大推力液氧煤油补燃发动机分级起动仿真分析

张睿文; 李斌; 王丹; 张晓光

doi:10.13224/j.cnki.jasp.20220555

大推力液氧煤油补燃发动机分级起动仿真分析

doi: 10.13224/j.cnki.jasp.20220555

1.
中国航天科技集团有限公司西安航天动力研究所，西安 710100
2.
中国航天科技集团有限公司航天推进技术研究院，西安 710100

详细信息

作者简介:
张睿文（1983-），男，工程师，博士，研究方向为液体火箭发动机系统设计

中图分类号: V430
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- 文章访问数: 55
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- 被引次数: 0
出版历程
- 收稿日期: 2022-07-31
- 网络出版日期: 2023-10-19

Simulation analysis of staged startup of large thrust LOX/kerosene staged combustion rocket engine

1.
Xi’an Aerospace Propulsion Institute，China Aerospace Science and Technology Corporation，Xi’an 710100，China
2.
Academy of Aerospace Propulsion Technology，China Aerospace Science and Technology Corporation，Xi’an 710100，China

摘要

摘要:
分级起动是提高大推力液氧煤油补燃发动机起动品质和发射可靠性的重要措施。通过系统动力学仿真，分析了发动机分级起动特性。采用Modelica语言开发了通用模块化液体动力系统动态特性仿真模型库（Tulips）。基于模型库，自底向上逐层构建和验证了发动机系统仿真模型。仿真结果表明：初级工况设置在推力高于额定值40%时起动品质较好；初级工况越低，进入初级工况的延迟时间越长；初级工况较低时，提前推力室点火和燃料节流阀转级时刻，有利于提高起动品质；涡轮泵转动惯量较大时，进入初级工况更平稳。
- 补燃发动机 /
- 分级起动 /
- 系统动态仿真 /
- 模型库 /
- 初级工况
Abstract:
The staged startup is an important measure to improve the startup quality and launch reliability of large thrust liquid-oxygen (LOX)/kerosene staged combustion rocket engines. The staged startup characteristics of the engine were studied by system dynamics simulation. The modular universal model library of transient simulation of liquid propulsion system (Tulips) was developed by using the Modelica language. Based on the model library, the system dynamics simulation models of the engine were built and validated layer-by-layer from bottom to top. The simulation results showed that, the startup quality was preferable when the prestage was set at the level where the thrust was higher than 40% of the rated value. The delay of entering the prestage was longer if the level of the prestage was lower. When the level of the prestage was low, the startup quality can be improved by advancing the moment of igniting the thrust chamber and the moment of transferring the resistance condition of the fuel throttle valve. If the turbopump rotational inertia was larger, the system became more stable when entering the prestage.
- staged combustion rocket engine /
- staged startup /
- simulation of system dynamic characteristics /
- model library /
- prestage

HTML

图 1 典型大推力液氧煤油补燃发动机系统原理图

Figure 1. Schematic of the typical large thrust LOX/kerosene staged combustion rocket engine system

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图 2 发动机分级起动过程

Figure 2. Staged startup process of the engine

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图 3 MWorks中的模型库结构树

Figure 3. Structure tree of the simulation model library in MWorks

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图 4 接口变量

Figure 4. Parameters of the interfaces

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图 5 发动机系统仿真模型

Figure 5. Simulation model of the engine system

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图 6 仿真模型的试验验证

Figure 6. Validation of the simulation models by physical experiments

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图 7 分级起动过程仿真结果

Figure 7. Simulation results of the staged startup process

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图 8 不同初级工况的起动特性

Figure 8. Startup characteristics of the engine with different prestages

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图 9 不同时序的起动特性

Figure 9. Startup characteristics of the engine with different timing sequences

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图 10 转级速率对起动特性的影响

Figure 10. Effects of the transfer rate on startup characteristics

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图 11 发生器容积对起动特性的影响

Figure 11. Effects of the gas generator volume on the startup characteristics

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图 12 燃气导管容积对起动特性的影响

Figure 12. Effects of the gas pipe volume on the startup characteristics

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图 13 系统惯性对起动特性的影响

Figure 13. Effects of the inertia on the startup characteristics

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图 14 起动方案优化

Figure 14. Improvement of the startup scheme

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