Rocket hose evacuation blowdown test system and method

Abstract

This invention discloses a rocket hose purging and blowing test system and method. The invention includes, in descending order of height, an inlet tank, an inlet pipeline, a test hose, a drain pipeline, and a collection tank mounted on a weighing platform. The inlet tank is equipped with a first liquid path shut-off valve, the purging gas supply unit is equipped with a first gas path shut-off valve, and the collection tank is equipped with a second gas path shut-off valve. When the first liquid path shut-off valve is opened and both the first and second gas path shut-off valves are closed, propellant in the inlet tank fills the test hose through the inlet pipeline. When the first liquid path shut-off valve is closed and both the first and second gas path shut-off valves are opened, the purging gas supply unit purges the propellant from the test hose, allowing the propellant to enter the collection tank through the drain pipeline. The purging status of the propellant in the test hose is determined by observing changes in the weighing platform parameters.

Description

Technical Field

[0001] This invention relates to the field of rocket testing, specifically to a rocket hose purging and blowing test system and method. Background Technology

[0002] The propellant loading and venting lines of ground launch support facilities typically need to be connected to the rocket interface via a flexible hose to accommodate changes in the rocket-ground interface position. For launch modes where the rocket-ground interface position changes significantly (such as launch modes where the loading and venting lines detach within zero seconds or the erector support collapses within zero seconds), this flexible hose needs to be very long.

[0003] After refueling is completed and before separation from the rocket interface, the propellant refueling venting pipeline needs to be purged with inert gas to remove any remaining propellant. This is to avoid safety hazards caused by propellant leakage during separation from the rocket interface, which could lead to deflagration, detonation, or vaporization and expansion of cryogenic liquid propellant.

[0004] The propellant purging pressure and purging time are related to factors such as the opening pressure of the onboard valve safety valve, the length and diameter of the injection and venting hose, the working posture of the hose, and the internal structure of the hose. These factors often need to be determined through experiments. Therefore, providing a hose purging test system and test method is a problem that needs to be solved. Summary of the Invention

[0005] To address the aforementioned technical problems in related technologies, this invention proposes a rocket hose purging and blowing test system and method. The purging and blowing test system is used to test the fueling and venting hoses before rocket launch. Based on the test results, the appropriate blowing time and blowing pressure can be selected, improving the safety of hose detachment during rocket launch and eliminating safety hazards such as combustion and explosion caused by propellant leakage.

[0006] This invention provides a rocket hose purging and blowing test system, comprising: a liquid inlet tank, a liquid inlet pipeline, a blowing gas supply unit, a drain pipeline, and a collection tank; the liquid inlet tank is installed at a high position and is used to store propellant; one end of the liquid inlet pipeline is connected to the liquid outlet of the liquid inlet tank, and the other end is used to connect to the liquid inlet end of the hose under test; the blowing gas supply unit is located at the end of the liquid inlet pipeline near the hose under test; the end of the drain pipeline at the high position is used to connect to the liquid outlet end of the hose under test, and the end at the low position is used for draining liquid; the bottom of the collection tank is installed on a weighbridge, and the top is connected to the end of the drain pipeline used for draining liquid.

[0007] The inlet tank is equipped with a first liquid path shut-off valve, the purging gas supply unit is equipped with a first gas path shut-off valve, and the collection tank is equipped with a second gas path shut-off valve. When the first liquid path shut-off valve is opened and the first and second gas path shut-off valves are closed, the propellant in the inlet tank fills the tested hose through the inlet pipeline; when the first liquid path shut-off valve is closed and the first and second gas path shut-off valves are opened, the purging gas supply unit purges the propellant from the tested hose, allowing the propellant to enter the collection tank through the drain pipeline, so that the purging status of the propellant in the tested hose can be judged by the parameter changes of the weighbridge.

[0008] In one embodiment, a third gas path shut-off valve is provided on the side of the drain line near the tested hose; opening the third gas path shut-off valve allows the propellant to fill the tested hose.

[0009] In one embodiment, the drainage pipeline includes a rigid drainage pipe and a flexible drainage pipe; one end of the rigid drainage pipe is connected to the outlet end of the flexible pipe being tested, and the other end is connected to the flexible drainage pipe, which is connected to the collection tank; the third gas circuit shut-off valve is located on the rigid drainage pipe.

[0010] In one embodiment, the liquid inlet pipeline includes a rigid liquid inlet pipe and a flexible liquid inlet pipe; one end of the flexible liquid inlet pipe is connected to the outlet of the liquid inlet tank, and the other end is connected to the rigid liquid inlet pipe, the rigid liquid inlet pipe is connected to the inlet end of the flexible pipe under test; the first gas circuit shut-off valve is disposed on the rigid liquid inlet pipe.

[0011] In one embodiment, the liquid inlet tank is provided with a liquid inlet at its high position, and a first pressure measuring unit and a fourth gas circuit shut-off valve are provided next to the liquid inlet. A first level gauge connecting the bottom and top of the tank is also provided on one side of the liquid inlet tank. The liquid collection tank is provided with a second pressure measuring unit and a second gas circuit shut-off valve at its high position, and a second level gauge connecting the bottom and top of the tank is provided on one side of the liquid collection tank.

[0012] In one embodiment, the drain pipe is provided with a third pressure measuring unit near the third gas circuit shut-off valve; the third pressure measuring unit is used to measure the pressure change of the drain pipe; the inlet pipe is provided with a fourth pressure measuring unit near the first gas circuit shut-off valve; the fourth pressure measuring unit is used to measure the pressure change of the inlet pipe.

[0013] Another aspect of the present invention provides a method for testing the purging and blowing out of a rocket hose, characterized by comprising the following steps:

[0014] Step 1: Connect the inlet tank, inlet pipe, test hose, drain pipe, and collection tank on the weighbridge in sequence, arranged from high to low.

[0015] Step 2: Set the purging gas supply unit at one end of the liquid inlet pipe near the hose being tested, and set parameters such as purging time and purging gas pressure;

[0016] Step 3: Open the first liquid circuit shut-off valve of the liquid inlet tank, and close the first gas circuit shut-off valve of the purging gas supply unit and the second gas circuit shut-off valve of the liquid collection tank, so that the propellant in the liquid inlet tank is filled into the test hose;

[0017] Step 4: After the test hose is filled with propellant, close the first liquid circuit shut-off valve and open the first gas circuit shut-off valve and the second gas circuit shut-off valve. Use the purging gas supply unit to purge the test hose so that the propellant in the test hose is collected in the collection tank.

[0018] Step 5: After the purging time ends, close the first gas path shut-off valve and the second gas path shut-off valve to obtain the weight change of the collection tank.

[0019] Step 6: Determine the test result of the purging test of the tested hose based on the weight change of the collection tank.

[0020] Furthermore, before purging the tested hose using the purging gas supply unit, the method further includes: when the pressure in the drain line continues to rise, briefly opening the third gas shut-off valve of the drain line to release the gas at the end of the drain line.

[0021] Furthermore, the method for obtaining the weight change of the collection tank is as follows: obtaining the liquid level change of the propellant in the inlet tank according to the liquid level gauge installed in the inlet tank, and converting the liquid level change into a weight change; or, directly obtaining the weight change of the collection tank according to the reading of the weighbridge.

[0022] Furthermore, the method for determining the test result of the purging test of the tested hose based on the weight change of the collection tank is as follows:

[0023] Calculate the propellant filling weight inside the hose based on its diameter and length.

[0024] The residual propellant content of the tested hose is calculated using the formula: Residual propellant content in the tested hose = Propellant filling weight - Weight change of the collection tank.

[0025] If the residual propellant content in the tested hose meets the requirements, the test is complete;

[0026] If the propellant content remaining in the tested hose exceeds the required value, the purging time or purging pressure should be appropriately extended and the test repeated until the requirements are met.

[0027] The rocket hose purging and blowing test system and method of this invention can intuitively measure the effect of hose purging and blowing before rocket launch, and then verify the purging and blowing of rocket loading and venting hoses. It can obtain parameters such as air pressure and duration of purging and blowing of loading and venting hoses during rocket launch, and ensure that the propellant in the loading and venting hoses is basically completely purged, thereby completely eliminating the safety hazards such as combustion and explosion that may occur after the loading and venting hoses separate and detach.

[0028] Upon reading the detailed embodiments and examining the accompanying drawings, those skilled in the art will recognize additional features and advantages. Attached Figure Description

[0029] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0030] Figure 1 This is a schematic diagram of the overall structure of the hose venting and blowing test system according to an embodiment of the present invention.

[0031] Figure 2 This is a schematic diagram of the liquid inlet tank and liquid inlet pipeline of an embodiment of the present invention.

[0032] Figure 3 This is a schematic diagram of the drainage pipeline and the collection tank in an embodiment of the present invention.

[0033] Figure 4 This is a diagram showing the positional relationship between the drain pipe and the inlet pipe in an embodiment of the present invention.

[0034] Figure 5 This is a flowchart of the hose purging and blowing test method according to an embodiment of the present invention. Detailed Implementation

[0035] The technical solution of the present invention will be further described below with reference to the accompanying drawings and specific embodiments. Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for ease of description to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device other than those shown in the figures. Additionally, for example, "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. Furthermore, terms such as "first," "second," etc., are also used to describe individual elements, areas, parts, etc., and should not be considered limiting. Similar terms are used throughout the description to denote similar elements.

[0036] See Figure 1 This invention provides a rocket hose purging and blowing test system, including an inlet tank 1, an inlet pipe 2, a blowing gas supply unit 3, a drain pipe 4, and a collection tank 5. The inlet tank 1 is installed at a high position and stores propellant inside. An outlet 11 is provided at the bottom of the inlet tank 1. One end of the inlet pipe 2 is connected to the outlet 11 of the inlet tank 1, and the other end is connected to the inlet end of the hose under test 100, allowing the propellant in the inlet tank 1 to enter the hose under test 100 through the inlet pipe 2. The blowing gas supply unit 3 is located at the end of the inlet pipe 2 near the hose under test 100 and is used to blow air into the hose under test 100 to purge the propellant. The drain pipe 4 is connected at a high position to the outlet end of the hose under test 100, and at a low position to the inlet at the top of the collection tank. When the purging gas supply unit 3 purges the propellant in the tested hose 100, the purged propellant can be collected in the collection tank 5 through the drain pipe 4. The collection tank 5 is placed on the weighbridge 6, and the content of propellant collected in the collection tank 5 is determined by the reading of the weighbridge 6.

[0037] The inlet tank 1 is equipped with a first liquid circuit shut-off valve F1 for controlling propellant filling, the purge gas supply unit 3 is equipped with a first gas circuit shut-off valve V1 for controlling purge gas filling, and the top of the collection tank 5 is equipped with a second gas circuit shut-off valve V2 for venting. It should be noted that after the collection tank 5 is connected to the drain pipe 4, the collection tank is a sealed tank, ventilated only to the atmosphere through the second gas circuit shut-off valve V2. When the second gas circuit shut-off valve V2 is closed, the propellant in the tested hose 100 will not flow into the collection tank 5 under the pressure of the air inside the collection tank 5. When the second gas circuit shut-off valve V2 is open, the collection tank is ventilated, and under the action of the purge gas, the propellant in the tested hose 100 can be collected in the collection tank 5.

[0038] Specifically, the first liquid circuit shut-off valve F1 is opened and the first gas circuit shut-off valve V1 and the second gas circuit shut-off valve V2 are closed. The propellant in the liquid inlet tank 1 is filled into the test hose 100 through the liquid inlet pipe 2. After the test hose 100 is filled with propellant, the first liquid circuit shut-off valve F1 is closed and the first gas circuit shut-off valve V1 and the second gas circuit shut-off valve V2 are opened. Using the purge gas supply unit 3, which has been pressurized, the propellant in the test hose 100 is purged and purged, so that the propellant enters the collection tank 5 through the drain pipe 4. The purging status of the propellant in the test hose 100 is judged by the parameter changes of the weighbridge 6. The test results can be used to determine whether the purging force and purging time of the purge gas supply unit meet the requirements.

[0039] The hose purging and blowing test system of this invention can first apply the proposed purging scheme for the fuel and vent hoses during rocket launch to the test system for verification. The test system of this invention verifies whether the proposed scheme can meet the purging and blowing requirements. If it cannot, the blowing scheme can be modified and the test verification can be carried out again until the test results meet the requirements. This provides a reliable basis for the purging gas pressure and time of the fuel and vent hoses during rocket launch, and solves the safety hazard caused by propellant leakage when the fuel and vent hoses detach after rocket launch.

[0040] In one embodiment, a third gas shut-off valve V3 is provided on the side of the drain line 4 near the tested hose 100. Due to the effect of air pressure, there may be insufficient filling of the tested hose 100 near the drain line 4 during the propellant filling stage. Therefore, opening the third gas shut-off valve V3 in the drain line 4 can promote the filling of the tested hose 100 with propellant, thereby significantly improving the test accuracy of the hose purging test system of this embodiment.

[0041] See Figure 2 In one embodiment, to simulate the state of the tested hose as closely as possible during rocket launch, the hose needs to be suspended in the air, with the inlet end positioned at a high point and the outlet end at a low point. Furthermore, given the large size and heavy weight of the tested hose, the inlet pipe 2 can be configured as two parts: an inlet rigid pipe 21 and an inlet hose 22. Specifically, the inlet rigid pipe 21 is fixedly installed on a supporting structure, and one end of the inlet hose 22 is connected to the outlet 11 of the inlet tank 1, while the other end is connected to the inlet rigid pipe 21. The inlet rigid pipe 21 is used to connect to the inlet end of the tested hose 100. A first gas shut-off valve V1 can be installed on the inlet rigid pipe 21.

[0042] See Figure 3 Furthermore, the outlet end of the tested hose 100 can also be connected to a rigid pipe. For example, the drain line 4 includes a drain rigid pipe 41 and a drain hose 42. Specifically, the drain rigid pipe 41 is fixedly installed on a structure that can provide support. One end of the drain rigid pipe 41 is connected to the outlet end of the tested hose 100, and the other end is connected to the drain hose 42. The other end of the drain hose 42 is connected to the collection tank 5. The third gas path shut-off valve V3 can be installed on the drain rigid pipe 41. The drain hose 42 is sealed to the collection tank 5 to ensure that when the third gas path shut-off valve V3 and the second gas path shut-off valve V2 are closed, the propellant can be prevented from being charged into the drain hose and the collection tank under the action of the gas pressure inside the drain hose and the collection tank.

[0043] The rocket hose purging and blowing test system of this invention divides the inlet pipeline into two parts: an inlet hose and an inlet rigid pipe, and the outlet pipeline into an outlet hose and an outlet rigid pipe. The inlet and outlet rigid pipes, which are set on the support structure, are connected to both ends of the hose under test. On the one hand, this facilitates the connection between the two ends of the hose under test and the outlet and inlet pipelines. On the other hand, it allows the weight to be applied to the support structure, thereby preventing the outlet and inlet hoses from being pulled apart or deformed by the hose under test, thus improving the reliability and stability of the entire test system.

[0044] To prevent the two connecting ends of the tested hose from bending, the inlet and outlet hard pipes can each have an L-shaped bend to facilitate connection between the higher and lower pipes.

[0045] See Figure 4 It is important to note that, to accommodate both propellant filling and purging gas removal in the tested hose, ensuring proper propellant filling without overfilling while simultaneously guaranteeing effective purging gas removal, the positions of the inlet and outlet hard pipes can be adjusted adaptively based on the hose's length. Typically, the hose ends are positioned behind the inlet and outlet hard pipes, with the portion of the hose near the outlet hard pipe naturally drooping downwards. In this embodiment, the positional relationship between the inlet and outlet hard pipes can be adjusted to ensure that the height difference X1 between the outlet and inlet hard pipes, the height difference X2 between the outlet hard pipe and the drooping end, and the horizontal distance X3 between the outlet and inlet hard pipes are equal. Equal X1 and X2 prevent excessive propellant from filling the outlet hard pipe due to gravity during propellant filling. Equal X2 and X3 ensure a suitable bend in the drooping end of the tested hose, facilitating the introduction of purging gas. Therefore, the hose purging and blowing test system of this invention can ensure that the error of the test results is very small, and significantly improve the test accuracy.

[0046] See Figure 2 In one embodiment, the liquid inlet tank 1 is provided with a liquid inlet 12 at a high position. Next to the liquid inlet 12, a first pressure measuring unit P1 and a fourth gas path shut-off valve V4 are also provided. A first level gauge 13 connecting the bottom and top of the tank is also provided on one side of the liquid inlet tank. The liquid inlet tank 1 is replenished with propellant through the liquid inlet 12, and the pressure change of the liquid inlet tank 1 is observed through the first pressure measuring unit P1, while the liquid level change is observed through the first level gauge 13. When replenishing propellant, the liquid inlet tank 1 needs to close the first liquid path shut-off valve F1 and open the fourth gas path shut-off valve V4. After replenishment is complete, the fourth gas path shut-off valve V4 is closed.

[0047] See Figure 3Furthermore, the high position of the collection tank 5 is equipped with a second pressure measuring unit P2 and a second gas path shut-off valve V2. A second level gauge 51 connecting the bottom and top of the tank is located on one side of the collection tank 5. The low position of the collection tank 5 is also equipped with a drain port and a drain valve F2 located at the drain port. The drain port and drain valve F2 are used to discharge residual liquid from the collection tank. Specifically, during the propellant filling stage of the tested hose, the second gas path shut-off valve V2 and the drain valve F2 are closed, and the propellant filling status is determined based on the parameter changes of the second pressure measuring unit P2. After the propellant filling is completed and purging is performed using the purging gas supply unit, the second gas path shut-off valve V2 is opened, allowing the propellant in the tested hose to be collected in the collection tank 5. The purging status of the tested hose can be obtained based on the change in the parameter of the first level gauge and the parameter of the second level gauge 51.

[0048] See also Figure 2 and Figure 3 In the above embodiment, the drain pipe 41 is equipped with a third pressure measuring unit P3 near the third gas path shut-off valve V3. The third pressure measuring unit P3 is used to measure the pressure change of the drain pipe 41 and, in conjunction with the parameters of the second pressure measuring unit P2, to determine the propellant filling status of the tested hose. The inlet pipe 21 is equipped with a fourth pressure measuring unit P4 near the first gas path shut-off valve F1. The fourth pressure measuring unit P4 is used to measure the pressure change of the inlet pipe 21.

[0049] For example, by opening the first liquid circuit shut-off valve F1, propellant is injected into the test device through the inlet tank until both the first liquid level gauge 13 and the second liquid level gauge 51 have a certain liquid level, and the second pressure measuring unit P2 begins to show a pressure reading. If the fourth pressure measuring unit P4 also experiences a pressure rise after the second pressure measuring unit P2 begins to show a pressure reading, the third gas circuit shut-off valve V3 can be briefly opened to release the gas stored in the drain pipe section, thereby allowing the tested hose to be filled with propellant.

[0050] The above embodiments can be combined with each other and have corresponding technical effects.

[0051] See Figure 5 Another aspect of the present invention provides a method for testing hose venting and blowing, comprising the following steps:

[0052] S100. Connect the inlet tank, inlet pipeline, test hose, drain pipeline and collection tank set on the weighing scale in sequence from high to low.

[0053] S200. Set the purging gas supply unit at one end of the liquid inlet pipeline near the tested hose, and set parameters such as purging time and purging gas pressure.

[0054] S300. Open the first liquid circuit shut-off valve of the liquid inlet tank, and close the first gas circuit shut-off valve of the purging gas supply unit and the second gas circuit shut-off valve of the liquid collection tank, so that the propellant in the liquid inlet tank is filled into the test hose.

[0055] S400. After the test hose is filled with propellant, close the first liquid circuit shut-off valve and open the first gas circuit shut-off valve and the second gas circuit shut-off valve. Use the purging gas supply unit to purge the test hose so that the propellant in the test hose is collected in the liquid collection tank.

[0056] S500. After the purging time ends, close the first gas circuit shut-off valve and the second gas circuit shut-off valve to obtain the weight change of the collection tank.

[0057] S600. Determine the test result of the purging test of the tested hose based on the weight change of the collection tank.

[0058] Furthermore, S100 connects the inlet tank, inlet pipe, tested hose, drain pipe, and collection tank installed on the weighing scale in sequence from high to low. Then, according to the length of the tested hose, the positions of the inlet pipe and drain pipe are adjusted so that the height difference X1 between the drain pipe and the inlet pipe, the height difference X2 between the drain pipe and the lower end, and the horizontal distance X3 between the drain pipe and the inlet pipe are equal.

[0059] Furthermore, before purging the tested hose using the purging gas supply unit, the process includes: when the liquid level gauge in the collection tank has a certain liquid level and the pressure measurement point in the drain pipe also has a pressure rise, briefly opening the third gas shut-off valve of the drain pipe to release the gas stored in the drain pipe section, so that the tested hose is filled with propellant.

[0060] Furthermore, the method for obtaining the weight change of the collection tank is as follows: The change in the propellant level in the inlet tank is obtained based on the level gauge installed in the inlet tank, and the level change is converted into a weight change. Alternatively, the weight change of the collection tank can be obtained directly based on the reading of the weighbridge.

[0061] Furthermore, the method for obtaining the test results of the purging test of the tested hose based on the change in liquid level in the inlet tank and the change in weight in the collection tank is as follows:

[0062] Calculate the propellant filling weight inside the hose based on its diameter and length.

[0063] The residual propellant content of the tested hose is calculated using the formula: Residual propellant content in the tested hose = Propellant filling weight - Weight change of the collection tank.

[0064] If the residual propellant content in the tested hose meets the requirements, the test is complete;

[0065] If the propellant content remaining in the tested hose exceeds the required value, the purging time or purging pressure should be appropriately extended and the test repeated until the requirements are met.

[0066] The above embodiments can be combined with each other and have corresponding technical effects.

[0067] The hose venting and blowing test system of the present invention can also be used for testing and evaluating the insulation effect of the insulation layer of the hose under test. The specific steps are as follows:

[0068] Step 1: Close all gas and liquid shut-off valves in the entire system;

[0069] Step 2: Pour propellant into the inlet tank until the first level gauge shows a certain level, then stop pouring and open the fourth gas circuit shut-off valve.

[0070] Step 3: After a settling time S1, obtain the liquid level change L1 in the inlet tank through the first liquid level gauge;

[0071] Step 4: Calculate the evaporation rate K1 of the liquid inlet tank itself: evaporation rate K1 of the liquid inlet tank itself = liquid level change L1 ÷ settling time S1;

[0072] Step 5: Open the first liquid circuit shut-off valve and the second gas circuit shut-off valve to pre-cool the entire tested hose until a stable flow of propellant is observed in the collection tank, then close the second gas circuit shut-off valve.

[0073] Step 6: Fill the inlet tank with propellant to the same level as in Step 2, and open the fourth gas circuit shut-off valve; after a settling time S1, obtain the liquid level change L2 in the inlet tank through the first liquid level gauge;

[0074] Step 7: Calculate the static evaporation rate K2: Static evaporation rate K2 = Liquid level change L2 ÷ Static time S1;

[0075] Step 8: Calculate the static evaporation rate K3 of the tested hose after it is wrapped with the insulation layer: K3 = K2 - K1; Determine the insulation effect of the insulation layer based on the value of K3.

[0076] The rocket hose purging and blowing test system and method of this invention can intuitively measure the effect of hose purging and blowing before rocket launch, verify the purging and blowing process of rocket loading and venting hoses, and provide reliable basis for parameters such as air pressure and duration of loading and venting hose purging and blowing during rocket launch. This ensures that the propellant in the loading and venting hoses that are detached from the rocket interface after rocket launch is basically completely emptied, thereby completely eliminating the safety hazards such as combustion and explosion that may exist after the loading and venting hoses are separated.

[0077] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A rocket hose evacuation blowdown test system, characterized by, The application relates to a propellant filling and blowing device for a measured hose. The device comprises: a liquid inlet tank, which is installed at a high position and is used for storing propellant; a liquid inlet pipeline, one end of which is connected with a liquid outlet of the liquid inlet tank, and the other end of which is used for connecting with a liquid inlet end of the measured hose; a blowing gas supply unit, which is arranged at one end of the liquid inlet pipeline close to the measured hose; a liquid outlet pipeline, one end of which is used for connecting with a liquid outlet end of the measured hose at a high position, and the other end of which is used for discharging liquid at a low position; a liquid collecting tank, the bottom of which is arranged on a ground scale, and the top of which is connected with the liquid outlet pipeline at the liquid discharging end; wherein the liquid inlet tank is provided with a first liquid path stop valve, the blowing gas supply unit is provided with a first gas path stop valve, and the liquid collecting tank is provided with a second gas path stop valve; when the first liquid path stop valve is opened and the first gas path stop valve and the second gas path stop valve are closed, the propellant in the liquid inlet tank is filled into the measured hose through the liquid inlet pipeline; 2. The rocket hose purge and blowdown test system of claim 1, wherein, when the first liquid path stop valve is closed and the first gas path stop valve and the second gas path stop valve are opened, the blowing gas supply unit is used for emptying and blowing the propellant in the measured hose, so that the propellant enters the liquid collecting tank through the liquid outlet pipeline, and the propellant blowing condition in the measured hose is judged by parameter change of the ground scale.

3. The rocket hose purging test system of claim 2, wherein, A third gas path stop valve is arranged at one side of the liquid outlet pipeline close to the measured hose; opening the third gas path stop valve can make the propellant fill the measured hose. The liquid inlet pipeline comprises a liquid inlet hard pipeline and a liquid inlet soft pipeline; one end of the liquid inlet soft pipeline is connected with the liquid outlet of the liquid inlet tank, and the other end of the liquid inlet soft pipeline is connected with the liquid inlet hard pipeline; the liquid inlet hard pipeline is connected with the liquid inlet end of the measured hose; 4. The rocket hose purging test system of claim 3, wherein, The first gas path stop valve is arranged in the liquid inlet hard pipeline. The liquid outlet pipeline comprises a liquid outlet hard pipeline and a liquid outlet soft pipeline; one end of the liquid outlet hard pipeline is connected with the liquid outlet end of the measured hose, and the other end of the liquid outlet hard pipeline is connected with the liquid outlet soft pipeline; the liquid outlet soft pipeline is connected with the liquid collecting tank; 5. The rocket hose purging test system of claim 4, wherein, The third gas path stop valve is arranged in the liquid outlet hard pipeline. The high position of the liquid inlet tank is provided with a liquid inlet, and a first pressure measuring unit and a fourth gas path stop valve are arranged beside the liquid inlet; one side of the liquid inlet tank is further provided with a first liquid level meter, which is connected with the tank bottom and the tank top; 6. The rocket hose purging test system of claim 5, wherein, The high position of the liquid collecting tank is provided with a second pressure measuring unit and the second gas path stop valve; one side of the liquid collecting tank is provided with a second liquid level meter, which is connected with the tank bottom and the tank top. A third pressure measuring unit is arranged at a position close to the third gas path stop valve of the liquid outlet hard pipeline; the third pressure measuring unit is used for measuring pressure change of the liquid outlet hard pipeline; 7. A method of purging and testing a rocket hose for evacuation, characterized by, A fourth pressure measuring unit is arranged at a position close to the first gas path stop valve of the liquid inlet hard pipeline; the fourth pressure measuring unit is used for measuring pressure change of the liquid inlet hard pipeline. The application further discloses a method for filling and blowing propellant into a measured hose. The method comprises the following steps: sequentially connecting a liquid inlet tank, a liquid inlet pipeline, a measured hose, a liquid outlet pipeline and a liquid collecting tank arranged on a ground scale from high to low; arranging a blowing gas supply unit at one end of the liquid inlet pipeline close to the measured hose, and setting blowing time and blowing gas pressure and other parameters; opening a first liquid path stop valve of the liquid inlet tank, and closing a first gas path stop valve of the blowing gas supply unit and a second gas path stop valve of the liquid collecting tank, so that propellant in the liquid inlet tank is filled into the measured hose; After the measured hose is filled with propellant, the first liquid path stop valve is closed and the first gas path stop valve and the second gas path stop valve are opened, the measured hose is emptied and purged by the purging gas supply unit, and the propellant in the measured hose is collected in the liquid collection tank; After the purging time is cut off, the first gas path stop valve and the second gas path stop valve are closed, and the weight change amount of the liquid collection tank is obtained; The test result of the emptying and purging of the measured hose is determined according to the weight change amount of the liquid collection tank.

8. The method of Figure 7, further comprising: Before the measured hose is emptied and purged by the purging gas supply unit, the third gas path stop valve of the liquid discharge pipeline is briefly opened when the pressure of the liquid discharge pipeline continuously rises, and the gas at the end of the liquid discharge pipeline is discharged.

9. The method of Figure 8, wherein the method further comprises, The method for obtaining the weight change amount of the liquid collection tank is: The liquid level change amount of the propellant in the liquid inlet tank is obtained according to the liquid level meter arranged on the liquid inlet tank, and the liquid level change amount is converted into the weight change amount; Alternatively, the weight change of the liquid collection tank is directly obtained according to the reading of the ground scale.

10. The method of the rocket hose purge test according to claim 9, wherein, The method for determining the test result of the emptying and purging of the measured hose according to the weight change amount of the liquid collection tank is: The propellant filling weight inside the measured hose is calculated according to the diameter and length of the measured hose; The residual propellant content of the measured hose is calculated by the formula: residual propellant content of the measured hose = propellant filling weight - weight change amount of the liquid collection tank; If the residual propellant content of the measured hose meets the requirements, the test is completed; If the residual propellant content of the measured hose exceeds the required value, the purging time or the purging gas pressure is appropriately extended for retesting until the requirements are met.

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