diameter of the end that seals with the end 242 is tightened to form a second step 340, the length of which is also much smaller than that of the middle section.

[0068] In this design, the boss 226 of the first step 320 abuts against the side facing the limiting cavity 120, meaning that the boss 226 of the valve core 200 is completely contained within the stepped hole of the valve seat 300. The inner diameter of the first step 320 is smaller than the diameter of the boss 226, so that when the valve seat 300 and the valve core 200 move relative to each other, the movement range of the boss 226 of the valve core 200 is limited within the stepped hole of the valve seat 300. The inner diameter of the second step 340 is equal to the diameter of the end 242, so that when the inner wall of the second step 340 reaches the position of contact with the outer wall of the end 242, the two can form a sealing fit.

[0069] Understandably, since the diameter of end 242 is slightly smaller than that of boss 226, the inner diameter of the second step 340 is also slightly smaller than that of boss 226. That is, when the second step 340 moves to a position close to boss 226, it can abut against the other end face of boss 226 (the end face facing the outlet of the moving cavity 160), so that when valve seat 300 and valve core 200 move relative to each other, the range of motion of boss 226 of valve core 200 is restricted in both relative directions, and it is always within the stepped hole of valve seat 300. On the other hand, when the first step 320 reaches the position of abutting the boss 226, the continued movement can drive the valve core 200 as a whole to move towards the outlet direction of the moving cavity 160; when the second step 340 reaches the position of abutting the boss 226, the continued movement can drive the valve core 200 as a whole to move away from the outlet direction of the moving cavity 160. That is, by applying external force to both ends of the valve seat 300, the valve seat 300 can drive the valve core 200 to move in two opposite directions, thereby achieving the sealing and opening of the outlet of the moving cavity 160.

[0070] The propellant filling device provided by this invention applies an external force to the second step 340 during filling, causing the valve seat 300 to be pushed into the container 100 until the first step 320 moves to abut against the boss 226. Further, by pushing the boss 226, the valve core 200 moves, allowing the flow hole 224 to connect with the outside and fully opening the outlet of the moving chamber 160. This allows the filling liquid to be injected at a large flow rate for rapid filling. Simultaneously, the elastic element 400 is compressed and continues to exert its elastic restoring force. When filling is finished, simply removing the external force applied to the second step 340 causes the elastic element 400 to release its elastic restoring force, allowing the valve seat 300 to spring back, restoring the second step 340 to its sealed position with the end 242. The device has a simple structure and good stability.

[0071] Example 3

[0072] Please see Figures 1 to 2 In this embodiment, at least one sealing element 500 is provided around the periphery of the end 242;

[0073] At least one seal 500 is provided around the outer perimeter of the second step 340.

[0074] In this embodiment, the sealing element 500 is disposed around the periphery of the valve seat 300. The sealing element 500 can be an O-ring, and correspondingly, a groove can be provided around the outer wall of the end 242 for placing the O-ring. The number of sealing elements 500 can be set according to actual needs. In this embodiment, the sealing element 500 consists of two O-rings arranged parallel to each other around the periphery of the end 242. In some embodiments, the sealing element 500 can also be one, three, four, or even more, without specific limitation.

[0075] Similarly, the sealing element 500 is also disposed around the periphery of the second step 340. A groove may also be disposed around the outer wall of the second step 340 for placing an O-ring. The number of sealing elements 500 can be set according to actual needs. In this embodiment, the sealing elements 500 are two O-rings disposed parallel to each other around the periphery of the second step 340. In some embodiments, the sealing elements 500 may be one, three, four, or even more, without specific limitation.

[0076] The O-ring can be made of perfluoroether.

[0077] When the elastic element 400 is in the extended state, the sealing element 500 located around the valve seat 300 engages with the inner wall of the container 100 to achieve a primary seal. Simultaneously, the sealing element 500 located around the second step 340 engages with the inner wall of the valve seat 300 to achieve a secondary seal. The two seals combine to seal the outlet of the moving chamber 160 together with the valve seat 300.

[0078] The propellant filling device provided by the present invention achieves a seal between the valve core 200 and the valve seat 300 by means of a sealing element 500 arranged around the periphery of the end 242; and achieves a seal between the valve seat 300 and the container 100 by means of a sealing element 500 arranged around the periphery of the second step 340, thereby ensuring the airtightness of the container 100 through two-stage sealing and preventing leakage of residual filling liquid.

[0079] Example 4

[0080] Please see Figures 1 to 2 In this embodiment, the seal 500 is elastic;

[0081] Under compression, the compression range of seal 500 is 8% to 15%.

[0082] In this embodiment, both the seal 500 on the valve core 200 and the seal 500 on the valve seat 300 are elastic and can undergo a certain degree of deformation. Specifically, when in a compressed state, the seal 500 is compressed by 8% to 15%. Since the sealing fit at both locations is a dynamic seal, this compression range can achieve a sealing effect while preventing excessive frictional resistance caused by excessive compression.

[0083] The propellant filling device provided by the present invention has a dynamic seal between the valve core 200 and the valve seat 300, and between the valve seat 300 and the container 100. It can achieve a sealing effect within the compression range of 8% to 15%, and also prevent excessive frictional resistance caused by excessive compression.

[0084] Example 5

[0085] Please see Figures 1 to 7 In this embodiment, a limiting ring 600 is sleeved around one end of the valve core 200;

[0086] A limiting platform 180 is provided between the receiving cavity 140 and the limiting cavity 120;

[0087] The limiting ring 600 abuts against the limiting platform 180.

[0088] In this embodiment, the limiting ring 600 is sleeved on the end of the valve core 200 away from the outlet of the moving cavity 160. The limiting ring 600 can be configured as a hollow structure with internal threads, and correspondingly, the valve core 200 can be provided with external threads. The threads cooperate to achieve fixation. The limiting ring 600 can limit the movement of the valve core 200.

[0089] The limiting ring 600 has an end face facing the receiving cavity 140. When the valve core 200 moves toward the outlet of the moving cavity 160, this end face can abut against the limiting platform 180 provided between the receiving cavity 140 and the limiting cavity 120, thereby stopping the valve core 200 from moving. The limiting platform 180 can be regarded as the boundary between the receiving cavity 140 and the limiting cavity 120, and the limiting platform 180 can always confine the limiting ring 600 within the limiting cavity 120.

[0090] The propellant filling device provided by the present invention, through the abutment and cooperation between the limiting ring 600 and the limiting platform 180, restricts the displacement distance of the valve core 200 when it rebounds under the action of the elastic element 400, so that when it stops, it just falls into the position that cooperates with the valve seat 300 to seal the outlet of the receiving cavity, thereby achieving precise control, reducing the number of manual adjustments, and further improving safety.

[0091] Example 6

[0092] Please see Figures 1 to 2 In this embodiment, an adapter plug 700 is also connected to the entrance of the limiting cavity 120.

[0093] In this embodiment, the adapter plug 700 can be used to fix the refueling device to the propellant container. The plug can be configured as a hollow structure with an internal thread at one end. Correspondingly, at the inlet of the limiting cavity 120 (i.e., the inlet of the container 100), the outer wall of the container 100 can be provided with an external thread. The internal and external threads cooperate to fix the device. In addition, the seal between the adapter plug 700 and the container 100 can be achieved by an O-ring fitted on the container 100.

[0094] The propellant loading device provided by this invention can be fixed to the propellant container as a whole through the adapter plug 700, which is simple to connect and further improves the loading efficiency.

[0095] Example 7

[0096] Please see Figures 1 to 2 In this embodiment, a retaining ring 720 is also provided at the entrance of the limiting cavity 120. The inner diameter of the retaining ring 720 is smaller than the outer diameter of one end of the valve core 200.

[0097] In this embodiment, the retaining ring 720 is disposed at the entrance of the limiting cavity 120, that is, between the entrance of the receiver 100 and the adapter plug 700. The retaining ring 720 can be configured as a stepped circular ring structure. Specifically, the stepped circular ring structure includes two stages. The diameter of the first stage is approximately equal to the inner diameter of the limiting cavity 120 and extends into the limiting cavity 120. The diameter of the second stage is larger than the inner diameter of the limiting cavity 120, but approximately equal to the outer diameter of the limiting cavity 120. It is located outside the limiting cavity 120 and abuts against the end face of the entrance of the limiting cavity 120. In this way, the limiting ring 600 separates the valve core 200 from the adapter plug 700. When the valve core 200 moves close to the adapter plug 700, it will be blocked by the limiting ring 600 and cannot directly contact the adapter plug 700.

[0098] The limiting ring 600 can be made of rubber, which can enhance the cushioning effect by utilizing the elasticity of rubber.

[0099] The propellant filling device provided by the present invention, during the process of filling, when the valve core 200 is pushed into the container 100, the displacement distance of the valve core 200 is limited by the retaining ring 720, thereby achieving buffering and preventing the valve core 200 from impacting the adapter plug 700 during reciprocating motion and causing damage.

[0100] Example 8

[0101] Please see Figures 1 to 2 In this embodiment, a filter element 740 is also provided at the connection between the adapter plug 700 and the limiting cavity 120.

[0102] In this embodiment, the filter element 740 can be configured to be fixed to the adapter plug 700 by a threaded connection, and one end is pressed by the retaining ring 720. The filter element 740 is provided with a plurality of filter holes. Preferably, in some embodiments, the mesh size of the filter element 740 is in the range of 80 to 100.

[0103] The propellant filling device provided by the present invention can filter the filling liquid through the filter element 740 provided at the connection between the adapter plug 700 and the limiting cavity 120, filter out impurities, reduce the workload of cleaning and disassembling the inside of the device, and further improve efficiency.

[0104] Example 9

[0105] Please see Figure 1 , 2 In this embodiment, the valve core 200 is also provided with at least one pressure relief hole in the middle.

[0106] The number and size of the pressure relief holes can be set according to actual usage needs, and are not specifically limited here. In this embodiment, the main body section 220 of the valve core 200 is provided with two large pressure relief holes 228 on its side, and the external thread relief groove of the main body section 220 is also provided with two small pressure relief holes 229. Both the large pressure relief holes 228 and the small pressure relief holes 229 are connected to the blind hole 222.

[0107] The propellant filling device provided by the present invention avoids the situation where the pressure difference between the inside and outside of the valve core 200 is too large during filling, causing the valve core 200 to deform and thus become unable to move, by setting a pressure relief hole in the middle of the valve core 200.

[0108] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A propellant loading device for a liquid orbital attitude control propulsion system, characterized in that, include: A container is provided with a motion cavity, a receiving cavity, and a limiting cavity connected in sequence; A valve core that runs through the motion cavity, the receiving cavity, and the limiting cavity. The valve core includes a main body section with one end facing the limiting cavity and having a blind hole, a plurality of flow holes in the middle, and a boss at the other end; and an extension section with one end connected to the boss and the other end facing the motion cavity and having an end head. A valve seat is movably fitted onto the valve core and can move within the moving cavity. One end of the valve seat faces the limiting cavity and can abut against the boss, while the other end can be sealed to the end head. An elastic element with one end fixed to the accommodating cavity and the other end connected to one end of the valve seat; When the elastic element is in the extended state, the end and the other end of the valve seat together seal the outlet of the motion chamber; The valve seat is provided with a stepped hole, and the end of the stepped hole connected to the elastic element is provided with a first step, and the end that is sealed to the end head is provided with a second step. The first step abuts against the side of the boss facing the limiting cavity, and its inner diameter is smaller than the diameter of the boss.

2. The propellant loading device according to claim 1, characterized in that, The inner diameter of the second step is equal to the diameter of the end.

3. The propellant loading device according to claim 2, characterized in that, At least one sealing element is provided around the periphery of the end; At least one seal is provided around the outer perimeter of the second step.

4. The propellant loading device according to claim 3, characterized in that, The seal is elastic; In the compressed state, the compression of the seal ranges from 8% to 15%.

5. The propellant loading device according to claim 1, characterized in that, A limiting ring is fitted around one end of the valve core; A limiting platform is provided between the accommodating cavity and the limiting cavity; The limiting ring abuts against the limiting platform.

6. The propellant loading device according to claim 4, characterized in that, An adapter plug is also connected to the entrance of the limiting cavity.

7. The propellant loading device according to claim 5, characterized in that, A retaining ring is also provided at the entrance of the limiting cavity, and the inner diameter of the retaining ring is smaller than the outer diameter of one end of the valve core.

8. The propellant loading device according to claim 6, characterized in that, A filter element is also provided at the connection between the adapter plug and the limiting cavity.

9. The propellant loading device according to claim 8, characterized in that, The mesh size of the filter element ranges from 80 to 100.

10. The propellant loading device according to claim 1, characterized in that, At least one pressure relief hole is also provided in the middle of the valve core.

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