Multi-start system with pneumatic pressurizing units for liquid-propellant rocket engine

Abstract

The invention relates to a multi-start system with pneumatic pressurizing units for a liquid-propellant rocket engine, and belongs to the field of design of start systems for pump pressure type liquid-propellant rocket engines. The multi-start system comprises the two pneumatic pressurizing units, a pressurizing gas source, a gas generator, two turbopumps, two control valves and two upward check valves. The two pneumatic pressurizing units communicate with the pressurizing gas source respectively. Each pneumatic pressurizing unit communicates with one end of one control valve and one end of one upward check valve respectively. The other ends of the two control valves both communicate with the gas generator. The other end of each upward check valve communicates with one turbopump. The two turbopumps both communicate with an exhaust pipeline of the gas generator. An oxidizing agent is supplied into one pneumatic pressurizing unit and the corresponding turbopump, and fuel is supplied intothe other pneumatic pressurizing unit and the corresponding turbopump respectively. The multi-start system with the pneumatic pressurizing units has the advantages of being simple in system, light instructural mass, high in work efficiency, high in consistency of working conditions of all starts, and low in gas consumption.

Description

technical field [0001] The invention belongs to the design field of a pump-pressed liquid rocket engine starting system, and relates to a multiple starting system of a liquid rocket engine pneumatic supercharging device. Background technique [0002] In order to meet the needs of space launch missions such as multi-satellite launch, deep space exploration, and orbital service technology, the main engine of the upper stage needs to have the ability to start more than 20 times. At the same time, in order to reduce the structural quality as much as possible and improve the carrying capacity of the upper stage, the multi-start system of the main engine needs to share the pressurized air source with the attitude control engine. [0003] At present, domestic pump-pressed liquid rocket engines are generally started by propellant starters, which are used to perform one-time or two-start tasks. If more than 20 multiple starts are required, more than 20 propellant starters need to be ...

AI Technical Summary

Problems solved by technology

[0003] At present, domestic pump-pressed liquid rocket engines are generally started by propellant starters, which are used to perform one-time or two-start tasks. If more than 20 multiple starts are required, more than 20 propellant starters need to be installed. Complex system, high structural quality and poor reliability

[0004] In addition, in the development of an upper stage engine with multiple starts, in order to realize the multiple start capability of more than 20 times, a starter box type multiple start system is proposed. However, in this starting method, the starter box needs to be filled repeatedly, causing the engine to start and accelerate slowly. At the same time, the pressure of the starter box is more sensitive to the ambient temperature, resulting in poor consistency of each start.

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