A vertical recovery rocket tank pressure supplementing and air sealing system design

Abstract

This invention specifically relates to the design of a pressurization and gas sealing system for a vertically recoverable rocket propellant tank, comprising the following steps: An auxiliary propulsion system is installed, comprising, sequentially along the gas supply direction of the pipeline, a gas cylinder, a main solenoid valve of the auxiliary propulsion system, a pressure reducing valve, and multiple thrust chambers; a branch pipeline is installed between the gas cylinder and the main solenoid valve of the auxiliary propulsion system, connecting and supplying gas to the propellant tank pressurization system and the propellant tank gas sealing system; during rocket flight, the gas cylinder supplies gas to the auxiliary propulsion system to meet attitude control requirements, and simultaneously supplies gas to the propellant tank gas sealing system to meet gas sealing requirements; after rocket landing, the solenoid valve on the propellant tank pressurization system opens, utilizing the remaining gas in the auxiliary propulsion system cylinder to meet the pressurization requirements for the released propellant. This invention eliminates the need for separate gas cylinders for the propellant tank pressurization and gas sealing systems, simplifying the propulsion system, reducing the overall system weight, and achieving high gas utilization in the auxiliary propulsion system cylinder, significantly improving rocket efficiency.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, specifically to the design of a vertically recoverable rocket propellant tank pressurization and gas sealing system. Background Technology

[0002] For vertically recoverable rockets, the propellant in the propellant tanks needs to be vented after landing, which requires pressurization. Currently, domestically deployed expendable cryogenic liquid launch vehicles typically employ gas pressurization, self-generated pressurization, and gas cylinder pressurization methods, using dedicated gas cylinders to meet the pressurization requirements. Simultaneously, after flight and landing, the exhaust valve control chamber and exhaust pipe need to be gas-sealed to prevent the cryogenic propellant from causing the exhaust valve and safety valve to freeze during cold suction; this gas sealing also requires gas cylinders. However, using dedicated gas cylinders for rocket tank pressurization and gas sealing increases system complexity and manufacturing costs. Therefore, a new vertically recoverable rocket tank pressurization and gas sealing system is needed, using a simpler gas supply system to meet the rocket tank pressurization and exhaust valve control chamber / exhaust pipe sealing requirements, while reducing the overall system weight. Summary of the Invention

[0003] This invention proposes a system for pressurizing and sealing the propellant tanks of a vertically recovered rocket using auxiliary power gas cylinders. This system significantly reduces the complexity of the propulsion system and manufacturing costs, meets the propellant tank pressurization requirements after rocket landing, thus satisfying the propellant venting requirements, and simultaneously fulfills the gas sealing requirements to prevent the exhaust valves and safety valves from freezing and malfunctioning.

[0004] The specific solution of this invention is: a design for a pressurization and gas sealing system for a vertically recovered rocket propellant tank, comprising the following steps:

[0005] S1. An auxiliary power system is set up, which includes a gas cylinder, a main solenoid valve of the auxiliary power system, a pressure reducing valve and multiple thrust chambers in sequence along the gas supply direction of the pipeline.

[0006] S2. A branch pipeline is installed between the gas cylinder and the main solenoid valve of the auxiliary power system, and gas is supplied to the tank pressurization system and the tank gas sealing system through the pipeline.

[0007] S3. During rocket flight, gas cylinders supply gas to the auxiliary power system to meet attitude control requirements, and at the same time supply gas to the propellant tank gas sealing system to meet gas sealing requirements. After the rocket lands, the solenoid valve on the propellant tank pressurization system opens, using the remaining gas in the auxiliary power system gas cylinders to meet the pressurization requirements of the released propellant.

[0008] Furthermore, the branch pipes are controlled by solenoid valves and connected to the tank pressurization system and the tank gas sealing system, respectively. The tank includes an oxidizer tank and a fuel tank. Typically, the oxidizer is liquid oxygen and the fuel is liquid methane.

[0009] Furthermore, an oxygen tank pressure replenishing solenoid valve is installed on the pipeline between the branch pipeline and the oxygen tank. The pipeline between the oxygen tank pressure replenishing solenoid valve and the oxygen tank is also connected to the ground pressurization gas pipeline and is equipped with a ground pressurization check valve.

[0010] Furthermore, an oxidant tank pressure-replenishing solenoid valve is installed between the branch pipeline and the oxidant tank. The pipeline between the oxidant tank pressure-replenishing solenoid valve and the oxidant tank is also connected to the oxidant tank ground pressurization pipeline, and an oxidant tank ground pressurization check valve is installed on the oxidant tank ground pressurization pipeline.

[0011] A fuel tank pressure replenishing solenoid valve is installed on the pipeline between the branch pipeline and the fuel tank. The pipeline between the fuel tank pressure replenishing solenoid valve and the fuel tank is also connected to the fuel tank ground pressurization pipeline. A fuel tank ground pressurization check valve is installed on the fuel tank ground pressurization pipeline.

[0012] A gas-sealing solenoid valve and an oxidant tank exhaust valve are installed on the pipeline between the branch pipeline and the oxidant tank. An oxidant tank exhaust pipe gas-sealing check valve and an oxidant tank exhaust valve control chamber gas-sealing check valve are connected in parallel on the pipeline between the gas-sealing solenoid valve and the oxidant tank exhaust valve, respectively, to gas-seal the control chamber inside the oxidant tank exhaust pipe and the oxidant tank exhaust valve.

[0013] A gas-sealing solenoid valve and a fuel tank exhaust valve are installed on the pipeline between the branch pipeline and the fuel tank. A fuel tank exhaust pipe gas-sealing check valve and a fuel tank exhaust valve control chamber gas-sealing check valve are connected in parallel on the pipeline between the gas-sealing solenoid valve and the fuel tank exhaust valve, respectively gas-sealing the control chamber inside the fuel tank exhaust pipe and the fuel tank exhaust valve.

[0014] A filter is also installed in the pipeline between the gas cylinder and the branch pipeline on the main line of the auxiliary power system.

[0015] The branch pipelines connected to the tank pressurization system and the tank gas sealing system are also equipped with multiple orifice plates to throttle the gas flowing to the tank and the gas sealing system, thereby reducing the gas pressure.

[0016] During use, the system of the present invention opens the solenoid valve according to attitude control requirements, and the high-pressure gas cylinder gas enters the thrust chamber, generating high-speed gas that is ejected to produce thrust; the on-board gas seal solenoid valve is opened, and the gas passes through the gas seal solenoid valve and the gas seal check valve in sequence into the exhaust valve control chamber and the exhaust pipe for gas sealing; after the rocket lands, the solenoid valve on the pressurization system opens, and the remaining gas in the auxiliary power system cylinder is used to pressurize the storage tank and release the remaining propellant.

[0017] Compared with existing technologies, this invention utilizes auxiliary power gas cylinders, which are connected to the propellant tank and gas sealing system via branch pipe routes and electromagnetic valves. This satisfies the attitude control requirements of the auxiliary power system, the rocket gas sealing requirements after flight and landing, and the propellant tank pressurization requirements after landing. The system is simple and easy to construct. This invention eliminates the need for separate gas cylinders for propellant tank pressurization and gas sealing systems, simplifying the overall complexity of the power system, reducing the total system weight, and achieving high gas utilization in the auxiliary power system cylinders, thus significantly improving rocket efficiency. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the design of the vertical recovery rocket tank pressurization and gas sealing system of the present invention.

[0019] Symbol Explanation: 1-Charging / Discharging Manual Valve, 2-Gas Cylinder, 3-Filter, 4-Auxiliary Power System Main Circuit Solenoid Valve, 5-Pressure Reducing Valve, 6-Auxiliary Power System Branch Circuit Solenoid Valve, 7-Thrust Chamber, 8-Oxidant Tank Pressure Replenishment Solenoid Valve, 9-Orifice Plate, 10-Gas Seal Solenoid Valve, 11-Fuel Tank Pressure Replenishment Solenoid Valve, 12-Oxidant Tank Ground Pressure Boost Check Valve, 13-Oxidant Tank Exhaust Pipe Gas Seal Check Valve, 14-Oxidant Tank Exhaust Valve Control Chamber Gas Seal Check Valve, 15-Oxidant Tank Exhaust Valve, 16-Fuel Tank Ground Pressure Boost Check Valve, 17-Fuel Tank Exhaust Valve Control Chamber Gas Seal Check Valve, 18-Fuel Tank Exhaust Pipe Gas Seal Check Valve, 19-Fuel Tank Exhaust Valve, 20-Oxidant Tank, 21-Fuel Tank, 22-Oxidant Tank Exhaust Pipe, 23-Fuel Tank Exhaust Pipe. Detailed Implementation

[0020] To facilitate understanding of the present invention, further explanation is provided below with reference to specific examples.

[0021] The present invention proposes a design for a pressurization and gas sealing system for a vertically recovered rocket propellant tank, comprising the following steps:

[0022] S1. An auxiliary power system is set up, which includes a gas cylinder, a main solenoid valve of the auxiliary power system, a pressure reducing valve and multiple thrust chambers in sequence along the gas supply direction of the pipeline.

[0023] S2. A branch pipeline is installed between the gas cylinder and the main solenoid valve of the auxiliary power system, and gas is supplied to the tank pressurization system and the tank gas sealing system through the pipeline.

[0024] S3. During rocket flight, gas cylinders supply gas to the auxiliary power system to meet attitude control requirements, and at the same time supply gas to the propellant tank gas sealing system to meet gas sealing requirements. After the rocket lands, the solenoid valve on the propellant tank pressurization system opens, using the remaining gas in the auxiliary power system gas cylinders to meet the pressurization requirements of the released propellant.

[0025] The branch pipes are controlled by solenoid valves and connected to the tank pressurization system and the tank gas sealing system, respectively. The tank includes an oxidizer tank and a fuel tank. In this embodiment, the oxidizer is oxygen and the fuel is methane.

[0026] The specific design of the system is as follows: Figure 1 As shown;

[0027] An oxygen tank pressure-boosting solenoid valve is installed on the pipeline between the branch pipeline and the oxygen tank. The pipeline between the oxygen tank pressure-boosting solenoid valve and the oxygen tank is also connected to the ground booster gas pipeline and is equipped with a ground booster check valve.

[0028] An oxidizer tank pressure-replenishing solenoid valve is installed between the branch pipeline and the oxidizer tank. The pipeline between the oxidizer tank pressure-replenishing solenoid valve and the oxidizer tank is also connected to the oxidizer tank ground pressurization pipeline. An oxidizer tank ground pressurization check valve is installed on the oxidizer tank ground pressurization pipeline.

[0029] A fuel tank pressure replenishing solenoid valve is installed on the pipeline between the branch pipeline and the fuel tank. The pipeline between the fuel tank pressure replenishing solenoid valve and the fuel tank is also connected to the fuel tank ground pressurization pipeline. A fuel tank ground pressurization check valve is installed on the fuel tank ground pressurization pipeline.

[0030] A gas-sealing solenoid valve and an oxidizer tank exhaust valve are installed on the pipeline between the branch pipeline and the oxidizer tank. An oxidizer tank exhaust pipe gas-sealing check valve and an oxidizer tank exhaust valve control chamber gas-sealing check valve are connected in parallel on the pipeline between the gas-sealing solenoid valve and the oxidizer tank exhaust valve, respectively, to gas-seal the control chamber inside the oxidizer tank exhaust pipe and the oxidizer tank exhaust valve.

[0031] The pressurization system's pipeline ultimately connects to the storage tank, and an energy dissipator is installed at the gas outlet of the pipeline to reduce the impact force on the liquid when the gas enters.

[0032] A gas-sealed solenoid valve and a fuel tank exhaust valve are installed on the pipeline between the branch pipeline and the fuel tank. A fuel tank exhaust pipe gas-sealed check valve and a fuel tank exhaust valve control chamber gas-sealed check valve are connected in parallel on the pipeline between the gas-sealed solenoid valve and the fuel tank exhaust valve, respectively gas-sealing the control chamber inside the fuel tank exhaust pipe and the fuel tank exhaust valve.

[0033] On the main auxiliary power system, filters are installed in the pipelines between the gas cylinders and branch pipelines. A manual valve for filling or releasing gas is also installed on the pipelines connected to the gas cylinders. The manual valve is used to control the filling or releasing of gas into the gas cylinders.

[0034] Multiple orifice plates are installed in the branch pipelines that connect to the tank pressurization system and the tank gas sealing system to throttle the gas flowing to the tank and the gas sealing system, thereby reducing the gas pressure.

[0035] During operation, the system of this invention opens a solenoid valve according to attitude control requirements, allowing high-pressure gas from the cylinder to enter the thrust chamber. The resulting high-speed gas ejection generates thrust. The onboard gas seal solenoid valve opens, and the gas sequentially passes through the gas seal solenoid valve, the gas seal check valve, and then into the exhaust valve control chamber and exhaust pipe for gas sealing. After landing, the solenoid valve on the repressurization system opens, utilizing the remaining gas from the auxiliary propulsion system cylinder to repressurize the propellant tank and release the remaining propellant. By utilizing the gas from the auxiliary propulsion cylinder, and connecting it to the propellant tank and gas seal system via branch pipes controlled by solenoid valves, this system satisfies the attitude control requirements of the auxiliary propulsion system, the rocket gas seal requirements after flight and landing, and the propellant release and repressurization requirements of the propellant tank after landing. This system is simple to construct, eliminates the need for separate cylinders for propellant tank repressurization and gas seal systems, simplifies the overall complexity of the propulsion system, reduces the total system weight, and achieves high gas utilization in the auxiliary propulsion system cylinders, significantly improving rocket efficiency.

Claims

1. A design method for a pressurization and gas sealing system for a vertically recovered rocket propellant tank, characterized in that, Includes the following steps: S1. An auxiliary power system is set up, which includes a gas cylinder, a main solenoid valve of the auxiliary power system, a pressure reducing valve and multiple thrust chambers in sequence along the gas supply direction of the pipeline. S2. A branch pipeline is installed between the gas cylinder and the main solenoid valve of the auxiliary power system, and the pipeline is connected to supply gas to the tank pressurization system and the tank gas sealing system. S3. During rocket flight, gas cylinders supply gas to the auxiliary power system to meet attitude control requirements, and at the same time supply gas to the propellant tank gas sealing system to meet gas sealing requirements. After the rocket lands, the solenoid valve on the propellant tank pressurization system opens, and the remaining gas in the auxiliary power system gas cylinders meets the pressurization requirements of the released propellant. A gas-sealing solenoid valve and an oxidant tank exhaust valve are installed on the pipeline between the branch pipeline and the oxidant tank. An oxidant tank exhaust pipe gas-sealing check valve and an oxidant tank exhaust valve control chamber gas-sealing check valve are connected in parallel on the pipeline between the gas-sealing solenoid valve and the oxidant tank exhaust valve, respectively gas-sealing the control chamber inside the oxidant tank exhaust pipe and the oxidant tank exhaust valve. A gas-sealing solenoid valve and a fuel tank exhaust valve are installed on the pipeline between the branch pipeline and the fuel tank. A fuel tank exhaust pipe gas-sealing check valve and a fuel tank exhaust valve control chamber gas-sealing check valve are connected in parallel on the pipeline between the gas-sealing solenoid valve and the fuel tank exhaust valve, respectively gas-sealing the control chamber inside the fuel tank exhaust pipe and the fuel tank exhaust valve.

2. The design method for a vertically recovered rocket propellant tank pressurization and gas sealing system according to claim 1, characterized in that, An oxidant tank pressure-replenishing solenoid valve is installed on the pipeline between the branch pipeline and the oxidant tank. The pipeline between the oxidant tank pressure-replenishing solenoid valve and the oxidant tank is also connected to the oxidant tank ground pressurization pipeline, which is equipped with an oxidant tank ground pressurization check valve.

3. The design method for a vertically recovered rocket propellant tank pressurization and gas sealing system according to claim 1, characterized in that, A fuel tank pressure replenishing solenoid valve is installed on the pipeline between the branch pipeline and the fuel tank. The pipeline between the fuel tank pressure replenishing solenoid valve and the fuel tank is also connected to the fuel tank ground pressurization pipeline. A fuel tank ground pressurization check valve is installed on the fuel tank ground pressurization pipeline.

4. The design method for a vertically recovered rocket propellant tank pressurization and gas sealing system according to claim 1, characterized in that, On the main auxiliary power system line, filters are also installed in the pipelines between the gas cylinders and the branch pipelines.

5. The design method for a vertically recovered rocket propellant tank pressurization and gas sealing system according to claim 1, characterized in that, The branch pipelines that connect to the tank pressurization system and the tank air sealing system are also equipped with multiple orifice plates.

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