Multi-liquid hydrogen storage tank parallel-connection injection method for hydrogen-oxygen rocket tests

Abstract

The invention discloses a multi-liquid hydrogen storage tank parallel-connection injection method for hydrogen-oxygen rocket tests. A multi-storage tank parallel-connection system consists of a precooling injection storage tank group 1, a small-flow injection storage tank group 2, a large-flow injection storage tank group 3, a liquid hydrogen storage tank 4, branch pipelines 5, a main pipeline 6, precooling isolating valves7, small-flow isolating valves 8, a main liquid discharge valve 9, liquid hydrogen storage tank supply and discharge valves 10, a liquid hydrogen storage tank self-pressurizing system 11, and a hydrogen-oxygen rocket 12. Due to function grouping of the storage tanks and switching of the isolating valves, isolation of different flow procedures of precooling, small-flow injection and large-flow injection can be achieved; due to adoption of the liquid hydrogen storage tank self-pressurizing system, effective control on flow, temperature and liquid level in the injection process is achieved; due to arrangement and switching of pipeline components, and an abutting structure of branch / main pipelines, fluctuation impact of the injection process can be eliminated. The multi-liquid hydrogen storage tank parallel-connection injection method disclosed by the invention is simple and reliable, and is already successfully applied.

Description

technical field

[0001] The invention relates to a liquid hydrogen filling method, which is used for rocket body dynamic test or shooting range launch of hydrogen-oxygen carrier rocket, and belongs to the field of carrier rocket ground engineering application. Background technique

[0002] When a hydrogen-oxygen launch vehicle is undergoing large-scale ground tests, it is necessary to fill the hydrogen tank of the rocket body with liquid hydrogen propellant, and the filling amount is nearly a thousand cubic meters. Due to the large amount of filling and consumption of hydrogen tanks in the rocket body, and the limited volume of liquid hydrogen storage tanks on the ground, multiple liquid hydrogen storage tanks are required to provide them at the same time. In addition, the liquid hydrogen filling process is complex, divided into pre-cooling filling, small flow filling and large flow filling; the diameter, length and flow components connected to the branch pipeline of the liqu...

Examples

Embodiment Construction

[0008] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0009] As shown in the accompanying drawings, the present invention consists of a precooling filling storage tank group 1, a small flow filling storage tank group 2, a large flow filling storage tank group 3, a liquid hydrogen storage tank 4, a branch pipeline 5, a main pipeline 6, It is composed of pre-cooling cut-off valve 7, small flow cut-off valve 8, total liquid outlet valve 9, liquid hydrogen storage tank filling and discharging valve 10, liquid hydrogen storage tank self-pressurization system 11 and other parts. First of all, when designing the branch pipeline and the main pipeline, the angle β between the branch pipeline and the main pipeline is considered, generally 30°~45°, which reduces the impact during the confluence process of the branch pipeline and is conducive to the stability of filling. Furthermore, according to the distan...

technical field

[0001] The invention relates to a liquid hydrogen filling method, which is used for rocket body dynamic test or shooting range launch of hydrogen-oxygen carrier rocket, and belongs to the field of carrier rocket ground engineering application. Background technique

[0002] When a hydrogen-oxygen launch vehicle is undergoing large-scale ground tests, it is necessary to fill the hydrogen tank of the rocket body with liquid hydrogen propellant, and the filling amount is nearly a thousand cubic meters. Due to the large amount of filling and consumption of hydrogen tanks in the rocket body, and the limited volume of liquid hydrogen storage tanks on the ground, multiple liquid hydrogen storage tanks are required to provide them at the same time. In addition, the liquid hydrogen filling process is complex, divided into pre-cooling filling, small flow filling and large flow filling; the diameter, length and flow components connected to the branch pipeline of the liqu...

Examples

Embodiment Construction

[0008] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0009] As shown in the accompanying drawings, the present invention consists of a precooling filling storage tank group 1, a small flow filling storage tank group 2, a large flow filling storage tank group 3, a liquid hydrogen storage tank 4, a branch pipeline 5, a main pipeline 6, It is composed of pre-cooling cut-off valve 7, small flow cut-off valve 8, total liquid outlet valve 9, liquid hydrogen storage tank filling and discharging valve 10, liquid hydrogen storage tank self-pressurization system 11 and other parts. First of all, when designing the branch pipeline and the main pipeline, the angle β between the branch pipeline and the main pipeline is considered, generally 30°~45°, which reduces the impact during the confluence process of the branch pipeline and is conducive to the stability of filling. Furthermore, according to the distan...

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