一种补燃循环氢氧火箭发动机半系统试验系统
By using the thrust chamber as a gas exhaust device and cooling jacket in the semi-system test of the staged combustion cycle hydrogen-oxygen rocket engine, the complexity and risk of the semi-system test were solved, and higher test safety and reliability were achieved.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- BEIJING AEROSPACE PROPULSION INST
- Filing Date
- 2022-12-26
- Publication Date
- 2026-07-17
AI Technical Summary
The semi-system test of the staged combustion cycle hydrogen-oxygen rocket engine has many components and is complex, making it difficult to reduce the test risk and complexity. In addition, it requires the additional design of a simulated thrust chamber and gas emission system.
The thrust chamber is used as a gas exhaust device, and the liquid hydrogen after the pump is heated by the cooling jacket of the thrust chamber, which reduces the difficulty of high-pressure gas hydrogen. At the same time, the thrust chamber is used as the general assembly structure support of the engine test system, which simplifies the design of the gas exhaust device and simulator.
It reduces the system complexity and risk of the test bench, improves the safety and reliability of the test, and the engine semi-system assembly state is close to that of the whole system, reducing the changes in the engine assembly state.
Smart Images
Figure CN116201659B_ABST