Low-temperature propellant filling system for rocket core-level power system test

Abstract

The invention relates to a low-temperature propellant filling system for a rocket core-level power system test. The low-temperature propellant filling system comprises a propellant supply subsystem, a ground pipeline precooling and discharging subsystem, a filling port discharging subsystem and a filling port deflating subsystem. The propellant supply subsystem is connected with the rocket body storage tank through a propellant supply pipeline of the propellant supply subsystem, and low-temperature propellant filling can be achieved; the ground pipeline pre-cooling discharge subsystem, the filling port discharge subsystem and the filling port deflation subsystem are respectively and independently connected with a propellant supply pipeline; and the connecting points of the filling port discharge subsystem and the filling port deflation subsystem on the propellant supply pipeline are respectively positioned on the propellant supply pipeline between the ground pipeline pre-cooling discharge subsystem and the rocket body storage tank. The device can prevent a large amount of low-temperature steam from entering the storage box to cause back pressure in the ground filling process, can adapt to impact vibration in the rocket body filling deformation and test ignition stage, and completes remote control to safely discharge the residual propellant of the rocket body, so that the filling index is met.

Description

Technical Field

[0001] The present application relates to a cryogenic propellant filling system for a rocket core stage power system test, and is applicable to the technical field of a rocket core stage power system test. Background Art

[0002] The existing field of rocket core stage power system testing has high requirements for the ground refueling system. During the rocket core stage power system test, the rocket is equipped with the necessary engines, tanks, pressurized delivery pipelines and other on-board equipment for the core stage. At this time, the state of the rocket is basically the same as the launch state. During the power system test, the rocket does not take off as it does during launch, but the load-bearing device keeps the rocket body fixed on the test bench at all times; during the entire test process, during the rocket filling stage, ignition stage, and post-processing stage, the ground refueling pipeline needs to meet the functional requirements of the entire rocket deformation caused by propellant filling, the vibration of the rocket body during ignition, and the leakage of propellant. The external load that the interface connection part of the rocket body can withstand is very small, and the ground refueling pipeline cannot generate reverse additional force during the test to avoid damage to the rocket body. Therefore, the docking method of the ground refueling pipeline and the reasonable design of the support structure are also key links in the power test. Summary of the invention

[0003] The purpose of this application is to design a cryogenic propellant filling system for rocket core stage power system test, aiming to solve the existing cryogenic propellant filling problems, and to achieve accurate filling, safe discharge and reasonable support of cryogenic propellant. This application can avoid the back pressure caused by a large amount of cryogenic steam entering the tank during the ground filling process, can adapt to the deformation of the rocket body during filling and the impact vibration during the test ignition stage, and complete the remote control of the safe discharge of the remaining propellant in the rocket body, thereby meeting the filling indicators.

[0004] The present application relates to a cryogenic propellant filling system for a rocket core stage power system test, the 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 its propellant supply pipeline and is capable of filling cryogenic propellant; 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.

[0005] Furthermore, the propellant supply subsystem may include a propellant storage tank and a ground filling valve; one end of the propellant supply pipeline is connected to the propellant storage 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 storage 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.

[0006] The propellant supply subsystem may further include a connecting hose, through which the propellant supply pipeline is connected to the rocket tank; the other end of the propellant supply pipeline is connected to one end of the connecting hose, and the other end of the connecting hose is connected to the rocket tank. The propellant supply subsystem may further include a support assembly, which may include a fixed bracket, a sliding hinged bracket, and a vertically adjustable bracket; the fixed bracket is fixedly arranged on the propellant supply pipeline at the front end of the connecting hose to limit the movement of the propellant supply pipeline; the sliding hinged bracket is arranged at one end of the connecting hose connected to the propellant supply pipeline to support the connecting hose; the connecting hose can move in the horizontal direction on the sliding hinged bracket; the vertically adjustable bracket is arranged at one end of the connecting hose connected to the rocket tank, and the connecting hose can move in the vertical direction on the vertically adjustable bracket.

[0007] Furthermore, the vertically adjustable bracket may include a clamp, a fixed base and a bracket; the bracket is arranged on the fixed base through a height adjustment member; 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 connected and fixed to the connecting hose through the insulating elastic buffer layer.

[0008] Among them, the ground pipeline precooling discharge subsystem may include a ground pipeline precooling discharge pipeline and a precooling discharge valve, and the connection point of the ground pipeline precooling discharge pipeline on the propellant supply pipeline is located on the propellant supply pipeline between the ground filling valve and the rocket body tank; the precooling discharge valve is arranged on the ground pipeline precooling discharge pipeline. The propellant supply subsystem includes a filling filter and a flow meter; the filling filter and the flow meter are respectively arranged on the propellant supply pipeline. The filling port discharge subsystem may include 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, and is located at the low point of the connecting hose; the filling port discharge valve is arranged on the filling port discharge pipeline. The filling port bleed subsystem may include a filling port bleed pipeline and a bleed valve; the connection point of the filling port bleed pipeline on the propellant supply pipeline is located on the propellant supply pipeline between the ground filling valve and the connecting hose, and is located at the high point of the connecting hose; the bleed valve is arranged on the filling port bleed pipeline.

[0009] Furthermore, the non-vacuum insulation part of the propellant supply pipeline may be provided with a liquid-to-air flow guide device; the liquid-to-air flow guide device is provided below the propellant supply pipeline. The liquid-to-air flow guide device may include a liquid collecting tank and a flow guide pipe; the liquid collecting tank is provided below the propellant supply pipeline at an angle downward; the outer layer of the liquid collecting tank is provided with a heat preservation layer; one end of the flow guide pipe is connected to the lowest point of the liquid collecting tank, and the other end of the flow guide pipe is connected to an open area at normal temperature. The cryogenic propellant may be liquid hydrogen, and a hydrogen concentration monitoring device may be provided on the propellant supply pipeline.

[0010] The present application also relates to a cryogenic propellant filling method for a rocket core stage power system test, which can be performed using the cryogenic propellant filling system as described above, and comprises the following steps:

[0011] The following steps are involved:

[0012] (1) Connect the propellant supply pipeline to the rocket body, install the propellant supply subsystem, and perform thermal insulation treatment on the non-vacuum insulation parts;

[0013] (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 vent 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;

[0014] (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;

[0015] (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;

[0016] (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 is controlled by the ground filling valve or by the liquid outlet valve of the propellant tank;

[0017] (6) After the filling of the rocket body tank is completed, the ground filling valve is closed. 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, the vent valve is opened 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 volatilization state until the end of the test;

[0018] (7) After the rocket body is ignited, the propellant storage tank and the propellant supply pipeline that have completed pressure relief are ready to discharge the remaining propellant. At this time, the rocket body filling valve is opened, the air release valve is closed, and the ground filling is turned on, and the propellant is discharged back to the propellant storage tank along the original route;

[0019] (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.

[0020] The cryogenic propellant filling system for rocket core stage power system test proposed in this application has the following technical advantages:

[0021] (1) The cryogenic propellant filling system for the rocket core stage power system test proposed in this application can strictly control the flow rate at different filling stages by independently setting up various ground cryogenic pipelines, thereby avoiding a large amount of cryogenic steam from entering the tank and causing back pressure during the ground filling process, and can meet the filling indicators during the cryogenic propellant filling process;

[0022] (2) The cryogenic propellant filling system for the rocket core stage power system test proposed in this application can avoid the reaction force caused by the cryogenic deformation of the ground pipeline on the rocket body interface by designing a support component in the system pipeline, and adapt to the cryogenic deformation and vibration of the rocket body;

[0023] (3) The cryogenic propellant filling system for the rocket core stage power system test proposed in this application can effectively and safely discharge the remaining propellant in the rocket body by maintaining the use status of the filling system. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of a cryogenic propellant filling system for a rocket core stage power system test in the present application.

[0025] Figure 2 It is a schematic diagram of the arrow-to-ground butt pipe support structure of the present application.

[0026] Figure 3 It is a schematic diagram of the vertically adjustable bracket of the present application.

[0027] Figure 4 It is a schematic diagram of the liquid-air guide device of the present application.

[0028] 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

[0029] 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 can understand that a cryogenic propellant filling system for a rocket core stage power system test of the present application can be applied to the field of rocket core stage power system tests. Its main function is to complete the filling and discharge of the cryogenic propellant ground pipeline to the rocket body filling port, and can meet the test test. The cryogenic propellant of the present application usually uses liquid oxygen, liquid methane or liquid hydrogen.

[0030] like Figure 1As shown, a cryogenic propellant filling system for a rocket core stage power system test of the present application, the filling system includes a propellant supply subsystem, a ground pipeline precooling 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 cryogenic propellant filling. Furthermore, the ground pipeline precooling discharge subsystem, the filling port discharge subsystem and the filling port venting subsystem are independently connected to the propellant supply pipeline 2, and can realize their respective functions. Specifically, the ground pipeline precooling 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. The ground pipeline precooling discharge subsystem is used for separate precooling and discharge of the ground pipeline, and 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 tank 1 and the ground filling valve 11, close to the ground filling valve 11. The ground filling valve 11 is arranged on one end of the propellant supply pipeline 2 close to the rocket body. The filling port discharge subsystem is used to discharge the remaining cryogenic propellant in the rocket body tank 6. The filling port venting subsystem is used to vent the filling system. The cryogenic propellant filling system for the rocket core stage power system test designed in the present application can avoid a large amount of cryogenic steam entering the tank and causing back pressure during the ground filling process by strictly controlling the flow rate at different filling stages during the rocket body filling process. During the test, the ground pipeline pressure of the filling system needs to be kept lower than the pressure of the rocket tank 6 to avoid replenishing gas or liquid from the rocket filling port. After the test is completed, the cryogenic pipeline and equipment still need to maintain good connection and use status, and the remaining propellant in the rocket body needs to be safely discharged and handled to meet the filling indicators.

[0031] like Figure 1 As shown, the cryogenic propellant filling system for the rocket core stage power system test designed by the present application has a ground filling valve 11 disposed on the propellant supply pipeline 2 at one end close to the rocket body. The precooling process of the ground pipeline precooling and discharge subsystem 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 in front of 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 over-pressure, which is not conducive to product quality control.

[0032] like Figure 1As shown, the cryogenic propellant filling system for the rocket core stage power system test designed by the present application can fill the rocket body and also discharge the liquid oxygen in the rocket body tank 6. Specifically:

[0033] When the rocket body is filled: open the ground filling valve 11, open the rocket body filling valve, open the rocket body tank 6 to exhaust, pressurize the propellant tank 1, and squeeze or use a cryogenic pump to fill the cryogenic propellant into the rocket body tank 6;

[0034] When the cryogenic propellant in the rocket body tank 6 is discharged back or discharged: first, the propellant tank 1 is depressurized and the exhaust port of the propellant tank 1 is opened, the ground filling valve 11 is opened, the rocket body filling valve is opened, and the cryogenic propellant in the rocket body tank 6 is squeezed into the propellant tank 1 for discharge back. Further, in an emergency, the cryogenic propellant needs to be discharged urgently, the filling port discharge valve 9 is opened, the rocket body filling valve is opened, and the cryogenic propellant in the rocket body tank 6 is squeezed directly for emergency discharge. The outlet of the filling port discharge valve 9 is connected to the safety discharge device.

[0035] like Figure 1 As shown, the cryogenic propellant filling system for the rocket core stage power system test 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 above the pipeline located at 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.

[0036] Preferably, in combination with the above scheme, Figure 1As shown, the cryogenic propellant filling system for the rocket core stage power system test proposed in this application, its propellant supply subsystem 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 is arranged on the propellant supply pipeline 2, and the flow meter 10 is arranged on the propellant supply pipeline 2; the filling filter 8 is arranged on the propellant supply pipeline 2 for filtering 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.

[0037] The cryogenic propellant filling system for the rocket core stage power system test of the present application needs to keep the pressure of the propellant supply pipeline 2 and the connecting hose 7 lower than the pressure of the rocket body tank 6 during the test to avoid air or liquid replenishment 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 to safely discharge the remaining propellant in the rocket body.

[0038] Preferably, in combination with the above scheme, Figure 1 As shown, the present application proposes a cryogenic propellant filling system for a rocket core stage power system test, wherein the 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 to 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.

[0039] Preferably, in combination with the above scheme, Figures 2 to 3 As shown, the cryogenic propellant filling system of the rocket core stage power system test proposed in this application, after the cryogenic propellant filling is completed, the filling system is generally not separated from the rocket body, so the ground pipeline needs to avoid the reaction force caused by the low-temperature deformation of the ground pipeline on the rocket body interface, and 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 cryogenic 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. Therefore, the propellant supply subsystem 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.

[0040] As shown in the figure, 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 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 low-temperature 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 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 the hinged structure compensates for the angular deformation caused by the low-temperature downward displacement of the arrow-ground interface. Further, the vertically adjustable bracket 13 is arranged at one end of the connecting hose 7 connected to the arrow body tank 6 as a tertiary support, close to the connection port of the arrow body tank 6, to ensure that the ground pipeline does not generate additional force on the arrow body. Furthermore, 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 arrow body during the filling stage.

[0041] 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.

[0042] 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:

[0043] ΔL=H·α·ΔT+Δε,

[0044] Among them, H is the vertical height from the rocket body filling port to the fixed point of the test bench; α is the thermal deformation coefficient of the rocket body material during the change of the corresponding temperature zone during the low-temperature propellant filling process; ΔT is the temperature change range from before the propellant filling to after the low-temperature propellant filling is completed; Δε is the other deformation of the rocket body caused by the low-temperature propellant filling process.

[0045] Preferably, in combination with the above scheme, Figure 1 As shown, the cryogenic propellant filling system for the rocket core stage power system test proposed in this 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 cryogenic propellant filling system for the rocket core stage power system test proposed in this 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.

[0046] Preferably, in combination with the above scheme, Figure 1 As shown, the present application proposes a cryogenic propellant filling system for a rocket core stage power system test, wherein the 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.

[0047] Preferably, in combination with the above scheme, Figure 1 and Figure 4As shown, for the low-temperature propellant filling of liquid hydrogen medium, the discharge pipelines such as the ground pipeline pre-cooling discharge subsystem, the filling port discharge 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. The non-vacuum insulation part of the propellant supply pipeline 2 is provided with a liquid-air diversion device to prevent low-temperature liquid air from damaging other equipment; the liquid-air diversion 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 vacuum insulation, foaming stack insulation or insulation material coating. Except for the vacuum insulation method, the insulation effect will not be very good. For liquid hydrogen propellant, liquid air is easy to generate. At this time, in order to avoid low-temperature liquid air from damaging other equipment, a liquid-air diversion device can be selected. The liquid-air flow guide device of the present application can prevent the situation that the 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 flow guide device of the present application can guide the liquid air to a safe area. Furthermore, the liquid-air flow guide device is fixed by relying on the pipeline. A hydrogen concentration monitoring device can be set at the hydrogen pipeline connection part of the propellant supply pipeline 2 to realize liquid hydrogen concentration monitoring. In addition, when liquid methane is used as a cryogenic propellant, since it is a flammable and explosive medium like liquid hydrogen, a concentration monitoring device also needs to be installed.

[0048] 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. In the cryogenic propellant filling system of the rocket core stage power system test of the present application, 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.

[0049] The cryogenic propellant filling system for rocket core stage power system test proposed in this application has the following technical advantages:

[0050] (1) The cryogenic propellant filling system for the rocket core stage power system test proposed in this application can strictly control the flow rate at different filling stages by independently setting up various ground cryogenic pipelines, thereby avoiding a large amount of cryogenic steam from entering the tank and causing back pressure during the ground filling process, and can meet the filling indicators during the cryogenic propellant filling process;

[0051] (2) The cryogenic propellant filling system for the rocket core stage power system test proposed in this application can avoid the additional force on the rocket body interface caused by the cryogenic deformation of the ground pipeline by designing a three-stage support assembly and a flexible connection in the system pipeline, and adapt to the cryogenic deformation and vibration of the rocket body;

[0052] (3) The cryogenic propellant filling system for the rocket core stage power system test proposed in this application can effectively and safely discharge the remaining propellant in the rocket body by maintaining the use status of the filling system.

[0053] The present application also relates to a cryogenic propellant filling method for a rocket core stage power system test, comprising the following steps:

[0054] (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;

[0055] (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;

[0056] (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;

[0057] (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;

[0058] (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;

[0059] (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 safe 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;

[0060] (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;

[0061] (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.

[0062] 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.

[0063] 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.

[0064] 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 cryogenic propellant filling system for rocket core stage power system test, characterized in that: The filling system comprises a propellant supply subsystem, a ground pipeline precooling discharge subsystem, a filling port discharge subsystem and a filling port venting subsystem; the propellant supply subsystem is connected to a rocket body tank (6) via a propellant supply pipeline (2) to achieve low-temperature propellant filling; the ground pipeline precooling discharge subsystem, the filling port discharge subsystem and the filling port venting subsystem are independently connected to the propellant supply pipeline (2) respectively; 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 discharge subsystem and the rocket body tank (6).

2. The cryogenic propellant filling system for rocket core stage power system test according to claim 1, 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).

3. The cryogenic propellant filling system for rocket core stage power system test according to claim 2, characterized in that: It also comprises a connecting hose (7), and the propellant supply pipeline (2) is connected to the rocket body tank (6) through the connecting hose (7).

4. The cryogenic propellant filling system for rocket core stage power system test according to claim 3, characterized in that: The propellant supply subsystem further comprises a support assembly, the support assembly comprising a fixed support (22), a sliding articulated support (12) and a vertically adjustable support (13); the fixed support (22) is fixedly arranged at the end of the propellant supply pipeline (2) at the front end of the connecting hose (7) to limit the displacement of the end of the propellant supply pipeline (2) due to low temperature deformation; the sliding articulated support (12) is arranged at the middle of the connecting hose (7) to support the connecting hose (7); the connecting hose (7) can freely move in the horizontal direction on the sliding articulated support (12); the sliding articulated support (12) can adapt to the angular displacement of the connecting hose (7) in the 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).

5. The cryogenic propellant filling system for rocket core stage power system test according to claim 4, 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).

6. The cryogenic propellant filling system for rocket core stage power system test according to claim 5, characterized in that: The ground pipeline precooling discharge subsystem comprises a ground pipeline precooling discharge pipeline and a precooling discharge valve (3), wherein the precooling discharge valve (3) is arranged on the ground pipeline precooling discharge pipeline; the propellant supply subsystem also comprises a filling filter (8) and a flow meter (10); the flow meter (10) is respectively arranged on the propellant supply pipeline (2), and the filling filter (8) is arranged at the end of the propellant supply pipeline (2) close to the connecting hose (7).

7. The cryogenic propellant filling system for rocket core stage power system test according to claim 6, 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), and is located at the lowest point of the connecting hose (7); the filling port discharge valve (9) is arranged on the filling port discharge pipeline.

8. The cryogenic propellant filling system for rocket core stage power system test according to claim 7, 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), and is located at the highest point of the connecting hose (7); the venting valve (5) is arranged on the filling port venting pipeline.

9. The cryogenic propellant filling system for rocket core stage power system test according to claim 8, 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).

10. A method for filling cryogenic propellant for a rocket core stage power system test, comprising the following steps: (1) Connect the propellant supply pipeline to the rocket body, install the propellant supply subsystem, and perform thermal insulation treatment on the non-vacuum insulation parts; (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 vent 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; (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; (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; (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 is controlled by the ground filling valve or by the liquid outlet valve of the propellant tank; (6) After the filling of the rocket body tank is completed, the ground filling valve is closed. 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, the vent valve is opened 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 volatilization state until the end of the test; (7) After the rocket body is ignited, the propellant storage tank and the propellant supply pipeline that have completed pressure relief are ready to discharge the remaining propellant. At this time, the rocket body filling valve is opened, the air release valve is closed, and the ground filling is turned on, and the propellant is discharged back to the propellant storage tank along the original route; (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.

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