Liquid nitrogen vaporization pressurization system and liquid rocket

Abstract

The embodiment of the invention provides a liquid nitrogen vaporization pressurization system and a liquid rocket. The liquid nitrogen vaporization pressurization system comprises a liquid oxygen tank, a fuel tank, a liquid nitrogen tank, a liquid nitrogen pump, a cavitation pipe and a warmer assembly. The liquid oxygen tank is used for storing liquid oxygen, the fuel tank is used for storing fuel, the liquid nitrogen tank is used for storing liquid nitrogen, the liquid nitrogen tank is arranged in the liquid oxygen tank, the fuel tank is arranged on the side, close to an engine, of the liquid oxygen tank, the liquid nitrogen pump is used for increasing the output pressure of the liquid nitrogen, the cavitation pipe is used for stabilizing the flow of the liquid nitrogen, and the heater assembly is used for vaporizing and heating the liquid nitrogen into high-temperature nitrogen. A liquid nitrogen conveying pipe is arranged at the bottom of the liquid nitrogen tank, the liquid nitrogen pump is arranged on the liquid nitrogen conveying pipe, the end, away from the liquid nitrogen pump, of the liquid nitrogen conveying pipe is connected with an inlet of the warmer assembly, and the liquid oxygen tank air pillow, the fuel tank air pillow and the liquid nitrogen tank air pillow are connected with an outlet of the warmer assembly through pipelines. According to the liquid nitrogen vaporization pressurization system and the liquid rocket provided by the embodiment of the invention, the cost and weight of the pressurization system can be effectively reduced.

Description

Technical Field

[0001] The present invention relates to the field of rocket technology, in particular to a liquid nitrogen vaporization and pressurization system and a liquid rocket. Background Art

[0002] The new generation of launch vehicles is mainly developed for deep space probes and uses a new power system. The new power system uses non-toxic and non-polluting propellants to replace conventional toxic and polluting propellants. Due to the high reliability requirements for the launch of deep space probes, the reliability requirements for the new generation of launch vehicles are higher than those for conventional launch vehicles. The booster delivery system is an important system of the launch vehicle and directly affects the flight reliability of the launch vehicle. Therefore, when designing the booster delivery system of the new generation of launch vehicles, high reliability should be the primary consideration.

[0003] The selection of boosting schemes for launch vehicles at home and abroad mainly considers improving boosting efficiency, system simplicity and reliability, and taking into account factors such as technical capabilities. At present, the mainstream cryogenic engines mainly use a combination of liquid oxygen / kerosene propellants. The commonly used boosting schemes mainly consist of four boosting schemes: autogenous boosting, room temperature helium boosting, room temperature helium boosting, and cold helium boosting. For liquid oxygen / kerosene engines, the kerosene tank mainly uses a room temperature helium boosting scheme.

[0004] In the process of implementing the present invention, the inventors found that there are at least the following problems in the prior art:

[0005] Normal temperature helium heating and pressurization requires independent pressurized gas source storage devices such as high-pressure gas cylinders, as well as supporting pipelines and valves. The system composition is relatively complex and the cost is high. For large and heavy launch vehicles, especially for low-temperature rocket tank pressurization, the required gas volume is large and the number of gas storage devices is large. At the same time, the gas cylinder cools down during the deflation process, the density increases, and the residual pressure of the gas cylinder is high, resulting in a helium utilization rate of less than 70% for normal temperature helium heating and pressurization. At the same time, helium is very expensive, so for large rockets, the cost of normal temperature helium heating and pressurization is relatively high.

[0006] By explaining and comparing the above-mentioned pressurization methods, it can be seen that the kerosene in the kerosene tanks of large launch vehicles has a high boiling point and is not easy to pressurize. The pressurization cost of the kerosene tanks is high and the pressurization system is heavy. Therefore, it is urgently needed and of great significance to carry out engineering application research on low-cost and lightweight pressurization systems based on kerosene tanks. Summary of the invention

[0007] In view of this, the purpose of the embodiments of the present invention is to provide a liquid nitrogen vaporization pressurization system and a liquid rocket to improve the problems existing in the prior art such as high pressurization cost and heavy weight of the pressurization system.

[0008] In the first aspect, an embodiment of the present invention provides a liquid nitrogen vaporization and pressurization system for a liquid rocket, comprising a liquid oxygen tank, a fuel tank, a liquid nitrogen tank, a liquid nitrogen pump cavitation tube and a heater assembly; the liquid oxygen tank is used to store liquid oxygen, the fuel tank is used to store fuel, the liquid nitrogen tank is used to store liquid nitrogen, the liquid nitrogen tank is arranged in the liquid oxygen tank, the fuel tank is arranged on the side of the liquid oxygen tank close to the engine, the liquid nitrogen pump is used to increase the output pressure of the liquid nitrogen, the cavitation tube is used to stabilize the liquid nitrogen flow rate, and the heater assembly is used to heat the liquid nitrogen into high-temperature nitrogen; a liquid nitrogen delivery pipe is provided at the bottom of the liquid nitrogen tank, the liquid nitrogen pump is arranged on the liquid nitrogen delivery pipe, the end of the liquid nitrogen delivery pipe away from the liquid nitrogen pump is connected to the inlet of the heater assembly, and the liquid oxygen tank air pillow, the fuel tank air pillow and the liquid nitrogen tank air pillow are respectively connected to the outlet of the heater assembly through pipelines.

[0009] Furthermore, the liquid nitrogen vaporization and boosting system also includes a main boosting pipeline, a liquid nitrogen tank boosting pipe and a fuel tank boosting pipe; the liquid oxygen tank air pillow is connected to the heater assembly through the main boosting pipeline; one end of the liquid nitrogen tank boosting pipe is connected to the liquid nitrogen tank air pillow, and the other end is connected to the main boosting pipeline; one end of the fuel tank boosting pipe is connected to the fuel tank air pillow, and the other end is connected to the main boosting pipeline between the liquid nitrogen tank boosting pipe and the heater assembly.

[0010] Furthermore, the liquid nitrogen vaporization and pressurization system also includes an integrated purge and pressurization component, which includes a main pipeline and multiple branch pipelines, wherein one end of the main pipeline close to the engine is used to be connected to a ground nitrogen source, and the inlet of each branch pipeline is respectively connected to the main pipeline, and the outlet of the first branch pipeline is connected to the liquid oxygen discharge pipeline of the engine to provide an air seal for the liquid oxygen discharge pipeline; the outlet of the second branch pipeline is connected to the tail end cabin section purge pipe to purge the cabin for the first-stage tail end cabin; the outlet of the third branch pipeline is connected to the inter-box section purge pipe to purge the cabin for the inter-box section; the outlet of the fourth branch pipeline is connected to the liquid nitrogen tank pressurization pipe to pressurize the liquid nitrogen tank; the outlet of the fifth branch pipeline is connected to the exhaust pipeline of the liquid oxygen tank to provide an air seal for the exhaust pipeline of the liquid oxygen tank; the outlet of the sixth branch pipeline is connected to the inter-stage section purge pipe to purge the cabin for the inter-stage section.

[0011] Furthermore, the liquid nitrogen vaporization and pressurization system also includes a first liquid nitrogen filling and precooling component, which includes a first liquid nitrogen filling and precooling pipeline and a liquid nitrogen stop valve, and the liquid nitrogen stop valve is arranged on the first liquid nitrogen filling and precooling pipeline. One end of the first liquid nitrogen filling and precooling pipeline is connected to the pipeline between the liquid nitrogen pump and the heater assembly, and the other end is used to be detachably connected to the liquid nitrogen filling system and the first liquid nitrogen discharge stop valve respectively.

[0012] Furthermore, the liquid nitrogen vaporization and pressurization system further includes a liquid oxygen tank pressure-compensating assembly, a fuel tank pressure-compensating assembly, and a first pre-fire pressurization assembly;

[0013] The liquid oxygen tank pressure-compensating assembly comprises a liquid oxygen tank pressure-compensating pipeline, one end of which is connected to the liquid oxygen tank pressure-compensating helium bottle, and the other end is connected to the main boosting pipeline; a liquid oxygen tank pressure-compensating solenoid valve and a liquid oxygen tank pressure-compensating orifice plate are sequentially arranged on the liquid oxygen tank pressure-compensating pipeline from the liquid oxygen tank pressure-compensating helium bottle to the main boosting pipeline;

[0014] The fuel tank pressure boosting assembly comprises a fuel tank pressure boosting pipeline, one end of which is connected to the fuel tank pressure boosting helium bottle, and the other end is connected to the fuel tank pressure boosting pipe; the fuel tank pressure boosting pipeline is provided with a fuel tank pressure boosting solenoid valve and a fuel tank pressure boosting orifice plate in sequence from the fuel tank pressure boosting helium bottle to the fuel tank pressure boosting pipe;

[0015] One end of the first pre-shot boost assembly is connected to the main boost pipeline between the liquid nitrogen box boost pipe and the heater assembly, and the other end is used for detachable connection with a ground helium source; the first pre-shot boost assembly includes a first pre-shot boost one-way valve and a first pre-shot boost solenoid valve which are sequentially arranged from the main boost pipeline to the ground helium source.

[0016] Furthermore, the liquid nitrogen vaporization and pressurization system further comprises a main pressurization pipeline, a liquid nitrogen tank pressurization pipe and a fuel tank pressurization pipe; the liquid nitrogen pump comprises a first liquid nitrogen pump and a second liquid nitrogen pump connected in parallel, and the heater assembly comprises a first heater assembly and a second heater assembly;

[0017] The first liquid nitrogen pump is connected to one end of the main boost pipeline through the first heater assembly, and the other end of the main boost pipeline is connected to the liquid oxygen tank air pillow; the second liquid nitrogen pump is connected to one end of the fuel tank boost pipe through the second heater assembly, and the other end of the fuel tank boost pipe is connected to the fuel tank air pillow; one end of the liquid nitrogen tank boost pipe is connected to the liquid nitrogen tank air pillow, and the other end is connected to the main boost pipeline;

[0018] Furthermore, the liquid nitrogen vaporization and pressurization system also includes a second liquid nitrogen filling and precooling component, which includes a second liquid nitrogen filling and precooling pipeline, a pipeline one-way valve and a second liquid nitrogen discharge stop valve, the pipeline one-way valve is arranged on the second liquid nitrogen filling and precooling pipeline, one end of the second liquid nitrogen filling and precooling pipeline is connected to the pipeline between the liquid nitrogen pump and the liquid nitrogen tank, and the other end is used for detachable connection with the liquid nitrogen filling system; the second liquid nitrogen discharge stop valve is connected to the outlet ends of the two liquid nitrogen pumps through pipelines.

[0019] Furthermore, the liquid nitrogen vaporization and pressurization system also includes a second pre-shot boosting assembly and a third pre-shot boosting assembly, one end of the second pre-shot boosting assembly is connected to the main boosting pipeline between the liquid nitrogen tank boosting pipe and the first heater assembly, and the other end is used for detachable connection to a ground helium source; one end of the third pre-shot boosting assembly is connected to the fuel tank boosting pipe, and the other end is used for detachable connection to the ground helium source.

[0020] Furthermore, the gas generators of at least two engines are redundantly connected in parallel and are used together to provide high-temperature gas for the liquid nitrogen pump, and the high-temperature gas is the driving force of the liquid nitrogen pump.

[0021] In a second aspect, an embodiment of the present invention provides a liquid rocket, comprising the liquid nitrogen vaporization and pressurization system as described above.

[0022] The above technical solution has the following beneficial effects: the liquid nitrogen vaporization and pressurization system provided by the present application stores the pressurization medium nitrogen in the form of liquid, and heats the liquid nitrogen to vaporize it into nitrogen when the rocket is pressurized, and is used to pressurize the liquid oxygen tank, fuel tank and liquid nitrogen tank at the same time. Compared with the method of heating and pressurizing helium at room temperature, the consumption of helium resources is reduced, and its cost is significantly reduced. The liquid nitrogen vaporization and pressurization system of the present application stores the pressurization medium nitrogen in the form of liquid, and the utilization rate of the pressurization medium is significantly improved compared with the helium pressurization method. At the same time, the liquid nitrogen box is immersed in the liquid oxygen box, and the buoyancy of liquid oxygen is used to reduce the fixed mechanical load of the liquid nitrogen box. The liquid nitrogen vaporization and pressurization system of the present application is lighter than the normal temperature helium heating and pressurization system, which improves the carrying capacity of liquid rockets. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. 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 creative work.

[0024] Figure 1 It is a schematic diagram of the overall structure of a liquid nitrogen vaporization and pressurization system according to an embodiment of the present application.

[0025] Figure 2 yes Figure 1 Schematic diagram of the partial structure of the liquid nitrogen vaporization and pressurization system.

[0026] Figure 3 yes Figure 1 Schematic diagram of the structure of the liquid nitrogen pump gas drive system of the liquid nitrogen vaporization and pressurization system.

[0027] Figure 4 yes Figure 1Schematic diagram of the structure of the pressurization integrated component of the liquid nitrogen vaporization and pressurization system.

[0028] Figure 5 yes Figure 1 A schematic structural diagram of the first liquid nitrogen filling and precooling component of the liquid nitrogen vaporization and pressurization system.

[0029] Figure 6 yes Figure 1 Schematic diagram of the control logic of the liquid oxygen tank regulating one-way valve of the liquid nitrogen vaporization and pressurization system.

[0030] Figure 7 yes Figure 1 Schematic diagram of the control logic of the fuel tank regulating one-way valve of the liquid nitrogen vaporization boosting system.

[0031] Figure 8 yes Figure 1 The air pillow pressure curve of the liquid oxygen tank of the liquid nitrogen vaporization booster system.

[0032] Fig. 9 yes Figure 1 The air pillow pressure curve of the fuel tank of the liquid nitrogen vaporization booster system.

[0033] Fig.10 It is a schematic diagram of the overall structure of a liquid nitrogen vaporization and pressurization system according to another embodiment of the present application.

[0034] Fig.11 yes Figure 2 Schematic diagram of the partial structure of the liquid nitrogen vaporization and pressurization system.

[0035] Fig.12 yes Figure 2 Schematic diagram of the structure of the liquid nitrogen pump gas drive system of the liquid nitrogen vaporization and pressurization system.

[0036] Fig.13 yes Figure 2 Schematic diagram of the structure of the second liquid nitrogen filling and pre-cooling component of the liquid nitrogen vaporization and pressurization system.

[0037] Fig.14 yes Figure 2 A schematic diagram of the structures of the second pre-shot boosting component and the third pre-shot boosting component of the liquid nitrogen vaporization boosting system.

[0038] The meanings of the symbols in the accompanying drawings are as follows:

[0039] 10. Liquid oxygen tank; 11. Main boost pipeline; 12. Liquid oxygen tank regulating non-return valve; 13. Liquid oxygen tank energy dissipator; 14. Liquid oxygen tank air pillow pressure sensor; 15. Liquid oxygen tank boost controller; 16. Liquid oxygen tank overflow valve; 17. Liquid oxygen tank pressure boosting assembly; 171. Liquid oxygen tank pressure boosting helium cylinder; 172. Liquid oxygen tank pressure boosting pipeline; 173. Liquid oxygen tank pressure boosting solenoid valve; 174. Liquid oxygen tank pressure boosting orifice plate;

[0040] 20. Fuel tank; 21. Fuel tank boost pipe; 22. Fuel tank regulating one-way valve; 23. Fuel tank air pillow pressure sensor; 24. Fuel tank boost controller; 25. Fuel tank energy dissipator; 26. Fuel tank pressure boost assembly; 261. Fuel tank pressure boost pipeline; 262. Fuel tank pressure boost orifice plate; 263. Fuel tank pressure boost solenoid valve; 264. Fuel tank pressure boost helium cylinder; 27. Fuel tank overflow valve; 28. Liquid nitrogen tank exhaust pipe; 29. ​​Liquid nitrogen tank safety valve;

[0041] 30. Liquid nitrogen tank; 31. Liquid nitrogen delivery pipe; 32. Liquid nitrogen tank booster pipe; 33. Liquid nitrogen tank check valve; 34. Liquid nitrogen pump; 341. Orifice plate; 342. First liquid nitrogen pump; 343. Second liquid nitrogen pump; 35. First liquid nitrogen filling and precooling assembly; 351. First liquid nitrogen filling and precooling pipeline; 352. Liquid nitrogen stop valve; 353. Tail end plug connector; 36. Liquid nitrogen filling system; 361. Liquid nitrogen filling valve; 362. Liquid nitrogen filling check valve; 363. First liquid nitrogen discharge stop valve; 37. Liquid nitrogen tank exhaust valve; 38. Liquid nitrogen tank insurance valve; 39. Second liquid nitrogen filling and precooling assembly; 391. Second liquid nitrogen filling and precooling pipeline; 392. Pipeline check valve; 393. Second liquid nitrogen discharge stop valve;

[0042] 40. First pre-shot boost assembly; 41. First pre-shot boost check valve; 42. First pre-shot boost solenoid valve; 43. First-stage tail end plug connector;

[0043] 50. Blow-off and pressurization integrated assembly; 51. First branch pipeline; 511. Liquid oxygen discharge pipeline; 52. Second branch pipeline; 521. Tail compartment blow-off pipe; 53. Third branch pipeline; 531. Inter-tank section blow-off pipe; 54. Fourth branch pipeline; 55. Fifth branch pipeline; 551. Exhaust pipeline; 56. Sixth branch pipeline; 561. Inter-stage blow-off pipe; 57. Main pipeline; 58. Ground nitrogen source; 581. Nitrogen filter; 582. Nitrogen pressure reducing valve;

[0044] 60. Engine; 61. Heater unit; 611. Heater check valve; 612. Liquid nitrogen heater; 613. Cavitation tube; 614. Heater liquid nitrogen stop valve; 62. Liquid nitrogen stop valve control solenoid valve; 63. Control gas cylinder; 64. Gas generator; 65. Check valve;

[0045] 70. Second pre-shot boost assembly; 71. Second pre-shot boost check valve; 72. Second pre-shot boost solenoid valve;

[0046] 80. A third pre-shot boost assembly; 81. A third pre-shot boost check valve; 82. A third pre-shot boost solenoid valve;

[0047] 90. Ground helium source; 91. Filter; 92. Pressure reducer. DETAILED DESCRIPTION

[0048] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed in order to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by illustrating examples of the present invention. In the drawings and the following description, at least part of the known structures and technologies are not shown in order to avoid unnecessary ambiguity of the present invention; and, for clarity, the size of some structures may be exaggerated. In addition, the features, structures or characteristics described below may be combined in one or more embodiments in any suitable manner.

[0049] An embodiment of the present application provides a liquid rocket, which includes a first-stage rocket system, a liquid nitrogen vaporization and pressurization system in the first-stage rocket system, and also includes 9 engines 60.

[0050] like Figure 1 and Figure 2 As shown, the liquid nitrogen vaporization and pressurization system includes a liquid oxygen tank 10, a fuel tank 20, a liquid nitrogen tank 30, a liquid nitrogen pump 34, a cavitation tube 613 and a heater assembly; the liquid oxygen tank 10 is used to store liquid oxygen, the fuel tank 20 is used to store fuel, the liquid nitrogen tank 30 is used to store liquid nitrogen, the liquid nitrogen tank 30 is arranged in the liquid oxygen tank 10, the fuel tank 20 is arranged on the side of the liquid oxygen tank 10 close to the engine 60, the liquid nitrogen pump 34 is used to increase the output pressure of the liquid nitrogen, the cavitation tube 613 is used to stabilize the liquid nitrogen flow, and the heater assembly is used to vaporize and heat the liquid nitrogen into high-temperature nitrogen; a liquid nitrogen delivery pipe 31 is provided at the bottom of the liquid nitrogen tank 30, the liquid nitrogen pump 34 is arranged on the liquid nitrogen delivery pipe 31, and one end of the liquid nitrogen delivery pipe 31 away from the liquid nitrogen pump 34 is connected to the inlet of the heater assembly, and the liquid oxygen tank air pillow, the fuel tank air pillow and the liquid nitrogen tank air pillow are respectively connected to the outlet of the heater assembly through pipelines. The liquid nitrogen vaporization and pressurization system of the embodiment of the present application heats the liquid nitrogen into high-temperature nitrogen gas and then uses it to pressurize the liquid oxygen tank 10, the fuel tank 20 and the liquid nitrogen tank 30 at the same time, thereby simplifying the overall structure of the liquid nitrogen vaporization and pressurization system and significantly reducing the pressurization cost and the utilization rate of the pressurization medium compared to the helium pressurization method.

[0051] The liquid nitrogen vaporization and pressurization system of this embodiment immerses the liquid nitrogen tank 30 in the liquid oxygen tank 10, and uses the buoyancy of the liquid oxygen in the liquid oxygen tank 10 to reduce the fixed mechanical load of the liquid nitrogen tank 30. When the liquid nitrogen tank 30 is immersed in the liquid oxygen in the liquid oxygen tank 10, the liquid oxygen generates an upward buoyancy on the liquid nitrogen tank 30, which can offset the gravity and other loads on the liquid nitrogen tank 30, thereby reducing its mechanical load. As the rocket flight overload continues to increase, the benefits of the liquid nitrogen tank mechanical load conditions generated by the liquid oxygen buoyancy will become more obvious. In some embodiments, the liquid nitrogen vaporization boosting system also includes a main boosting pipeline 11, a liquid nitrogen tank boosting pipe 32 and a fuel tank boosting pipe 21; the liquid oxygen tank air pillow is connected to the heater assembly through the main boosting pipeline 11; one end of the liquid nitrogen tank boosting pipe 32 is connected to the liquid nitrogen tank air pillow, and the other end is connected to the main boosting pipeline 11; one end of the fuel tank boosting pipe 21 is connected to the fuel tank air pillow, and the other end is connected to the main boosting pipeline 11 between the liquid nitrogen tank boosting pipe 32 and the heater assembly.

[0052] Specifically, if Figure 2 and Figure 3 As shown, the heater assembly is arranged corresponding to the engine 60. In this embodiment, nine engines 60 correspond to nine groups of heater units 61, and each group of heater units 61 includes a heater liquid nitrogen stop valve 614, a cavitation tube 613, a liquid nitrogen heater 612 and a heater check valve 611 arranged in sequence on the pipeline. Each heater liquid nitrogen stop valve 614 is connected to the control gas cylinder 63 through a liquid nitrogen stop valve control solenoid valve 62. The heater check valve 611 is arranged close to the main boost pipeline 11, and the nine groups of heater units 61 are connected in parallel. A liquid oxygen tank energy dissipator 13 is provided in the liquid oxygen tank air pillow, one end of the main boost pipeline 11 is connected to the liquid oxygen tank energy dissipator 13, and a liquid oxygen tank regulating non-return valve 12 is also provided on the main boost pipeline 11 between the liquid oxygen tank energy dissipator 13 and the liquid nitrogen tank boost pipe 32. The liquid oxygen tank regulating non-return valve 12 is connected to the liquid oxygen tank air pillow pressure sensor 14 and the liquid oxygen tank boost controller 15 fixed on the outer wall of the liquid oxygen tank 10 through a pipeline. The liquid nitrogen tank boost pipe 32 is connected to the main boost pipeline 11 through a tee, and a liquid nitrogen tank non-return valve 33 is provided on the liquid nitrogen tank boost pipe 32. A fuel tank energy dissipator 25 is provided in the fuel tank air pillow, one end of the fuel tank boost pipe 21 is connected to the fuel tank energy dissipator 25, and the other end is connected to the main boost pipeline 11 through a tee. A fuel tank regulating one-way valve 22 is provided on the fuel tank boost pipe 21 , and the fuel tank regulating one-way valve 22 is connected to a fuel tank air pillow pressure sensor 23 and a fuel tank boost controller 24 fixed on the outer wall of the fuel tank 20 through a pipeline.

[0053] During the first-stage flight phase of the rocket, the liquid nitrogen in the liquid nitrogen tank 30 is divided into three paths after passing through the liquid nitrogen delivery pipe 31, the liquid nitrogen pump 34, the heater liquid nitrogen stop valve 614, the cavitation tube 613, the liquid nitrogen heater 612, the heater check valve 611 and the boost main line 57. One path enters the fuel tank boost pipe 21, and enters the fuel tank air pillow after passing through the fuel tank regulating check valve 22 and the fuel tank energy dissipator 25 to boost the fuel tank air pillow; one path enters the liquid oxygen tank air pillow through the liquid oxygen tank regulating check valve 12 and the liquid oxygen tank energy dissipator 13 to boost the liquid oxygen tank air pillow; and another path enters the liquid nitrogen tank boost pipe 32, and boosts the liquid nitrogen tank 30 through the liquid nitrogen tank check valve 33.

[0054] The liquid nitrogen vaporization and pressurization system of this embodiment sets the liquid nitrogen tank 30 in the liquid oxygen tank 10, increases the pressure of the liquid nitrogen by the liquid nitrogen pump 34, controls the flow rate by the cavitation tube 613, and heats the liquid nitrogen heater component. After the liquid nitrogen is heated to high-temperature nitrogen, it is divided into three paths, one for pressurizing the liquid oxygen tank 10, one for pressurizing the fuel tank 20, and one for pressurizing the liquid nitrogen tank 30, that is, after the liquid nitrogen is heated, the pressurization of the three tanks is realized. The liquid oxygen tank 10, the fuel tank 20 and the liquid nitrogen tank 30 all adopt the scheme of liquid nitrogen heating and pressurization. After the liquid nitrogen is heated by the liquid nitrogen heater component to form nitrogen, it is divided into three paths, one for pressurizing the liquid oxygen tank 10 by controlling the flow rate (and also controlling the flow direction) through the liquid oxygen tank regulating check valve 12, one for pressurizing the fuel tank 20 by controlling the flow rate through the fuel tank regulating check valve 22, and finally a small stream is divided into the liquid nitrogen tank 30 for pressurization. In this embodiment, the liquid oxygen tank 10 and the fuel tank 20 both adopt a closed pressurization solution, and the liquid nitrogen tank 30 adopts an open liquid nitrogen heating and pressurization solution.

[0055] like Figure 1 As shown, the liquid nitrogen box 30 of this embodiment is also provided with a liquid nitrogen box exhaust pipe 28 and two liquid nitrogen box safety valves 29. One end of the liquid nitrogen box exhaust pipe 28 is connected to the top of the liquid nitrogen box 30, and the other end is connected to the atmosphere. The two liquid nitrogen box safety valves 29 are connected to the liquid nitrogen box exhaust pipe 28 in parallel.

[0056] The liquid nitrogen box 30 of this embodiment uses two safety valves (liquid nitrogen box safety valve 29) of DN4 (opening pressure 1.5MPa) and DN20 (opening pressure 2.0MPa) for exhaust, and the technical features are as follows:

[0057] By setting a safety valve (liquid nitrogen box safety valve 29), it can ensure that the liquid nitrogen box 30 always maintains a positive pressure of about 1.5MPa, which can effectively prevent the external pressure of the liquid nitrogen box 30 from being greater than the air pillow pressure of the liquid nitrogen box 30, causing the liquid nitrogen box 30 to collapse due to negative pressure. At the same time, the air pillow pressure of the liquid nitrogen box can be controlled by opening and closing the DN4 safety valve, reducing the number of times the DN20 safety valve is opened and increasing the life of the DN20 safety valve.

[0058] Precise primary pressure relief: When the pressure in the liquid nitrogen tank 30 rises to 1.5MPa, the DN4 safety valve opens first to exhaust and relieve pressure. At this stage, the system pressure changes slowly, and the small flow exhaust of the DN4 safety valve can accurately stabilize the pressure at about 1.5MPa, preventing the pressure from continuing to rise rapidly, and providing initial pressure protection for the system.

[0059] Rapid and strong pressure relief: If the pressure continues to rise to 2.0MPa, the DN20 safety valve opens to release the exhaust pressure with a large flow rate. At this time, the DN20 safety valve can quickly reduce the pressure in the liquid nitrogen box 30, avoiding damage to the liquid nitrogen box 30 caused by excessive pressure or even causing serious accidents such as explosion, playing a key secondary protection role.

[0060] Fault backup: The two safety valves (liquid nitrogen tank safety valve 29) serve as backup for each other. When the DN4 safety valve cannot be opened normally due to a fault, the DN20 safety valve can still function when the pressure reaches 2.0MPa to relieve the pressure; when the DN4 safety valve cannot be closed normally due to a fault, the air pillow pressure of the liquid nitrogen tank changes slowly, and the pressure of the liquid nitrogen tank can also meet the design requirements. Conversely, if the DN20 safety valve cannot be opened, the DN4 safety valve can also provide certain protection at 1.5MPa, reducing the risk of safety accidents caused by valve failure.

[0061] The present embodiment only utilizes one liquid nitrogen delivery pipe 31, one liquid nitrogen pump 34, and one main boosting pipeline 11 to realize the boosting of the liquid oxygen tank 10, the fuel tank 20, and the liquid nitrogen tank 30. Compared with the three sets of boosting equipment in the traditional design, the present embodiment only requires one set of boosting equipment to complete the boosting of the three tanks, thereby reducing the number of boosting equipment used, reducing the production cost and the complexity of the structure. At the same time, the present embodiment utilizes one set of liquid nitrogen vaporization boosting system to realize the boosting of the three tanks, adopts a unified gas supply and distribution boosting technology, and greatly reduces the types and number of pre-launch boosting pipelines.

[0062] In this embodiment, the liquid nitrogen heaters 612 of the nine engines 60 are used to heat the liquid nitrogen into high-temperature nitrogen gas, and the boost flow rate of the liquid oxygen tank 10 is regulated through the liquid oxygen tank regulating one-way valve 12, the boost flow rate of the fuel tank 20 is regulated through the fuel tank regulating one-way valve 22, and the boost flow rate of the liquid nitrogen tank 30 is controlled by diverting the liquid nitrogen tank one-way valve 33.

[0063] In this embodiment, a main boosting pipeline 11 and two flow regulating check valves (liquid oxygen tank regulating check valve 12 and fuel tank regulating check valve 22) are used to respectively realize the flow control of the two tanks, and a liquid nitrogen tank check valve 33 realizes the control of the boosting flow of the liquid nitrogen tank 30. The regulating check valve of this embodiment integrates the flow regulating valve and the check valve, and the regulating check valve has the functions of boosting flow regulation and reverse sealing check valve at the same time.

[0064] During the period of filling the liquid oxygen tank 10 with liquid oxygen and the period of filling the fuel tank 20 with fuel, a one-way valve 65 is respectively provided on the main boosting pipeline 11, the liquid nitrogen tank boosting pipe 32 and the fuel tank boosting pipe 21, so as to prevent the propellant vapor from flowing back to other tanks and prevent the safety risks such as explosion caused by the mixing of kerosene vapor in the fuel tank 20 and oxygen vapor in the liquid oxygen tank 10.

[0065] like Figure 4 As shown, the liquid nitrogen vaporization and pressurization system of this embodiment also includes a blowdown and pressurization integrated assembly 50, which includes a main pipeline 57 and multiple branch pipelines. The end of the main pipeline 57 close to the engine 60 is used to connect to the ground nitrogen source 58, and the inlet of each branch pipeline is respectively connected to the main pipeline 57. The outlet of the first branch pipeline 51 is connected to the liquid oxygen discharge pipeline 511 of the engine 60 to provide a gas seal for the liquid oxygen discharge pipeline 511; the outlet of the second branch pipeline 52 is connected to the tail compartment blowdown pipe 521. The outlet of the third branch pipeline 53 is connected to the inter-tank section blowing pipe 531, which is used to blow off the cabin section for the inter-tank section; the outlet of the fourth branch pipeline 54 is connected to the liquid nitrogen tank booster pipe 32, which is used to pressurize the liquid nitrogen tank 30; the outlet of the fifth branch pipeline 55 is connected to the exhaust pipeline 551 of the liquid oxygen tank 10, which is used to provide an air seal for the exhaust pipeline 551 of the liquid oxygen tank 10; the outlet of the sixth branch pipeline 56 is connected to the inter-stage section blowing pipe 561, which is used to blow off the cabin section for the inter-stage section.

[0066] Specifically, branch orifice plates are provided on the first branch pipeline 51, the second branch pipeline 52, the third branch pipeline 53, the fourth branch pipeline 54, the fifth branch pipeline 55 and the sixth branch pipeline 56, respectively. The outlet of the first branch pipeline 51 is respectively connected to the liquid oxygen discharge pipeline 511 of the nine engines 60, and a branch check valve is provided in front of the branch orifice plate of the fourth branch pipeline 54. The outlet of the fourth branch pipeline 54 is connected to the liquid nitrogen tank booster pipe 32 behind the liquid nitrogen tank check valve 33, and the outlet of the fifth branch pipeline 55 is connected to the liquid oxygen tank exhaust gas seal interface of the exhaust pipeline 551 of the liquid oxygen tank 10. After the ground nitrogen source 58, the nitrogen filter 581 and the nitrogen pressure reducing valve 582 are connected in sequence through pipelines, they are detachably connected to the main pipeline 57 through the first-stage tail end plug connector.

[0067] This embodiment integrates the pre-launch pressurization system of the liquid nitrogen tank with the cabin blowing system of the rocket. The ground nitrogen source 58 is divided into six routes after passing through the nitrogen filter 581, the nitrogen pressure reducing valve 582 and the plug-in connector at the tail end of the first stage. The first route is through the branch orifice plate and the liquid oxygen discharge gas seal interface on the first branch pipeline 51 to provide an air seal for the liquid oxygen discharge pipeline 511 of the nine machines in parallel, to prevent water vapor from being reversely sucked into the liquid oxygen discharge pipeline 511, thereby preventing water vapor from condensing and causing blockage of the liquid oxygen discharge pipeline 511; the second route enters the tail cabin blowing pipe 521 through the branch orifice plate on the second branch pipeline 52 to blow the cabin of the first tail cabin; the third route enters the inter-tank section blowing pipe through the branch orifice plate on the third branch pipeline 53 to blow the cabin. The pipe 531 performs section purge for the inter-tank section; the fourth route enters the liquid nitrogen tank 30 through the branch one-way valve and the branch orifice plate on the fourth branch pipe 54 to pressurize the liquid nitrogen tank 30; the fifth route provides an air seal for the exhaust pipe 551 of the liquid oxygen tank 10 through the branch orifice plate and the liquid oxygen tank exhaust gas seal interface on the fifth branch pipe 55 to prevent water vapor from being reversely sucked into the exhaust pipe 551, thereby avoiding blockage of the exhaust pipe 551 of the liquid oxygen tank 10 and the liquid oxygen tank safety overflow valve 16 due to condensation of water vapor; the sixth route enters the inter-stage purge pipe 561 through the branch orifice plate on the sixth branch pipe 56 to purge the first and second inter-stage sections.

[0068] During the ground refueling and parking phase of the rocket, the cabin can be blown down to reduce the water vapor content in the cabin and reduce the impact of frost on the equipment. Blowing down the cabin can also dilute possible oxygen leakage in the cabin pipelines and slow down the temperature drop in the cabin.

[0069] An annular blow-off pipe is installed in the front bottom tank of the liquid oxygen tank and in the engine compartment to blow off the heated nitrogen in the cabin. Nitrogen heating can be done by water bath, and the water bath heat exchanger is installed at the outlet of the gas distribution table. After the cabin blow-off pipeline is heat exchanged by the heat exchanger, it is connected to the plug-in connector on the arrow. A bypass is set for the cabin blow-off pipeline passing through the heat exchanger. During the test, the heat exchange pipeline does not work, and the bypass is used for gas supply. The cabin blow-off starts 5 minutes after the liquid oxygen filling starts.

[0070] like Figure 1 and Figure 5 As shown, the liquid nitrogen vaporization and pressurization system of this embodiment also includes a first liquid nitrogen filling and precooling component 35, the first liquid nitrogen filling and precooling component 35 includes a first liquid nitrogen filling and precooling pipeline 351 and a liquid nitrogen stop valve 352, the liquid nitrogen stop valve 352 is arranged on the first liquid nitrogen filling and precooling pipeline 351, one end of the first liquid nitrogen filling and precooling pipeline 351 is connected to the pipeline between the liquid nitrogen pump 34 and the heater assembly, and the other end is used for detachable connection with the liquid nitrogen filling system 36 and the first liquid nitrogen discharge stop valve 363 respectively.

[0071] Specifically, in this embodiment, one end of the first liquid nitrogen filling precooling pipeline 351 is connected to the pipeline between the liquid nitrogen pump 34 and the heater assembly through a tee, and the other end is detachably connected to the liquid nitrogen filling system 36 through the tail plug connector 353, and a liquid nitrogen filling check valve 362 and a liquid nitrogen filling valve 361 are sequentially provided on the pipeline between the tail plug connector 353 and the liquid nitrogen filling system 36. The inlet of the first liquid nitrogen discharge stop valve 363 is connected to the pipeline between the tail plug connector 353 and the liquid nitrogen filling check valve 362 through a pipeline, and the outlet is connected to the atmosphere.

[0072] The liquid nitrogen filling system 36 delivers the liquid nitrogen to the liquid nitrogen tank 30 through the liquid nitrogen filling valve 361 , the liquid nitrogen filling check valve 362 , the tail end plug connector 353 , the liquid nitrogen stop valve 352 and the liquid nitrogen delivery pipe 31 , so as to fill the liquid nitrogen tank 30 with liquid nitrogen.

[0073] When the rocket is flying, the tail end plug connector 353 is disconnected, and the liquid nitrogen in the liquid nitrogen tank 30 can be prevented from leaking through the liquid nitrogen stop valve 352. The liquid nitrogen filling port is arranged downstream of the liquid nitrogen pump 34, and the liquid nitrogen pump 34 can be pre-cooled when the liquid nitrogen is filled, thereby improving the reliability of the pre-cooling of the liquid nitrogen pump 34.

[0074] When the liquid nitrogen pump 34 is started, it is necessary to precool the liquid nitrogen pump 34. The cryogenic coolant flows through the liquid nitrogen delivery pipe 31 and the turbine pump cavity of the liquid nitrogen pump 34, cools the liquid nitrogen delivery pipe 31 and the turbine pump body, and then is precooled and discharged from the liquid nitrogen pump body to the outside of the rocket body. This precooling method is called discharge precooling.

[0075] Due to the low temperature characteristics of liquid nitrogen, the engine 60, the liquid nitrogen delivery pipe 31 and the external environment form a high temperature heat source relative to the liquid nitrogen. After the liquid nitrogen enters the liquid nitrogen pump 34, it is heated to boil and vaporize, which will affect the blades of the liquid nitrogen pump 34 and cause cavitation of the liquid nitrogen pump 34. In order to ensure the normal operation of the liquid nitrogen pump 34, the liquid nitrogen pump 34 needs to be precooled to the same temperature as the liquid nitrogen to ensure that the liquid nitrogen will not vaporize into gas when passing through the liquid nitrogen pump 34 during normal operation.

[0076] During the discharge pre-cooling process of the ground liquid nitrogen pump 34, the liquid nitrogen in the liquid nitrogen tank 30 is directly discharged into the atmosphere through the liquid nitrogen delivery pipe 31, the liquid nitrogen pump 34, the liquid nitrogen stop valve 352, the tail end plug connector 353 and the first liquid nitrogen discharge stop valve 363, so as to ensure the reliable operation of the ignition of the liquid nitrogen pump 34 and prevent the cavitation caused by the vaporization of liquid nitrogen when the liquid nitrogen pump 34 is ignited.

[0077] When the rocket is ignited and flying, the first liquid nitrogen discharge stop valve 363 remains closed, and the liquid nitrogen after the liquid nitrogen pump 34 is heated by the heater assembly to become high-temperature nitrogen gas to pressurize the liquid oxygen tank 10 and the fuel tank 20.

[0078] The liquid nitrogen pump discharge precooling is only performed before the liquid nitrogen pump 34 works. The liquid nitrogen pump discharge precooling is not performed after the liquid nitrogen pump 34 works, so the first liquid nitrogen discharge stop valve 363 is closed.

[0079] In this embodiment, the liquid nitrogen filling system and the liquid nitrogen pump precooling system are integrated into a design, and the first liquid nitrogen filling and precooling component 35 is arranged downstream of the liquid nitrogen pump 34, so that the liquid nitrogen pump 34 can be precooled during the liquid nitrogen filling period, and the first liquid nitrogen discharge stop valve 363 is arranged on the liquid nitrogen filling pipeline, so that the first liquid nitrogen filling and precooling component 35 can realize both the function of liquid nitrogen filling and the function of liquid nitrogen discharge precooling.

[0080] like Figure 1 As shown, the liquid nitrogen vaporization and pressurization system of this embodiment further includes a liquid oxygen tank pressure supplement component 17 , a fuel tank pressure supplement component 26 and a first pre-fire pressurization component 40 .

[0081] The liquid oxygen tank pressure compensating assembly 17 includes a liquid oxygen tank pressure compensating pipeline 172, one end of the liquid oxygen tank pressure compensating pipeline 172 is connected to the liquid oxygen tank pressure compensating helium bottle 171, and the other end is connected to the main boosting pipeline 11; the liquid oxygen tank pressure compensating solenoid valve 173 and the liquid oxygen tank pressure compensating orifice plate 174 are sequentially provided on the liquid oxygen tank pressure compensating pipeline 172 from the liquid oxygen tank pressure compensating helium bottle 171 to the main boosting pipeline 11.

[0082] Specifically, the liquid oxygen tank pressure-compensating pipeline 172 is connected to the main boost pipeline 11 between the liquid oxygen tank regulating non-return valve 12 and the liquid oxygen tank energy dissipator 13 through a three-way connection. When the rocket engine 60 is ignited at time t0, the liquid oxygen tank pressure-compensating solenoid valve 173 is opened, and the helium in the liquid oxygen tank pressure-compensating helium bottle 171 compensates the liquid oxygen tank 10 through the liquid oxygen tank pressure-compensating solenoid valve 173, the liquid oxygen tank pressure-compensating orifice plate 174 and the liquid oxygen tank energy dissipator 13. When the rocket engine 60 is turned off at time t1, the liquid oxygen tank pressure-compensating solenoid valve 173 is closed.

[0083] The fuel tank pressure-compensating assembly 26 includes a fuel tank pressure-compensating pipeline 261, one end of which is connected to a fuel tank pressure-compensating helium bottle 264, and the other end is connected to a fuel tank pressure-compensating pipe 21; the fuel tank pressure-compensating pipeline 261 is provided with a fuel tank pressure-compensating solenoid valve 263 and a fuel tank pressure-compensating orifice plate 262 in sequence from the fuel tank pressure-compensating helium bottle 264 to the fuel tank pressure-compensating pipe 21.

[0084] Specifically, the fuel tank pressure-compensating pipeline 261 is connected to the fuel tank pressure-compensating pipe 21 between the fuel tank regulating non-return valve 22 and the main pressure-compensating pipeline 11. At the moment t0 when the rocket engine 60 is ignited, the fuel tank pressure-compensating solenoid valve 263 is opened, and the helium in the fuel tank pressure-compensating helium cylinder 264 compensates the fuel tank 20 through the fuel tank pressure-compensating solenoid valve 263, the fuel tank pressure-compensating orifice plate 262, the fuel tank regulating non-return valve 22 and the fuel tank energy dissipator 25.

[0085] One end of the first pre-shot boost assembly 40 is connected to the main boost pipeline 11 between the liquid nitrogen box boost pipe 32 and the heater assembly through a tee, and the other end is used for detachable connection with the ground helium source 90; the first pre-shot boost assembly 40 includes a first pre-shot boost check valve 41 and a first pre-shot boost solenoid valve 42 which are sequentially arranged from the main boost pipeline 11 to the ground helium source 90.

[0086] Specifically, in this embodiment, the first pre-shot pressurization assembly 40 is detachably connected to the ground helium source via a first-stage tail end plug connector 43 .

[0087] During the ground pre-launch pressurization, the ground helium source realizes the pre-launch pressurization of the liquid oxygen tank 10, the liquid nitrogen tank 30 and the fuel tank 20 through the ground pressurization pipeline, the first-stage tail end plug-in connector 43, the first pre-launch pressurization solenoid valve 42, the first pre-launch pressurization check valve 41 and the main pressurization pipeline 11.

[0088] The pre-fire boost flow rate of the liquid oxygen tank 10 is controlled by adjusting the one-way valve 12 of the liquid oxygen tank, and the pre-fire boost flow rate of the fuel tank 20 is controlled by adjusting the one-way valve 22 of the fuel tank. The boost flow rate of the liquid nitrogen tank 30 is controlled by adjusting the one-way valve 33 of the liquid nitrogen tank.

[0089] This embodiment adopts the unified gas supply and pressure boosting technology, and realizes the pressure boosting function of three tanks with one main pipeline 57, which reduces the types and complexity of the pressure boosting system, reduces the difficulty of rocket development and the number and cost of supporting products. At the same time, the first pre-launch pressure boosting component 40 uses the main pressure boosting pipeline 11 to perform pre-launch pressure boosting on each tank, which greatly reduces the number of pipelines used and makes the overall structure more compact and reasonable.

[0090] The liquid oxygen tank 10 of this embodiment is a first-stage liquid oxygen tank, and a liquid oxygen tank overflow valve 16 is also provided on the first-stage liquid oxygen tank. The liquid oxygen tank overflow valve 16 integrates the safety valve and the exhaust valve. When the ground oxygen tank is filled with liquid oxygen for the first-stage liquid oxygen tank, the liquid oxygen tank overflow valve 16 opens. The fuel tank 20 of this embodiment is a first-stage fuel tank, and a fuel tank overflow valve 27 is provided on the first-stage fuel tank. The fuel tank overflow valve 27 integrates the safety valve and the exhaust valve. When the ground fuel tank is filled with fuel for the first-stage fuel tank, the fuel tank overflow valve 27 opens.

[0091] During the first stage flight, when the liquid oxygen tank air pillow pressure is higher than the opening pressure of the liquid oxygen tank safety overflow valve 16, the liquid oxygen tank safety overflow valve 16 opens; when the air pillow pressure is lower than the closing pressure of the liquid oxygen tank safety overflow valve 16, the liquid oxygen tank safety overflow valve 16 closes; when the fuel tank air pillow pressure is higher than the opening pressure of the fuel tank safety overflow valve 27, the fuel tank safety overflow valve 27 opens; when the air pillow pressure is lower than the closing pressure of the fuel tank safety overflow valve 27, the fuel tank safety overflow valve 27 closes.

[0092] The liquid oxygen tank air pillow pressure is controlled by adjusting the one-way valve 12 of the liquid oxygen tank. The control logic of the one-way valve 12 of the liquid oxygen tank is as follows: Figure 6 As shown. Y1 Indicates the lower limit of the liquid oxygen tank pressure control band, P Y2 Indicates the upper limit of the liquid oxygen tank pressure control band, O Y1 Indicates the minimum opening of the liquid oxygen tank regulating check valve, O Y2 Indicates the maximum opening of the liquid oxygen tank regulating check valve.

[0093] The fuel tank air pillow pressure is controlled by the fuel tank regulating check valve 22. The control logic of the fuel tank regulating check valve 22 is as follows: Figure 7 As shown. Among them, P R1 Indicates the lower limit of the fuel tank pressure control band, P R2 Indicates the upper limit of the fuel tank pressure control band, O R1 Indicates the minimum opening of the fuel tank regulating check valve, O R2 Indicates the maximum opening of the fuel tank regulating check valve.

[0094] The air pillow pressure curve of the first-stage liquid oxygen tank is as follows: Figure 8 As shown, P Ybxfdk Indicates the opening pressure of the liquid oxygen tank overflow valve, P Ybxfgb Indicates the closing pressure of the liquid oxygen tank overflow valve, P Y0 Indicates the air pillow pressure of the liquid oxygen tank, P Ymin Indicates the minimum air pillow pressure of the liquid oxygen tank required by the engine. The air pillow pressure curve of the fuel tank 20 is as follows Fig. 9 As shown, P Rbxfdk Indicates the fuel tank overflow valve opening pressure, P Rbxfgb Indicates the closing pressure of the fuel tank overflow valve, P R0 Indicates the fuel tank air cushion pressure, P Rmin Indicates the minimum fuel tank air pressure required by the engine.

[0095] like Figure 3 As shown, the gas generators 64 of at least two engines 60 are connected in parallel and used together to provide driving force for the liquid nitrogen pump 34. For example, in this embodiment, the gas generators 64 of the two engines 60 are respectively connected to a one-way valve 65 and then connected in parallel, and then connected to the turbine of the liquid nitrogen pump 34 through a tee and an orifice plate 341. The high-temperature combustion gas generated by the two gas generators 64 passes through two one-way valves 65, is collected through a tee, and reaches the turbine of the liquid nitrogen pump 34 through the orifice plate 341, providing driving combustion gas to the turbine of the liquid nitrogen pump, and then directly discharged into the atmosphere through an exhaust pipe after driving the turbine of the liquid nitrogen pump.

[0096] By using the gas generators 64 of the two engines 60 to provide gas, the risk of shutting down the driving gas source when one of the engines 60 is shut down can be avoided, thereby improving the redundancy and reliability of the system. By using the gas generators 64 of the two engines 60 and the corresponding two one-way valves 65, driving gas can still be provided when one of the engines 60 is shut down, thereby ensuring the working reliability of the liquid nitrogen pump 34.

[0097] This embodiment utilizes the high-temperature fuel gas generated by the fuel gas generator 64 of the engine 60 to drive the liquid nitrogen pump 34, thereby ensuring the reliable operation of the liquid nitrogen pump 34. Compared with using an independent gas source to drive the liquid nitrogen pump or using a motor to drive the liquid nitrogen pump, this solution utilizes the fuel gas in the existing fuel gas generator 64 to drive the liquid nitrogen pump 34, and the system integration is high, while simplifying the driving system of the liquid nitrogen pump 34.

[0098] An orifice plate 341 is provided at the inlet of the liquid nitrogen pump 34. During the system test phase, the gas flow rate of the liquid nitrogen pump 34 can be regulated by adjusting or replacing the size of the orifice plate 341. By adjusting the size of the orifice plate 341, the gas intake flow rate of the liquid nitrogen pump 34 can be controlled, thereby achieving control of the power of the liquid nitrogen pump 34 and control of the liquid nitrogen head of the liquid nitrogen pump 34.

[0099] The liquid nitrogen vaporization and pressurization system of this embodiment stores the pressurization medium in the form of liquid, and heats and vaporizes the liquid nitrogen into nitrogen when the rocket is pressurized, and performs liquid nitrogen heating and pressurization on the liquid oxygen tank 10, the fuel tank 20, and the liquid nitrogen tank 30. Compared with the pressurization method of heating and pressurizing the liquid oxygen tank 10 and the fuel tank 20 with normal temperature helium, this solution uses a liquid nitrogen vaporization and pressurization system to reduce the use of test cold helium cylinders and expensive helium resources, and the cost of liquid nitrogen heating and pressurization is lower.

[0100] This embodiment uses liquid nitrogen for heating and pressurization, and the remaining pressurization medium is stored in liquid form. During the rocket flight, 4kg of liquid nitrogen remains, and the utilization rate reaches 99.5%. In the traditional cold helium heating and pressurization, the helium gas cools down rapidly during the degassing process. The helium in the cold helium cylinder drops from the initial 90K to 50K, and the remaining cylinder pressure is 5MPa. The density of helium at 90K and 23MPa is 90kg / m3, and the density of helium at 50K and 5MPa is 42.97kg / m 3 During the cold helium heating process, the helium utilization rate of the helium cylinder is 52%. For normal temperature helium heating and pressurization, the normal temperature helium heating and pressurization gas drops from 288K to 190K, and the cylinder pressure remains 5MPa. The density of helium at 288K and 23MPa is 34.5kg / m 3 , 190K, 5MPa helium density is 12.2kg / m 3 During the normal temperature helium heating process, the helium utilization rate of the helium cylinder is 64%.

[0101] In summary, compared with 52% helium pressurization medium utilization rate of cold helium heating and 64% helium pressurization utilization rate of room temperature helium heating, a small amount of liquid nitrogen can be left over after liquid nitrogen heating and pressurization in this embodiment. When there is remaining pressurization medium after liquid nitrogen heating and pressurization, the liquid utilization rate can be increased to 99.5%, which greatly improves the utilization rate of the pressurization medium.

[0102] Through scheme demonstration, the weight of the liquid nitrogen vaporization pressurization system of this embodiment is equivalent to that of the cold helium heating pressurization system, and is 420kg lighter than the normal temperature helium heating pressurization system, thereby improving the carrying capacity of the rocket.

[0103] The liquid nitrogen vaporization and pressurization system of this embodiment uses a liquid nitrogen pump 34 to pressurize liquid nitrogen, and the liquid nitrogen is controlled by the cavitation tube 613. The liquid nitrogen is heated by nine liquid nitrogen heaters 612 to vaporize the liquid nitrogen into high-temperature nitrogen gas, which is then divided into three paths to pressurize the liquid oxygen tank 10, the fuel tank 20 and the liquid nitrogen tank 30 respectively, which greatly simplifies the difficulty of system development and system matching.

[0104] The liquid nitrogen vaporization pressurization system of this embodiment adopts a unified gas supply and distribution technology, and uses a liquid nitrogen delivery pipe 31, a liquid nitrogen pump 34, and a main pressurization pipeline 11 to realize the pressurization control of three tanks. By adopting the unified gas supply and distribution pressurization technology, the types and number of pressurization pipelines are reduced, thereby reducing the difficulty of developing the pressurization system, the number of supporting components, and the supporting cost.

[0105] This embodiment provides high-temperature driving gas by means of the gas generators 64 of the two engines 60 and two one-way valves 65, which effectively avoids the risk of insufficient gas source caused by a failure of one of the engines 60 and improves the reliability of the liquid nitrogen vaporization and pressurization system.

[0106] In this embodiment, an orifice plate 341 is provided at the gas inlet of the liquid nitrogen pump 34. During the ground test, the size of the orifice plate 341 is adjusted to control the intake flow of the liquid nitrogen pump 34, thereby realizing the control and determination of the power of the liquid nitrogen pump 34. The size of the orifice plate 341 is determined by whether the liquid nitrogen pump 34 reaches the rated power during the test. This design reduces the difficulty of system development, design and simulation.

[0107] The liquid nitrogen vaporization and pressurization system of this embodiment utilizes the high-temperature fuel gas generated by the gas generator 64 of the engine 60 to drive the liquid nitrogen pump 34, thereby ensuring the reliable operation of the liquid nitrogen pump 34. Compared with using an independent gas source to drive the liquid nitrogen pump or using a motor to drive the liquid nitrogen pump, this solution utilizes the fuel gas in the gas generator 64 of the engine 60 to drive the liquid nitrogen pump 34, and has a high system integration, simplifies the drive system of the liquid nitrogen pump 34, and reduces the effective mass of the pressurization system.

[0108] The liquid nitrogen vaporization and pressurization system of this embodiment is provided with a one-way valve 65 at the outlet of the gas generator 64, which can effectively prevent the gas generated by a normal engine 60 from flowing out through the gas generator 64 of the damaged engine 60 when a certain engine 60 is damaged, thereby improving the risk resistance of the system.

[0109] The liquid nitrogen vaporization and pressurization system of this embodiment utilizes the liquid nitrogen heaters 612 of nine engines 60 to heat the liquid nitrogen into high-temperature nitrogen gas, and then utilizes the unified gas supply and distribution pressurization technology to realize the closed control of the pressurization flow of the liquid oxygen tank 10 through a main pressurization pipeline 11 and a liquid oxygen tank regulating non-return valve 12, realize the closed control of the pressurization flow of the fuel tank 20 through the fuel tank regulating non-return valve 22, and realize the limitation of the pressurization flow of the liquid nitrogen tank 30 through the liquid nitrogen tank non-return valve 33, thereby realizing the pressurization of the three storage tanks of the liquid oxygen tank 10, the fuel tank 20 and the liquid nitrogen tank 30 at the same time.

[0110] The liquid nitrogen vaporization and pressurization system of the present embodiment is provided with a first pre-fire boost assembly 40 on the main boost pipeline 11, which can effectively shorten the length of the pre-fire boost pipeline. At the same time, a unified gas supply and distribution boosting technology is adopted, so that the pre-fire boost pipeline and the main boost pipeline 11 are designed in an integrated manner, thereby improving the integration of the main boost pipeline 11, and the pressure control of three tanks can be achieved by using only one pre-fire boost pipeline.

[0111] The liquid nitrogen vaporization and pressurization system of this embodiment integrates the liquid nitrogen filling system and the liquid nitrogen pump precooling system into an integrated design. The liquid nitrogen filling system is arranged downstream of the liquid nitrogen pump 34, and the liquid nitrogen pump 34 can be precooled during the liquid nitrogen filling period. By arranging a liquid nitrogen discharge stop valve on the liquid nitrogen ground filling pipeline, the first liquid nitrogen filling and precooling component 35 can simultaneously meet the dual functions of liquid nitrogen filling and liquid nitrogen pump 34 precooling discharge.

[0112] The liquid nitrogen vaporization pressurization system of this embodiment is provided with a pressure boosting assembly to ensure the smooth start-up process of the rocket. The test shows that the pressure boosting assembly can better meet the start-up requirements of the engine 60. The pressure boosting assembly is relatively simple, with a single type and a small number of valves and pipelines, low difficulty in development, and a short processing and production cycle.

[0113] like Fig.10 and Fig.11 As shown, in another embodiment, the liquid nitrogen vaporization boosting system also includes a main boosting pipeline 11, a liquid nitrogen tank 30 boosting pipe and a fuel tank boosting pipe 21; the liquid nitrogen pump 34 includes a first liquid nitrogen pump 342 and a second liquid nitrogen pump 343 connected in parallel, and the heater assembly includes a first heater assembly and a second heater assembly.

[0114] The first liquid nitrogen pump 342 is connected to one end of the main boost pipeline 11 through the first heater assembly, and the other end of the main boost pipeline 11 is connected to the liquid oxygen tank air pillow; the second liquid nitrogen pump 343 is connected to one end of the fuel tank boost pipe 21 through the second heater assembly, and the other end of the fuel tank boost pipe 21 is connected to the fuel tank air pillow; one end of the liquid nitrogen tank boost pipe 32 is connected to the liquid nitrogen tank air pillow, and the other end is connected to the main boost pipeline 11.

[0115] Specifically, Fig.11 and Fig.12 As shown, in this embodiment, the 9 groups of heater units 61 of the 9 engines 60 are divided into two parts, the first part is the first heater assembly, the first heater assembly includes 5 groups of heater units 61, and the second part is the second heater assembly, the second heater assembly includes 4 groups of heater units 61. Each heater unit 61 includes a heater liquid nitrogen stop valve 614, a liquid nitrogen heater 612 and a heater check valve 611 arranged in sequence on the pipeline. In other embodiments, the heater unit 61 can also be provided with the same components as the heater unit 61 in the above embodiment, and this embodiment only lists a composition form of the heater unit 61. One end of the liquid nitrogen delivery pipe 31 of this embodiment is connected to the bottom of the liquid nitrogen tank 30, and the other end is connected to the first nitrogen pump through a tee, and then connected to one end of the main boost pipeline 11 through the first heater assembly, and the other end of the main boost pipeline 11 is connected to the liquid oxygen tank energy dissipator 13. One end of the liquid nitrogen tank boost pipe 32 is connected to the main boost pipe 11 through a tee, and the other end is connected to the top of the liquid nitrogen tank 30. A liquid nitrogen tank check valve 33 is also provided on the liquid nitrogen tank boost pipe 32. The liquid nitrogen tank 30 of this embodiment is also provided with a liquid nitrogen tank exhaust valve 37 and a liquid nitrogen tank safety valve 38. The liquid nitrogen tank exhaust valve 37 and the liquid nitrogen tank safety valve 38 are connected to the liquid nitrogen tank boost pipe 32 located inside the liquid oxygen tank 10 through a pipeline. One end of the liquid nitrogen delivery pipe 31 of this embodiment is connected to the bottom of the liquid nitrogen tank 30, and the other end is connected to the second liquid nitrogen pump 343, and then connected to one end of the fuel tank boost pipe 21 through the second heater assembly, and the other end of the fuel tank boost pipe 21 is connected to the fuel tank air pillow through the fuel tank energy dissipator 25.

[0116] During the first stage of the rocket flight, the liquid nitrogen in the liquid nitrogen tank 30 is used to pressurize the liquid oxygen tank 10 via the liquid nitrogen delivery pipe 31, the first liquid nitrogen pump 342, the first heater assembly, the main boost pipeline 11, and the liquid oxygen tank energy dissipator 13.

[0117] The liquid nitrogen in the liquid nitrogen box 30 is pressurized to the fuel tank 20 via the liquid nitrogen delivery pipe 31 , the second liquid nitrogen pump 343 , the second liquid nitrogen heater 612 assembly, the fuel tank 20 pressurization pipe, and the fuel tank energy dissipator 25 .

[0118] In the first-stage flight phase, the liquid nitrogen in the liquid nitrogen tank 30 is pressurized via the liquid nitrogen delivery pipe 31, the first liquid nitrogen pump 342, the first liquid nitrogen heater 612 assembly, the main pressurization pipeline 11, the liquid nitrogen tank pressurization pipe 32, and the liquid nitrogen tank one-way valve 33.

[0119] In this embodiment, the liquid nitrogen tank 30 is stored in the liquid oxygen tank 10, and the liquid nitrogen pressure is increased by two liquid nitrogen pumps, one for pressurizing the liquid oxygen tank 10 and the other for pressurizing the fuel tank 20. A tee is provided on the main pressurizing pipeline 11 of the liquid oxygen tank, and one for pressurizing the liquid nitrogen tank 30. That is, the pressurization of the three storage tanks is achieved by heating the liquid nitrogen.

[0120] The liquid oxygen tank 10 adopts a liquid nitrogen heating and pressurizing solution. The liquid nitrogen is heated by the liquid nitrogen heater 612 to form nitrogen gas. The high-temperature nitrogen gas is pressurized to the liquid oxygen tank 10 through the main pressurizing pipeline 11, and is pressurized to the fuel tank 20 through the fuel tank pressurizing pipe 21. A small amount of high-temperature nitrogen is separated from the liquid oxygen tank 10 and is pressurized to the liquid nitrogen tank 30 through the liquid nitrogen tank one-way valve 33 and the liquid nitrogen tank pressurizing pipe 32.

[0121] The liquid nitrogen vaporization and pressurization system of this embodiment utilizes the liquid nitrogen heaters 612 of five engines 60 to heat the liquid nitrogen into high-temperature nitrogen gas for pressurizing the liquid oxygen tank 10, and utilizes the liquid nitrogen heaters 612 of four engines 60 to heat the liquid nitrogen into high-temperature nitrogen gas for pressurizing the fuel tank 20, thereby realizing independent pressurization of the liquid oxygen tank 10 and the fuel tank 20.

[0122] like Fig.13 As shown, the liquid nitrogen vaporization and pressurization system of this embodiment also includes a second liquid nitrogen filling and precooling component 39, which includes a second liquid nitrogen filling and precooling pipeline 391, a pipeline one-way valve 392 and a second liquid nitrogen discharge stop valve 393. The pipeline one-way valve 392 is arranged on the second liquid nitrogen filling and precooling pipeline 391, one end of the second liquid nitrogen filling and precooling pipeline 391 is connected to the pipeline between the liquid nitrogen pump 34 and the liquid nitrogen tank 30, and the other end is used for detachable connection with the liquid nitrogen filling system 36; the second liquid nitrogen discharge stop valve 393 is connected to the outlet ends of the two liquid nitrogen pumps through pipelines.

[0123] Specifically, the second liquid nitrogen filling precooling pipeline 391 is detachably connected to the liquid nitrogen filling system 36 through the first-stage tail end plug connector, and a liquid nitrogen filling valve 361 is also provided between the first-stage tail end plug connector and the liquid nitrogen filling system 36. The two liquid nitrogen pumps are connected in parallel to the inlet of the second liquid nitrogen discharge stop valve 393.

[0124] When the liquid nitrogen tank 30 is filled, the liquid nitrogen filling system 36 delivers the liquid nitrogen into the liquid nitrogen tank 30 through the liquid nitrogen filling valve 361, the first-stage tail end plug connector, the second liquid nitrogen filling precooling pipeline 391, the pipeline one-way valve 392 and the liquid nitrogen delivery pipe 31 to fill it with liquid nitrogen.

[0125] When the rocket is flying, the plug-in connector at the tail end of the first stage is disconnected, and the liquid nitrogen filling one-way valve 362 can ensure that the liquid nitrogen in the liquid nitrogen tank 30 does not leak.

[0126] During the pre-cooling process of the ground liquid nitrogen pump 34, the liquid nitrogen in the liquid nitrogen tank 30 is divided into two paths after passing through the liquid nitrogen delivery pipe 31. One path passes through the first liquid nitrogen pump 342 and the second liquid nitrogen discharge stop valve 393 to discharge the liquid nitrogen directly into the atmosphere, thereby ensuring the reliability of the ignition of the first liquid nitrogen pump 342. The other path passes through the second liquid nitrogen pump 343 and the second liquid nitrogen discharge stop valve 393 to discharge the pre-cooled liquid nitrogen directly into the atmosphere, thereby ensuring the reliability of the ignition of the second liquid nitrogen pump 343.

[0127] When the rocket is ignited and flying, the liquid nitrogen discharge stop valve remains closed, and the liquid nitrogen after the liquid nitrogen pump 34 is heated by the liquid nitrogen heater 612 to become high-temperature nitrogen gas to pressurize the liquid oxygen tank 10 and the fuel tank 20.

[0128] The discharge precooling of the liquid nitrogen pump 34 is only performed before the liquid nitrogen pump 34 works. The discharge precooling of the liquid nitrogen pump 34 is not performed after the liquid nitrogen pump 34 works, so the second liquid nitrogen discharge stop valve 393 is closed.

[0129] like Fig.14 As shown, the liquid nitrogen vaporization and pressurization system of this embodiment also includes a second pre-shot pressurization assembly 70 and a third pre-shot pressurization assembly 80. One end of the second pre-shot pressurization assembly 70 is connected to the main pressurization pipeline 11 between the pressurization pipe of the liquid nitrogen tank 30 and the first heater assembly through a tee, and the other end is used for detachable connection with the ground helium source 90; one end of the third pre-shot pressurization assembly 80 is connected to the pressurization pipe of the fuel tank 20 through a tee, and the other end is used for detachable connection with the ground helium source 90.

[0130] Specifically, in the present embodiment, the second pre-fire boost assembly 70 includes a second pre-fire boost check valve 71 and a second pre-fire boost solenoid valve 72 which are sequentially connected to the main boost pipeline 11 through a pipeline. The third pre-fire boost assembly 80 includes a third pre-fire boost check valve 81 and a third pre-fire boost solenoid valve 82 which are sequentially connected to the boost pipe of the fuel tank 20 through a pipeline. The second pre-fire boost assembly 70 and the third pre-fire boost assembly 80 are detachably connected to the ground helium source 90 through a first-stage tail end plug connector. In the present embodiment, the number of ground helium sources 90 is also two, and the first ground helium source 90 is respectively connected to a filter 91 and a pressure reducer 92 in sequence, and the outlet of one pressure reducer 92 is connected to the second pre-fire boost assembly 70 through a first-stage tail end plug connector, and the outlet of the other pressure reducer 92 is connected to the third pre-fire boost assembly 80 through a first-stage tail end plug connector.

[0131] During the ground pre-launch pressurization, the ground helium source 90 performs pre-launch pressurization on the liquid oxygen tank 10 through the filter 91, the pressure reducer 92, the first-stage tail end plug-in connector, the second pre-launch pressurization solenoid valve 72, the second pre-launch pressurization check valve 71, the second pre-launch pressurization pipeline and the liquid oxygen tank energy dissipator 13.

[0132] During the ground pre-launch pressurization, the ground helium source 90 performs pre-launch pressurization on the fuel tank 20 through the filter 91, the pressure reducer 92, the first-stage tail end plug-in connector, the third pre-launch pressurization solenoid valve 82, the third pre-launch pressurization check valve 81, the third pre-launch pressurization pipeline and the fuel tank energy dissipator 25.

[0133] The liquid nitrogen vaporization pressurization system of this embodiment separates the liquid oxygen tank pressurization system from the fuel tank pressurization system, which can achieve independent pressurization of the two tanks and avoid safety problems caused by the gas in the liquid oxygen tank 10 flowing back to the fuel tank 20.

[0134] The second pre-shot boosting assembly 70 and the third pre-shot boosting assembly 80 of this embodiment also have a pressure supplementing function, and the pre-shot boosting system and the pressure supplementing system are integrated into one design.

[0135] After the rocket's power system test ignition, the liquid oxygen tank is pressurized on the rocket using liquid nitrogen heating and pressurization. At this time, the liquid nitrogen is delivered during the pressurization in the same way as during the rocket's first-stage flight stage, so it will not be repeated. The fuel tank is pressurized on the rocket using liquid nitrogen heating and pressurization. At this time, the liquid nitrogen is delivered during the pressurization in the same way as during the rocket's first-stage flight stage, so it will not be repeated.

[0136] During the power system test, the second pre-launch boost assembly 70 is used to supplement the pressure of the liquid oxygen tank 10. During the first-level power system test, the pressurization process of the liquid oxygen tank 10 is the same as the pre-launch boost process on the ground, and will not be repeated.

[0137] During the power system test, the third pre-fire boost assembly 80 is used to supplement the pressure of the fuel tank 20. During the first-level power system test, the pressurization process of the fuel tank 20 is the same as the pre-fire boost process on the ground, and will not be repeated.

[0138] The pre-fire boost solenoid valves in the second pre-fire boost assembly 70 and the third pre-fire boost assembly 80 not only control the pre-fire boost of the liquid oxygen tank before the power system test ignition, but also control the logic of the ground pressure replenishment system of the liquid oxygen tank after the power system test ignition, so that a simple pre-fire boost solenoid valve can achieve multiple functions and simplify the structure of the ground pressure replenishment system. At the same time, the overall structure of the pre-fire boost assembly is simple, the types of valves and pipelines are single and the number is small, the research and development difficulty is low, and the processing and production cycle is short.

[0139] like Fig.12As shown, the gas generators 64 of at least two engines 60 are connected in parallel and used together to provide driving force for the liquid nitrogen pump 34. For example, in this embodiment, the gas generators 64 of the two engines 60 are respectively connected to a one-way valve 65 and then connected in parallel, and then respectively connected to the first liquid nitrogen pump 342 and the second liquid nitrogen pump 343 connected in parallel through a tee, and an orifice plate 341 is also provided between the liquid nitrogen pump and the tee. The high-temperature combustion gas generated by the two gas generators 64 passes through two one-way valves 65, is collected in one path through the tee, and then is divided into two paths, and passes through the orifice plate 341 to provide driving gas for the first liquid nitrogen pump 342 and the second liquid nitrogen pump 343.

[0140] This embodiment can also be similar to the above-mentioned embodiment, in which a liquid oxygen tank overflow valve 16 is provided on the liquid oxygen tank 10, which will not be described in detail here.

[0141] The liquid nitrogen vaporization and pressurization system provided in this embodiment uses two liquid nitrogen pumps 34 to heat the liquid nitrogen. The first liquid nitrogen pump 342 pressurizes the liquid nitrogen, and then heats it through five liquid nitrogen heaters 612 to pressurize the liquid oxygen tank 10, and a branch is separated to pressurize the liquid nitrogen tank 30. The second liquid nitrogen pump 343 pressurizes the liquid nitrogen, and then heats it through four liquid nitrogen heaters 612 to pressurize the fuel tank 20. Both the liquid oxygen tank 10 and the fuel tank 20 adopt an open pressurization method, which greatly simplifies the difficulty of system development and system matching.

[0142] This embodiment provides high-temperature driving gas by means of the gas generators of two engines and two one-way valves, which effectively avoids the problem of insufficient gas source due to the failure of one engine and improves the reliability of the boosting system.

[0143] In this embodiment, an orifice plate 341 is provided at the gas inlet of the liquid nitrogen pump 34. During the ground test, the size of the orifice plate 341 can be adjusted to control the intake flow of the first liquid nitrogen pump 342 and the second liquid nitrogen pump 343, thereby controlling and determining the power of the liquid nitrogen pump. The size of the orifice plate 341 is determined by the liquid nitrogen pump 34 reaching the rated power during the test, which is conducive to reducing the difficulty of development, design and simulation of the system.

[0144] This embodiment utilizes the high-temperature fuel gas generated by the gas generator 64 of the engine 60 to drive the liquid nitrogen pump, thereby ensuring the reliable operation of the liquid nitrogen pump. Compared with the method of using an independent gas source to drive the liquid nitrogen pump or using a motor to drive the liquid nitrogen pump, this solution utilizes the fuel gas in the gas generator 64 of the engine 60 to drive the liquid nitrogen pump, and the system integration is high, the driving system of the liquid nitrogen pump is simplified, and the effective mass of the boosting system is reduced.

[0145] The liquid nitrogen vaporization and pressurization system of this embodiment is provided with a one-way valve 65 at the outlet of the gas generator 64, which can effectively prevent the gas generated by a normally working engine 60 from flowing out through the gas generator 64 of the damaged engine when a certain engine 60 is damaged, thereby improving the risk resistance of the system.

[0146] This embodiment utilizes the liquid nitrogen heaters 612 of five engines to heat liquid nitrogen into high-temperature nitrogen gas to pressurize the liquid oxygen tank 10, and utilizes the liquid nitrogen heaters 612 of four engines to heat liquid nitrogen into high-temperature nitrogen gas to pressurize the fuel tank 20, thereby achieving independent pressurization of the liquid oxygen tank 10 and the fuel tank 20.

[0147] The pre-launch boost pipeline is provided on the main boost pipeline 11 of the liquid oxygen tank 10 and the fuel tank boost pipeline 21, which can effectively shorten the length of the pre-launch boost pipeline, so that the pre-launch boost pipeline and the main boost pipeline 11 are designed in an integrated manner, thereby improving the integration of the main boost pipeline 11.

[0148] In the pre-fire boost system (the second pre-fire boost component 70 and the third pre-fire boost component 80) of the present embodiment, during the ground pre-fire boost process, the pre-fire boost solenoid valve not only plays the role of pre-fire boosting the liquid oxygen tank before the power system test ignition, but also plays the role of logical control of the ground pressurization system of the liquid oxygen tank after the power system test ignition, so that a simple pre-fire boost solenoid valve can realize multiple functions, simplifying the structure of the ground pressurization system, and the boost and pressure replenishment system (the second pre-fire boost component 70 and the third pre-fire boost component 80) has a simple structure, a single type of valves and pipelines and a small number, low research and development difficulty, and a short processing and production cycle.

[0149] In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "upper, lower, inner and outer" are based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first, second or third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0150] In the present invention, unless otherwise clearly specified and limited, the terms "install, connect, connect" should be understood in a broad sense, for example: it can be a fixed connection, a detachable connection or an integral connection; it can also be a mechanical connection, an electrical connection or a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0151] Although the present invention has been described with reference to preferred embodiments, various modifications may be made thereto and parts thereof may be replaced by equivalents without departing from the scope of the present invention. In particular, the various technical features mentioned in the various embodiments may be combined in any manner as long as there are no structural conflicts. The present 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 liquid nitrogen vaporization and pressurization system for liquid rockets, characterized in that: The invention comprises a liquid oxygen tank (10), a fuel tank (20), a liquid nitrogen tank (30), a liquid nitrogen pump (34), a cavitation tube (613) and a heater assembly; the liquid oxygen tank (10) is used to store liquid oxygen, the fuel tank (20) is used to store fuel, the liquid nitrogen tank (30) is used to store liquid nitrogen, the liquid nitrogen tank (30) is arranged inside the liquid oxygen tank (10), the fuel tank (20) is arranged on a side of the liquid oxygen tank (10) close to the engine (60), and the liquid nitrogen pump (34) is used to increase the output of liquid nitrogen. pressure, the cavitation tube (613) is used to stabilize the liquid nitrogen flow rate, and the heater assembly is used to vaporize the liquid nitrogen and heat it into high-temperature nitrogen gas; a liquid nitrogen delivery pipe (31) is provided at the bottom of the liquid nitrogen tank (30), the liquid nitrogen pump (34) is arranged on the liquid nitrogen delivery pipe (31), one end of the liquid nitrogen delivery pipe (31) away from the liquid nitrogen pump (34) is connected to the inlet of the heater assembly, and the liquid oxygen tank air pillow, the fuel tank air pillow and the liquid nitrogen tank air pillow are respectively connected to the outlet of the heater assembly through pipelines.

2. The liquid nitrogen vaporization and pressurization system according to claim 1, characterized in that: It also comprises a main boosting pipeline (11), a liquid nitrogen tank boosting pipe (32) and a fuel tank boosting pipe (21); the liquid oxygen tank air pillow is connected to the heater assembly via the main boosting pipeline (11); one end of the liquid nitrogen tank boosting pipe (32) is connected to the liquid nitrogen tank air pillow, and the other end is connected to the main boosting pipeline (11); one end of the fuel tank boosting pipe (21) is connected to the fuel tank air pillow, and the other end is connected to the main boosting pipeline (11) between the liquid nitrogen tank boosting pipe (32) and the heater assembly.

3. The liquid nitrogen vaporization and pressurization system according to claim 2, characterized in that: The system also includes a blowdown and pressurization integrated assembly (50), wherein the blowdown and pressurization integrated assembly (50) includes a main pipeline (57) and a plurality of branch pipelines, wherein one end of the main pipeline (57) close to the engine (60) is used to be connected to a ground nitrogen source (58), and the inlet of each branch pipeline is respectively connected to the main pipeline (57); the outlet of the first branch pipeline (51) is connected to the liquid oxygen discharge pipeline (511) of the engine (60) to provide a gas seal for the liquid oxygen discharge pipeline (511); the outlet of the second branch pipeline (52) is connected to the tail cabin blowdown pipe (521) to be used to The first-stage tail cabin section is blown off; the outlet of the third branch pipeline (53) is connected to the inter-tank section blow-off pipe (531) for blowing off the inter-tank section cabin section; the outlet of the fourth branch pipeline (54) is connected to the liquid nitrogen tank pressurizing pipe (32) for pressurizing the liquid nitrogen tank (30); the outlet of the fifth branch pipeline (55) is connected to the exhaust pipeline (551) of the liquid oxygen tank (10) for providing an air seal for the exhaust pipeline (551) of the liquid oxygen tank (10); the outlet of the sixth branch pipeline (56) is connected to the inter-stage section blow-off pipe (561) for blowing off the cabin section of the inter-stage section.

4. The liquid nitrogen vaporization and pressurization system according to claim 2, characterized in that: The invention also comprises a first liquid nitrogen filling and precooling component (35), wherein the first liquid nitrogen filling and precooling component (35) comprises a first liquid nitrogen filling and precooling pipeline (351) and a liquid nitrogen stop valve (352), wherein the liquid nitrogen stop valve (352) is arranged on the first liquid nitrogen filling and precooling pipeline (351), wherein one end of the first liquid nitrogen filling and precooling pipeline (351) is connected to the pipeline between the liquid nitrogen pump (34) and the heater component, and the other end is used for being detachably connected to the liquid nitrogen filling system (36) and the first liquid nitrogen discharge stop valve (363) respectively.

5. The liquid nitrogen vaporization and pressurization system according to claim 2, characterized in that: It also includes a liquid oxygen tank pressure replenishing assembly (17), a fuel tank pressure replenishing assembly (26) and a first pre-fire pressurization assembly (40); The liquid oxygen tank pressure-compensating assembly (17) comprises a liquid oxygen tank pressure-compensating pipeline (172), one end of the liquid oxygen tank pressure-compensating pipeline (172) is connected to a liquid oxygen tank pressure-compensating helium bottle (171), and the other end is connected to the main pressure-compensating pipeline (11); a liquid oxygen tank pressure-compensating solenoid valve (173) and a liquid oxygen tank pressure-compensating orifice plate (174) are sequentially arranged on the liquid oxygen tank pressure-compensating pipeline (172) from the liquid oxygen tank pressure-compensating helium bottle (171) to the main pressure-compensating pipeline (11); The fuel tank pressure boosting assembly (26) comprises a fuel tank pressure boosting pipeline (261), one end of the fuel tank pressure boosting pipeline (261) is connected to a fuel tank pressure boosting helium bottle (264), and the other end is connected to the fuel tank pressure boosting pipe (21); the fuel tank pressure boosting pipeline (261) is provided with a fuel tank pressure boosting solenoid valve (263) and a fuel tank pressure boosting orifice plate (262) in sequence from the fuel tank pressure boosting helium bottle (264) to the fuel tank pressure boosting pipe (21); One end of the first pre-shot boosting assembly (40) is connected to the main boosting pipeline (11) between the liquid nitrogen box boosting pipe (32) and the heater assembly, and the other end is used for detachable connection with a ground helium source (90); the first pre-shot boosting assembly (40) comprises a first pre-shot boosting one-way valve (41) and a first pre-shot boosting solenoid valve (42) which are sequentially arranged from the main boosting pipeline (11) to the ground helium source (90).

6. The liquid nitrogen vaporization and pressurization system according to claim 1, characterized in that: It also includes a main boosting pipeline (11), a liquid nitrogen tank boosting pipe (32) and a fuel tank boosting pipe (21); the liquid nitrogen pump (34) includes a first liquid nitrogen pump (342) and a second liquid nitrogen pump (343) connected in parallel, and the heater assembly includes a first heater assembly and a second heater assembly; The first liquid nitrogen pump (342) is connected to one end of the main boost pipeline (11) through the first heater assembly, and the other end of the main boost pipeline (11) is connected to the liquid oxygen tank air pillow; the second liquid nitrogen pump (343) is connected to one end of the fuel tank boost pipe (21) through the second heater assembly, and the other end of the fuel tank boost pipe (21) is connected to the fuel tank air pillow; one end of the liquid nitrogen tank boost pipe (32) is connected to the liquid nitrogen tank air pillow, and the other end is connected to the main boost pipeline (11).

7. The liquid nitrogen vaporization and pressurization system according to claim 6, characterized in that: The invention also comprises a second liquid nitrogen filling and precooling component (39), wherein the second liquid nitrogen filling and precooling component (39) comprises a second liquid nitrogen filling and precooling pipeline (391), a pipeline one-way valve (392) and a second liquid nitrogen discharge stop valve (393), wherein the pipeline one-way valve (392) is arranged on the second liquid nitrogen filling and precooling pipeline (391), one end of the second liquid nitrogen filling and precooling pipeline (391) is connected to the pipeline between the liquid nitrogen pump and the liquid nitrogen tank (30), and the other end is used for being detachably connected to the liquid nitrogen filling system (36); the second liquid nitrogen discharge stop valve (393) is respectively connected to the outlet ends of the two liquid nitrogen pumps through pipelines.

8. The liquid nitrogen vaporization and pressurization system according to claim 6, characterized in that: The invention also comprises a second pre-shot pressurization assembly (70) and a third pre-shot pressurization assembly (80), wherein one end of the second pre-shot pressurization assembly (70) is connected to the main pressurization pipeline (11) between the liquid nitrogen tank pressurization pipe (32) and the first heater assembly, and the other end is used for detachable connection with a ground helium source (90); one end of the third pre-shot pressurization assembly (80) is connected to the fuel tank pressurization pipe (21), and the other end is used for detachable connection with the ground helium source (90).

9. The liquid nitrogen vaporization and pressurization system according to any one of claims 1 to 8, characterized in that: The gas generators (64) of at least two engines (60) are connected in parallel for redundancy and are used together to provide driving force for the liquid nitrogen pump.

10. A liquid rocket, characterized in that: The invention comprises a liquid nitrogen vaporization and pressurization system as claimed in any one of claims 1 to 9.

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