Liquid carrier rocket pressurization system and pressurization method

Abstract

The invention discloses a liquid carrier rocket pressurization system and method, and belongs to the technical field of carrier rocket power, and the liquid carrier rocket pressurization system comprises an extrusion gas storage device, a carbon dioxide storage device, an extrusion pipeline and a pressurization pipeline; the carbon dioxide storage device comprises a gas extrusion cavity and a carbon dioxide storage cavity; the carbon dioxide storage device is communicated with the extrusion gas storage device through an extrusion pipeline; the carbon dioxide storage device is communicated with the propellant storage tank through a pressurizing pipeline; a supercharging device is arranged on the supercharging pipeline; and the supercharging device is configured to gasify the liquid carbon dioxide passing through the interior of the supercharging device and supercharge the liquid carbon dioxide to preset pressure so as to extrude the propellant in the propellant storage cavity in the propellant storage box. Pressurizing is carried out in a normal-temperature carbon dioxide gasification mode, normal-temperature inflation and normal-temperature filling can be carried out in the launching preparation stage, the scheme is simple, and the system reliability is high.

Description

Technical Field

[0001] The present invention relates to the field of launch vehicle power technology, and in particular to a liquid launch vehicle pressurization system and a pressurization method. Background Art

[0002] In order to ensure the rigidity of the tank during the rocket flight and meet the inlet pressure requirements of the engine pump, a certain amount of gas needs to enter the tank for pressurization during the flight. Common pressurization methods often include using engine gas to pressurize, using the gas generated by the gasification of the propellant itself for self-pressurization, or carrying an additional gas storage system for gas storage pressurization.

[0003] The liquid oxygen-kerosene propellant combination is currently the mainstream rocket propellant combination in China, and kerosene tanks are almost all gas storage-type pressurization, usually room temperature helium pressurization or helium heated pressurization, as well as cold helium pressurization to increase helium utilization. As helium is a strategic resource, its cost is relatively high. The emergence of liquid nitrogen vaporization pressurization in recent years can effectively reduce costs.

[0004] In daily practice, it is found that the existing technical solutions have the following problems:

[0005] The helium pressurization solution mainly takes advantage of the low density of helium. In order to maximize its advantages, the room temperature high-pressure helium is usually heated to a high temperature, or the high-pressure cold helium is directly heated to a high temperature to improve the utilization rate of helium. However, helium is a strategic resource and is expensive. In addition, helium itself has a small molecular weight and is prone to leakage, making storage difficult. The cold helium storage solution requires a cold helium heat exchanger on the ground during the rocket refueling phase. The refueling process is complicated and the ground equipment is huge.

[0006] The liquid nitrogen pressurization solution reduces the dependence on helium, and nitrogen is a common gas with low cost, but liquid nitrogen needs to be stored at low temperature. During the filling process, it is immersed in liquid oxygen and filled with liquid nitrogen to maintain a low temperature to prevent evaporation. Liquid nitrogen pressurization also requires a ground-based liquid nitrogen filling system. The filling process is complicated and the ground equipment is huge.

[0007] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the invention

[0008] In order to solve the above-mentioned technical problems, the present application provides a liquid carrier rocket pressurization system and pressurization method, which utilizes the gasification of carbon dioxide at room temperature for pressurization, and can perform room-temperature inflation and room-temperature refueling during the launch preparation stage. The solution is simple and the system reliability is high.

[0009] A liquid launch vehicle pressurization system, comprising:

[0010] squeezed gas storage device;

[0011] A carbon dioxide storage device; the carbon dioxide storage device comprises a gas extrusion chamber and a carbon dioxide storage chamber; liquid carbon dioxide is stored in the carbon dioxide storage chamber;

[0012] An extrusion pipeline; the inlet end of the extrusion pipeline is communicated with the extrusion gas storage device, and the outlet end of the extrusion pipeline is communicated with the gas extrusion chamber; a deflation valve and a decompression device are provided on the extrusion pipeline; the decompression device is configured to decompress the gas in the extrusion gas storage device to a preset pressure to extrude the liquid carbon dioxide in the carbon dioxide storage chamber;

[0013] A pressurizing pipeline; the inlet end of the pressurizing pipeline is communicated with the carbon dioxide storage chamber, and the outlet end of the pressurizing pipeline is communicated with the extrusion chamber in the propellant tank; a pressurizing device is arranged on the pressurizing pipeline; the pressurizing device is configured to gasify the liquid carbon dioxide passing through the inside thereof and pressurize it to a preset pressure so as to squeeze out the propellant in the propellant storage chamber in the propellant tank.

[0014] Preferably, the boosting device is an engine heat exchanger having pipelines inside.

[0015] Preferably, it further comprises a flow regulating device disposed on the boosting pipeline between the outlet of the carbon dioxide storage chamber and the boosting device.

[0016] Preferably, the flow regulating device comprises a plurality of parallel flow regulating pipelines; each of the flow regulating pipelines is provided with a boosting valve and an orifice plate.

[0017] Preferably, the orifice plate is used to calibrate the flow rate on the corresponding flow regulating pipeline.

[0018] Preferably, it also includes a liquid filling pipe for filling liquid carbon dioxide into the carbon dioxide storage chamber; and a filling valve is arranged on the liquid filling pipe.

[0019] Preferably, it also includes an air circuit filling pipe for filling the squeezed air storage device with squeezed air; and an air charging valve is arranged on the air circuit filling pipe.

[0020] Preferably, the gas stored in the squeezed gas storage device is nitrogen or helium.

[0021] According to another aspect of the present application, a liquid launch vehicle pressurization method is also provided, which uses the liquid launch vehicle pressurization system to perform pressurization, comprising:

[0022] Before the rocket is launched, the compressed gas storage device is filled with compressed gas and the carbon dioxide storage chamber is filled with liquid carbon dioxide;

[0023] After the rocket is launched, the vent valve is opened, and the gas in the squeezed gas storage device is decompressed by the decompression device to the pressure required to squeeze out the liquid carbon dioxide in the carbon dioxide storage chamber;

[0024] Liquid carbon dioxide enters the extrusion cavity of the propellant tank through a pressurizing pipeline provided with a pressurizing device, and squeezes out the propellant in the propellant storage cavity in the propellant tank.

[0025] Compared with the prior art, this application has at least the following beneficial effects:

[0026] 1. The present invention utilizes the gasification of liquid carbon dioxide at room temperature for pressurization. There is no low-temperature storage in existing pressurization schemes. Normal-temperature inflation and normal-temperature refueling can be performed during the launch preparation stage. The scheme is simple and the system reliability is high.

[0027] 2. The present invention stores carbon dioxide in liquid form by pressurizing at room temperature, thereby increasing the storage rate of the medium.

[0028] 3. The present invention utilizes liquid carbon dioxide to pressurize the storage tank after heating, thereby improving the utilization rate of gas pressurization.

[0029] 4. The liquid launch vehicle booster system of the present invention is provided with a flow regulating device, which makes the outflow in the propellant tank a constant pressure extrusion state, thereby reducing the interference caused by pressure fluctuations.

[0030] 5. The liquid carrier rocket pressurization system of the present invention has no low-temperature state, is reliable and safe, and the carbon dioxide gas is low in price and easy to obtain. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale.

[0032] In the figure:

[0033] Figure 1 It is a schematic diagram of the liquid launch vehicle pressurization system of the present invention.

[0034] The above drawings include the following reference numerals:

[0035] 1. Extrusion pipeline; 2. Carbon dioxide storage device; 3. Filling valve; 4. Liquid filling pipe; 5. Booster valve; 6. Flow regulating pipeline; 7. Orifice plate; 8. Engine heat exchanger; 9. Booster pipeline; 10. Propellant tank; 11. Gas filling pipe; 12. Inflating valve; 13. Extruded gas storage device; 14. Deflation valve; 15. Pressure reducing device. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.

[0037] like Figure 1 As shown, a liquid launch vehicle pressurization system includes: an extruded gas storage device 13, a carbon dioxide storage device 2; an extrusion pipeline 1 and a pressurization pipeline 9.

[0038] The carbon dioxide storage device 2 includes a gas extrusion chamber and a carbon dioxide storage chamber which are independently arranged, and liquid carbon dioxide is stored in the carbon dioxide storage chamber. The carbon dioxide storage device 2 has a similar structure to the propellant tank 10, and can discharge the liquid carbon dioxide in the carbon dioxide storage chamber through the extrusion of the gas extrusion chamber.

[0039] The inlet end of the extrusion pipeline 1 is connected to the extrusion gas storage device 13, and the outlet end is connected to the gas extrusion chamber. At the same time, the extrusion pipeline 1 is provided with a vent valve 14 and a pressure reducing device 15; the pressure reducing device 15 is configured to reduce the pressure of the gas in the extrusion gas storage device 13 to a preset pressure to squeeze out the liquid carbon dioxide in the carbon dioxide storage chamber. Among them, the pressure reducing device 15 is preferably a pressure reducing valve or a pressure reducing orifice plate.

[0040] The inlet end of the boosting pipeline 9 is connected to the carbon dioxide storage chamber, and the outlet end of the boosting pipeline 9 is connected to the extrusion chamber in the propellant tank 10; a boosting device is provided on the boosting pipeline 9; the boosting device is configured to gasify the liquid carbon dioxide passing through the inside thereof and pressurize it to a preset pressure so as to squeeze out the propellant in the propellant storage chamber in the propellant tank 10.

[0041] In this embodiment, the boosting device is an engine heat exchanger 8 with a pipeline inside. The pipeline inside the engine heat exchanger 8 is used to connect the engine heat exchanger 8 with the boosting pipeline 9, thereby achieving heat exchange. It should be noted that the engine heat exchanger 8 is a heat exchange device used in a rocket engine system, and its main function is to achieve heat transfer and exchange to meet the needs of the rocket engine at different working stages. In a rocket engine, the heat of high-temperature fuel gas is usually used to heat or vaporize low-temperature propellant, or low-temperature propellant is used to cool high-temperature engine components.

[0042] Preferably, the gas stored in the squeezed gas storage device 13 is nitrogen or helium.

[0043] Furthermore, a liquid launch vehicle pressurization system further includes a liquid filling pipe 4 for filling liquid carbon dioxide into the carbon dioxide storage chamber; a filling valve 3 for controlling the on-off of the liquid filling pipe 4 is arranged on the liquid filling pipe 4. The filling valve 3 is preferably a manual valve.

[0044] Furthermore, a liquid launch vehicle pressurization system further includes a gas circuit filling pipe 11 for filling the squeezed gas into the squeezed gas storage device 13. The gas circuit filling pipe 11 is provided with a charging valve 12 for controlling its on-off. The charging valve 12 is preferably a manual valve.

[0045] Carbon dioxide is a non-toxic medium. It can be liquefied at room temperature above 3MPa. Liquid carbon dioxide with a high density can be obtained immediately by slightly pressurizing it, and the density changes little with increasing pressure. This solution takes advantage of the easy liquefaction of carbon dioxide gas. After liquefying the gaseous carbon dioxide under certain pressure conditions, it is stored in a normal temperature gas cylinder, which reduces the difficulty of the complex operation of filling and replenishing gas during the filling stage. At the same time, carbon dioxide is a common gas, cheap and easy to obtain.

[0046] During the rocket flight, the liquid carbon dioxide in the pressurizing device is heated and gasified, thereby pressurizing the propellant tank 10. This solution improves the storage efficiency by storing liquid carbon dioxide at room temperature, and improves the utilization rate of the pressurized gas by heating, which not only reduces the pressurization cost, but also reduces the complexity of the system by filling and storing at room temperature.

[0047] As another embodiment of the present invention, a liquid launch vehicle pressurization system further includes a flow regulating device disposed on a pressurization pipeline 9 between the outlet of the carbon dioxide storage chamber and the pressurization device. The flow regulating device includes a plurality of parallel flow regulating pipelines 6, each of which is provided with an orifice plate 7 and a pressurization valve 5 for controlling the on-off of the corresponding flow regulating pipeline 6. The pressurization valve 5 is preferably a solenoid valve.

[0048] As another embodiment of the present invention, a pressure sensor is provided in the carbon dioxide storage device 2, and the boost valve 5 can be opened and closed or the opening degree controlled according to the pressure data output by the pressure sensor.

[0049] As another embodiment of the present invention, the orifice plate 7 is used to calibrate the flow on the corresponding flow regulating pipeline 6 .

[0050] It should be noted that when the fluid passes through the orifice plate, due to the throttling effect of the orifice plate, the flow velocity of the fluid increases and the pressure decreases when passing through the small holes of the orifice plate, forming a pressure difference before and after the orifice plate. According to the Bernoulli equation and flow formula, the flow rate of the fluid can be calculated by measuring the pressure difference.

[0051] As another embodiment of the present invention, a boosting device in a liquid carrier rocket boosting system is not arranged on the boosting pipeline 9, but is arranged in the carbon dioxide storage device 2, and utilizes heating to gasify liquid carbon dioxide in a self-generated boosting manner, thereby achieving the purpose of boosting.

[0052] Based on the same inventive concept, a liquid launch vehicle pressurization method is also provided, which uses the liquid launch vehicle pressurization system described in the claims to perform pressurization, comprising the following steps:

[0053] S1. Before the rocket is launched, the squeezed gas storage device is filled with squeezed gas and the carbon dioxide storage chamber is filled with liquid carbon dioxide.

[0054] S2. After the rocket is launched, the vent valve is opened and the gas in the squeezed gas storage device 13 is decompressed by the decompression device to the pressure required to squeeze out the liquid carbon dioxide in the carbon dioxide storage chamber.

[0055] S3. Liquid carbon dioxide enters the extrusion cavity of the propellant tank through a pressurizing pipeline provided with a pressurizing device, and squeezes out the propellant in the propellant storage cavity in the propellant tank.

[0056] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0057] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0058] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0059] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A liquid launch vehicle pressurization system, characterized in that: include: squeezed gas storage device; Carbon dioxide storage devices; The carbon dioxide storage device comprises a gas extrusion chamber and a carbon dioxide storage chamber; liquid carbon dioxide is stored in the carbon dioxide storage chamber; Extrusion pipe; The inlet end of the extrusion pipeline is communicated with the extrusion gas storage device, and the outlet end of the extrusion pipeline is communicated with the gas extrusion chamber; a deflation valve and a decompression device are provided on the extrusion pipeline; the decompression device is configured to decompress the gas in the extrusion gas storage device to a preset pressure, so as to extrude the liquid carbon dioxide in the carbon dioxide storage chamber; A pressurizing pipeline; the inlet end of the pressurizing pipeline is communicated with the carbon dioxide storage chamber, and the outlet end of the pressurizing pipeline is communicated with the extrusion chamber in the propellant tank; a pressurizing device is arranged on the pressurizing pipeline; the pressurizing device is configured to gasify the liquid carbon dioxide passing through the inside thereof and pressurize it to a preset pressure so as to squeeze out the propellant in the propellant storage chamber in the propellant tank.

2. The liquid launch vehicle pressurization system according to claim 1, characterized in that: The supercharging device is an engine heat exchanger with pipelines inside.

3. The liquid launch vehicle pressurization system according to claim 2, characterized in that: It also includes a flow regulating device disposed on the pressurizing pipeline between the outlet of the carbon dioxide storage chamber and the pressurizing device.

4. The liquid launch vehicle pressurization system according to claim 3, characterized in that: The flow regulating device comprises a plurality of parallel flow regulating pipelines; each of the flow regulating pipelines is provided with a boosting valve and an orifice plate.

5. The liquid launch vehicle pressurization system according to claim 4, characterized in that: The orifice plate is used to calibrate the flow rate on the corresponding flow regulating pipeline.

6. The liquid launch vehicle pressurization system according to claim 1, characterized in that: It also includes a liquid filling pipe for filling liquid carbon dioxide into the carbon dioxide storage chamber; the liquid filling pipe is provided with a filling valve.

7. The liquid launch vehicle pressurization system according to claim 1, characterized in that: It also includes an air circuit filling pipe for filling the squeezed air into the squeezed air storage device; the air circuit filling pipe is provided with an inflation valve.

8. The liquid launch vehicle pressurization system according to claim 1, characterized in that: The gas stored in the squeezed gas storage device is nitrogen or helium.

9. A method for pressurizing a liquid launch vehicle, characterized in that: The liquid launch vehicle boosting system according to any one of claims 1 to 8 is used for boosting, comprising: Before the rocket is launched, the compressed gas storage device is filled with compressed gas and the carbon dioxide storage chamber is filled with liquid carbon dioxide; After the rocket is launched, the vent valve is opened, and the gas in the squeezed gas storage device is decompressed by the decompression device to the pressure required to squeeze out the liquid carbon dioxide in the carbon dioxide storage chamber; Liquid carbon dioxide enters the extrusion cavity of the propellant tank through a pressurizing pipeline provided with a pressurizing device, and squeezes out the propellant in the propellant storage cavity in the propellant tank.

Images