Support components for the propellant supply system and the refueling system incorporating such components

Abstract

This application relates to a support assembly for a propellant supply system and a refueling system equipped with the assembly. The support assembly includes a fixed bracket, a sliding hinged bracket, and a vertically adjustable bracket. The fixed bracket is fixedly disposed at the end of the propellant supply pipeline to limit displacement caused by low-temperature deformation. The sliding hinged bracket is disposed in the middle of the connecting hose to support the connecting hose. The vertically adjustable bracket is disposed at the end of the connecting hose connected to the rocket body tank and can move vertically along the vertical direction. This application can adapt to rocket body refueling deformation and impact vibration during the test ignition stage, and can remotely control the safe return of remaining propellant from the rocket body.

Description

Technical Field

[0001] This application relates to a support component for a propellant supply system and a refueling system equipped with the component, applicable to the technical field of rocket core stage propulsion system testing. Background Technology

[0002] During core stage propulsion system testing, the rocket requires essential onboard equipment such as the engine, propellant tanks, and pressurization pipelines. The rocket's condition is essentially the same as during launch, but it does not ascend; instead, a load-bearing structure holds the rocket body fixed to the test stand. Throughout the test, the ground-based refueling pipeline must meet functional requirements related to propellant loading, rocket deformation, ignition vibration, and propellant leakage. The external loads that the rocket body interface connections can withstand are very small, and the ground-based refueling pipeline must not generate significant reaction forces during the test to avoid rocket damage. Therefore, the docking method of the ground-based refueling pipeline and the rational design of the support structure are crucial to the success of the propulsion test.

[0003] Therefore, existing technologies require the design of a support component for the propellant supply system to ensure the safety of the ground refueling pipeline during rocket core stage propulsion system testing, and to prevent damage to the pipeline or rocket body. Summary of the Invention

[0004] The purpose of this application is to design a support component for a propellant supply system and a refueling system equipped with the component, aiming to provide reasonable support for the cryogenic propellant supply pipeline during rocket core stage propulsion system testing, so that it can adapt to the deformation of the rocket body during refueling and the impact vibration during the test ignition stage, so as to avoid damage to the rocket body or the supply pipeline.

[0005] This application relates to a support assembly for a propellant supply system. The propellant supply system includes a propellant supply line and a connecting hose. The propellant supply line is connected to a rocket body tank via the connecting hose. The support assembly includes a fixed bracket, a sliding hinge bracket, and a vertically adjustable bracket. The fixed bracket is fixedly disposed at the end of the propellant supply line to limit displacement caused by low-temperature deformation at the end of the propellant supply line. The sliding hinge bracket is disposed in the middle of the connecting hose to support the connecting hose. The connecting hose is capable of free movement along the axial direction and angular displacement in the vertical plane on the sliding hinge bracket. The vertically adjustable bracket is disposed at the end of the connecting hose connected to the rocket body tank, and the connecting hose is capable of moving vertically on the vertically adjustable bracket.

[0006] The vertically adjustable bracket may further include a clamp, a fixed base, and a bracket; the bracket is mounted on the fixed base via a height adjustment component; the clamp is mounted on the bracket, and the inner wall of the clamp is provided with a heat-insulating elastic buffer layer; the clamp is used to secure the connecting hose through the heat-insulating elastic buffer layer.

[0007] This application also relates to a propellant loading system, including a propellant supply subsystem, a ground pipeline pre-cooling and discharge subsystem, a loading port venting subsystem, and a loading port venting subsystem; the propellant supply subsystem is connected to the rocket body tank via a propellant supply pipeline to achieve cryogenic propellant loading; the ground pipeline pre-cooling and discharge subsystem, the loading port venting subsystem, and the loading port venting subsystem are each independently connected to the propellant supply pipeline; the connection points of the loading port venting subsystem and the loading port venting subsystem on the propellant supply pipeline are respectively located on the propellant supply pipeline between the ground pipeline pre-cooling and discharge subsystem and the rocket body tank, and the propellant supply subsystem is provided with the support components described above.

[0008] The propellant supply subsystem includes a propellant storage tank and a ground refueling valve. One end of the propellant supply pipeline is connected to the propellant storage tank, and the other end is connected to the rocket body tank. The ground refueling valve is located on the propellant supply pipeline. The connection point of the ground pipeline pre-cooling and venting subsystem on the propellant supply pipeline is located on the propellant supply pipeline between the propellant storage tank and the ground refueling valve. The connection points of the refueling port venting subsystem and the refueling port venting subsystem on the propellant supply pipeline are respectively located on the propellant supply pipeline between the ground refueling valve and the rocket body tank. The ground pipeline pre-cooling and venting subsystem includes a ground pipeline pre-cooling and venting pipeline and a pre-cooling and venting valve, with the pre-cooling and venting valve located on the ground pipeline pre-cooling and venting pipeline. The refueling port venting subsystem includes a refueling port venting pipeline and a refueling port venting valve; the connection point of the refueling port venting pipeline to the propellant supply pipeline is located on the propellant supply pipeline between the ground refueling valve and the connecting hose; the refueling port venting valve is located on the refueling port venting pipeline. The refueling port venting subsystem includes a refueling port venting pipeline and a venting valve; the connection point of the refueling port venting pipeline to the propellant supply pipeline is located on the propellant supply pipeline between the ground refueling valve and the connecting hose; the venting valve is located on the refueling port venting pipeline.

[0009] The cryogenic propellant is liquid hydrogen, and the non-vacuum insulated part of the propellant supply pipeline is equipped with a liquid air guiding device; the liquid air guiding device includes a liquid collection tank and a guiding pipe; the liquid collection tank is inclined downward and located below the propellant supply pipeline; the outer layer of the liquid collection tank is provided with a heat insulation layer; the guiding pipe is connected to the lowest point of the liquid collection tank. When fueling the rocket body, open the ground fueling valve and the rocket body fueling valve, open the rocket body tank vent, pressurize the propellant tank, and then squeeze or use a cryogenic pump to fuel the cryogenic propellant into the rocket body tank. When draining or releasing the cryogenic propellant from the rocket body tank, first depressurize the propellant tank and open the vent port of the propellant tank, open the ground fueling valve and the rocket body fueling valve, and squeeze the cryogenic propellant in the rocket body tank back into the propellant tank. Alternatively, when releasing the cryogenic propellant from the rocket body tank, open the fueling port vent valve and the rocket body fueling valve, and squeeze the cryogenic propellant from the rocket body tank directly out. The outlet of the fueling port vent valve is connected to a safety release device.

[0010] The support component for a propellant supply system and the refueling system equipped with the component proposed in this application can not only protect the propellant supply pipeline and the rocket body from low-temperature deformation and vibration, and reasonably compensate for the low-temperature deformation generated simultaneously by the propellant supply pipeline and the rocket body, but also maintain the flexibility of the refueling nozzle under the huge vibration of the rocket body during the test phase, without generating additional force at the rocket-to-ground interface; moreover, by independently setting up each ground low-temperature pipeline, the flow rate at different refueling stages can be strictly controlled to avoid a large amount of low-temperature vapor entering the storage tank and causing back pressure during the ground refueling process. It can meet the refueling indicators during the low-temperature propellant refueling process, and can also effectively and safely discharge the remaining propellant in the rocket body. Attached Figure Description

[0011] Figure 1 This is a schematic diagram of a support component of a propellant supply system and a filling system equipped with the component, according to this application.

[0012] Figure 2 This is a schematic diagram of the arrow-to-ground pipeline support structure of this application.

[0013] Figure 3 This is a schematic diagram of the vertically adjustable bracket of this application.

[0014] Figure 4 This is a schematic diagram of the liquid air guiding device of this application.

[0015] In the diagram: 1. Propellant tank; 2. Propellant supply pipeline; 3. Pre-cooling discharge valve; 4. Discharge port gas seal; 5. Venting valve; 6. Rocket body tank; 7. Connecting hose; 8. Filling filter; 9. Filling port vent valve; 10. Flow meter; 11. Ground filling valve; 12. Sliding hinge bracket; 13. Vertically adjustable bracket; 14. Thermal insulation elastic buffer layer; 15. Clamp; 16. Height adjustment component; 17. Fixed base; 18. Bracket; 19. Liquid collection tank; 20. Insulation layer; 21. Guide pipe; 22. Fixed bracket. Detailed Implementation

[0016] To make the objectives, technical solutions, and advantages of this application clearer, the embodiments of this application will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other. Those skilled in the art will understand that the support component of a propellant supply system and the refueling system equipped with the component, as described in this application, are applicable to the field of rocket core stage propulsion system testing. The cryogenic propellant used in this application is typically liquid oxygen, liquid methane, or liquid hydrogen.

[0017] like Figure 1 As shown, this application discloses a support component for a propellant supply system and a refueling system equipped with the component. The refueling system includes a propellant supply subsystem, a ground pipeline pre-cooling and discharge subsystem, a refueling port venting subsystem, and a refueling port venting subsystem. The propellant supply subsystem is connected to the rocket body storage tank 6 via its propellant supply pipeline 2, enabling cryogenic propellant refueling. A ground refueling valve 11 is provided between the propellant supply pipeline 2 and the rocket body storage tank 6 for switching the refrigerant supply pipeline on and off. The ground refueling valve 11 is located on the propellant supply pipeline 2 near the rocket body. The ground pipeline pre-cooling and discharge subsystem, the refueling port venting subsystem, and the refueling port venting subsystem are each designed as independent system pipelines and are respectively connected to the propellant supply pipeline 2 to realize the refueling and venting of propellant at the refueling port of the rocket body storage tank 6. Furthermore, the connection points of the refueling port venting subsystem and the refueling port venting subsystem on the propellant supply line 2 are respectively located on the propellant supply line 2 between the ground refueling valve 11 and the rocket body tank 6.

[0018] The ground pipeline pre-cooling discharge subsystem is used for separate pre-cooling discharge from the ground pipeline. The connection point of the ground pipeline pre-cooling discharge subsystem on the propellant supply pipeline 2 is located on the propellant supply pipeline 2 between the propellant storage tank 1 and the ground refueling valve 11, near the ground refueling valve 11. The refueling port venting subsystem is used to vent the remaining cryogenic propellant in the rocket body storage tank 6, and the refueling port venting subsystem is used to vent the refueling system. The refueling system of this application can prevent a large amount of cryogenic vapor from entering the storage tank and causing back pressure during the ground refueling process by strictly controlling the flow rate at different refueling stages. During the test, the pressure of the ground pipeline of the refueling system needs to be maintained lower than the pressure of the rocket body storage tank 6 to avoid adding gas or liquid from the rocket body refueling port. After the test, the cryogenic pipeline and equipment still need to maintain good connection and operational condition, and the remaining propellant in the rocket body needs to be safely discharged back to meet the refueling specifications.

[0019] like Figure 1 As shown, the propellant supply subsystem of the fueling system proposed in this application also includes a connecting hose 7. The propellant supply line 2 is connected to the rocket body tank 6 via the connecting hose 7 to achieve a flexible connection between the two, meeting the requirements for flexible deformation. The other end of the propellant supply line 2 is connected to one end of the connecting hose 7, and the other end of the connecting hose 7 is connected to the rocket body tank 6. After the cryogenic propellant fueling is completed, the fueling system is generally not disconnected from the rocket body. Therefore, the ground pipeline needs to avoid the reaction force on the rocket body interface caused by the cryogenic deformation of the ground pipeline. At the same time, the ground pipeline must also adapt to the cryogenic deformation and vibration of the rocket body to avoid affecting the strength or sealing of the rocket body interface during fueling and testing. After the test is completed, the ground cryogenic pipeline, i.e., the propellant supply line 2 and equipment, still needs to maintain good connection and use to safely drain the remaining propellant from the rocket body.

[0020] To achieve the above objectives, the propellant supply subsystem of this application further includes a support assembly for supporting the propellant supply pipeline 2 and the connecting hose 7, and for withstanding deformation and vibration caused by the rocket body. Figure 2-3As shown, the support components of the propellant supply system according to this application include a fixed bracket 22, a sliding hinge bracket 12, and a vertically adjustable bracket 13. The fixed bracket 22, as a primary support, is fixedly installed on the propellant supply line 2 at the front end of the connecting hose 7, and is positioned close to the connecting hose 7 to restrict the movement of the propellant supply line 2. This is used to isolate the low-temperature deformation of the ground cryogenic pipeline propellant supply line 2 and prevent the propellant supply line 2 from causing displacement of the connecting hose 7. Further, the sliding hinge bracket 12, as a secondary support, can be installed at the end where the connecting hose 7 connects to the propellant supply line 2, specifically in the middle of the connecting hose 7, to support the weight and deformation of the connecting hose 7. Specifically, the connecting hose 7 can move horizontally on the sliding hinge bracket 12, allowing the connecting hose 7 to move axially back and forth during low-temperature deformation. At the same time, the hinge structure compensates for the angular deformation caused by the downward displacement of the arrow-ground interface at low temperatures. Furthermore, the vertically adjustable bracket 13, serving as a tertiary support, can be positioned at the end where the connecting hose 7 connects to the rocket body storage tank 6, near the connection port of the rocket body storage tank 6, ensuring that the ground pipeline does not exert additional force on the rocket body. Additionally, the connecting hose 7 can move vertically on the vertically adjustable bracket 13 to accommodate the vertical deformation of the rocket body during the fueling phase.

[0021] Preferably, in combination with the above schemes, such as Figure 3 As shown, in this embodiment, the vertically adjustable support 13 includes a clamp 15, a fixed base 17, and a bracket 18. The bracket 18 is mounted on the fixed base 17 via a height adjustment component 16. The clamp 15 is mounted on the bracket 18, and an insulating elastic buffer layer 14 is provided on the inner wall of the clamp 15. Specifically, the clamp 15 is connected to the fixed connecting hose 7 via the insulating elastic buffer layer 14, meaning an insulating elastic buffer layer 14 is laid between the clamp 15 and the connecting hose 7. Specifically, during the fueling process, the deformation ΔL of the insulating elastic buffer layer 14 during the fueling stage can be achieved by mechanically adjusting the vertical height of the vertically adjustable support 13 to accommodate the deformation of the rocket body during the fueling stage. Simultaneously, the insulating elastic buffer layer 14 can compensate for the vibration displacement caused by the rocket body during the testing stage. The ground pipeline can move in tandem with the rocket body during both the fueling and ignition testing stages, ensuring that the ground pipeline does not exert additional force on the rocket body.

[0022] Specifically, during the injection process, the deformation ΔL of the thermally insulating elastic buffer layer 14 during the injection stage can be achieved by mechanically adjusting the vertical height of the adjustable vertical support 13 to accommodate the deformation of the rocket body during the injection stage. ΔL can be calculated using the following formula:

[0023] ΔL=H·α·ΔT+Δε,

[0024] Where H is the vertical height from the cryogenic tank filling port to the fixed point between the rocket body and the test stand; α is the thermal deformation coefficient of the rocket body material during the corresponding temperature change process in the cryogenic propellant filling process; ΔT is the temperature change range from before the propellant filling to after the cryogenic propellant filling is completed; and Δε is other deformations of the rocket body caused by the cryogenic propellant filling process.

[0025] The propellant supply system support components proposed in this application, through the design of three-level support and flexible connection in the system pipeline, can avoid the additional force on the rocket body interface caused by the low-temperature deformation of the ground pipeline, and adapt to the low-temperature deformation and vibration of the rocket body.

[0026] like Figure 1 As shown, the precooling process of the ground pipeline precooling discharge subsystem in the cryogenic propellant loading system designed in this application is as follows: the ground loading valve 11 is closed, and the precooling discharge valve 3 is opened, allowing cryogenic propellant to be discharged from the precooling discharge valve 3 at a small flow rate, thereby precooling the ground pipeline before the ground loading valve 11. Therefore, this application, by adopting a series of safety measures including the aforementioned precooling, avoids the generation of a large amount of cryogenic steam in the ground pipeline caused by direct rocket body loading, which could lead to a rapid increase in tank pressure and overpressure, thus being detrimental to product quality control.

[0027] like Figure 1 As shown, the cryogenic propellant loading system designed in this application can load the rocket body and also release liquid oxygen from the rocket body storage tank 6. When loading the rocket body, the ground loading valve 11 is opened, the rocket body loading valve located on the rocket body is opened, the rocket body storage tank 6 is vented, the propellant tank 1 is pressurized, and then the cryogenic propellant is squeezed or injected into the rocket body storage tank 6 using a cryogenic pump. When releasing or draining the cryogenic propellant from the rocket body storage tank 6, the propellant tank 1 is first depressurized and its vent is opened. The ground loading valve 11 is opened, the rocket body loading valve is opened, and the cryogenic propellant in the rocket body storage tank 6 is squeezed back into the propellant tank 1 for release. Furthermore, in an emergency, the cryogenic propellant needs to be urgently released. The loading port drain valve 9 is opened, the rocket body loading valve is opened, and the cryogenic propellant in the rocket body storage tank 6 is squeezed directly for emergency release. The outlet of the loading port drain valve 9 is connected to a safety release device.

[0028] like Figure 1As shown, in the cryogenic propellant loading system designed in this application, the connection point of the venting pipe at the loading port on the propellant supply pipe 2 is located between the ground loading valve 11 and the connecting hose 7. This connection point is at the highest point of the pipeline route, connecting above the pipe at the highest point. This allows for venting of the pipeline by opening the venting valve 5. After propellant loading is completed, the rocket body loading valve is closed. The cryogenic liquid inside the pipeline will gradually increase in temperature and pressure due to heat conduction. At this time, opening the venting valve 5 ensures that the pressure in the ground pipeline of the propellant loading system remains lower than the pressure in the rocket body storage tank 6, preventing the addition of gas or liquid to the rocket body storage tank through the loading port, making the entire loading system more stable and controllable. During the test, the pressure of the propellant supply pipe 2 and the connecting hose 7 needs to be kept lower than the pressure in the rocket body storage tank 6 to prevent the addition of gas or liquid through the loading port. After the test, the propellant supply pipe 2 and equipment still need to be kept in good connection and operational condition, and the remaining propellant in the rocket body should be safely drained back.

[0029] Preferably, in combination with the above schemes, such as Figure 1 As shown, the propellant supply subsystem of this application includes a propellant tank 1, a refueling filter 8, a ground refueling valve 11, and a flow meter 10. One end of the propellant supply pipeline 2 is connected to the propellant tank 1, and the other end is connected to the rocket body tank 6. The ground refueling valve 11, the flow meter 10, and the refueling filter 8 are all installed on the propellant supply pipeline 2, and the refueling filter 8 is used to filter the cryogenic propellant. Specifically, the connection point of the ground pipeline pre-cooling discharge subsystem on the propellant supply pipeline 2 is located on the propellant supply pipeline 2 between the propellant tank 1 and the ground refueling valve 11, thus enabling separate pre-cooling discharge. The connection points of the refueling port venting subsystem and the refueling port venting subsystem on the propellant supply pipeline 2 are respectively located on the propellant supply pipeline 2 between the ground refueling valve 11 and the rocket body tank 6, thereby enabling propellant venting and venting.

[0030] Preferably, in combination with the above schemes, such as Figure 1As shown, the cryogenic propellant refueling system proposed in this application includes a ground pipeline pre-cooling discharge subsystem comprising a ground pipeline pre-cooling discharge pipeline and a pre-cooling discharge valve 3, with the pre-cooling discharge valve 3 installed on the ground pipeline pre-cooling discharge pipeline. The cryogenic propellant refueling system also includes a refueling port venting subsystem comprising a refueling port venting pipeline and a refueling port venting valve 9. The connection point of the refueling port venting pipeline to the propellant supply pipeline 2 is located on the propellant supply pipeline 2 between the ground refueling valve 11 and the connecting hose 7, and is located at the lowest point of the connecting hose 7. The refueling port venting valve 9 is installed on the refueling port venting pipeline. Furthermore, the refueling port venting pipeline is also equipped with a vent gas seal 4, which discharges a room-temperature inert gas. When the refueling venting valve 9 is opened, after the propellant has been discharged, there is a risk of cryogenic backflow in the pipeline. Opening the vent gas seal 4 at this time can prevent air backflow into the propellant supply pipeline.

[0031] Preferably, in combination with the above schemes, such as Figure 1 As shown, the cryogenic propellant refueling system proposed in this application includes a refueling port venting subsystem comprising a refueling port venting pipeline and a venting valve 5. The connection point of the refueling port venting pipeline to the propellant supply pipeline 2 is located on the propellant supply pipeline 2 between the ground refueling valve 11 and the connecting hose 7, and is located at the highest point of the connecting hose 7. The venting valve 5 is installed on the refueling port venting pipeline. For cryogenic propellant refueling with liquid hydrogen, the ground pipeline pre-cooling discharge subsystem, the refueling port venting subsystem, and other discharge pipelines need to undergo safe discharge treatment, for example, they can be connected to a safe discharge device for safe discharge.

[0032] Preferably, the non-vacuum insulated portion of the propellant supply pipeline 2 is equipped with a liquid air diversion device to prevent cryogenic liquid air from damaging other equipment; the liquid air diversion device is located below the propellant supply pipeline 2 to divert the liquid air. The aforementioned non-vacuum insulated portion refers to the non-vacuum insulated portion of the propellant supply pipeline. For the insulation of the propellant supply pipeline, there are generally forms such as vacuum insulation, foamed insulation, or insulation material covering. Except for vacuum insulation, the insulation effect is not very good. For liquid hydrogen propellants, liquid air is easily generated. In this case, to prevent cryogenic liquid air from damaging other equipment, a liquid air diversion device can be selected. The liquid air diversion device of this application can prevent air liquefaction outside the pipeline of the refueling system during the propellant refueling stage due to the low temperature of the propellant. The liquefied air is very cold and may freeze surrounding equipment. The liquid air diversion device of this application can divert the liquid air to a safe area. Furthermore, the liquid air diversion device is fixed to the pipeline. A hydrogen concentration monitoring device can be installed at the hydrogen pipeline connection point of propellant supply line 2 to monitor the liquid hydrogen concentration. Additionally, when liquid methane is used as the cryogenic propellant, since it is a flammable and explosive medium like liquid hydrogen, a concentration monitoring device is also required.

[0033] Preferably, in combination with the above schemes, such as Figure 4 As shown, in this embodiment, the liquid-air diversion device specifically includes a liquid collection tank 19 and a diversion pipe 21. The liquid collection tank 19 is an elongated tank, tilted downwards below the propellant supply pipeline 2, facilitating liquid collection by gravity. Furthermore, the outer layer of the liquid collection tank 19 is provided with a heat insulation layer 20, preferably located in the lower part of the tank to prevent heat loss and subsequent drainage failure. One end of the diversion pipe 21 is connected to the lowest point of the liquid collection tank 19, and the other end guides the collected liquid to a safe discharge area. The propellant supply system support component and the refueling system equipped with this component in this application use liquid hydrogen as the cryogenic propellant, and a hydrogen concentration monitoring device is provided on the propellant supply pipeline 2 to monitor the liquid hydrogen and improve safety monitoring.

[0034] The propellant loading system with supporting components proposed in this application not only protects against low-temperature deformation and vibration of the propellant supply pipeline and the rocket body, and reasonably compensates for the low-temperature deformation generated simultaneously by the propellant supply pipeline and the rocket body, but also maintains the flexibility of the loading nozzle under the huge vibration of the rocket body during the test phase, without generating additional force at the rocket-to-ground interface. Moreover, by independently setting up each ground low-temperature pipeline, the flow rate at different loading stages is strictly controlled to avoid a large amount of low-temperature vapor entering the storage tank and causing back pressure during the ground loading process. It can meet the loading indicators during the low-temperature propellant loading process and can also effectively and safely drain the remaining propellant from the rocket body.

[0035] This application also relates to a cryogenic propellant loading method for conducting rocket core stage propulsion system tests using the above-mentioned propellant loading system, comprising the following steps:

[0036] (1) Connect the propellant supply pipeline to the rocket body, install the propellant supply subsystem, including the above-mentioned support components, and perform heat insulation treatment on the non-vacuum insulation parts;

[0037] (2) Pressurize the propellant supply pipeline through the external gas pipeline of the propellant storage tank or the propellant supply pipeline; when pressurizing, open the ground filling valve, close the pre-cooling discharge valve, close the vent valve, and close the filling port drain valve. The pressurization pressure is 0.2 MPa, and the pressure of the rocket body storage tank is kept greater than 0.2 MPa.

[0038] (3) Depressurize by opening the pre-cooling discharge valve, the vent valve and the filling port drain valve respectively. When the pressure reaches below 0.05MPa, close the pre-cooling discharge valve, the vent valve and the filling port drain valve. Repeat this cycle until the gas index inside the propellant supply pipeline meets the filling requirements.

[0039] (4) Pressurize the propellant tank, open the pre-cooling discharge valve, open the liquid outlet valve of the propellant tank, and pre-cool the ground pipeline before the ground filling valve of the propellant supply pipeline at a small flow rate until the temperature sensor reading before the pre-cooling discharge valve meets the pre-cooling requirements. Then close the pre-cooling discharge valve. At this time, the propellant supply pipeline is connected to the propellant tank, and the pipeline pressure is kept consistent with the propellant tank pressure. The ground filling valve is kept closed.

[0040] (5) Open the discharge valve of the rocket body tank to depressurize the rocket body tank. When the pressure is lower than 0.05MPa, open the rocket body refueling valve; open the ground refueling valve and adjust the flow rate to the minimum state. After the pressure of the rocket body tank stabilizes, slowly increase the refueling flow rate; the refueling flow rate can be controlled by the ground refueling valve. At this time, the ground refueling valve must be a regulating valve. The refueling flow rate can also be controlled by the liquid outlet valve of the propellant tank.

[0041] (6) After the rocket body tank is filled, close the ground filling valve. At this time, the propellant tank is connected to the propellant supply pipeline, and the propellant tank is depressurized to prevent the low temperature pipeline from heating up and causing the pressure to exceed the safe range. After the filling valve of the rocket body tank is closed, open the vent valve to release the low temperature gas in the pipeline between the ground filling valve and the rocket body tank, so that the pressure inside the pipeline is close to the atmospheric pressure, and the residual low temperature liquid in the pipeline is in a natural evaporation state until the end of the test.

[0042] (7) After the rocket body is ignited, the propellant tank and propellant supply pipeline, which have been depressurized, are ready for the return of remaining propellant. At this time, open the rocket body refueling valve, close the venting valve, and open the ground refueling valve. The propellant can then be returned to the propellant tank via the original route. In case of refueling abnormality or propellant discharge, the ground refueling valve must be closed, the refueling port discharge valve opened, and the rocket body refueling valve opened to allow the propellant to be discharged directly and quickly from the refueling port discharge valve.

[0043] (8) After the propellant has been discharged, close the discharge valve at the filling port and open the gas seal at the discharge port until the pipeline at the outlet of the discharge valve at the filling port reaches normal temperature.

[0044] In this application, after the cryogenic propellant begins to pre-cool the pipeline and rocket tank downstream of the ground loading valve, the rocket-ground connection pipeline and rocket tank begin to undergo cryogenic deformation under the influence of the cryogenic propellant. The rocket-ground connection hose shrinks due to the cryogenic temperature, and as the loading flow rate increases, the loading pressure also increases, causing the hose to stretch under pressure. During this process, the connection hose moves axially along the sliding hinge support to compensate for the pipeline deformation during loading. As the propellant enters the rocket tank, the liquid level continuously rises, and the shrinkage of the cryogenic portion of the rocket gradually increases. The fixed point between the rocket and the test platform remains unchanged, but the rocket tank material shrinks. At this point, it is necessary to pay attention to the deformation ΔL below the insulating elastic buffer layer; this deformation is the rocket deformation. When a deformation ΔL occurs, the height adjustment component of the vertically adjustable bracket needs to be adjusted so that the bracket rises and falls along the direction of rocket body contraction. The connection between the connecting hose and the rocket body storage tank also rises and falls accordingly until the deformation ΔL below the thermally insulating elastic buffer layer = 0. At this point, during the release of displacement by the bracket, the connecting hose moves in accordance with the direction of low-temperature deformation of the rocket body. As the storage tank filling port rises and falls, it will no longer exert additional force on the rocket body storage tank filling interface. After the connecting hose and the rocket body connection end descend, the hose will undergo an angular change in the vertical plane. At this time, the sliding hinge bracket at the hinge point will rotate at an angle, following the connecting hose to complete the angular compensation. The entire filling pipeline is in a free state with no stress concentration points, ensuring reliable quality of the filling process.

[0045] During rocket ignition, the massive vibration causes all connected piping and equipment to vibrate. This vibration is buffered and isolated by an insulating elastic buffer layer, preventing direct transmission to connecting hoses and protecting the strength of the pipes and connections. During propellant loading, if the medium is liquid hydrogen, a large amount of liquid air will be generated in the non-vacuum insulated section of the propellant supply pipeline. This liquid air near the rocket body can flow towards surrounding equipment and cables, affecting their functionality. This invention incorporates a liquid air diversion device located below the propellant supply pipeline. The device is fixed to the pipeline, and an insulation layer is provided at the bottom of the collection tank to prevent liquid air from falling into the tank and evaporating instantly, thus preventing the accumulation of low-temperature vapor that could obstruct visibility or remote monitoring. The liquid air is collected in the collection tank to the lowest point and then guided along the diversion pipe to a room-temperature open area.

[0046] Although the embodiments disclosed in this application are as described above, the content is merely for the purpose of facilitating understanding of this application and is not intended to limit this application. Any person skilled in the art to which this application pertains may make any modifications and changes in the form and details of the implementation without departing from the spirit and scope disclosed in this application; however, the scope of patent protection of this application shall still be determined by the scope defined in the appended claims.

Claims

1. A support assembly for a propellant supply system, characterized in that, The propellant supply system includes a propellant supply... The propellant supply line (2) is connected to the rocket body tank (6) via the connecting hose (7). The support assembly includes a fixed bracket (22), a sliding hinge bracket (12), and a vertically adjustable bracket (13). The fixed bracket (22) is fixedly disposed at the end of the propellant supply line (2) to limit the displacement of the end of the propellant supply line (2) caused by low-temperature deformation. The sliding hinge bracket (12) is disposed in the middle of the connecting hose (7) to support the connecting hose (7). The connecting hose (7) is able to move freely in the axial direction on the sliding hinge bracket (12) and generate angular displacement in the vertical plane. The vertically adjustable bracket (13) is located at one end of the connecting hose (7) connected to the rocket body storage tank (6), and the connecting hose (7) is able to move vertically on the vertically adjustable bracket (13).

2. The support assembly of the propellant supply system according to claim 1, characterized in that, The vertically adjustable bracket (13) includes a clamp (15), a fixed base (17), and a bracket (18); the bracket (18) is mounted on the fixed base (17) via a height adjustment component (16); the clamp (15) is mounted on the bracket (18), and the inner wall of the clamp (15) is provided with a heat-insulating elastic buffer layer (14); the clamp (15) is used to fix the connecting hose (7) through the heat-insulating elastic buffer layer (14).

3. A propellant loading system, characterized in that, The refueling system includes a propellant supply subsystem, a ground pipeline pre-cooling and discharge subsystem, a refueling port venting subsystem, and a refueling port venting subsystem. The propellant supply subsystem is connected to the rocket body tank (6) via a propellant supply pipeline (2) to achieve cryogenic propellant refueling. The ground pipeline pre-cooling and discharge subsystem, the refueling port venting subsystem, and the refueling port venting subsystem are each independently connected to the propellant supply pipeline (2). The connection points of the refueling port venting subsystem and the refueling port venting subsystem on the propellant supply pipeline (2) are respectively located on the propellant supply pipeline (2) between the ground pipeline pre-cooling and discharge subsystem and the rocket body tank (6). The propellant supply subsystem is also provided with a support component according to claim 1 or 2. The ground pipeline pre-cooling and discharge subsystem includes a ground pipeline pre-cooling and discharge pipeline and a pre-cooling and discharge valve (3). The pre-cooling and discharge valve (3) is located on the ground pipeline pre-cooling and discharge pipeline.

4. The propellant loading system according to claim 3, characterized in that, The propellant supply subsystem includes a propellant tank (1) and a ground refueling valve (11); one end of the propellant supply pipeline (2) is connected to the propellant tank (1), and the other end of the propellant supply pipeline (2) is connected to the rocket body tank (6); the ground refueling valve (11) is located on the propellant supply pipeline (2); the connection point of the ground pipeline precooling and discharge subsystem on the propellant supply pipeline (2) is located on the propellant supply pipeline (2) between the propellant tank (1) and the ground refueling valve (11); the connection points of the refueling port venting subsystem and the refueling port venting subsystem on the propellant supply pipeline (2) are respectively located on the propellant supply pipeline (2) between the ground refueling valve (11) and the rocket body tank (6).

5. The propellant loading system according to claim 4, characterized in that, The refueling port venting subsystem includes a refueling port venting pipeline and a refueling port venting valve (9); the connection point of the refueling port venting pipeline on the propellant supply pipeline (2) is located on the propellant supply pipeline (2) between the ground refueling valve (11) and the connecting hose (7); the refueling port venting valve (9) is provided on the refueling port venting pipeline.

6. The propellant loading system according to claim 5, characterized in that, The venting subsystem of the filling port includes a venting pipeline and a venting valve (5); the connection point of the venting pipeline on the propellant supply pipeline (2) is located on the propellant supply pipeline (2) between the ground filling valve (11) and the connecting hose (7); the venting valve (5) is located on the venting pipeline of the filling port.

7. The propellant loading system according to claim 6, characterized in that, The cryogenic propellant is liquid hydrogen, and the non-vacuum insulated part of the propellant supply pipeline (2) is provided with a liquid air guiding device; the liquid air guiding device includes a liquid collection tank (19) and a guiding pipe (21); the liquid collection tank (19) is inclined downward and located below the propellant supply pipeline (2); the outer layer of the liquid collection tank (19) is provided with a heat insulation layer (20); the guiding pipe (21) is connected to the lowest point of the liquid collection tank (19).

8. The propellant loading system according to any one of claims 4-7, characterized in that, When fueling the rocket body, open the ground fueling valve and the rocket body fueling valve, open the rocket body storage tank to vent, pressurize the propellant storage tank, and then squeeze or use a cryogenic pump to fuel the cryogenic propellant into the rocket body storage tank. When the cryogenic propellant in the rocket body tank is drained or discharged, first depressurize the propellant tank and open the vent of the propellant tank. Then open the ground filling valve and the rocket body filling valve to squeeze the cryogenic propellant in the rocket body tank into the propellant tank for draining.

9. The propellant loading system according to any one of claims 5-7, characterized in that, When fueling the rocket body, open the ground fueling valve and the rocket body fueling valve, open the rocket body storage tank to vent, pressurize the propellant storage tank, and then squeeze or use a cryogenic pump to fuel the cryogenic propellant into the rocket body storage tank. When the cryogenic propellant in the rocket body tank is vented, the vent valve at the loading port and the loading valve in the rocket body are opened to squeeze and vent the cryogenic propellant directly out of the rocket body tank. The outlet of the vent valve at the loading port is connected to a safety release device.

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