Novel liquid rocket pressurization system combining self-generation pressurization and gas cylinder heating pressurization

Abstract

The invention relates to a novel liquid rocket pressurization system combining self-generated pressurization and gas cylinder heating pressurization. The novel liquid rocket pressurization system comprises a liquid oxygen storage tank, a kerosene storage tank, a self-generated pressurization pipeline, a gas cylinder heating pressurization pipeline, a first heater and a third heater. The self-generating pressurizing pipeline is communicated with the liquid oxygen storage tank and is communicated with a thrust chamber head oxygen head cavity of the first engine, and liquid oxygen is led out of the thrust chamber head oxygen head cavity of the first engine, then is subjected to heat exchange with turbine waste gas through the first heater and then is conveyed to the liquid oxygen storage tank; and the gas cylinder heating and pressurizing pipeline is communicated with the kerosene storage tank, and pressurized gas exchanges heat with waste gas of the turbine through the third heater and then is conveyed to the kerosene storage tank. According to the application, self-pressurization of the low-temperature liquid oxygen storage tank is realized, and heating and pressurization of the kerosene storage tank are also realized, so that the pressurization efficiency of the kerosene storage tank is greatly improved.

Description

Technical Field

[0001] The present application relates to the field of rocket technology, and in particular to a novel liquid rocket pressurization system that combines self-generated pressurization with gas cylinder heating and pressurization. Background Art

[0002] The pressurization system is used to provide the air cushion pressure of the liquid rocket propellant tank to meet the requirements of the propellant inlet working pressure and the internal pressure of the thin-walled structure of the rocket propellant tank required during engine startup and flight, and to ensure that the tank structure has sufficient strength and rigidity. Its main working process is: the pressurized gas enters the propellant tank, occupies the space where the propellant is discharged after expansion, and exerts working pressure on the liquid propellant. Commonly used pressurization methods generally include three types: gas pressurization using the combustion products of the engine as the pressurization medium; self-pressurization using the rocket's propellant components through engine evaporation and vaporization as the pressurization medium; gas storage pressurization equipped with independent storage of pressurization medium. At present, the liquid oxygen-kerosene propellant combination is still the main propellant combination in the aerospace field. Oxygen tanks usually use self-pressurization or gas cylinder (helium) pressurization, and kerosene tanks usually use gas cylinder (helium) pressurization. Traditional boosting systems are generally the following two combinations: oxygen boxes use self-generated boosting, and kerosene tanks use gas cylinders (helium) for boosting; oxygen boxes use gas cylinders (helium) for heated boosting, and kerosene tanks use normal temperature gas cylinders (helium) for boosting. Both self-generated boosting and heated boosting require the use of the engine's heater to heat the boosted gas to improve boosting efficiency, but only one of the two can be chosen, that is, if the engine's heater is used for boosting the oxygen box, the kerosene tank cannot be used. From the perspective of boosting gas, the traditional boosting system analyzes that although helium or nitrogen can be selected as the boosting gas in the gas cylinder, helium is commonly used in the current mature liquid rocket models at home and abroad. This is because the density of helium is much smaller than that of nitrogen, so a small flow change will cause a large fluctuation in the tank pressure. Nitrogen has a relatively poor boosting capacity due to its own high density. The mass of nitrogen is much larger than that of helium at the same volume. Since the rocket flight time is fixed, the boost flow rate of nitrogen per unit time is also much larger than that of helium. Therefore, if nitrogen is directly selected as the boost gas, the boost gas volume requirement of nitrogen is nearly twice that of helium. A larger space is needed to place more gas cylinders, and the corresponding valves, pipelines, orifice plates, etc. must match a larger size than the helium boost system to adapt. However, it is well known that helium is an irreplaceable key element in modern high-tech industries and an important strategic resource. my country's helium resources are extremely scarce. It is estimated that the total amount of helium resources is about 1.1 billion cubic meters, of which the total amount that can be directly recovered is about 50 million cubic meters, less than 0.1% of the global reserves. It is bound to study a new boost system and use nitrogen instead of helium for boosting, which can not only improve the boosting efficiency but also save helium resources.

[0003] Therefore, how to utilize the liquid oxygen tank and the kerosene tank simultaneously to improve the pressurization efficiency is a technical problem that technicians in this field urgently need to solve. Summary of the invention

[0004] The present application provides a new liquid rocket pressurization system that combines self-generated pressurization with gas cylinder heating pressurization, so that the liquid oxygen tank and the kerosene tank can use the rocket engine heater at the same time to improve the pressurization efficiency, so that nitrogen can be used as the pressurization gas when selecting the pressurization gas, thereby reducing the use of strategic resource helium in space launches, and allowing my country's limited helium resources to be applied to high-tech fields that are in greater need.

[0005] In order to solve the above technical problems, this application provides the following technical solutions:

[0006] A new liquid rocket pressurization system combining self-generated pressurization with gas cylinder heating pressurization comprises: a liquid oxygen tank, a kerosene tank, a self-generated pressurization pipeline, a first ground pressurization pipeline, a second ground pressurization pipeline, a gas cylinder heating pressurization pipeline, a first heater, and a third heater; the first ground pressurization pipeline is connected to the liquid oxygen tank to transport pressurized gas to the liquid oxygen tank; the self-generated pressurization pipeline is connected to the liquid oxygen tank, and at the same time, the self-generated pressurization pipeline is connected to the oxygen head cavity of the thrust chamber head of the first engine and contacts with the first heater, after the liquid oxygen is drawn out of the oxygen head cavity of the thrust chamber head of the first engine, it is transported to the liquid oxygen tank for pressurization after heat exchange with turbine exhaust gas through the first heater; the second ground pressurization pipeline is connected to the kerosene tank to transport pressurized gas to the kerosene tank; the gas cylinder heating pressurization pipeline is connected to the kerosene tank and contacts with the third heater, and the pressurized gas is transported to the kerosene tank after heat exchange with turbine exhaust gas through the third heater.

[0007] As above, it also includes a second heater. The self-generated pressurization pipeline is connected to the oxygen head cavity of the thrust chamber head of the second engine and contacts the second heater. After the liquid oxygen is drawn out of the oxygen head cavity of the thrust chamber head of the second engine, it is transported to the liquid oxygen tank for pressurization after heat exchange with the turbine exhaust gas through the second heater.

[0008] As mentioned above, the first ground boosting circuit is also connected to a first filter and a first one-way valve.

[0009] As mentioned above, the liquid oxygen drawn out from the oxygen head chamber of the thrust chamber head of the first to second engines is pure liquid oxygen.

[0010] As mentioned above, the top of the liquid oxygen tank is also connected to a pressure sensor to perform pressure detection on the entire liquid oxygen tank.

[0011] As mentioned above, the second ground boosting circuit is also connected to a second filter and a second one-way valve.

[0012] As above, it also includes a plurality of pressurized gas cylinders, which are respectively connected to the charging valve and the gas cylinder heating and pressurizing pipeline, and the pressurized gas stored through the charging valve is delivered to the gas cylinder heating and pressurizing pipeline.

[0013] As above, the gas cylinder heating and pressurizing pipeline is also connected to a third filter, a first solenoid valve, a second solenoid valve, a third solenoid valve, a first orifice plate, a second orifice plate and a third orifice plate.

[0014] As above, wherein the third filter is connected to one end of the first to third solenoid valves respectively, the first solenoid valve is connected to one end of the first orifice plate, and the other end of the first orifice plate is connected to the gas cylinder heating and pressurizing pipeline; the second solenoid valve is connected to one end of the second orifice plate, and the other end of the second orifice plate is connected to the gas cylinder heating and pressurizing pipeline; the third solenoid valve is connected to one end of the third orifice plate, and the other end of the third orifice plate is connected to the gas cylinder heating and pressurizing pipeline, and the gas cylinder heating and pressurizing pipeline is connected to the top of the kerosene storage tank after contacting the third heater.

[0015] As above, wherein the number of the first one-way valve and the second one-way valve is plural.

[0016] Compared with the above background technology, the pressurization system in this application realizes both the self-pressurization of the cryogenic liquid oxygen tank and the heating and pressurization of the kerosene tank, which greatly increases the pressurization efficiency of the kerosene tank. For a system with multiple engines in parallel, a certain number of engines are used to provide self-pressurization of the liquid oxygen tank, and the remaining engines are used to heat and pressurize the gas cylinders of the kerosene tank, so that the temperature of the pressurized gas is increased, and the pressurization efficiency of the kerosene tank is improved. The pressurized gas for the kerosene tank can use either helium or nitrogen. The pressurization system greatly reduces the amount of helium used, reduces the use of strategic resource helium in space launches, and enables my country's limited helium resources to be applied to more needed high-tech fields. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] 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 recorded in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0018] Figure 1 It is a schematic diagram of a new liquid rocket pressurization system that combines self-generated pressurization with gas cylinder heating pressurization provided in an embodiment of the present application. DETAILED DESCRIPTION

[0019] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. In addition, spatial relationship terms such as "upper", "lower", "left", "right", "front", "rear", etc. are used to facilitate description to explain the positional relationship between two components. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and are not to be construed as limitations on the present invention.

[0020] like Figure 1 As shown, the present application provides a new liquid rocket pressurization system that combines self-pressurization with gas cylinder heating and pressurization, including: a liquid oxygen storage tank 110, a kerosene storage tank 120, a self-pressurization pipeline 130, a first ground pressurization pipeline 140, a second ground pressurization pipeline 150, a gas cylinder heating and pressurization pipeline 160, a first heater 170, a second heater 180, and a third heater 190.

[0021] The first ground pressurization line 140 is connected to the top of the liquid oxygen tank 110 , and is also connected to a first filter 141 and a first non-return valve 142 .

[0022] The inlet of the first ground boosting circuit is connected to the liquid oxygen tank 110, and the outlet is connected to the ground boosting device. The boosted gas input from the first ground boosting device is filtered through the first filter 141, and the boosted gas is transported to the liquid oxygen tank 110 when the first one-way valve 142 is opened.

[0023] The inlet end of the self-pressurizing pipeline 130 is respectively connected to the thrust chamber head oxygen head cavity of engine 1 (first engine) and the thrust chamber head oxygen head cavity of engine 2 (second engine), and the outlet end of the self-pressurizing pipeline 130 is connected to the liquid oxygen tank 110.

[0024] When the self-pressurizing pipeline 130 is connected to the oxygen head cavity of the thrust chamber head of engine 1, it is also in contact with the first heater. When the self-pressurizing pipeline 130 is connected to the oxygen head cavity of the thrust chamber head of engine 2, it is also in contact with the second heater.

[0025] The heat of the first and second heaters is provided by engines 1 and 2 respectively.

[0026] When boosting is required, a certain flow of liquid oxygen is drawn out from the oxygen head chambers at the thrust chamber heads of engines 1 and 2. A certain flow of liquid oxygen is drawn out from the oxygen head chambers at the thrust chamber heads of the first to second engines and is heat exchanged with the turbine exhaust gas through the first and second heater heat exchangers respectively to form gaseous oxygen with a certain temperature and pressure, which is then input into the liquid oxygen storage tank 110 through the self-generated boosting pipeline to pressurize the oxygen tank of the rocket body.

[0027] The liquid oxygen used for self-pressurization is pure liquid oxygen without combustion product impurities. Since the liquid oxygen vaporization self-pressurization scheme has obvious advantages over the cylinder pressurization scheme in terms of system complexity and economy, the self-pressurization scheme is preferred for basic-stage rocket oxygen tank pressurization when there are no other key restrictive conditions.

[0028] Preferably, there are plural first one-way valves.

[0029] The top of the liquid oxygen tank 110 is also connected to a pressure sensor, which can detect the pressure of the entire liquid oxygen tank 110.

[0030] The second ground pressure boosting path 150 is connected to the top of the kerosene tank 120 , and is also connected to a second filter 151 and a second one-way valve 152 .

[0031] The inlet end of the second ground boosting circuit 150 is connected to the kerosene tank 120, and the outlet end is connected to the ground boosting device. The boosted gas input from the second ground boosting device is filtered by the second filter 151, and is transported to the kerosene tank 120 when the second one-way valve 152 is opened.

[0032] The inlet end of the gas cylinder heating and pressurizing pipeline 160 is connected to multiple pressurized gas cylinders, and the outlet end is connected to the kerosene storage tank 120. The third filter 161, the first solenoid valve 162, the second solenoid valve 163, the third solenoid valve 164, the first orifice plate 165, the second orifice plate 166 and the third orifice plate 167 are also connected in the gas cylinder heating and pressurizing pipeline 160.

[0033] The third filter 161 is communicated with one end of the first to third solenoid valves respectively, the first solenoid valve 162 is communicated with one end of the first orifice plate 165, and the other end of the first orifice plate 165 is communicated with the gas cylinder heating and pressurizing pipeline 160. The second solenoid valve 162 is communicated with one end of the second orifice plate 166, and the other end of the second orifice plate 166 is communicated with the gas cylinder heating and pressurizing pipeline 160. The third solenoid valve 164 is communicated with one end of the third orifice plate 167, and the other end of the third orifice plate 167 is communicated with the gas cylinder heating and pressurizing pipeline 160, and the gas cylinder heating and pressurizing pipeline 160 is communicated with the top of the kerosene storage tank 120 after contacting the third heater 190.

[0034] The heat of the third heater 190 is provided by the engine 3 (third engine).

[0035] The plurality of pressurized gas cylinders are all connected to the charging valve, and the pressurized gas is stored through the charging valve. The plurality of pressurized gas cylinders are connected to form a gas cylinder group.

[0036] When boosting is required, the pressurized gas stored in multiple boosting gas cylinders enters the third filter 161 and is divided into three paths. Each gas path passes through its own opened solenoid valve and orifice plate, and then passes through the third heater 190 of the engine 3 to exchange heat with the exhaust gas of the turbine, and is finally output to the kerosene storage tank 120.

[0037] As an example, after the pressurized gas passes through the opened first solenoid valve 162 (or the second solenoid valve 162, the third solenoid valve 164), it is limited by the first orifice plate 165 (or the second orifice plate 166, the third orifice plate 167) to enter the third heater of the engine 3 for heat exchange with the turbine exhaust gas, and is output to the kerosene tank 120.

[0038] The arrow controller determines the opening and closing of the first to third solenoid valves according to the relationship between the tank pressure and the set pressure bands of the first to third solenoid valves.

[0039] Specifically, an upper pressure limit and a lower pressure limit are set for each solenoid valve. When the tank pressure is higher than the upper pressure limit of the solenoid valve, the solenoid valve is closed. If the tank pressure is lower than the lower pressure limit of the solenoid valve, the solenoid valve is opened. If the tank pressure is between the upper pressure limit and the lower pressure limit of the solenoid valve, the current state of the solenoid valve is maintained unchanged.

[0040] The upper and lower pressure limits of each solenoid valve can be set by the staff according to the actual situation, and the specific values ​​are not limited here.

[0041] Preferably, the number of pressurized gas cylinders is twelve.

[0042] Preferably, there are plural second one-way valves.

[0043] After the above-mentioned one or more solenoid valves are opened, the pressurized gas enters the engine heater through the orifice plate to exchange heat with the turbine exhaust gas, so that the temperature of the pressurized gas increases and the pressurization efficiency of the kerosene tank is improved.

[0044] Kerosene pressurizing gas can be selected as room temperature nitrogen. The number of nitrogen cylinders is the same as that of normal temperature helium pressurization (without heating). Since the flow rate of heated pressurized gas will not be very large, the size of pipes, valves, filters, etc. in the pressurization system does not need to be increased, and the pressurization components used for normal temperature helium pressurization can be borrowed. In addition, when using the heated pressurization solution, helium can also be used as the pressurized gas in the kerosene tank. If helium is used, the number of cylinders can be further reduced, the helium consumption can be reduced, and the weight of the rocket body can be reduced.

[0045] The top of the kerosene tank 120 is also connected to a pressure sensor, which can detect the pressure of the entire kerosene tank 120.

[0046] For a system with multiple engines connected in parallel, this embodiment can use a certain number of engines to provide self-generated supercharging of the liquid oxygen tank according to the supercharging calculation result, and the remaining engines are used for heating and supercharging the gas cylinders of the kerosene tank.

[0047] Beneficial effects of this application:

[0048] The pressurization system provided by the present application realizes both the self-pressurization of the cryogenic liquid oxygen tank and the heating and pressurization of the kerosene tank, thereby greatly increasing the pressurization efficiency of the kerosene tank. For a system with multiple engines in parallel, a certain number of engines are used to provide the self-pressurization of the liquid oxygen tank, and the remaining engines are used to heat and pressurize the gas cylinders of the kerosene tank, so that the temperature of the pressurized gas is increased, thereby improving the pressurization efficiency of the kerosene tank. The pressurized gas for the kerosene tank can use either helium or nitrogen. The pressurization system greatly reduces the amount of helium used, reduces the use of strategic resource helium in space launches, and enables my country's limited helium resources to be applied to more needed high-tech fields.

[0049] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

[0050] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A new liquid rocket supercharging system combining self-generated supercharging and cylinder heating supercharging, characterized in that: include: Liquid oxygen tank, kerosene tank, self-generated pressurization pipeline, first ground pressurization pipeline, second ground pressurization pipeline, gas cylinder heating pressurization pipeline, first heater, third heater; The first ground pressurization line is connected to the liquid oxygen tank to deliver ground pressurized gas to the liquid oxygen tank; The self-generated pressurization pipeline is connected to the liquid oxygen tank, and at the same time, the self-generated pressurization pipeline is connected to the oxygen head cavity of the thrust chamber head of the first engine and contacts the first heater. After the liquid oxygen is drawn out of the oxygen head cavity of the thrust chamber head of the first engine, it is heat-exchanged with the turbine exhaust gas through the first heater and then transported to the liquid oxygen tank for pressurization; The second ground pressurizing line is connected to the kerosene tank to deliver ground pressurized gas to the kerosene tank; The cylinder heating and pressurizing pipeline is connected with the kerosene tank and contacts with the third heater. The pressurized gas is transported to the kerosene tank after heat exchange with the exhaust gas of the turbine through the third heater.

2. The novel liquid rocket supercharging system combining self-generated supercharging and cylinder heating supercharging as claimed in claim 1 is characterized in that: It also includes a second heater. The self-pressurizing pipeline is connected to the oxygen head cavity of the thrust chamber head of the second engine and contacts the second heater. After liquid oxygen is drawn out of the oxygen head cavity of the thrust chamber head of the second engine, it is transported to the liquid oxygen storage tank for pressurization after heat exchange with the turbine exhaust gas through the second heater.

3. The novel liquid rocket supercharging system combining self-generated supercharging and heated supercharging as claimed in claim 1 is characterized in that: The first ground boosting path is also connected to a first filter and a first one-way valve.

4. The novel liquid rocket supercharging system combining self-generated supercharging and heating supercharging as claimed in claim 2 is characterized in that: The liquid oxygen drawn out from the oxygen head chamber of the thrust chamber head of the first and second engines is pure liquid oxygen.

5. The novel liquid rocket supercharging system combining autogenous supercharging and heating supercharging as claimed in claim 1 is characterized in that: The top of the liquid oxygen tank is also connected to a pressure sensor to perform pressure detection on the entire liquid oxygen tank.

6. The novel liquid rocket supercharging system combining self-generated supercharging and heated supercharging as claimed in claim 1 is characterized in that: The second ground boosting path is also connected to a second filter and a second one-way valve.

7. The novel liquid rocket supercharging system combining self-generated supercharging and heating supercharging as claimed in claim 1 is characterized in that: It also includes a plurality of pressurized gas cylinders, which are respectively connected to the charging valve and the gas cylinder heating and pressurizing pipeline, and the pressurized gas stored through the charging valve is delivered to the gas cylinder heating and pressurizing pipeline.

8. The novel liquid rocket supercharging system combining self-generated supercharging and heating supercharging as claimed in claim 7 is characterized in that: The gas cylinder heating and pressurizing pipeline is also connected with a third filter, a first solenoid valve, a second solenoid valve, a third solenoid valve, a first orifice plate, a second orifice plate and a third orifice plate.

9. The novel liquid rocket supercharging system combining self-generated supercharging and cylinder heating supercharging as claimed in claim 8 is characterized in that: The third filter is connected to one end of the first to third solenoid valves respectively, the first solenoid valve is connected to one end of the first orifice plate, and the other end of the first orifice plate is connected to the gas cylinder heating and pressurizing pipeline; the second solenoid valve is connected to one end of the second orifice plate, and the other end of the second orifice plate is connected to the gas cylinder heating and pressurizing pipeline; the third solenoid valve is connected to one end of the third orifice plate, and the other end of the third orifice plate is connected to the gas cylinder heating and pressurizing pipeline, and the gas cylinder heating and pressurizing pipeline is connected to the top of the kerosene storage tank after contacting the third heater.

10. The novel liquid rocket supercharging system combining self-generated supercharging and cylinder heating supercharging as claimed in any one of claims 1 to 9 is characterized in that: There are plural first and second one-way valves.

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