A system for recovering and safely disposing of residual oxidizer liquid oxygen from a rocket launched at sea

Abstract

The present application relates to a kind of leakage and safe handling system of marine recovery rocket residual oxidizer liquid oxygen, it is related to the field of marine rocket substage recovery, it is arranged on offshore recovery ship, and automatic leak connector is arranged on landing deck, automatic leak connector can be moved to landing deck and automatically complete with the filling port and the leak port of rocket body liquid oxygen storage tank butt joint, automatic leak connector is connected with nitrogen purging system and liquid oxygen leak treatment system by two hoses respectively;Nitrogen purging system includes high-pressure nitrogen gas cylinder group, nitrogen purging first pressure reducing valve group, nitrogen purging hose automatic retraction device, liquid oxygen buffer tank, dilution electric remote control valve;Liquid oxygen leak treatment system includes connection, liquid oxygen stainless steel cryogenic hose automatic retraction device, liquid oxygen discharge pump group, gasifier.The present application is conducive to guaranteeing the rapid leak of residual liquid oxygen in rocket propellant storage tank and carrying out safe handling, to ensure that rocket body is smoothly and safely returned to port after landing on ship.

Description

Technical Field

[0001] This invention relates to the field of marine rocket stage recovery, and particularly focuses on a system for the safe release and safe handling of residual liquid oxygen oxidizer from a rocket after it has safely landed on a marine recovery vessel. Background Technology

[0002] The development of marine rocket recovery ship technology will facilitate the reuse of rockets after launch, significantly reduce the cost of launching carrier rockets, and further promote the expansion of the aerospace industry's economic scale.

[0003] Currently, the descent process of rocket boosters recovered at sea typically employs engine reverse thrust for deceleration, enabling the rocket to land at a low speed on the recovery vessel. After landing, a significant amount of liquid oxygen remains in the rocket's fuel tanks. To prevent the residual liquid oxygen from vaporizing and undergoing a phase change inside the fuel tank, causing overpressure and leakage that could lead to deflagration, and to mitigate the increased costs of storing and transporting cryogenic hazardous chemicals during ship operations, as well as the potential risks of explosions, it is necessary to drain the remaining liquid oxygen from the rocket and safely dispose of it.

[0004] Existing rocket residual fuel handling technology involves connecting a robot to the rocket's fuel tanks and then using kerosene transfer pumps to drain the fuel into kerosene tanks on the deck for storage. This system does not consider the low-temperature condensation and endothermic phase changes of the medium during the draining and handling process; therefore, it is only suitable for media that are chemically stable at room temperature. Furthermore, storing residual fuel on a recovery vessel for extended periods inevitably increases maintenance costs. Summary of the Invention

[0005] To address the aforementioned problems, this invention provides a system for the release and safe disposal of residual liquid oxygen from rockets after landing on a spacecraft. This system ensures the rapid release and safe disposal of residual liquid oxygen from the rocket's propellant tanks, thereby guaranteeing a smooth and safe return to port after landing.

[0006] To achieve the above objectives, the technical solution of the present invention provides a system for the release and safe handling of residual liquid oxygen oxidizer from a marine recovery rocket. The system is installed on a marine recovery vessel, and an automatic filling and releasing connector is provided on the landing deck. The automatic filling and releasing connector can be moved to the landing deck to automatically connect with the filling port and the releasing port of the liquid oxygen storage tank in the rocket body. The automatic filling and releasing connector is connected to a nitrogen purging system and a liquid oxygen release treatment system through two hoses respectively.

[0007] The nitrogen purging system includes a high-pressure nitrogen cylinder group. The high-pressure nitrogen cylinder group is connected to the automatic filling and releasing connector by a nitrogen purging first pressure reducing valve group and an automatic nitrogen purging hose retraction device. The high-pressure nitrogen cylinder group is connected to a liquid oxygen buffer tank through a nitrogen purging second pressure reducing valve group. The high-pressure nitrogen cylinder group is connected to a dilution electric remote control valve through a nitrogen dilution pressure reducing valve group. The liquid oxygen leakage treatment system includes an automatic retraction device for a liquid oxygen stainless steel cryogenic hose connected between the automatic retraction device for the nitrogen purging hose and the liquid oxygen buffer tank. A liquid oxygen discharge pump set and a vaporizer are connected between the liquid oxygen buffer tank and the dilution electric remote control valve.

[0008] Preferably, the marine recovery vessel is equipped with a central control system, which can remotely operate the nitrogen purging system and the liquid oxygen leakage treatment system.

[0009] Preferably, the dilution injection unit has two air inlet ports, one connected to an oxygen treatment pipeline and the other connected to a nitrogen pipeline; the dilution injection unit is equipped with an oxygen concentration meter.

[0010] Preferably, a pressurization electric remote control valve is provided on the purge pipeline from the high-pressure nitrogen cylinder group to the automatic filling and releasing connector; a first discharge electric remote control valve is provided on the pipeline from the automatic filling and releasing connector to the liquid oxygen buffer tank; a purge electric remote control valve is provided on the purge port from the high-pressure nitrogen cylinder group to the liquid oxygen buffer tank; a second discharge electric remote control valve is provided on the treatment pipeline from the liquid oxygen buffer tank vent to the liquid oxygen discharge pump group; and a dilution electric remote control valve is provided on the pipeline from the high-pressure nitrogen cylinder group to the dilution injection unit; each electric remote control valve is controlled by the central control system.

[0011] Preferably, the automatic filling and releasing connector includes a pipe support arm for supporting and guiding the connecting hose, a follow-up settling filling and releasing connector that can automatically adjust with the position of the liquid oxygen storage tank of the rocket body, a laser radar positioning module for accurately locating the position of the rocket body, a control monitoring and external connection module responsible for monitoring the status of the connector and communicating with the central control system, and a moving mechanism for flexibly moving to a designated position.

[0012] Preferably, the automatic filling and emptying connector is located on the aft treatment deck and can be used to pull the liquid oxygen stainless steel cryogenic hose and nitrogen purging hose to the location of the rocket body via the moving mechanism.

[0013] Preferably, a first electric flow regulating valve is provided on the pipeline from the automatic filling and releasing connector to the filling port of the liquid oxygen buffer tank; a second electric flow regulating valve is provided on the output pipeline of the liquid oxygen discharge pump group; each electric flow regulating valve is controlled by the central control system.

[0014] Preferably, the liquid oxygen discharge pump set consists of two discharge pumps and valve accessories connected in parallel, and the discharge pumps have automatic start-stop and switching functions.

[0015] Preferably, the purge electric remote control valve can be opened first to inertify and purge the liquid oxygen buffer tank, and then the second discharge electric remote control valve can be opened. The liquid oxygen discharge pump group will pump the liquid oxygen in the liquid oxygen buffer tank to the vaporizer for vaporization. The vaporized oxygen enters the dilution injection unit, and the dilution electric remote control valve is opened. The pure oxygen gas is mixed and diluted with nitrogen and discharged into the atmosphere from a safe position on the deck in the form of a high jet.

[0016] Preferably, the system includes the landing deck, the blast wall, the post-processing deck, and the deck, with the rocket stage landing on the landing deck.

[0017] The advantages of this invention are: 1) The remaining liquid oxygen inside the rocket body can be quickly discharged and safely disposed of through this system, thereby maximizing the safety of the rocket body and the recovery ship.

[0018] 2) The liquid oxygen is vaporized and diluted before being discharged, thus avoiding the potential risks and costs associated with storing and transporting low-temperature hazardous chemicals.

[0019] 3) The entire process of handling the leakage of residual oxidizer and liquid oxygen adopts an electric remote control design, which can realize unattended remote control operation and avoid the risk of personnel being harmed by deflagration caused by the leakage of low temperature medium and liquid oxygen. Attached Figure Description

[0020] Figure 1 This is a system diagram of a system for the safe handling and discharge of residual liquid oxygen from a rocket recovered at sea, according to the present invention. Figure 2 This is a top view schematic diagram of a marine recovery vessel in a marine recovery system for the release and safe handling of residual oxidizer liquid oxygen from a rocket, as described in this invention. Figure 3 For the present invention Figure 2 Side view; Figure 4 This is a system control diagram of a system for the safe handling and leakage of residual liquid oxygen from a marine rocket, as described in this invention.

[0021] Reference numerals: 1. Landing deck; 2. Blast barrier; 3. Reprocessing deck; 4. Deck; 5. Liquid oxygen storage tank for rocket body; 6. Automatic filling and releasing connector; 7. High-pressure nitrogen cylinder assembly; 8. First pressure reducing valve assembly for nitrogen purging; 9. Liquid oxygen buffer tank; 10. Second pressure reducing valve assembly for nitrogen purging; 11. Liquid oxygen discharge pump assembly; 12. Vaporizer; 13. Nitrogen dilution pressure reducing valve assembly; 14. Dilution injection unit; 15. Pressurization electric remote control valve; 16. First venting electric remote control valve; 17. Purge electric remote control valve; 18. Second venting electric remote control valve; 19. Dilution electric remote control valve; 20. First electric flow regulating valve; 21. Second electric flow regulating valve; 22. Liquid oxygen stainless steel cryogenic hose; 23. Nitrogen purging hose; 24. Automatic retraction device for liquid oxygen stainless steel cryogenic hose; 25. Automatic retraction device for nitrogen purging hose. Detailed Implementation

[0022] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0023] This invention discloses a system for the release and safe handling of residual liquid oxygen from a marine recovery rocket. The system is installed on a marine recovery vessel and includes a landing deck 1, a post-processing deck 3, a deck 4, and related processing equipment.

[0024] The landing deck 1 is surrounded by a blast wall 2, whose main function is to prevent accidental explosions from damaging the surrounding area during rocket landing. The landing deck 1 is connected to the reprocessing decks 3 and 4. The venting and treatment system is mainly located on the reprocessing decks 3 and 4, used to treat the residual liquid oxygen after the rocket stage lands on the landing deck 1. The landing deck 1 is equipped with an automatic filling and venting connector 6, which can move freely on the landing deck 1. One end of its pipe support arm automatically connects to the filling port and venting port of the liquid oxygen storage tank 5 in the rocket body, and the other end connects to the nitrogen purging system and the liquid oxygen venting and treatment system via hoses.

[0025] The automatic filling and draining connector 6 includes a pipe support arm, a follow-up settling filling and draining connector, a lidar positioning module, a control monitoring and external connection module, and a moving mechanism. Before the rocket body lands safely, the automatic filling and draining connector 6 is positioned on the aft processing deck 3, and the moving mechanism pulls the liquid oxygen stainless steel cryogenic hose 22 and the nitrogen purging hose 23 to the location of the rocket body. The pipe support arm, carrying the follow-up settling filling and draining connector, automatically docks with the filling port and venting port of the liquid oxygen storage tank 5 on the rocket body, completing the connection with the liquid oxygen storage tank, the liquid oxygen venting treatment system, and the nitrogen purging system. One end of the liquid oxygen stainless steel cryogenic hose 22 is connected to the venting port of the automatic filling and draining connector 6, and the other end is connected in sequence to the liquid oxygen buffer tank 9, the liquid oxygen discharge pump group 11, the vaporizer 12, and the mixing and dilution injection unit 14. On the automatic filling and emptying connector 6, the liquid oxygen stainless steel cryogenic hose 22 and the nitrogen purging hose 23 are connected to the control monitoring and external connection module of the automatic filling and emptying connector 6. The automatic filling and emptying connector 6 can pull the liquid oxygen stainless steel cryogenic hose 22 and the nitrogen purging hose 23 to move on the landing deck 1 and automatically complete the docking with the filling port and the emptying port of the rocket body liquid oxygen storage tank 5.

[0026] The nitrogen purging system components are located on the aft treatment deck 3, including an automatic nitrogen purging hose retraction device 25, an automatic liquid oxygen stainless steel cryogenic hose retraction device 24, a first nitrogen purging pressure reducing valve assembly 8, a second nitrogen purging pressure reducing valve assembly 10, a nitrogen dilution pressure reducing valve assembly 13, and a high-pressure nitrogen cylinder assembly 7. The nitrogen purging system is equipped with the high-pressure nitrogen cylinder assembly 7, pressure reducing valve assemblies, and electrically controlled valves, which are connected to the filling port of the automatic filling / removing connector 6 and the liquid oxygen leakage treatment system via pipelines. The nitrogen purging system has three pressure reducing valve assemblies. One end of each of the three valve assemblies is connected to the high-pressure nitrogen cylinder assembly 7. The other end of the first nitrogen purging pressure reducing valve assembly 8 is sequentially connected to the automatic nitrogen purging hose retraction device 25, the automatic filling / removing connector 6, and the rocket body liquid oxygen storage tank 5. The other end of the second nitrogen purging pressure reducing valve assembly 10 is connected to the liquid oxygen buffer tank 9. The other end of the nitrogen dilution pressure reducing valve assembly 13 is connected to the dilution injection unit 14. The liquid oxygen leak handling system includes an automatic liquid oxygen stainless steel cryogenic hose retraction device 24. One end of the hose is connected sequentially to the automatic filling / leaking connector 6 and the liquid oxygen storage tank 5 of the rocket body, while the other end is connected sequentially to the liquid oxygen buffer tank 9, the liquid oxygen discharge pump set 11, the vaporizer 12, and the dilution injection unit 14. The dilution injection unit 14 has two air inlet ports, one connected to the oxygen treatment pipeline and the other connected to the nitrogen pipeline. The dilution injection unit 14 is equipped with an oxygen concentration meter.

[0027] The marine recovery vessel is equipped with a central control system, which can remotely operate the nitrogen purging system and the liquid oxygen venting system. A pressurization electric remote control valve 15 is installed on the purging pipeline from the high-pressure nitrogen cylinder group 7 to the automatic filling / refilling connector 6; a first venting electric remote control valve 16 is installed on the pipeline from the automatic filling / refilling connector 6 to the liquid oxygen filling port of the liquid oxygen buffer tank 9; a purging electric remote control valve 17 is installed at the purging port of the high-pressure nitrogen cylinder group 7 to the liquid oxygen buffer tank 9; a second venting electric remote control valve 18 is installed on the treatment pipeline from the vent of the liquid oxygen buffer tank 9 to the liquid oxygen discharge pump group 11; and a dilution electric remote control valve 19 is installed on the pipeline from the high-pressure nitrogen cylinder group 7 to the dilution injection unit 14. All electric remote control valves are controlled by the central control system. A first electric flow regulating valve 20 is installed on the pipeline from the automatic filling / refilling connector 6 to the filling port of the liquid oxygen buffer tank 9; and a second electric flow regulating valve 21 is installed on the output pipeline of the liquid oxygen discharge pump group 11. All electric flow regulating valves are controlled by the central control system. The liquid oxygen discharge pump set 11 consists of two discharge pumps and valve accessories connected in parallel. The discharge pumps have automatic start-stop and switching functions.

[0028] A first discharge electric remote control valve 16 is installed on the liquid oxygen stainless steel cryogenic hose 22 connecting to the vent of the liquid oxygen storage tank 5 on the rocket body, and a pressurization electric remote control valve 15 is installed on the nitrogen purging line. During operation, the pressurization electric remote control valve 15 is first opened to pressurize the liquid oxygen storage tank, forcing liquid oxygen out of the tank. Then, the first discharge electric remote control valve 16 is opened, and the liquid oxygen is discharged into the liquid oxygen buffer tank 9 via the liquid oxygen stainless steel cryogenic hose 22. A purging electric remote control valve 17 is installed on the nitrogen purging line to the liquid oxygen buffer tank 9, and a second discharge electric remote control valve 18 is installed at the inlet of the liquid oxygen discharge pump group 11. The purging electric remote control valve 17 is first opened to inertify the liquid oxygen buffer tank 9, and then the second discharge electric remote control valve 18 is opened, allowing the liquid oxygen in the liquid oxygen buffer tank 9 to be pumped by the liquid oxygen discharge pump group 11 to the vaporizer 12 for vaporization. The vaporized oxygen then enters the dilution injection unit 14. The dilution electric remote control valve 19 is opened, and pure oxygen gas is mixed and diluted with nitrogen gas and discharged into the atmosphere from a safe position on deck 4 in the form of a high jet. The oxygen concentration detector of the dilution injection unit 14 can be linked with the second electric flow regulating valve 21 to control the rate of liquid oxygen leakage.

[0029] After the rocket successfully lands on landing deck 1, the automatic venting connector 6 enters landing deck 1 from the post-processing deck 3 through the blast wall 2. The lidar positioning module on the device scans and captures the location of the rocket. The device pulls the liquid oxygen stainless steel cryogenic hose 22 and nitrogen purging hose 23 connected to the device to the landing position of the rocket. The pipeline support arm, carrying the follow-up settling venting connector, extends upward to the height of the liquid oxygen tank. The venting connector completes the docking between interfaces through radar positioning. After docking, the pressurization electric remote control valve 15 is opened remotely to add nitrogen to the tank for pressurization, thereby expelling the remaining liquid oxygen in the tank. The first venting electric remote control valve 16 is opened remotely and the first electric flow regulating valve 20 is adjusted to a small opening. The venting pipeline is pre-cooled with a small flow rate first. After completion, the first electric flow regulating valve 20 is adjusted to a large opening for rapid venting of liquid oxygen.

[0030] Subsequently, the purge electric remote control valve 17 is remotely opened to purge and pressurize the liquid oxygen buffer tank 9 with nitrogen. Then, the second discharge electric remote control valve 18 is remotely opened, and liquid oxygen is discharged by the liquid oxygen discharge pump unit 11. After the remaining liquid oxygen in the rocket body tank has been completely discharged, the first discharge electric remote control valve 16 and the pressurization electric remote control valve 15 are closed sequentially by remote control. After the liquid oxygen in the liquid oxygen buffer tank 9 has been completely processed, the second discharge electric remote control valve 18 and the purge electric remote control valve 17 are closed sequentially by remote control. The vaporizer 12 completely vaporizes the liquid oxygen in the discharge pipeline, which then enters the dilution injection unit 14, mixes with nitrogen, and is discharged into the atmosphere in the form of a high jet. After completing the liquid oxygen discharge process and performing nitrogen inerting purging on the relevant systems, the remote control valves and discharge pumps of the processing system are closed.

[0031] Liquid oxygen buffer tank 9, liquid oxygen discharge pump set 11, vaporizer 12, and dilution injection unit 14 are arranged on deck 4. These devices work together to ensure the safe release and treatment of liquid oxygen. The entire system is controlled by a central control system, enabling efficient and safe treatment of residual liquid oxygen from recovered rockets at sea.

[0032] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. 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 system for the release and safe handling of residual liquid oxygen from marine-recovered rockets, characterized in that, Located on a sea recovery vessel, an automatic filling and emptying connector (6) is provided on the landing deck (1). The automatic filling and emptying connector (6) can be moved to the landing deck (1) to automatically connect with the filling port and the emptying port of the liquid oxygen storage tank (5) of the rocket body. The automatic filling and emptying connector (6) is connected to a nitrogen purging system and a liquid oxygen leakage treatment system through two hoses respectively. The nitrogen purging system includes a high-pressure nitrogen cylinder group (7), and a nitrogen purging first pressure reducing valve group (8) and a nitrogen purging hose automatic retraction device (25) are connected between the high-pressure nitrogen cylinder group (7) and the automatic filling and releasing connector (6). The high-pressure nitrogen cylinder group (7) is connected to a liquid oxygen buffer tank (9) through a nitrogen purging second pressure reducing valve group (10). The high-pressure nitrogen cylinder group (7) is connected to a dilution electric remote control valve (19) through a nitrogen dilution pressure reducing valve group (13). The liquid oxygen leakage treatment system includes an automatic retraction device (24) for liquid oxygen stainless steel cryogenic hose connected between the nitrogen purging hose automatic retraction device (25) and the liquid oxygen buffer tank (9). The liquid oxygen buffer tank (9) is connected to the dilution electric remote control valve (19) by a liquid oxygen discharge pump group (11) and a vaporizer (12).

2. The system for releasing and safely handling residual liquid oxygen from a marine-recovered rocket, as described in claim 1, is characterized in that... The marine recovery vessel is equipped with a central control system, which can remotely operate the nitrogen purging system and the liquid oxygen leakage treatment system.

3. The system for releasing and safely handling residual liquid oxygen from a marine-recovered rocket, as described in claim 2, is characterized in that... The dilution injection unit (14) has two air inlets, one connected to the oxygen treatment pipeline and the other connected to the nitrogen pipeline; the dilution injection unit (14) is equipped with an oxygen concentration meter.

4. The system for releasing and safely handling residual liquid oxygen from a marine-recovered rocket, as described in claim 3, is characterized in that... A pressurization electric remote control valve (15) is provided on the purging pipeline from the high-pressure nitrogen cylinder group (7) to the automatic filling and releasing connector (6); a first discharge electric remote control valve (16) is provided on the pipeline from the automatic filling and releasing connector (6) to the liquid oxygen buffer tank (9); a purging electric remote control valve (17) is provided on the purging port from the high-pressure nitrogen cylinder group (7) to the liquid oxygen buffer tank (9); a second discharge electric remote control valve (18) is provided on the processing pipeline from the discharge port of the liquid oxygen buffer tank (9) to the liquid oxygen discharge pump group (11); a dilution electric remote control valve (19) is provided on the pipeline from the high-pressure nitrogen cylinder group (7) to the dilution injection unit (14); each electric remote control valve is controlled by the central control system.

5. The system for the release and safe handling of residual liquid oxygen from marine-recovered rockets according to claim 4, characterized in that, The automatic filling and draining connector (6) includes a pipe support arm for supporting and guiding the connecting hose, a follow-up settling filling and draining connector that can automatically adjust with the position of the liquid oxygen storage tank (5) of the rocket body, a laser radar positioning module for accurately locating the position of the rocket body, a control monitoring and external connection module responsible for monitoring the status of the connector and communicating with the central control system, and a moving mechanism for flexibly moving to a designated position.

6. The system for releasing and safely handling residual liquid oxygen from a marine-recovered rocket, as described in claim 5, is characterized in that... The automatic filling and emptying connector (6) is located on the post-processing deck (3) and can be used to pull the liquid oxygen stainless steel cryogenic hose (22) and nitrogen purging hose (23) to the location of the rocket body via the moving mechanism.

7. The system for releasing and safely handling residual liquid oxygen from a marine-recovered rocket, as described in claim 6, is characterized in that... A first electric flow regulating valve (20) is provided on the pipeline from the automatic filling connector (6) to the filling port of the liquid oxygen buffer tank (9); a second electric flow regulating valve (21) is provided on the output pipeline of the liquid oxygen discharge pump group (11); each electric flow regulating valve is controlled by the central control system.

8. The system for the release and safe handling of residual liquid oxygen from marine-recovered rockets according to claim 7, characterized in that, The liquid oxygen discharge pump set (11) consists of two discharge pumps and valve accessories connected in parallel, and the discharge pumps have automatic start-stop and switching functions.

9. A system for the release and safe handling of residual liquid oxygen from a marine-recovered rocket, as described in claim 8, is characterized in that... First, the purge electric remote control valve (17) can be opened to inertize the liquid oxygen buffer tank (9). Then, the second discharge electric remote control valve (18) can be opened, and the liquid oxygen in the liquid oxygen buffer tank (9) can be pumped to the vaporizer (12) by the liquid oxygen discharge pump group (11) for vaporization. The vaporized oxygen enters the dilution injection unit (14), and the dilution electric remote control valve (19) is opened. The pure oxygen gas is mixed and diluted with nitrogen and discharged into the atmosphere from a safe position on the deck (4) in the form of a high jet.

10. A system for the release and safe handling of residual liquid oxygen from a marine-recovered rocket, as described in claim 8, is characterized in that... The rocket stage includes the landing deck (1), the blast wall (2), the reprocessing deck (3), and the deck (4), and lands on the landing deck (1).

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