Support assembly for propellant supply system and filling system provided with such assembly

Abstract

The invention relates to a supporting assembly of a propellant supply system and a filling system provided with the supporting assembly. The supporting assembly comprises a fixed support, a sliding hinge support and a vertical adjustable support. The fixed bracket is fixedly arranged at the tail end of the propellant supply pipeline so as to limit displacement caused by low-temperature deformation; the sliding hinge support is arranged in the middle of the connecting hose to support the connecting hose. The vertical adjustable support is arranged at the end, connected with the rocket body storage box, of the connecting hose and can move on the vertical adjustable support in the vertical direction. The device can adapt to impact vibration in the rocket body filling deformation and test ignition stage, and remote control over safe release of the residual propellant of the rocket body is completed.

Description

Technical Field

[0001] The present application relates to a support component of a propellant supply system and a filling system provided with the component, and is applicable to the technical field of rocket core stage power system testing. Background Art

[0002] When testing the core stage power system of a rocket, it is necessary to carry the necessary engines, tanks, pressurized delivery pipelines and other onboard equipment for the core stage. At this time, the state of the rocket is basically the same as the launch state, but the rocket does not take off. Instead, the load-bearing device keeps the rocket body fixed on the test bench. During the entire test process, the ground filling pipeline needs to meet the functional requirements of the entire rocket caused by propellant filling, rocket body vibration during ignition, and propellant leakage. The external load that the interface connection part of the rocket body can withstand is very small, and the ground filling pipeline cannot generate a large reaction force during the test to avoid damage to the rocket body. Therefore, the docking method of the ground filling pipeline and the reasonable design of the support structure are the key links to the success of the power test.

[0003] Therefore, it is necessary in the prior art to design a support assembly for the propellant supply system so that during the test of the rocket core stage power system, the deformation safety of the ground filling pipeline can be ensured to prevent damage to the pipeline or the 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 filling system equipped with the component, aiming to provide reasonable support for the cryogenic propellant supply pipeline during the test of the rocket core stage power system, so that it can adapt to the impact vibration during the filling deformation of the rocket body and the test ignition stage, so as to avoid damage to the rocket body or the supply pipeline.

[0005] The present application relates to a support assembly of a propellant supply system, wherein the propellant supply system comprises a propellant supply pipeline and a connecting hose, wherein the propellant supply pipeline is connected to a rocket body tank via the connecting hose, and the support assembly comprises a fixed bracket, a sliding hinged bracket and a vertically adjustable bracket; the fixed bracket is fixedly arranged at the end of the propellant supply pipeline to limit the displacement of the end of the propellant supply pipeline caused by low-temperature deformation; the sliding hinged bracket is arranged at the middle of the connecting hose to support the connecting hose, and the connecting hose can freely move in an axial direction on the sliding hinged bracket and produce angular displacement in a vertical plane; the vertically adjustable bracket is arranged at one end of the connecting hose connected to the rocket body tank, and the connecting hose can move in a vertical direction on the vertically adjustable bracket.

[0006] Among them, the vertically adjustable bracket can also include a clamp, a fixed base and a bracket; the bracket is arranged on the fixed base through a height adjustment piece; the clamp is arranged on the bracket, and an insulating elastic buffer layer is provided on the inner wall of the clamp; the clamp is sleeved and fixed to the connecting hose through the insulating elastic buffer layer.

[0007] The present application also relates to a propellant filling system, comprising a propellant supply subsystem, a ground pipeline precooling and discharge subsystem, a filling port discharge subsystem and a filling port venting subsystem; the propellant supply subsystem is connected to a rocket body tank via a propellant supply pipeline to realize low-temperature propellant filling; the ground pipeline precooling and discharge subsystem, the filling port discharge subsystem and the filling port venting subsystem are independently connected to the propellant supply pipeline respectively; the connection points of the filling port discharge subsystem and the filling port venting subsystem on the propellant supply pipeline are respectively located on the propellant supply pipeline between the ground pipeline precooling and discharge subsystem and the rocket body tank, and the propellant supply subsystem is provided with a support assembly as described above.

[0008] Wherein, the propellant supply subsystem includes a propellant tank and a ground filling valve; one end of the propellant supply pipeline is connected to the propellant tank, the other end of the propellant supply pipeline is connected to the rocket body tank, and the ground filling valve is arranged on the propellant supply pipeline; the connection point of the ground pipeline precooling discharge subsystem on the propellant supply pipeline is located on the propellant supply pipeline between the propellant tank and the ground filling valve; the connection points of the filling port discharge subsystem and the filling port venting subsystem on the propellant supply pipeline are respectively located on the propellant supply pipeline between the ground filling valve and the rocket body tank. The ground pipeline precooling discharge subsystem includes a ground pipeline precooling discharge pipeline and a precooling discharge valve, and the precooling discharge valve is arranged on the ground pipeline precooling discharge pipeline. The filling port discharge subsystem includes a filling port discharge pipeline and a filling port discharge valve; the connection point of the filling port discharge pipeline on the propellant supply pipeline is located on the propellant supply pipeline between the ground filling valve and the connecting hose; the filling port discharge valve is arranged on the filling port discharge pipeline. The filling port venting subsystem includes a filling port venting pipeline and a venting valve; the connection point of the filling port venting pipeline on the propellant supply pipeline is located on the propellant supply pipeline between the ground filling valve and the connecting hose; the venting valve is arranged on the filling port venting pipeline.

[0009] Wherein, the cryogenic propellant is liquid hydrogen, and the non-vacuum insulation part of the propellant supply pipeline is provided with a liquid-to-air guide device; the liquid-to-air guide device includes a liquid collecting tank and a guide pipe; the liquid collecting tank is arranged downwardly inclined below the propellant supply pipeline; the outer layer of the liquid collecting tank is provided with an insulation layer; and the guide pipe is connected to the lowest point of the liquid collecting tank. When filling the rocket body, open the ground filling valve and the rocket body filling valve, open the rocket body tank to vent, pressurize the propellant tank, and then squeeze or use a cryogenic pump to fill the cryogenic propellant into the rocket body tank; when the cryogenic propellant in the rocket body tank is to be discharged back or discharged, first depressurize the propellant tank and open the vent of the propellant tank, open the ground filling valve and the rocket body filling valve, and squeeze the cryogenic propellant in the rocket body tank into the propellant tank for discharge back; or, when the cryogenic propellant in the rocket body tank is to be discharged, open the filling port discharge valve and the rocket body filling valve, squeeze the cryogenic propellant in the rocket body tank and discharge it directly, and the outlet of the filling port discharge valve is connected to the safety discharge device.

[0010] The present application proposes a support component for a propellant supply system and a filling system provided with the component, which can not only realize low-temperature deformation protection and vibration protection for the propellant supply pipeline and the rocket body, and reasonably compensate for the low-temperature deformation of the propellant supply pipeline and the rocket body simultaneously, but also maintain the flexible follow-up of the filling pipe mouth under the huge vibration of the rocket body during the test phase, and do not generate additional force on the arrow-ground interface; and by independently setting up each ground low-temperature pipeline, strictly control the flow rate at different filling stages, avoid a large amount of low-temperature steam entering the tank during the ground filling process to cause back pressure, and can meet the filling indicators during the low-temperature propellant filling process, and can also effectively and safely discharge the remaining propellant in the rocket body. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 It is a schematic diagram of a support component of a propellant supply system of the present application and a filling system provided with the component.

[0012] Figure 2 It is a schematic diagram of the arrow-to-ground butt pipe support structure of the present application.

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

[0014] Figure 4 It is a schematic diagram of the liquid-air guide device of the present application.

[0015] In the figure: 1. propellant storage tank; 2. propellant supply pipeline; 3. pre-cooling discharge valve; 4. discharge port air seal; 5. vent valve; 6. rocket body tank; 7. connecting hose; 8. filling filter; 9. filling port discharge valve; 10. flow meter; 11. ground filling valve; 12. sliding hinged bracket; 13. vertically adjustable bracket; 14. thermal insulation elastic buffer layer; 15. clamp; 16. height adjustment member; 17. fixed base; 18. bracket; 19. liquid collecting tank; 20. insulation layer; 21. guide pipe; 22. fixed bracket. DETAILED DESCRIPTION

[0016] In order to make the purpose, technical solutions and advantages of the present application clearer, the embodiments of the present application will be described in detail in conjunction with the accompanying drawings below. It should be noted that, in the absence of conflict, the embodiments in the present application and the features in the embodiments can be combined with each other arbitrarily. Those skilled in the art will understand that a support assembly of a propellant supply system of the present application and a filling system provided with the assembly can be applicable to the field of rocket core stage power system testing. The cryogenic propellant of the present application is usually liquid oxygen, liquid methane or liquid hydrogen.

[0017] like Figure 1 As shown, a support component of a propellant supply system of the present application and a filling system provided with the component, the filling system includes a propellant supply subsystem, a ground pipeline precooling and discharge subsystem, a filling port discharge subsystem and a filling port venting subsystem. Among them, the propellant supply subsystem is connected to the rocket body tank 6 through its propellant supply pipeline 2, and can realize low-temperature propellant filling. A ground filling valve 11 is provided between the propellant supply pipeline 2 and the rocket body tank 6, which is used to switch the refrigerant supply pipeline. The ground filling valve 11 is arranged on one end of the propellant supply pipeline 2 close to the rocket body. The ground pipeline precooling and discharge subsystem, the filling port discharge subsystem and the filling port venting subsystem are respectively designed as independent system pipelines, and are respectively connected to the propellant supply pipeline 2 to realize the filling and discharge of the propellant at the filling port of the rocket body tank 6. Furthermore, the connection points of the filling port discharge subsystem and the filling port venting subsystem on the propellant supply pipeline 2 are respectively located on the propellant supply pipeline 2 between the ground filling valve 11 and the rocket body tank 6 .

[0018] The ground pipeline precooling discharge subsystem is used for separate precooling and discharge of the ground pipeline. The connection point of the ground pipeline precooling 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 filling valve 11, close to the ground filling valve 11. The filling port discharge subsystem is used to discharge the remaining cryogenic propellant in the rocket body tank 6, and the filling port venting subsystem is used to vent the filling system. The filling system of the present application can avoid a large amount of low-temperature steam entering the tank during the ground filling process to cause back pressure by strictly controlling the flow rate at different filling stages. During the test, the ground pipeline pressure of the filling system needs to be kept lower than the pressure of the rocket body tank 6 to avoid air or fluid replenishment from the rocket body filling port. After the test is completed, the cryogenic pipeline and equipment still need to maintain a good connection and use state, and the safe discharge back of the remaining propellant in the rocket body must be handled to meet the filling indicators.

[0019] like Figure 1 As shown, the filling system proposed in the present application, its propellant supply subsystem also includes a connecting hose 7, and the propellant supply pipeline 2 is connected to the rocket body tank 6 through the connecting hose 7 to achieve a flexible connection between the two and meet the needs of flexible deformation. The other end of the propellant supply pipeline 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 low-temperature propellant filling is completed, the filling system is generally not separated from the rocket body. Therefore, the ground pipeline needs to avoid the low-temperature deformation of the ground pipeline bringing a reaction force to the rocket body interface. At the same time, the ground pipeline must also adapt to the low-temperature deformation and vibration of the rocket body to avoid affecting the rocket body interface strength or interface sealing during filling and testing. After the test is completed, the ground low-temperature pipeline, i.e., the propellant supply pipeline 2 and the equipment still need to maintain a good connection and use state to safely discharge the remaining propellant of the rocket body.

[0020] To achieve the above purpose, the propellant supply subsystem of the present application also includes a support assembly for supporting the propellant supply pipeline 2 and the connecting hose 7 to withstand the deformation and vibration caused by the rocket body. Figure 2-3As shown, the support assembly of the propellant supply system according to the present application includes a fixed bracket 22, a sliding hinge bracket 12 and a vertically adjustable bracket 13; the fixed bracket 22 is fixedly arranged on the propellant supply pipeline 2 at the front end of the connecting hose 7 as a primary support, and is close to the position of the connecting hose 7 to limit the movement of the propellant supply pipeline 2, and is used to isolate the low-temperature deformation of the propellant supply pipeline 2 of the ground cryogenic pipeline, and prevent the propellant supply pipeline 2 from causing displacement of the connecting hose 7. Further, the sliding hinge bracket 12 is arranged at one end of the connecting hose 7 connected to the propellant supply pipeline 2 as a secondary support, and can be specifically arranged 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 forward and backward when deformed at low temperature, and at the same time, the hinge structure compensates for the angular deformation caused by the low-temperature downward displacement of the arrow-ground interface. Furthermore, the vertically adjustable bracket 13, as a third-level support, can be arranged at one end of the connecting hose 7 connected to the rocket tank 6, close to the connection port of the rocket tank 6, to ensure that the ground pipeline does not generate additional force on the rocket. And the connecting hose 7 can move in the vertical direction on the vertically adjustable bracket 13, so as to adapt to the vertical deformation of the rocket during the filling stage.

[0021] Preferably, in combination with the above scheme, Figure 3 As shown, in this embodiment, the vertical adjustable bracket 13 includes a clamp 15, a fixed base 17 and a bracket 18; wherein the bracket 18 is arranged on the fixed base 17 through a height adjustment member 16; the clamp 15 is arranged on the bracket 18, and a heat-insulating elastic buffer layer 14 is arranged on the inner wall of the clamp 15. Specifically, the clamp 15 is sleeved and fixed to the connecting hose 7 through the heat-insulating elastic buffer layer 14, that is, the heat-insulating elastic buffer layer 14 is laid between the clamp 15 and the connecting hose 7. Specifically, during the filling process, the deformation amount ΔL of the heat-insulating elastic buffer layer 14 in the filling stage can be achieved by mechanically adjusting the vertical height of the vertical adjustable bracket 13 to adapt to the deformation amount of the arrow body in the filling stage, and the heat-insulating elastic buffer layer 14 can be used to compensate for the vibration displacement caused by the arrow body in the test stage, and the ground pipeline can form a follow-up with the arrow body in both the filling stage and the ignition test stage to ensure that the ground pipeline does not generate additional force on the arrow body.

[0022] Specifically, during the filling process, the deformation ΔL of the thermal insulation elastic buffer layer 14 during the filling stage can be achieved by mechanically adjusting the vertical height of the vertical adjustable bracket 13 to adapt to the deformation of the rocket body during the filling stage. ΔL can be calculated using the following formula:

[0023] ΔL=H·α·ΔT+Δε,

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

[0025] The support assembly of the propellant supply system proposed in this application can avoid the additional force on the rocket body interface caused by the low-temperature deformation of the ground pipeline by designing a three-level support and a flexible connection in the system 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 of the cryogenic propellant filling system designed by the present application is as follows: the ground filling valve 11 is closed, and the precooling discharge valve 3 is opened at this time, and the cryogenic propellant is discharged from the precooling discharge valve 3 at a small flow rate, thereby precooling the ground pipeline before the ground filling valve 11. Therefore, the present application adopts a series of safety measures including the above-mentioned precooling to avoid the generation of a large amount of cryogenic steam in the ground pipeline caused by direct filling of the rocket body, which in turn causes the pressure of the storage tank to rise rapidly and become overpressure, which is not conducive to product quality control.

[0027] like Figure 1 As shown, the cryogenic propellant filling system designed by the present application can be used to fill the rocket body, and can also discharge the liquid oxygen in the rocket body tank 6. When filling the rocket body, open the ground filling valve 11, open the rocket body filling valve set on the rocket body, open the rocket body tank 6 to exhaust, pressurize the propellant tank 1, and then squeeze or use a cryogenic pump to fill the cryogenic propellant into the rocket body tank 6. When the cryogenic propellant in the rocket body tank 6 is discharged back or discharged, first depressurize the propellant tank 1 and open the exhaust port of the propellant tank 1, open the ground filling valve 11, open the rocket body filling valve, and squeeze the cryogenic propellant in the rocket body tank 6 into the propellant tank 1 for discharge back. Further, in an emergency, the cryogenic propellant needs to be discharged urgently, open the filling port discharge valve 9, open the rocket body filling valve, and squeeze the cryogenic propellant in the rocket body tank 6 directly for emergency discharge. The outlet of the filling port discharge valve 9 is connected to the safety discharge device.

[0028] like Figure 1As shown, the filling system of cryogenic propellant designed by the present application has a connection point of the filling port venting pipeline on the propellant supply pipeline 2 between the ground filling valve 11 and the connecting hose 7. The connection point is at the highest point of the pipeline laying route and is connected to the pipeline located above the highest point, so that the pipeline can be vented by opening the venting valve 5. After the propellant filling is completed, the rocket body filling valve is closed, and the cryogenic liquid inside the pipeline will gradually increase in temperature and pressure due to the heat conduction of the pipeline. At this time, opening the venting valve 5 can make the ground pipeline pressure of the propellant filling system always lower than the pressure of the rocket body tank 6, avoiding the replenishment of air or liquid to the rocket body tank from the rocket body filling port, making the entire filling system more stable and controllable. During the test, the pressure of the propellant supply pipeline 2 and the connecting hose 7 needs to be kept lower than the pressure of the rocket body tank 6 to avoid replenishing air or liquid from the rocket body filling port; after the test is completed, the propellant supply pipeline 2 and the equipment still need to maintain a good connection and use state, and the remaining propellant of the rocket body is safely discharged back.

[0029] Preferably, in combination with the above scheme, Figure 1 As shown, the propellant supply subsystem of the present application includes a propellant storage tank 1, a filling filter 8, a ground filling valve 11 and a flow meter 10; one end of the propellant supply pipeline 2 is connected to the propellant storage tank 1, and the other end of the propellant supply pipeline 2 is connected to the rocket body tank 6. The ground filling valve 11, the flow meter 10 and the filling filter 8 are all arranged on the propellant supply pipeline 2, and the filling filter 8 is used to filter the cryogenic propellant. Specifically, the connection point of the ground pipeline precooling 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 filling valve 11, so that separate precooling discharge can be achieved. The connection points of the filling port discharge subsystem and the filling port venting subsystem on the propellant supply pipeline 2 are respectively located on the propellant supply pipeline 2 between the ground filling valve 11 and the rocket body tank 6, so as to achieve the discharge and exhaust of the propellant.

[0030] Preferably, in combination with the above scheme, Figure 1As shown, the filling system of cryogenic propellant proposed in the present application, its ground pipeline precooling discharge subsystem includes a ground pipeline precooling discharge pipeline and a precooling discharge valve 3, and the precooling discharge valve 3 is arranged on the ground pipeline precooling discharge pipeline. The filling system of cryogenic propellant proposed in the present application, its filling port discharge subsystem includes a filling port discharge pipeline and a filling port discharge valve 9; the connection point of the filling port discharge 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, and is located at the low point of the connecting hose 7; the filling port discharge valve 9 is arranged on the filling port discharge pipeline. Furthermore, a discharge port air seal 4 is also provided on the filling port discharge pipeline, and the discharge port air seal 4 discharges inert gas at room temperature. When the filling discharge valve 9 is opened, after the propellant is discharged, it is easy to cause low-temperature back suction in the pipeline. At this time, opening the discharge port air seal 4 can prevent air from being sucked back into the propellant supply pipeline.

[0031] Preferably, in combination with the above scheme, Figure 1 As shown, the filling system of cryogenic propellant proposed in the present application, its filling port venting subsystem includes a filling port venting pipeline and a venting valve 5; the connection point of the filling port 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, and is located at the high point of the connecting hose 7; the venting valve 5 is arranged on the filling port venting pipeline. For the filling of cryogenic propellant with liquid hydrogen medium, the discharge pipelines such as the ground pipeline precooling discharge subsystem, the filling port venting subsystem and the filling port venting subsystem need to be safely discharged, for example, they can be connected to a safe discharge device for safe discharge.

[0032] Preferably, the non-vacuum insulation part of the propellant supply pipeline 2 is provided with a liquid air guide device to prevent low-temperature liquid air from damaging other equipment; the liquid air guide device is arranged below the propellant supply pipeline 2 to achieve diversion. The non-vacuum insulation part mentioned above refers to the non-vacuum insulation part of the propellant supply pipeline. For the insulation setting of the propellant supply pipeline, there are generally forms such as vacuum insulation, foaming stack insulation or insulation material coating. In addition to the vacuum insulation method, the insulation effect will not be too good. For liquid hydrogen propellant, liquid air is easy to be generated. At this time, in order to avoid low-temperature liquid air from damaging other equipment, a liquid air guide device can be selected. The liquid air guide device of the present application can prevent the situation that air will be liquefied outside the pipeline of the filling system during the propellant filling stage due to the low temperature of the propellant. At this time, the temperature of the liquefied air is very low, which may frostbite the surrounding equipment. The liquid air guide device of the present application can guide the liquid air to a safe area. Furthermore, the liquid air guide device is fixed by relying on the pipeline. A hydrogen concentration monitoring device can be provided at the hydrogen pipeline connection portion of the propellant supply pipeline 2 to monitor the concentration of liquid hydrogen. In addition, when liquid methane is used as the cryogenic propellant, since it is a flammable and explosive medium like liquid hydrogen, a concentration monitoring device also needs to be installed.

[0033] Preferably, in combination with the above scheme, Figure 4 As shown, in this embodiment, the liquid-air diversion device specifically includes a liquid collecting tank 19 and a diversion pipe 21; wherein, the liquid collecting tank 19 is a long strip liquid collecting tank, and the liquid collecting tank 19 is tilted downward and arranged below the propellant supply pipeline 2, so that it is convenient to collect liquid by gravity. Furthermore, the outer layer of the liquid collecting tank 19 is provided with an insulation layer 20, and the insulation layer 20 is preferably arranged in the lower part of the liquid collecting tank 19 to avoid loss of drainage due to loss of temperature. One end of the diversion pipe 21 is connected to the lowest point of the liquid collecting tank 19, and the other end of the diversion pipe 21 can divert the collected liquid to a safe discharge area. The support component of the propellant supply system of the present application and the filling system provided with the component, the cryogenic propellant can be liquid hydrogen, and a hydrogen concentration monitoring device is provided on the propellant supply pipeline 2 to realize the monitoring of liquid hydrogen and improve the safety monitoring efforts.

[0034] The propellant filling system provided with a support assembly proposed in the present application can not only realize the low-temperature deformation protection and vibration protection of the propellant supply pipeline and the rocket body, and reasonably compensate for the low-temperature deformation of the propellant supply pipeline and the rocket body at the same time, but also maintain the flexible follow-up of the filling pipe mouth under the huge vibration of the rocket body during the test phase, and do not generate additional force on the arrow-ground interface; and by independently setting up each ground low-temperature pipeline, strictly control the flow rate at different filling stages, avoid a large amount of low-temperature steam entering the tank during the ground filling process to cause back pressure, and can meet the filling indicators during the low-temperature propellant filling process, and can also effectively and safely discharge the remaining propellant in the rocket body.

[0035] The present application also relates to a cryogenic propellant filling method for conducting a rocket core stage power system test using the above-mentioned propellant filling 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 assembly, and perform thermal insulation treatment on the non-vacuum insulation parts;

[0037] (2) Pressurize the propellant supply pipeline through the propellant storage tank or the external gas pipeline of the propellant supply pipeline; when pressurizing, open the ground filling valve, close the pre-cooling discharge valve, close the air release valve, close the filling port discharge valve, the pressurization pressure is 0.2MPa, and the pressure of the rocket body tank is maintained above 0.2MPa;

[0038] (3) Release the pressure by opening the precooling discharge valve, the air release valve and the filling port relief valve respectively. When the pressure reaches less than 0.05 MPa, close the precooling discharge valve, the air release valve and the filling port relief valve. Repeat this cycle until the gas indicators inside the propellant supply pipeline meet the filling requirements;

[0039] (4) Pressurize the propellant tank, open the precooling discharge valve, open the liquid outlet valve of the propellant tank, and precool the ground pipeline of the propellant supply pipeline before the ground filling valve at a small flow rate until the temperature sensor before the precooling discharge valve shows that it meets the precooling requirement, and then close the precooling discharge valve. At this time, the propellant supply pipeline is connected to the propellant tank, and the pipeline pressure is maintained consistent with the propellant tank pressure. The ground filling valve remains closed;

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

[0041] (6) After the rocket 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 safety range; after the filling valve of the rocket tank is closed, open the vent valve to release the low-temperature gas in the pipeline between the ground filling valve and the rocket tank, so that the internal pressure of the pipeline is close to the atmospheric pressure, and the residual low-temperature liquid in the pipeline is in a natural volatilization state until the end of the test;

[0042] (7) After the rocket body is ignited, the propellant tank and propellant supply pipeline that have completed pressure relief are ready to discharge the remaining propellant. At this time, open the rocket body filling valve, close the vent valve, open the ground filling, and the propellant can be discharged back to the propellant tank. In case of abnormal filling or propellant discharge, it is necessary to close the ground filling valve, open the filling port discharge valve, open the rocket body filling valve, and discharge the propellant directly and quickly from the filling port discharge valve;

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

[0044] After the cryogenic propellant in this application begins to pre-cool the pipelines and the rocket tank after the ground filling valve, the pipelines and the rocket tank that are connected to the ground begin to deform at low temperatures under the action of the cryogenic propellant. The rocket-ground connecting hose shrinks due to the low temperature, and after the filling flow rate increases, the filling pressure will increase, and the hose will extend under the pressure. During this process, the connecting hose will move along the axial direction of the hose on the sliding hinged bracket to compensate for the deformation of the pipeline during the filling process. As the propellant enters the rocket tank, the liquid level continues to rise, and the shrinkage of the low-temperature part of the rocket body gradually increases. The fixed point position of the rocket body and the test bench remains unchanged, and the material of the rocket tank shrinks. At this time, it is necessary to pay attention to the deformation ΔL below the thermal insulation elastic buffer layer, which is the deformation of the rocket body. When the deformation ΔL occurs, it is necessary to adjust the height adjustment part of the vertical adjustable bracket so that the bracket rises and falls along the direction of the arrow body contraction, and the connection part of the connecting hose and the arrow body tank also rises and falls accordingly, until the deformation ΔL below the thermal insulation elastic buffer layer is 0. At this time, the connecting hose moves in the direction of the low-temperature deformation of the arrow body during the process of the bracket releasing the displacement, and no additional force is generated on the filling interface of the arrow body tank as the tank filling port rises and falls. After the connecting hose and the arrow body connection end fall, it will drive the hose to produce an angle change in the vertical plane. At this time, the sliding hinge bracket will produce an angle flip at the hinge part, and follow the connecting hose to complete the angle compensation. The entire filling pipeline is in a free state, without stress concentration parts, ensuring the quality of the filling process is reliable.

[0045] When the rocket body is ignited, the huge vibration will drive all the pipeline equipment connected to the rocket body to vibrate. The vibration is buffered and isolated by the insulating elastic buffer layer, and will not be directly transmitted to the connecting hose, thereby protecting the strength of the pipeline and the connecting parts. During the propellant filling process, if the medium is liquid hydrogen, a large amount of liquid air will be generated in the non-vacuum insulation part of the propellant supply pipeline. The liquid air near the rocket body will flow to the equipment, cables, etc. around the rocket body, affecting the function of the equipment. The present invention is provided with a liquid air diversion device; the liquid air diversion device is arranged below the propellant supply pipeline. The liquid air diversion device is fixed to the pipeline, and an insulation layer is provided at the bottom of the outer side of the liquid collecting tank, so that the liquid air will not fall into the tank and evaporate instantly, causing the low-temperature steam on site to gather and affect the line of sight or remote monitoring. After the liquid air is concentrated to the lowest point along the liquid collecting tank, it is diverted along the diversion pipe to an open area at normal temperature.

[0046] Although the implementation methods disclosed in this application are as above, the contents described are only implementation methods adopted for facilitating the understanding of this application, and are not intended to limit this application. Any technician in the technical field to which this application belongs can make any modifications and changes in the form and details of implementation without departing from the spirit and scope disclosed in this application, but the scope of patent protection of this application shall still be based on the scope defined in the attached claims.

Claims

1. A support assembly for a propellant supply system, characterized in that: The propellant supply system comprises a propellant supply pipeline (2) and a connecting hose (7), wherein the propellant supply pipeline (2) is connected to a rocket body tank (6) via the connecting hose (7), and the supporting assembly comprises a fixed bracket (22), a sliding hinge bracket (12) and a vertically adjustable bracket (13); the fixed bracket (22) is fixedly arranged at the end of the propellant supply pipeline (2) to limit the displacement of the end of the propellant supply pipeline (2) caused by low temperature deformation; the sliding hinge bracket (12) is arranged at the middle of the connecting hose (7) to support the connecting hose (7), and the connecting hose (7) can freely move along the axial direction on the sliding hinge bracket (12) and generate angular displacement in a vertical plane; The vertically adjustable bracket (13) is arranged at one end of the connecting hose (7) connected to the rocket body tank (6), and the connecting hose (7) can move in a vertical direction 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) comprises a clamp (15), a fixed base (17) and a bracket (18); the bracket (18) is arranged on the fixed base (17) through a height adjustment member (16); the clamp (15) is arranged on the bracket (18), and a heat-insulating elastic buffer layer (14) is provided on the inner wall of the clamp (15); the clamp (15) is sleeved and fixed to the connecting hose (7) through the heat-insulating elastic buffer layer (14).

3. A propellant filling system, characterized in that: The filling system comprises a propellant supply subsystem, a ground pipeline precooling and discharge subsystem, a filling port discharge subsystem and a filling port venting subsystem; the propellant supply subsystem is connected to the rocket body tank (6) through a propellant supply pipeline (2) to realize low-temperature propellant filling; the ground pipeline precooling and discharge subsystem, the filling port discharge subsystem and the filling port venting subsystem are respectively and independently connected to the propellant supply pipeline (2); the connection points of the filling port discharge subsystem and the filling port venting subsystem on the propellant supply pipeline (2) are respectively located on the propellant supply pipeline (2) between the ground pipeline precooling and discharge subsystem and the rocket body tank (6), and the propellant supply subsystem is also provided with a support assembly according to claim 1 or 2.

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

5. The propellant filling system according to claim 4, characterized in that: The ground pipeline precooling discharge subsystem comprises a ground pipeline precooling discharge pipeline and a precooling discharge valve (3), and the precooling discharge valve (3) is arranged on the ground pipeline precooling discharge pipeline.

6. The propellant filling system according to claim 5, characterized in that: The filling port discharge subsystem comprises a filling port discharge pipeline and a filling port discharge valve (9); the connection point of the filling port discharge 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 filling port discharge valve (9) is arranged on the filling port discharge pipeline.

7. The propellant filling system according to claim 6, characterized in that: The filling port venting subsystem comprises a filling port venting pipeline and a venting valve (5); the connection point of the filling port 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 arranged on the filling port venting pipeline.

8. The propellant filling system according to claim 7, characterized in that: The cryogenic propellant is liquid hydrogen, and the non-vacuum insulation portion of the propellant supply pipeline (2) is provided with a liquid-to-air flow guide device; the liquid-to-air flow guide device comprises a liquid collecting tank (19) and a flow guide pipe (21); the liquid collecting tank (19) is arranged downwardly inclined below the propellant supply pipeline (2); the outer layer of the liquid collecting tank (19) is provided with a heat-insulating layer (20); and the flow guide pipe (21) is connected to the lowest point of the liquid collecting tank (19).

9. The propellant filling system according to any one of claims 4 to 8, characterized in that: When filling the rocket body, open the ground filling valve and the rocket body filling valve, open the rocket body tank to vent, pressurize the propellant tank, and then squeeze or use a cryogenic pump to fill the cryogenic propellant into the rocket body tank; When the cryogenic propellant in the rocket body tank is to be discharged back or out, first the propellant tank is depressurized and the exhaust port of the propellant tank is opened, the ground filling valve and the rocket body filling valve are opened, and the cryogenic propellant in the rocket body tank is squeezed into the propellant tank for discharge back.

10. The propellant filling system according to any one of claims 6 to 8, characterized in that: When filling the rocket body, open the ground filling valve and the rocket body filling valve, open the rocket body tank to vent, pressurize the propellant tank, and then squeeze or use a cryogenic pump to fill the cryogenic propellant into the rocket body tank; When the cryogenic propellant in the rocket body tank is to be discharged, the filling port discharge valve and the rocket body filling valve are opened to squeeze and directly discharge the cryogenic propellant in the rocket body tank, and the outlet of the filling port discharge valve is connected to the safety discharge device.

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