High-flow quick filling system and method for liquid rocket and liquid rocket

Abstract

The invention provides a high-flow quick filling system and method for a liquid rocket and the liquid rocket. The high-flow quick filling system comprises a ground liquid oxygen filling module, an on-rocket liquid oxygen filling module, an auxiliary liquid oxygen filling module and an on-rocket filling module. The ground liquid oxygen filling module is used for filling liquid oxygen into the rocket liquid oxygen filling module and the auxiliary liquid oxygen filling module; the on-rocket liquid oxygen filling module and the auxiliary liquid oxygen filling module are connected in parallel and then connected with the on-rocket filling module, and the auxiliary liquid oxygen filling module pressurizes the on-rocket liquid oxygen filling module through self-generated pressurization; and the on-rocket liquid oxygen filling module is used for carrying out extrusion filling on the rocket through the on-rocket filling module. The method of extrusion filling and low-temperature medium self-generation pressurization is adopted, and low-temperature propellant large-flow filling is achieved.

Description

Technical Field

[0001] This invention relates to the field of liquid rocket launch technology, specifically to a high-flow-rate rapid refueling system for liquid rockets, a refueling method, and a liquid rocket. Background Technology

[0002] In the aerospace field, liquid rockets, as crucial launch vehicles for sending spacecraft into space, play a vital role in every stage of their launch process. Cryogenic propellant loading is one of the key steps in pre-launch preparation. Cryogenic propellants, such as liquid hydrogen and liquid oxygen, are widely used in modern liquid rockets due to their advantages such as high density and high specific impulse. However, the storage, transportation, and loading of cryogenic propellants face numerous technical challenges.

[0003] Cryogenic propellants, such as liquid hydrogen and liquid oxygen, evaporate or solidify rapidly at room temperature and pressure. To ensure successful ignition and launch of the rocket, the propellant must be loaded into the rocket's fuel tanks before launch and kept in a liquid state. High-flow-rate loading allows a large amount of propellant to be loaded into the tanks in a short time, thus meeting the rocket's launch requirements.

[0004] Before a liquid rocket launch, the launch vehicle and all related systems need to complete a series of preparatory work, including various checks, tests, and pre-launch procedures. The completion of these tasks is a prerequisite for a successful rocket launch. The high-volume loading of cryogenic propellant is generally carried out within 24 hours before launch. This timeframe is chosen precisely to ensure that the propellant has been loaded by the time the rocket is ready for launch, thus avoiding changes to the launch plan due to loading too early or too late.

[0005] Traditional cryogenic propellant loading systems often suffer from slow loading rates, low control precision, complex equipment, and low reliability. Especially during high-volume loading, the low-temperature characteristics and volatility of cryogenic propellants can easily lead to the generation of large amounts of vapor during the loading process, causing increased tank pressure and potentially triggering safety accidents. Furthermore, traditional loading methods often rely on manual operation, resulting in a low degree of automation and failing to meet the demands of modern space launches for high efficiency, safety, and reliability.

[0006] Regarding the refueling method, traditional cryogenic propellant refueling often relies on cryogenic pumps. The working capacity of the cryogenic pump directly determines the refueling speed. However, current cryogenic pump technology is still in its early stages and is expensive, with a maximum refueling capacity of 5m³. 3 The current cryogenic refueling pump with a capacity of [number] min is far from meeting the refueling requirements of modern large liquid-fueled launch vehicles. Summary of the Invention

[0007] In view of this, the purpose of this invention is to provide a high-flow-rate rapid refueling system, refueling method, and liquid rocket for liquid rockets, so as to solve at least one of the above-mentioned technical problems.

[0008] To achieve the above objectives, in a first aspect, embodiments of the present invention provide a high-flow-rate rapid refueling system for liquid rockets, comprising: a ground liquid oxygen refueling module, an onboard liquid oxygen refueling module, an auxiliary liquid oxygen refueling module, and an onboard refueling module;

[0009] The ground-based liquid oxygen refueling module is used to refuel liquid oxygen into the rocket-mounted liquid oxygen refueling module and the auxiliary liquid oxygen refueling module;

[0010] The onboard liquid oxygen refueling module and the auxiliary liquid oxygen refueling module are connected in parallel. The auxiliary liquid oxygen refueling module pressurizes the onboard liquid oxygen refueling module through self-generated pressurization.

[0011] The onboard liquid oxygen refueling module is used to inject liquid oxygen into the rocket through an onboard refueling module.

[0012] In some possible implementations,

[0013] The onboard liquid oxygen refueling module includes a first liquid oxygen vacuum insulated container;

[0014] The auxiliary liquid oxygen filling module includes a second liquid oxygen vacuum insulation container and a vaporizer, wherein the inlet of the vaporizer is connected to the lower liquid inlet of the second liquid oxygen vacuum insulation container.

[0015] The outlet of the vaporizer is connected to the pressurization inlet of the first liquid oxygen vacuum insulation container and the second liquid oxygen vacuum insulation container, respectively.

[0016] The main outlet of the first liquid oxygen vacuum insulation container and the main outlet of the second liquid oxygen vacuum insulation container are connected to the main filling pipeline after being merged by the pipeline. The main filling pipeline is used to squeeze and fill the rocket through the on-rocket filling module.

[0017] The ground-based liquid oxygen refueling module is connected to the upper inlet pipes of the first liquid oxygen vacuum insulation container and the second liquid oxygen vacuum insulation container, respectively.

[0018] In some possible implementations, a first pressure sensor, a second pressure sensor, a third pressure sensor, and a fourth pressure sensor are also included;

[0019] The first pressure sensor is installed at the pressurization inlet of the first liquid oxygen vacuum insulation container, and the second pressure sensor is installed at the main liquid outlet of the first liquid oxygen vacuum insulation container.

[0020] The third pressure sensor is installed at the pressurization inlet of the second liquid oxygen vacuum insulation container, and the fourth pressure sensor is installed at the main outlet of the second liquid oxygen vacuum insulation container.

[0021] In some possible implementations, a first manual venting valve, a second manual venting valve, and a third manual venting valve are also included;

[0022] The first manual venting valve is located at the pressurization inlet of the first liquid oxygen vacuum insulated container;

[0023] The second manual venting valve is located at the pressurization inlet of the second liquid oxygen vacuum insulation container;

[0024] The third manual vent valve is located at the outlet of the vaporizer.

[0025] The first liquid oxygen vacuum insulation container and the second liquid oxygen vacuum insulation container are connected by their upper liquid inlet pipes.

[0026] In some possible implementations, the system further includes: a seventh pneumatic ball valve, an eighth pneumatic ball valve, a first differential pressure level gauge, and a second differential pressure level gauge;

[0027] The seventh pneumatic ball valve is installed on the upper liquid inlet pipe of the first liquid oxygen vacuum insulation container;

[0028] The eighth pneumatic ball valve is installed on the upper liquid inlet pipe of the second liquid oxygen vacuum insulation container;

[0029] The first differential pressure level gauge is installed inside the first liquid oxygen vacuum insulated container;

[0030] The second differential pressure level gauge is installed inside the second liquid oxygen vacuum insulated container.

[0031] In some possible implementations, the system further includes a subcooling module, disposed on the main filling pipeline, for online subcooling of the filling liquid oxygen.

[0032] In some possible implementations, the subcooling module includes: a liquid oxygen subcooler.

[0033] The liquid oxygen subcooler is equipped with a first filter, a fifth pressure sensor, and a first temperature sensor at the tube inlet.

[0034] The tube-side outlet of the liquid oxygen subcooler is equipped with a sixth pressure sensor and a second temperature sensor.

[0035] A first pneumatic regulating valve is provided at the shell-side inlet of the liquid oxygen subcooler;

[0036] A third differential pressure level gauge is installed in the shell side of the liquid oxygen subcooler.

[0037] In some possible implementations, the on-rocket refueling module includes a primary on-rocket refueling flow regulation channel and a secondary on-rocket refueling flow regulation channel; the primary on-rocket refueling flow regulation channel is connected to a primary liquid oxygen storage tank, and the secondary on-rocket refueling flow regulation channel is connected to a secondary liquid oxygen storage tank.

[0038] The first main valve, as well as one or more of the first flow regulation unit, the first flow monitoring unit, the first liquid oxygen recovery unit, the first pressure measurement unit, and the first temperature measurement unit are provided on the flow regulation channel of the first-stage rocket.

[0039] A second main valve, as well as one or more of a second flow regulation unit, a second flow monitoring unit, a second liquid oxygen recovery unit, a second pressure measurement unit, and a second temperature measurement unit, are provided on the flow regulation channel of the second-stage rocket.

[0040] In some possible implementations, the system further includes an auxiliary pressurization module connected to the first liquid oxygen vacuum insulation container and the second liquid oxygen vacuum insulation container, respectively, for maintaining the air cushion pressure inside the first liquid oxygen vacuum insulation container and the second liquid oxygen vacuum insulation container.

[0041] In some possible implementations, the auxiliary booster module includes a pressure compensation unit;

[0042] The pressurization unit includes a first gas flow control component, a second gas flow control component, and a thirteenth pneumatic ball valve; the first gas flow control component and the second gas flow control component are connected in parallel and then connected to the thirteenth pneumatic ball valve; the thirteenth pneumatic ball valve and the outlet of the vaporizer are connected through a pipeline and then connected to the pressurization inlet of the first liquid oxygen vacuum insulation container and the second liquid oxygen vacuum insulation container; wherein, the first flow control component includes a first solenoid valve and a first gas flow restrictor plate connected in series, and the second flow control component includes a second solenoid valve and a second gas flow restrictor plate connected in series;

[0043] A fourteenth pneumatic ball valve is installed on the pipeline between the outlet of the vaporizer and the pressurization inlet of the second liquid oxygen vacuum insulation container.

[0044] In some possible implementations, the auxiliary pressurization module further includes: the auxiliary pressurization module further includes an air cushion pressurization unit; the air cushion pressurization unit includes a third solenoid valve, a third gas flow restrictor plate and a fifteenth pneumatic ball valve connected in sequence, the fifteenth pneumatic ball valve being connected to the pressurization inlet of the second liquid oxygen vacuum insulation container through a pipeline.

[0045] In some possible implementations, a second filter and a ninth pressure sensor are provided at the pressurization gas inlet of the auxiliary pressurization module.

[0046] In some possible implementations, the ground-based liquid oxygen refueling module includes:

[0047] A plurality of filling components are connected in parallel and then connected in series with a third filter and a fourth filter; wherein each of the filling components includes a filling port and a manual valve connected in series.

[0048] A safety valve, an exhaust valve, and a check valve are provided between the third filter and the fourth filter.

[0049] Secondly, embodiments of the present invention provide a refueling method for a high-flow-rate rapid refueling system for liquid rockets, comprising the following steps:

[0050] S1, open the first pneumatic ball valve and the second pneumatic ball valve, open the ground liquid oxygen filling module to fill the first liquid oxygen vacuum insulation container and the second liquid oxygen vacuum insulation container with liquid oxygen, close the ground liquid oxygen filling module, and close the first pneumatic ball valve and the second pneumatic ball valve.

[0051] S2, open the fifth pneumatic ball valve at the liquid inlet of the second liquid oxygen vacuum insulation container, open the sixth pneumatic ball valve at the outlet of the liquid oxygen vaporizer, open the second pneumatic ball valve, and the liquid oxygen in the second liquid oxygen vacuum insulation container flows to the vaporizer under the initial gravity and vaporizes before being self-pressurized into the second liquid oxygen vacuum insulation container to the preset pressure value.

[0052] S3, open the fourth pneumatic ball valve at the outlet of the second liquid oxygen vacuum insulation container, and the liquid oxygen in the second liquid oxygen vacuum insulation container is squeezed sequentially into the main filling pipeline and the rocket filling module under the pressure of the air cushion for extended pipeline pre-cooling.

[0053] S4, close the second pneumatic ball valve, open the first and third pneumatic ball valves, the vaporizer pressurizes the first liquid oxygen vacuum insulation container through the sixth pneumatic ball valve, the first liquid oxygen vacuum insulation container squeezes liquid oxygen into the main filling pipeline through the third pneumatic ball valve, and the main filling pipeline squeezes and fills the rocket through the rocket filling module.

[0054] Thirdly, embodiments of the present invention provide a liquid rocket, wherein the liquid rocket employs a high-flow-rate rapid refueling system for liquid rockets as described in the first aspect and a refueling method for the high-flow-rate rapid refueling system for liquid rockets as described in the second aspect.

[0055] The embodiments of the present invention have the following beneficial effects:

[0056] The present invention provides a liquid rocket high-flow-rate rapid refueling system and method, which adopts the methods of extrusion refueling and cryogenic medium self-pressurization to achieve high-flow-rate refueling of cryogenic propellants;

[0057] The refueling system provided in this embodiment of the invention uses remotely automatically controllable valves such as pneumatic ball valves, electric ball valves, and electric regulating valves, which can realize remote unattended automated refueling, simplify the refueling process, and improve refueling efficiency. The refueling of the rocket's first and second stage tanks is controlled by a main refueling pipeline with two regulating valves at the end, which can realize simultaneous refueling of the first and second stages and flow distribution, reducing system construction costs and complexity.

[0058] The refueling system provided in this embodiment of the invention adopts a liquid oxygen subcooler with online subcooling throughout the process to reduce the liquid oxygen temperature, increase the degree of liquid oxygen subcooling, reduce the possibility of evaporation and two-phase flow during the high-flow-rate refueling process, and improve the reliability of high-flow-rate liquid oxygen refueling. Attached Figure Description

[0059] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0060] Figure 1 This is a schematic diagram of the overall structure of the first liquid rocket high-flow-rate rapid refueling system according to an embodiment of the present invention;

[0061] Figure 2 This is a schematic diagram of the overall structure of the second type of liquid rocket high-flow-rate rapid refueling system according to an embodiment of the present invention;

[0062] Figure 3 This is a schematic diagram of the overall structure of the third type of liquid rocket high-flow-rate rapid refueling system according to an embodiment of the present invention;

[0063] Figure 4 This is a schematic diagram of the structure of a supercooling module according to an embodiment of the present invention;

[0064] Figure 5 This is a schematic diagram of the structure of an arrow-mounted refueling module according to an embodiment of the present invention;

[0065] Figure 6 This is a schematic diagram of the structure of an auxiliary booster module according to an embodiment of the present invention;

[0066] Figure 7 This is a schematic diagram of the structure of a ground liquid oxygen refueling module according to an embodiment of the present invention;

[0067] Figure 8 This is a flowchart of a refueling method for a high-flow-rate rapid refueling system for liquid rockets, according to an embodiment of the present invention.

[0068] Explanation of icon numbers:

[0069] 1. Filling port; 2. Manual valve; 3-1. Third filter; 3-2. Fourth filter; 4. Safety valve; 5. Exhaust valve; 6. Check valve; 7-1. Seventh pneumatic ball valve; 7-2. Eighth pneumatic ball valve; 8. Fifth pneumatic ball valve; 9-1. First differential pressure level gauge; 9-2. Second differential pressure level gauge; 10-1. First manual vent valve; 10-2. Second manual vent valve; 10-3. Third manual vent valve; 11-1. First liquid oxygen vacuum insulated container; 11-2. Second liquid oxygen vacuum insulated container; 12-1. First pressure sensor; 12-2. Second pressure sensor; 12-3. Third pressure sensor; 12-4. Fourth pressure sensor;

[0070] 13-1, First pneumatic ball valve; 13-2, Second pneumatic ball valve; 13-3, Fourteenth pneumatic ball valve; 13-4, Sixth pneumatic ball valve; 14-1, Third pneumatic ball valve; 14-2, Fourth pneumatic ball valve; 15, Vaporizer; 16, Fifteenth pneumatic ball valve; 17-1, First gas flow restrictor; 17-2, Second gas flow restrictor; 17-3, Third gas flow restrictor; 18-1, First solenoid valve; 18-2, Second solenoid valve; 18-3, Third solenoid valve; 19, Ninth pressure sensor; 20, Second filter; 21, First filter; 22-1, Fifth pressure sensor; 22-2, Sixth pressure sensor; 23-1, First temperature sensor; 23-2, Second temperature sensor; 24, First pneumatic regulating valve; 25, Liquid oxygen subcooler;

[0071] 26-1, Second pneumatic regulating valve; 26-2, Third pneumatic regulating valve; 27-1, First oxygen mass flow meter; 27-2, Second oxygen mass flow meter; 28-1, Ninth pneumatic ball valve; 28-2, Tenth pneumatic ball valve; 29-1, Eleventh pneumatic ball valve; 29-2, Twelfth pneumatic ball valve; 30-1, Seventh pressure sensor; 30-2, Eighth pressure sensor; 31-1, Third temperature sensor; 31-2, Fourth temperature sensor; 32, Third differential pressure level gauge; 33, First-stage liquid oxygen storage tank; 33-1, First-stage on-rocket refueling flow regulation channel; 34, Second-stage liquid oxygen storage tank; 34-1, Second-stage on-rocket refueling flow regulation channel; 35, Main refueling pipeline. Detailed Implementation

[0072] The features and exemplary embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description in order to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. In the accompanying drawings and the following description, at least some well-known structures and techniques have not been shown in order to avoid unnecessarily obscuring the invention; and, for clarity, the dimensions of some structures may be exaggerated. Furthermore, the features, structures, or characteristics described below may be combined in any suitable manner in one or more embodiments.

[0073] Example 1

[0074] like Figure 1 As shown in the figure, an embodiment of the present invention provides a high-flow-rate rapid refueling system for liquid rockets, comprising: a ground liquid oxygen refueling module, an onboard liquid oxygen refueling module, an auxiliary liquid oxygen refueling module, and an onboard refueling module; the ground liquid oxygen refueling module is used to refuel the onboard liquid oxygen refueling module and the auxiliary liquid oxygen refueling module with liquid oxygen; the onboard liquid oxygen refueling module and the auxiliary liquid oxygen refueling module are connected in parallel, and the auxiliary liquid oxygen refueling module pressurizes the onboard liquid oxygen refueling module through self-pressurization; the onboard liquid oxygen refueling module is used to refuel the rocket by compression through the onboard refueling module.

[0075] This invention employs a cryogenic medium self-pressurization method for extrusion filling, achieving high-flow-rate filling of cryogenic propellant.

[0076] like Figure 2 As shown, in some embodiments, the onboard liquid oxygen refueling module includes a first liquid oxygen vacuum insulated container 11-1; the auxiliary liquid oxygen refueling module includes a second liquid oxygen vacuum insulated container 11-2 and a vaporizer 15, the inlet of the vaporizer being connected to the lower inlet of the second liquid oxygen vacuum insulated container 11-2; the outlet of the vaporizer 15 being connected to the pressurization inlets of the first liquid oxygen vacuum insulated container 11-1 and the second liquid oxygen vacuum insulated container 11-2 respectively; the main outlet of the first liquid oxygen vacuum insulated container 11-1 and the main outlet of the second liquid oxygen vacuum insulated container 11-2 are connected to the main refueling pipeline 35 after being merged by pipelines, and the main refueling pipeline 35 is used to refuel the rocket by compression through the onboard refueling module; the ground liquid oxygen refueling module is connected to the upper inlet pipelines of the first liquid oxygen vacuum insulated container 11-1 and the second liquid oxygen vacuum insulated container 11-2 respectively.

[0077] In this embodiment, a first pneumatic ball valve 13-1 is provided at the pressurization inlet of the first liquid oxygen vacuum insulation container 11-1 to control the pressurization pressure of the first liquid oxygen vacuum insulation container 11-1. A third pneumatic ball valve 14-1 is provided at the main outlet of the first liquid oxygen vacuum insulation container 11-1. A second pneumatic ball valve 13-2 is provided at the pressurization inlet of the second liquid oxygen vacuum insulation container 11-2 to control the pressurization pressure of the second liquid oxygen vacuum insulation container 11-2. The main outlet of the insulated container 11-2 is equipped with a fourth pneumatic ball valve 14-2. The outlets of the third pneumatic ball valve 14-1 and the fourth pneumatic ball valve 14-2 are connected to the main filling pipeline 35 via a pipeline. The main filling pipeline 35 fills the rocket via the on-rocket filling module, and the flow rate of liquid oxygen supplied to the rocket can be controlled by the third and fourth pneumatic ball valves 14-1 and 14-2. The lower inlet of the second liquid oxygen vacuum insulated container 11-2 is equipped with a fifth pneumatic ball valve 8, which is used to control the supply of liquid oxygen to the liquid oxygen vaporizer 15. The sixth pneumatic ball valve 13-4 at the outlet of the vaporizer 15 is connected to the inlets of the first and second pneumatic ball valves 13-1 and 13-2 of the first and second liquid oxygen vacuum insulated containers 11-1 and 11-2 respectively via pipelines. In this embodiment, the liquid oxygen vaporizer 15 is a booster vaporizer 15 capable of matching the large flow rate of liquid oxygen filling requirements. A sixth pneumatic ball valve 13-4 is provided at the outlet of the vaporizer 15 to control the gas flow rate of the vaporized low-temperature oxygen to the first liquid oxygen vacuum insulation container 11-1 and the second liquid oxygen vacuum insulation container 11-2.

[0078] All pneumatic ball valves, pneumatic regulating valves, solenoid valves, pressure sensors, temperature sensors, and flow meters provided in this embodiment are cryogenic start-up ball valves and cryogenic pneumatic regulating valves, and can all be remotely controlled and data acquired. The first liquid oxygen vacuum insulation container 11-1 and the second liquid oxygen vacuum insulation container 11-2 are both high-vacuum insulation containers, with a design pressure of 1.6 MPa or higher, which can meet high extrusion pressure requirements (a high-vacuum insulation container refers to a vacuum degree < 1.33 * 10^ -2 Pa, 1.6MPa is the standard design pressure of a container, or it can be 2.5MPa. "High extrusion" pressure refers to the pressure of the air cushion pressurization during use being close to the design pressure of the container. The first liquid oxygen vacuum insulated container 11-1 is mainly used to inject liquid oxygen into the rocket. The second liquid oxygen vacuum insulated container 11-2 is mainly used for pre-cooling the injection pipeline and providing liquid oxygen to the liquid oxygen vaporizer 15 for vaporization pressurization. Then, the first liquid oxygen vacuum insulated container 11-1 is pressurized through the first cryogenic pneumatic ball valve 13-1 for liquid oxygen extrusion injection.

[0079] In this embodiment, the oxygen generated by the vaporization of liquid oxygen vaporizer 15 can not only self-pressurize the second liquid oxygen vacuum insulated container 11-2, but also pressurize the first liquid oxygen vacuum insulated container 11-1, maintaining high pressure pressure for liquid oxygen refueling. In addition, in this embodiment, multiple cryogenic liquid oxygen containers and liquid oxygen vaporizers 15 can be connected in parallel according to the rocket's liquid oxygen refueling scale requirements to achieve larger-scale liquid oxygen refueling. This embodiment achieves high-flow-rate, high-pressure liquid oxygen refueling through dual-tank step-by-step pressurization. This embodiment not only utilizes the principle of liquid oxygen self-pressurization, but also meets the needs of large-scale liquid oxygen refueling of rockets by connecting multiple liquid oxygen vacuum insulated containers and liquid oxygen vaporizers 15 in parallel, significantly improving refueling efficiency.

[0080] This embodiment uses a single main refueling pipeline 35 to transport liquid oxygen, enabling simultaneous refueling of the first and second stages of the rocket and different refueling flow rates. Moreover, the refueling valves used in this embodiment can be remotely controlled and self-feedback adjusted, enabling automatic sequential refueling and automated refueling, meeting the high-efficiency, safe, and reliable requirements for large-scale liquid oxygen refueling of future aerospace large liquid rockets.

[0081] This invention, through a single main refueling pipeline 35 and two flow-regulating refueling channels (first-stage rocket refueling flow regulation channel 33-1 and second-stage rocket refueling flow regulation channel 34-1), enables the first and second stages of the rocket to be refueled simultaneously, and allows for flexible allocation of refueling flow as needed. This improves the flexibility and accuracy of refueling and meets the complex refueling requirements before rocket launch.

[0082] like Figure 2 As shown, in some embodiments, a first pressure sensor 12-1, a second pressure sensor 12-2, a third pressure sensor 12-3, and a fourth pressure sensor 12-4 are also included; the first pressure sensor 12-1 is disposed at the pressurization inlet of the first liquid oxygen vacuum insulation container 11-1, the second pressure sensor 12-2 is disposed at the main outlet of the first liquid oxygen vacuum insulation container 11-1, the third pressure sensor 12-3 is disposed at the pressurization inlet of the second liquid oxygen vacuum insulation container 11-2, and the fourth pressure sensor 12-4 is disposed at the main outlet of the second liquid oxygen vacuum insulation container 11-2.

[0083] Specifically, the first pressure sensor 12-1 is installed on the pipeline between the first pneumatic ball valve 13-1 and the first liquid oxygen vacuum insulation container 11-1; the second pressure sensor 12-2 is installed on the pipeline between the third pneumatic ball valve 14-1 and the first liquid oxygen vacuum insulation container 11-1; the third pressure sensor 12-3 is installed on the pipeline between the second pneumatic ball valve 13-2 and the second liquid oxygen vacuum insulation container 11-2; and the fourth pressure sensor 12-4 is installed on the pipeline between the fourth pneumatic ball valve 14-2 and the second liquid oxygen vacuum insulation container 11-2. In this embodiment, the first pressure sensor 12-1 monitors the air cushion pressure inside the first liquid oxygen vacuum insulation container 11-1; and the third pressure sensor 12-3 monitors the air cushion pressure inside the second liquid oxygen vacuum insulation container 11-2, to check whether the pressurization pressure of the two containers has reached the design value for use, thereby controlling the pressurization state of the two containers. The pressure at the outlets of the first liquid oxygen vacuum insulation container 11-1 and the second liquid oxygen vacuum insulation container 11-2 is detected by the second pressure sensor 12-2 and the fourth pressure sensor 12-4, respectively, to monitor whether the system is operating normally and to calculate the upstream and downstream flow resistance.

[0084] like Figure 2 As shown, in some embodiments, the system further includes a first manual venting valve 10-1, a second manual venting valve 10-2, and a third manual venting valve 10-3; the first manual venting valve 10-1 is located at the pressurization inlet of the first liquid oxygen vacuum insulated container 11-1; the second manual venting valve 10-2 is located at the pressurization inlet of the second liquid oxygen vacuum insulated container 11-2; and the third manual venting valve 10-3 is located at the outlet of the vaporizer 15.

[0085] Specifically, in this embodiment, the first manual venting valve 10-1 is located between the first liquid oxygen vacuum insulation container 11-1 and the first pneumatic ball valve 13-1; the second manual venting valve 10-2 is located between the second liquid oxygen vacuum insulation container 11-2 and the second pneumatic ball valve 13-2; and the third manual venting valve 10-3 is located between the vaporizer 15 and the sixth pneumatic ball valve 13-4.

[0086] In this embodiment, the first manual venting valve 10-1 and the second manual venting valve 10-2 are used to depressurize the first liquid oxygen vacuum insulation container 11-1 and the second liquid oxygen vacuum insulation container 11-2, respectively, and to drain the evaporating medium in the container during long-term storage. The third manual venting valve 10-3, which is set between the sixth pneumatic ball valve 13-4 and the liquid oxygen vaporizer 15, is used to discharge the gas in the vaporizer 15 and the connecting pipeline when the fifth pneumatic ball valve 8 and the sixth pneumatic ball valve 13-4 before and after the vaporizer 15 are both closed.

[0087] like Figure 2As shown, in some embodiments, the system further includes: a seventh pneumatic ball valve 7-1, an eighth pneumatic ball valve 7-2, a first differential pressure level gauge 9-1, and a second differential pressure level gauge 9-2; the seventh pneumatic ball valve 7-1 is disposed on the upper inlet pipe of the first liquid oxygen vacuum insulation container 11-1; the eighth pneumatic ball valve 7-2 is disposed on the upper inlet pipe of the second liquid oxygen vacuum insulation container 11-2; the upper inlet pipes of the first liquid oxygen vacuum insulation container 11-1 and the second liquid oxygen vacuum insulation container 11-2 are connected. The first differential pressure level gauge 9-1 is disposed inside the first liquid oxygen vacuum insulation container 11-1; the second differential pressure level gauge 9-2 is disposed inside the second liquid oxygen vacuum insulation container 11-2.

[0088] In this embodiment, the ground-based liquid oxygen refueling module relies on the upper inlet pipes of two containers to refuel the liquid oxygen during the refueling process. Therefore, in this embodiment, a seventh pneumatic ball valve 7-1 and an eighth pneumatic ball valve 7-2 are respectively installed at the refueling inlets of the upper inlet pipes of the two containers to control the refueling status of each container. In addition, a first differential pressure level gauge 9-1 and a second differential pressure level gauge 9-2 measure the liquid oxygen level inside the two containers, respectively.

[0089] like Figure 3 As shown, in some embodiments, the system further includes a subcooling module, which is installed on the main refueling line 35, for online subcooling of the refueling liquid oxygen.

[0090] This embodiment achieves online fully subcooled liquid oxygen refueling by installing a subcooling module on the main refueling pipeline 35, thereby increasing the subcooling degree of liquid oxygen, reducing flash evaporation loss, improving refueling efficiency and the stability of the refueling system, and ensuring that liquid oxygen is efficiently and stably refueled into the rocket in liquid form.

[0091] like Figure 4 As shown, in some embodiments, the subcooling module includes: a liquid oxygen subcooler 25, wherein a first filter 21, a fifth pressure sensor 22-1, and a first temperature sensor 23-1 are provided at the tube-side inlet of the liquid oxygen subcooler 25; a sixth pressure sensor 22-2 and a second temperature sensor 23-2 are provided at the tube-side outlet of the liquid oxygen subcooler 25; a first pneumatic regulating valve 24 is provided at the shell-side inlet of the liquid oxygen subcooler 25; and a third differential pressure level gauge 32 is provided in the shell-side of the liquid oxygen subcooler 25.

[0092] In this embodiment, the tube side of the liquid oxygen subcooler 25 transports liquid oxygen, which is supplied by the main filling line 35, while the shell side stores liquid nitrogen. The liquid nitrogen and liquid oxygen do not come into direct contact. During the subcooling process of the liquid oxygen supplied by the main filling line 35, liquid nitrogen needs to be continuously consumed, therefore, liquid nitrogen needs to be replenished periodically.

[0093] Specifically, the liquid oxygen subcooler 25 is used to subcool the liquid oxygen online during the extrusion and injection of liquid oxygen onto the rocket. The shell-side cooling medium is liquid nitrogen. The shell-side inlet of the liquid oxygen subcooler 25 is connected to the first pneumatic regulating valve 24, which adjusts the valve opening according to the liquid nitrogen consumption of the liquid oxygen subcooler 25 to control the liquid nitrogen injection flow rate. The shell-side outlet of the liquid oxygen subcooler 25 is directly discharged to the atmosphere. The fifth pressure sensor 22-1 and the first temperature sensor 23-1 installed at the tube-side inlet of the liquid oxygen subcooler 25 are used to monitor the state of the liquid oxygen at the inlet of the liquid oxygen subcooler 25. The sixth pressure sensor 22-2 and the second temperature sensor 23-2 installed at the outlet are used to monitor the state of liquid oxygen at the outlet of the liquid oxygen subcooler 25. The liquid oxygen state at the outlet of the liquid oxygen subcooler is compared with the liquid oxygen state at the inlet to evaluate the heat exchange effect of the liquid oxygen subcooler 25 and whether there are any abnormalities. The tube-side outlet of the liquid oxygen subcooler 25 is connected to a vacuum pipeline until the subcooled liquid oxygen is transported to the rocket. In addition, the liquid nitrogen level in the shell side of the liquid oxygen subcooler 25 can be measured by the third differential pressure level gauge 32. The control system controls the opening of the first pneumatic regulating valve 24 according to the drop in the liquid nitrogen level.

[0094] In this embodiment, in order to reduce the evaporation of the cryogenic medium and maintain its cooling capacity and quality, all pipelines before the inlet of the liquid oxygen subcooler 25 are insulated with polyurethane foam, and all pipelines after the outlet of the liquid oxygen subcooler 25 are insulated with vacuum-insulated pipelines.

[0095] like Figure 5 As shown, in some embodiments, the on-rocket refueling module includes: a primary on-rocket refueling flow regulating channel 33-1 and a secondary on-rocket refueling flow regulating channel 34-1. The primary on-rocket refueling flow regulating channel 33-1 is connected to a primary liquid oxygen storage tank 33, and the secondary on-rocket refueling flow regulating channel 34-1 is connected to a secondary liquid oxygen storage tank 34. A first main valve is provided on the primary on-rocket refueling flow regulating channel 33-1, as well as one or more of a first flow regulating unit, a first flow monitoring unit, a first liquid oxygen recovery unit, a first pressure measuring unit, and a first temperature measuring unit.

[0096] In this embodiment, the first flow regulating unit is the second pneumatic regulating valve 26-1, the first flow monitoring unit is the first oxygen mass flow meter 27-1, the first main valve is the ninth pneumatic ball valve 28-1, the first liquid oxygen recovery unit is connected to the recovery container through the eleventh pneumatic ball valve 29-1, the first pressure measuring unit is the seventh pressure sensor 30-1, and the first temperature measuring unit is the third temperature sensor 31-1.

[0097] The secondary rocket is equipped with a main valve on the injection flow regulation channel 34-1, as well as one or more of the following: a second flow regulation unit, a second flow monitoring unit, a second liquid oxygen recovery unit, a second pressure measurement unit, and a second temperature measurement unit.

[0098] In this embodiment, the second flow regulation unit is the third pneumatic regulating valve 26-2, the second flow monitoring unit is the second oxygen mass flow meter 27-2, the second main valve is the tenth pneumatic ball valve 28-2, the second liquid oxygen recovery unit is connected to the liquid oxygen recovery container through the twelfth pneumatic ball valve 29-2, the second pressure measurement unit is the eighth pressure sensor 30-2, and the second temperature measurement unit is the fourth temperature sensor 31-2.

[0099] Specifically, the second pneumatic regulating valve 26-1 is used to control the flow rate of liquid oxygen supplied to the first-stage liquid oxygen storage tank 33; the third pneumatic regulating valve 26-2 is used to control the flow rate of liquid oxygen supplied to the second-stage liquid oxygen storage tank 34; liquid oxygen is supplied from the outlet of the liquid oxygen supercooler 25 via a single liquid oxygen vacuum tube to the rocket launch area, where it is split into two, supplying liquid oxygen to the inlets of the second and third pneumatic regulating valves 26-1 and 26-2 respectively through the first-stage onboard flow rate regulating channel 33-1 and the second-stage onboard flow rate regulating channel 34-1; the outlets of the second and third pneumatic regulating valves 26-1 and 26-2 are connected to the first and second oxygen mass flow meters 27-1 and 27-2 respectively, which are used to measure the first and second stage supply flow rates. The pressure is measured and fed back to the second pneumatic regulating valve 26-1 and the third pneumatic regulating valve 26-2 to control the opening of the two regulating valves respectively; the ninth pneumatic ball valve 28-1 and the tenth pneumatic ball valve 28-2 are the main valves for injecting liquid oxygen into the first and second stages of the rocket; the eleventh pneumatic ball valve 29-1 and the twelfth pneumatic ball valve 29-2 are connected to the recovery container through pipelines to recover the liquid oxygen in the pipeline between the ninth pneumatic ball valve 28-1 and the tenth pneumatic ball valve 28-2 and the rocket; the seventh pressure sensor 30-1 and the eighth pressure sensor 30-2 are used to monitor the pressure of the liquid oxygen injection port of the first and second stages of the rocket; the third temperature sensor 31-1 and the fourth temperature sensor 31-2 are used to monitor the temperature of the liquid oxygen injection port of the first and second stages of the rocket. By monitoring the pressure and temperature of the liquid oxygen injection port of the first and second stages, the liquid oxygen injection status is monitored to ensure that there are no abnormalities in the liquid oxygen injection process.

[0100] like Figure 3 As shown, in some embodiments, the system further includes an auxiliary pressurization module, which is connected to the first liquid oxygen vacuum insulation container 11-1 and the second liquid oxygen vacuum insulation container 11-2 respectively, for maintaining the air cushion pressure in the first liquid oxygen vacuum insulation container 11-1 and the second liquid oxygen vacuum insulation container 11-2.

[0101] In this embodiment, the auxiliary pressurization module uses nitrogen pressurization. Only a small flow of nitrogen is needed to pressurize the second liquid oxygen vacuum insulation container 11-2 to supply liquid oxygen to the liquid oxygen vaporizer 15, thus achieving liquid oxygen vaporization and self-pressurization. During the filling process, the liquid oxygen vacuum insulation container can also be pressurized, effectively supplementing the pressurization capacity of the two vacuum liquid oxygen containers in the later stage of filling, ensuring a smooth filling process.

[0102] like Figure 6 As shown, in some embodiments, the auxiliary pressurization module includes a pressure replenishment unit; the pressure replenishment unit includes a first gas flow control component, a second gas flow control component, and a thirteenth pneumatic ball valve 13-5; the first gas flow control component and the second gas flow control component are connected in parallel and then connected to the thirteenth pneumatic ball valve 13-5; the thirteenth pneumatic ball valve 13-5 and the outlet of the vaporizer 15 are connected through a pipeline and then connected to the pressurization inlet of the first liquid oxygen vacuum insulation container 11-1 and the second liquid oxygen vacuum insulation container 11-2; wherein, the first flow control component includes a first solenoid valve 18-1 and a first gas flow restricting orifice plate 17-1 connected in series, the second flow control component includes a second solenoid valve 18-2 and a second gas flow restricting orifice plate 17-2 connected in series; a fourteenth pneumatic ball valve 13-3 is provided on the pipeline between the sixth pneumatic ball valve 13-4 and the vaporizer 15.

[0103] Specifically, in this embodiment, the first gas flow limiting orifice plate 17-1 and the second gas flow limiting orifice plate 17-2, the first solenoid valve 18-1 and the second solenoid valve 18-2, and the thirteenth pneumatic ball valve 13-5 constitute a pressure replenishment unit. The first gas flow limiting orifice plate 17-1 and the second gas flow limiting orifice plate 17-2 are orifice plates of different diameters, and are used in combination with the first solenoid valve 18-1 and the second solenoid valve 18-2 respectively, so as to provide gas pillow pressure to the first liquid oxygen vacuum insulation container 11-1 in a way that switches between different nitrogen pressurization flow rates. The third solenoid valve 18-3, the third gas flow limiting orifice plate 17-3, and the cryogenic fifteenth pneumatic ball valve 16 constitute a gas pillow pressurization unit, which is used to pressurize the second liquid oxygen vacuum insulation container 11-2 separately to maintain the container gas pillow pressure, thereby adjusting the liquid oxygen flow rate supplied by the liquid oxygen vaporizer 15 to the first liquid oxygen vacuum insulation container 11-1. In addition, in this embodiment, the fourteenth pneumatic ball valve 13-3 is installed on the pipeline between the sixth pneumatic ball valve 13-4 and the second pneumatic ball valve 13-2. By installing the fourteenth pneumatic ball valve 13-3 on the pipeline between the sixth pneumatic ball valve 13-4 and the second pneumatic ball valve 13-2, the pressure in the pressurized pipeline can be discharged. The outlets of the thirteenth pneumatic ball valve 13-5 and the sixth pneumatic ball valve 13-4 are connected to the inlets of the first pneumatic ball valve 13-1 and the second pneumatic ball valve 13-2 after being merged by the pipeline. The first flow control component includes a first solenoid valve 18-1 and a first gas flow restrictor 17-1 connected in series, and the second flow control component includes a second solenoid valve 18-2 and a second gas flow restrictor 17-2 connected in series. The fourteenth pneumatic ball valve 13-3 is installed on the pipeline between the sixth pneumatic ball valve 13-4 and the second pneumatic ball valve 13-2.

[0104] like Figure 6 As shown, in some embodiments, the auxiliary pressurization module further includes an air cushion pressurization unit; the air cushion pressurization unit includes a third solenoid valve 18-3, a third gas flow limiting orifice plate 17-3 and a fifteenth pneumatic ball valve 16 connected in sequence, and the fifteenth pneumatic ball valve 16 is connected to the pressurization inlet of the second liquid oxygen vacuum insulation container 11-2 through a pipeline.

[0105] In this embodiment, a small flow of nitrogen is used to pressurize the second liquid oxygen vacuum insulation container 11-2 using a pressurization unit. Liquid oxygen is then supplied to the liquid oxygen vaporizer 15 via the second liquid oxygen vacuum insulation container 11-2. The oxygen generated by vaporization in the liquid oxygen vaporizer 15 simultaneously provides self-pressurization to both the second liquid oxygen vacuum insulation container 11-2 and the first liquid oxygen vacuum insulation container 11-1, maintaining a high pressurization pressure in the first liquid oxygen vacuum insulation container 11-1 for liquid oxygen refueling. When the liquid oxygen volume in the second liquid oxygen vacuum insulation container 11-2 increases, the pressurization unit is used to further pressurize the second liquid oxygen vacuum insulation container 11-2. This embodiment can also connect multiple second liquid oxygen vacuum insulation containers 11-2 and liquid oxygen vaporizers 15 in parallel to achieve larger-scale liquid oxygen refueling, depending on the required scale of rocket liquid oxygen refueling.

[0106] In the later stages of liquid oxygen refueling, as the volume of the gas pillow in the first liquid oxygen vacuum insulation container 11-1 increases, the difficulty of pressurizing the gas pillow increases, and the self-generated pressurization capacity is limited. At this time, it is no longer necessary to use the vaporizer 15 to pressurize the first liquid oxygen vacuum insulation container 11-1. The sixth pneumatic ball valve 13-4 needs to be closed. By using different combinations of orifice plates and solenoid valves through the pressurization unit, different nitrogen flow rates can be supplemented and pressurized to ensure that the large-flow liquid oxygen refueling process is completed smoothly and without interruption or failure due to insufficient pressurization.

[0107] like Figure 6 As shown, in some embodiments, a second filter 20 and a ninth pressure sensor 19 are provided at the pressurized gas inlet of the auxiliary pressurization module. In this embodiment, by providing the second filter 20, the pressurized gas can be filtered, and the pressure at the inlet of the auxiliary pressurization module is measured by the ninth pressure sensor 19.

[0108] like Figure 7 As shown, in some embodiments, the ground liquid oxygen refueling module includes:

[0109] Several filling components are connected in parallel and then connected in series with the third filter 3-1 and the fourth filter 3-2; each filling component includes a filling port 1 and a hand valve 2 connected in series; a safety valve 4, an exhaust valve 5 and a one-way valve 6 are provided between the third filter 3-1 and the fourth filter 3-2.

[0110] In this embodiment, the filling port 1 is a standard tank truck horn-shaped filling port 1. Each filling port 1 is connected in series with a hand valve 2. The standard tank truck horn-shaped filling port 1 is connected to the liquid oxygen tank truck's filling metal hose. When filling the tank truck with liquid oxygen, the hand valve 2 needs to be opened. The third filter 3-1 and the fourth filter 3-2 are used in series to perform double filtration of the added liquid oxygen with different filtration accuracies. After the liquid oxygen filling is completed, the cryogenic hand valve 2 needs to be closed and the cryogenic exhaust valve 5 needs to be opened to release the residual liquid oxygen in the sealed pipeline to prevent overpressure. When the liquid oxygen is discharged from the pipeline, the one-way valve 6 can be used to prevent air from entering the oxygen pipeline.

[0111] Example 2

[0112] like Figure 8 As shown, this embodiment of the invention provides a refueling method for a high-flow-rate rapid refueling system for liquid rockets, comprising the following steps:

[0113] S1, open the first pneumatic ball valve 13-1 and the second pneumatic ball valve 13-2, open the ground liquid oxygen filling module to fill the first liquid oxygen vacuum insulation container 11-1 and the second liquid oxygen vacuum insulation container 11-2 with liquid oxygen, close the ground liquid oxygen filling module, and close the first pneumatic ball valve 13-1 and the second pneumatic ball valve 13-2.

[0114] S2, open the fifth pneumatic ball valve 8 at the lower liquid inlet of the second liquid oxygen vacuum insulation container 11-2, open the sixth pneumatic ball valve 13-4 at the outlet of the liquid oxygen vaporizer 15, open the second pneumatic ball valve 13-2, and the liquid oxygen in the second liquid oxygen vacuum insulation container 11-2 flows to the vaporizer 15 under the initial gravity and vaporizes, and then self-pressurizes into the second liquid oxygen vacuum insulation container 11-2 to the preset pressure value;

[0115] Specifically, during the initial vaporization and pressurization of liquid oxygen (low-pressure section), the fifth pneumatic ball valve 8 at the lower inlet of the second liquid oxygen vacuum insulated container 11-2 is opened, the sixth pneumatic ball valve 13-4 at the outlet of the liquid oxygen vaporizer 15 is opened, and the second pneumatic ball valve 13-2 at the pressurization inlet of the second liquid oxygen vacuum insulated container 11-2 is opened. Initially, the pressure of the gas pillow in the second liquid oxygen vacuum insulated container 11-2 is at atmospheric pressure, and it flows to the vaporizer 15 by its own weight. After the vaporizer 15 vaporizes the liquid oxygen, oxygen enters the second liquid oxygen vacuum insulated container 11-2 and pressurizes the gas pillow of the second liquid oxygen vacuum insulated container 11-2 by its own weight. At this time, the main driving force for the liquid oxygen outflow changes from its own weight to the gas pillow pressure. The third pressure sensor 12-3 is used to monitor the pressure of the gas pillow in the second liquid oxygen vacuum insulated container 11-2 until it is pressurized to the preset pressure value (about 0.2 to 0.3 MPa).

[0116] S3, open the fourth pneumatic ball valve 14-2 at the outlet of the second liquid oxygen vacuum insulation container 11-2, and the liquid oxygen in the second liquid oxygen vacuum insulation container 11-2 is squeezed sequentially to the main filling pipeline 35 and the rocket filling module under the pressure of the air cushion for extended pipeline pre-cooling.

[0117] S4, close the second pneumatic ball valve 13-2, open the first pneumatic ball valve 13-1 and the third pneumatic ball valve 14-1, the vaporizer 15 pressurizes the first liquid oxygen vacuum insulation container 11-1 through the sixth pneumatic ball valve 13-4, the first liquid oxygen vacuum insulation container 11-1 squeezes liquid oxygen into the main filling pipeline 35 through the third pneumatic ball valve 14-1, and the main filling pipeline 35 squeezes and fills the rocket through the rocket filling module.

[0118] The refueling method provided in this invention achieves high-flow-rate, high-pressure liquid oxygen refueling through step-by-step pressurization in dual storage tanks. Oxygen generated by vaporization in the liquid oxygen vaporizer 15 self-pressurizes the first liquid oxygen vacuum insulated container 11-1 and the second liquid oxygen vacuum insulated container 11-2, maintaining high pressure for refueling. Furthermore, multiple cryogenic liquid oxygen containers and liquid oxygen vaporizers 15 can be connected in parallel to achieve larger-scale liquid oxygen refueling, depending on the required scale of rocket liquid oxygen refueling.

[0119] In some embodiments, during the ground-based liquid oxygen refueling process, it is necessary to connect the standard tank truck's horn-shaped refueling port 1, open the hand valve 2 at each refueling port 1, and open the seventh pneumatic ball valve 7-1 and the eighth pneumatic ball valve 7-2 at the upper liquid inlet of the first liquid oxygen vacuum insulation container 11-1 and the second liquid oxygen vacuum insulation container 11-2 to ensure unobstructed container refueling pipelines. Then, open the first pneumatic ball valve 13-1, the second pneumatic ball valve 13-2, and the fourteenth pneumatic ball valve 13-3 to ensure unobstructed venting of the liquid oxygen containers. Liquid oxygen is then refueled from the tank truck into the first liquid oxygen vacuum insulation container 11-1 and the second liquid oxygen vacuum insulation container 11-2.

[0120] Once the liquid oxygen filling the first liquid oxygen vacuum insulation container 11-1 and the second liquid oxygen vacuum insulation container 11-2 meets the requirements, close the first pneumatic ball valve 13-1, the second pneumatic ball valve 13-2, the fourteenth pneumatic ball valve 13-3, the seventh pneumatic ball valve 7-1, and the eighth pneumatic ball valve 7-2, close the cryogenic hand valve 2, disconnect the filling port 1, open the cryogenic exhaust valve 5, and discharge the residual liquid oxygen in the sealed pipeline to prevent overpressure.

[0121] In some embodiments, during the precooling process of the filling pipeline, the fourth pneumatic ball valve 14-2, the ninth pneumatic ball valve 28-1, the eleventh pneumatic ball valve 29-1, the tenth pneumatic ball valve 28-2, the twelfth pneumatic ball valve 29-2, the second pneumatic regulating valve 26-1, and the third pneumatic regulating valve 26-2 are opened. Liquid oxygen is squeezed out and flows into the filling pipeline under the pressure of the air pillow in the second liquid oxygen vacuum insulation container 11-2, thereby achieving precooling of the extended pipeline. The precooled liquid oxygen flows from the outlet of the eleventh pneumatic ball valve 29-1 and the twelfth pneumatic ball valve 29-2 to the recovery container. The temperature sensors monitor the precooling process. After precooling to the specified temperature, the fourth pneumatic ball valve 14-2, the eleventh pneumatic ball valve 29-1, and the twelfth pneumatic ball valve 29-2 are closed.

[0122] In some embodiments, the added liquid oxygen can also be subcooled online. During the subcooling process, the first pneumatic regulating valve 24 at the inlet of the liquid oxygen subcooler 25 is opened to add liquid nitrogen to the shell side of the liquid oxygen subcooler 25. The liquid nitrogen level is monitored by the third differential pressure level gauge 32 and the liquid level height is fed back to the first pneumatic regulating valve 24. After the liquid nitrogen is added to the designated position, the first pneumatic regulating valve 24 is closed.

[0123] In some embodiments, during the onboard fueling process, the second pneumatic ball valve 13-2 is closed, the fifteenth pneumatic ball valve 16, the first pneumatic ball valve 13-1, and the third pneumatic ball valve 14-1 are opened, and the third solenoid valve 18-3 is opened. At this time, the second liquid oxygen vacuum insulation container 11-2 is only used to supply liquid oxygen to the liquid oxygen vaporizer 15. The second liquid oxygen vacuum insulation container 11-2 relies on nitrogen pressurization to maintain the pressure of the gas pillow. The oxygen generated from the outlet of the liquid oxygen vaporizer 15 is only used to pressurize the first liquid oxygen vacuum insulation container 11-1 to maintain the high pressure of the gas pillow inside the first liquid oxygen vacuum insulation container 11-1. The liquid oxygen supplied to the rocket in large quantities all comes from the first liquid oxygen container. Vacuum insulated container 11-1; monitoring parameters of the ninth pressure sensor 19 to ensure stable pressure of the pressurized gas (nitrogen source); since the pressure of the gas pillow in the first liquid oxygen vacuum insulated container 11-1 is pressurized by oxygen vaporized by vaporizer 15, and the pressure of the gas pillow in the second liquid oxygen vacuum insulated container 11-2 is pressurized by nitrogen, and the gas pillows of the two containers are isolated, the pressures of the gas pillows in the first liquid oxygen vacuum insulated container 11-1 and the second liquid oxygen vacuum insulated container 11-2 are different. By monitoring the parameters of the first pressure sensor 12-1 and the third pressure sensor 12-3, the parameters are ensured to be within the design range; the control system is based on the first oxygen mass flow meter 27-1 The flow measurement parameters fed back by the second oxygen mass flow meter 27-2 are used to adjust the opening of the second pneumatic regulating valve 26-1 and the third pneumatic regulating valve 26-2 to achieve flow distribution for simultaneous primary and secondary filling and flow adjustment for different filling stages; the feedback from the third temperature sensor 31-1 and the fourth temperature sensor 31-2 is monitored to ensure that the liquid oxygen filling temperature meets the requirements of the rocket; the parameter feedback from the seventh pressure sensor 30-1 and the eighth pressure sensor 30-2 is monitored to determine the filling liquid level of the primary liquid oxygen storage tank 33 and the secondary liquid oxygen storage tank 34 on the rocket based on the back pressure; during the filling process, the third differential pressure level gauge 32 sends real-time data to the control system. The system provides feedback on the consumption and level of liquid nitrogen in the shell side of the liquid oxygen subcooler 25. The control system sends a command to the first pneumatic regulating valve 24 to adjust the valve opening of the first pneumatic regulating valve 24, ensuring that the liquid nitrogen storage in the shell side of the liquid oxygen subcooler 25 remains within the required range during the liquid oxygen subcooling and refueling process. As the liquid oxygen refueling progresses, the volume of the gas pillow in the first liquid oxygen vacuum insulation container 11-1 increases, and the pressurization difficulty increases. The first solenoid valve 18-1 and / or the second solenoid valve 18-2 in the pressurization unit can be opened individually or simultaneously, and the thirteenth pneumatic ball valve 13-5 at low temperature can be opened to replenish and pressurize the first liquid oxygen vacuum insulation container 11-1 to maintain the liquid oxygen refueling flow rate.

[0124] In addition, after the filling is completed, close the third solenoid valve 18-3, close the fifteenth pneumatic ball valve 16, the fifth pneumatic ball valve 8 and the third pneumatic ball valve 14-1, and open the fourteenth cryogenic pneumatic ball valve 13-3 to depressurize the first liquid oxygen vacuum insulation container 11-1 and the second liquid oxygen vacuum insulation container 11-2; close the first cryogenic pneumatic regulating valve 24 to stop adding liquid nitrogen to the liquid oxygen subcooler 25, and let the remaining liquid nitrogen evaporate naturally; open the eleventh cryogenic pneumatic ball valve 29-1 and the twelfth pneumatic ball valve 29-2 to discharge the remaining liquid oxygen in the pipeline, monitor the readings of the pipeline pressure sensor and temperature sensor, and after the liquid oxygen in the pipeline has been discharged, close the second cryogenic pneumatic regulating valve 26-1, the third pneumatic regulating valve 26-2, the eleventh pneumatic ball valve 29-1 and the twelfth pneumatic ball valve 29-2.

[0125] In this embodiment, the second liquid oxygen vacuum insulation container 11-2 is mainly used for precooling the filling pipeline and pressurizing the first liquid oxygen vacuum insulation container 11-1. The first liquid oxygen vacuum insulation container 11-1 is used to fill the rocket with liquid oxygen. During the initial filling process, the second liquid oxygen vacuum insulation container 11-2 is used to pressurize the first liquid oxygen vacuum insulation container 11-1 through the liquid oxygen vaporizer 15. This is because the initial pressure inside the first liquid oxygen vacuum insulation container 11-1 is low, and the pressurization flow rate requirement is not high; self-pressurization can meet the pressurization needs. When the liquid level inside the first liquid oxygen vacuum insulation container 11-1 drops significantly, the volume of the gas pillow increases, the pressurization difficulty increases, and the pressurization flow rate requirement increases, necessitating the use of nitrogen (not liquid nitrogen) for pressurization.

[0126] The dual-tank step-by-step pressurization method provided in this invention enables high-flow-rate, high-pressure liquid oxygen refueling. This method not only utilizes the principle of self-generated pressurization of liquid oxygen, but also, by connecting multiple second liquid oxygen vacuum insulated containers 11-2 and liquid oxygen vaporizers 15 in parallel, can meet the needs of larger-scale liquid oxygen refueling for rockets, significantly improving refueling efficiency.

[0127] By setting up a pressurization unit, the pressurization capacity of the first liquid oxygen vacuum insulation container 11-1 was effectively supplemented in the later stage of filling. Through the combination of different orifice plates and solenoid valves, supplementary pressurization with different nitrogen flow rates was achieved, ensuring the smooth and successful completion of the large-flow liquid oxygen filling process and avoiding filling interruption or failure due to insufficient pressurization.

[0128] The present invention provides a combination of regulating valves for transporting liquid oxygen via a single main pipeline and two refueling channels, which allows the first and second stages of the rocket to be refueled simultaneously and the refueling flow rate to be flexibly allocated as needed. This improves the flexibility and accuracy of refueling and meets the complex refueling requirements before rocket launch.

[0129] The refueling valves provided in this invention can all be remotely controlled and self-feedback adjusted, realizing automatic timing refueling and automated refueling. This not only improves the efficiency and accuracy of refueling, but also reduces the risk of manual operation, meeting the high-efficiency, safe and reliable requirements for large-scale liquid oxygen refueling of future aerospace large liquid rockets.

[0130] By installing a subcooling module in the main refueling pipeline 35, the design of the online fully subcooled refueling method for liquid oxygen significantly improves the subcooling degree of liquid oxygen, reduces flash evaporation loss, improves refueling efficiency, enhances the stability of the refueling system, and ensures that liquid oxygen is efficiently and stably refueled into the rocket in liquid form, providing a strong guarantee for the successful launch of the rocket.

[0131] Example 3

[0132] This invention also provides a liquid rocket, which employs the high-flow-rate rapid refueling system for liquid rockets described in Embodiment 1 and the refueling method of the high-flow-rate rapid refueling system for liquid rockets described in Embodiment 2.

[0133] In the description of the embodiments of the present invention, it should be noted that the terms "upper," "lower," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the present invention. In addition, the terms "first," "second," or "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0134] Unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" in this invention embodiment should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integrated connections; similarly, they can refer to mechanical connections, electrical connections, or direct connections, or indirect connections through an intermediate medium, or internal connections between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0135] Although the invention has been described with reference to preferred embodiments, various modifications can be made and components can be replaced with equivalents without departing from the scope of the invention. In particular, the technical features mentioned in the various embodiments can be combined in any manner as long as there is no structural conflict. The invention is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A high-flow-rate rapid refueling system for liquid rockets, characterized in that, include: Ground-based liquid oxygen refueling module, onboard liquid oxygen refueling module, auxiliary liquid oxygen refueling module, and onboard refueling module; The ground-based liquid oxygen refueling module is used to refuel liquid oxygen into the rocket-mounted liquid oxygen refueling module and the auxiliary liquid oxygen refueling module; The onboard liquid oxygen refueling module and the auxiliary liquid oxygen refueling module are connected in parallel and then connected to the onboard refueling module. The auxiliary liquid oxygen refueling module pressurizes the onboard liquid oxygen refueling module through self-generated pressurization. The onboard liquid oxygen refueling module injects liquid oxygen into the rocket through the onboard refueling module.

2. The liquid rocket high-flow-rate rapid refueling system according to claim 1, characterized in that, The onboard liquid oxygen refueling module includes a first liquid oxygen vacuum insulated container (11-1); The auxiliary liquid oxygen filling module includes a second liquid oxygen vacuum insulation container (11-2) and a vaporizer (15). The inlet of the vaporizer is connected to the lower liquid inlet of the second liquid oxygen vacuum insulation container (11-2). The outlet of the vaporizer (15) is connected to the pressurization inlet of the first liquid oxygen vacuum insulation container (11-1) and the second liquid oxygen vacuum insulation container (11-2), respectively. The main outlet of the first liquid oxygen vacuum insulation container (11-1) and the main outlet of the second liquid oxygen vacuum insulation container (11-2) are connected to the main filling pipeline (35) after being merged by the pipeline. The main filling pipeline (35) fills the rocket by squeezing through the rocket filling module. The ground liquid oxygen refueling module is connected to the upper liquid inlet pipes of the first liquid oxygen vacuum insulation container (11-1) and the second liquid oxygen vacuum insulation container (11-2), respectively.

3. The liquid rocket high-flow-rate rapid refueling system according to claim 2, characterized in that, It also includes a first pressure sensor (12-1), a second pressure sensor (12-2), a third pressure sensor (12-3), and a fourth pressure sensor (12-4); The first pressure sensor (12-1) is installed at the pressurization inlet of the first liquid oxygen vacuum insulation container (11-1), and the second pressure sensor (12-2) is installed at the main outlet of the first liquid oxygen vacuum insulation container (11-1). The third pressure sensor (12-3) is located at the pressurization inlet of the second liquid oxygen vacuum insulation container (11-2), and the fourth pressure sensor (12-4) is located at the main outlet of the second liquid oxygen vacuum insulation container (11-2).

4. The liquid rocket high-flow-rate rapid refueling system according to claim 2, characterized in that, It also includes a first manual vent valve (10-1), a second manual vent valve (10-2), and a third manual vent valve (10-3); The first manual venting valve (10-1) is located at the pressurization inlet of the first liquid oxygen vacuum insulated container (11-1); The second manual venting valve (10-2) is located at the pressurization inlet of the second liquid oxygen vacuum insulation container (11-2); The third manual vent valve (10-3) is located at the outlet of the vaporizer (15).

5. A high-flow-rate rapid refueling system for liquid rockets according to claim 2, characterized in that, The system also includes: a seventh pneumatic ball valve (7-1), an eighth pneumatic ball valve (7-2), a first differential pressure level gauge (9-1), and a second differential pressure level gauge (9-2); The seventh pneumatic ball valve (7-1) is installed on the upper liquid inlet pipe of the first liquid oxygen vacuum insulation container (11-1); The eighth pneumatic ball valve (7-2) is installed on the upper liquid inlet pipe of the second liquid oxygen vacuum insulation container (11-2); The first differential pressure level gauge (9-1) is installed inside the first liquid oxygen vacuum insulated container (11-1); The second differential pressure level gauge (9-2) is installed inside the second liquid oxygen vacuum insulated container (11-2).

6. A high-flow-rate rapid refueling system for liquid rockets according to claim 2, characterized in that, The system also includes a subcooling module, which is installed on the main filling pipeline (35) for online subcooling of the added liquid oxygen.

7. A high-flow-rate rapid refueling system for liquid rockets according to claim 6, characterized in that, The subcooling module includes: a liquid oxygen subcooler (25), The liquid oxygen subcooler (25) is equipped with a first filter (21), a fifth pressure sensor (22-1), and a first temperature sensor (23-1) at the tube inlet. The liquid oxygen subcooler (25) is equipped with a sixth pressure sensor (22-2) and a second temperature sensor (23-2) at the tube outlet; A first pneumatic regulating valve (24) is provided at the shell-side inlet of the liquid oxygen subcooler (25); A third differential pressure level gauge (32) is provided in the shell side of the liquid oxygen subcooler (25).

8. A high-flow-rate rapid refueling system for liquid rockets according to claim 1, characterized in that, The on-rocket refueling module includes a primary on-rocket refueling flow regulation channel (33-1) and a secondary on-rocket refueling flow regulation channel (34-1); the primary on-rocket refueling flow regulation channel (33-1) is connected to the primary liquid oxygen storage tank (33), and the secondary on-rocket refueling flow regulation channel (34-1) is connected to the secondary liquid oxygen storage tank (34); A first main valve, and one or more of a first flow regulation unit, a first flow monitoring unit, a first liquid oxygen recovery unit, a first pressure measurement unit, and a first temperature measurement unit are provided on the first-stage rocket's injection flow regulation channel (33-1); A second main valve, as well as one or more of a second flow regulation unit, a second flow monitoring unit, a second liquid oxygen recovery unit, a second pressure measurement unit, and a second temperature measurement unit, are provided on the flow regulation channel (34-1) on the second-stage rocket.

9. A high-flow-rate rapid refueling system for liquid rockets according to claim 2, characterized in that, The system also includes an auxiliary booster module. The auxiliary pressurization module is connected to the first liquid oxygen vacuum insulation container (11-1) and the second liquid oxygen vacuum insulation container (11-2) respectively, and is used to maintain the air cushion pressure in the first liquid oxygen vacuum insulation container (11-1) and the second liquid oxygen vacuum insulation container (11-2).

10. A high-flow-rate rapid refueling system for liquid rockets according to claim 9, characterized in that, The auxiliary booster module includes a pressure compensation unit; The pressurization unit includes a first gas flow control component, a second gas flow control component, and a thirteenth pneumatic ball valve (13-5); the first gas flow control component and the second gas flow control component are connected in parallel and then connected to the thirteenth pneumatic ball valve (13-5); the thirteenth pneumatic ball valve (13-5) and the outlet of the vaporizer (15) are connected through a pipeline and then connected to the pressurization inlet of the first liquid oxygen vacuum insulation container (11-1) and the second liquid oxygen vacuum insulation container (11-2); wherein, the second gas flow control component includes a first solenoid valve (18-1) and a first gas flow restrictor plate (17-1) connected in series, and the second gas flow control component includes a second solenoid valve (18-2) and a second gas flow restrictor plate (17-2) connected in series; A fourteenth pneumatic ball valve (13-3) is installed on the pipeline between the outlet of the vaporizer (15) and the pressurization inlet of the second liquid oxygen vacuum insulation container (11-2).

11. A high-flow-rate rapid refueling system for liquid rockets according to claim 9, characterized in that, The auxiliary booster module also includes an air pillow booster unit; The air cushion pressurization unit includes a third solenoid valve (18-3), a third gas flow limiting orifice plate (17-3), and a fifteenth pneumatic ball valve (16) connected in sequence. The fifteenth pneumatic ball valve (16) is connected to the pressurization inlet of the second liquid oxygen vacuum insulation container (11-2) through a pipeline.

12. A high-flow-rate rapid refueling system for liquid rockets according to claim 9, characterized in that, A second filter (20) and a ninth pressure sensor (19) are provided at the pressurized gas inlet of the auxiliary pressurization module.

13. A high-flow-rate rapid refueling system for liquid rockets according to claim 1, characterized in that, The ground-based liquid oxygen refueling module includes: A plurality of filling components are connected in parallel and then connected in series with a third filter (3-1) and a fourth filter (3-2); wherein each of the filling components includes a filling port (1) and a hand valve (2) connected in series; A safety valve (4), an exhaust valve (5), and a check valve (6) are provided between the third filter (3-1) and the fourth filter (3-2).

14. A method for adding fuel to a high-flow-rate rapid fueling system for liquid rockets, characterized in that, Includes the following steps: S1, open the first pneumatic ball valve (13-1) and the second pneumatic ball valve (13-2), open the ground liquid oxygen filling module to fill the first liquid oxygen vacuum insulation container (11-1) and the second liquid oxygen vacuum insulation container (11-2) with liquid oxygen, close the ground liquid oxygen filling module, and close the first pneumatic ball valve (13-1) and the second pneumatic ball valve (13-2); S2, open the fifth pneumatic ball valve (8) at the liquid inlet of the second liquid oxygen vacuum insulation container (11-2), open the sixth pneumatic ball valve (13-4) at the outlet of the liquid oxygen vaporizer (15), open the second pneumatic ball valve (13-2), and the liquid oxygen in the second liquid oxygen vacuum insulation container (11-2) flows to the vaporizer (15) under the initial gravity and vaporizes before being self-pressurized into the second liquid oxygen vacuum insulation container (11-2) to the preset pressure value; S3, open the fourth pneumatic ball valve (14-2) at the outlet of the second liquid oxygen vacuum insulation container (11-2), and the liquid oxygen in the second liquid oxygen vacuum insulation container (11-2) is squeezed sequentially into the main filling pipeline and the rocket filling module under the pressure of the air cushion for extended pipeline pre-cooling; S4, close the second pneumatic ball valve (13-2), open the first pneumatic ball valve (13-1) and the third pneumatic ball valve (14-1), the vaporizer (15) pressurizes the first liquid oxygen vacuum insulation container (11-1) through the sixth pneumatic ball valve (13-4), the first liquid oxygen vacuum insulation container (11-1) squeezes liquid oxygen into the main filling pipeline (35) through the third pneumatic ball valve (14-1), and the main filling pipeline (35) squeezes and fills the rocket through the rocket filling module.

15. A liquid rocket, characterized in that, The liquid rocket employs a high-flow-rate rapid refueling system for liquid rockets as described in any one of claims 1-13 and a refueling method for the high-flow-rate rapid refueling system for liquid rockets as described in claim 14.

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