阀门开启时差对150 N自燃推进剂发动机工作过程的影响

陈锐达; 田增; 陈泓宇; 徐辉

doi:10.13224/j.cnki.jasp.20220683

阀门开启时差对150 N自燃推进剂发动机工作过程的影响

doi: 10.13224/j.cnki.jasp.20220683

陈锐达^{1, 2,},
田增^{1, 2},
陈泓宇^{1, 2},
徐辉^{1, 2}

1.
中国航天科技集团有限公司上海空间推进研究所，上海 201112
2.
上海空间发动机工程技术研究中心，上海 201112

基金项目: “十四五”装备预研共用技术项目（50922010XXX）

详细信息

作者简介:
陈锐达（1995-），男，工程师，硕士，主要从事空间液体火箭发动机研究

中图分类号: V434
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- 文章访问数: 69
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- 被引次数: 0
出版历程
- 收稿日期: 2022-09-13
- 网络出版日期: 2023-11-06

Effect of valve opening time difference on working process of 150 N hypergolic propellant liquid rocket engine

CHEN Ruida^{1, 2
,},
TIAN Zeng^{1, 2},
CHEN Hongyu^{1, 2},
XU Hui^{1, 2}

1.
Shanghai Institute of Space Propulsion，China Aerospace Science and Technology Corporation，Shanghai 201112，China
2.
Shanghai Engineering Research Center of Space Engine，Shanghai 201112，China

摘要

摘要:
为了研究阀门较大开启时差对采用自燃推进剂的空间液体火箭发动机工作过程的影响，对150 N发动机开展高空模拟热试车，考察了氧阀、燃阀分别先开40、100、500、1 000 ms对发动机工作稳定性、点火推力峰值和响应时间的影响。试验结果表明，发动机均可以成功点火，稳定后的推力值基本不变。氧阀先开、燃阀先开时的点火推力峰值分别约为稳定推力的1.01～1.05倍和 1.04～1.07倍，与两阀同步信号开启时相当。燃阀先开时，启动响应时间延长了约16 ms。阀门单独打开时，氧化剂发生了充分闪蒸，流场中部夹杂冰粒喷出，燃料发生了部分闪蒸。当阀门开启时差达到500、1 000 ms时，氧阀、燃阀单独打开过程中，输出推力分别约11、6 N，分别占稳定推力的7%和4%，且后者输出推力呈现波动下降的趋势。
- 液体火箭发动机 /
- 阀门开启时差 /
- 工作稳定性 /
- 点火推力峰 /
- 启动响应时间 /
- 推进剂闪蒸
Abstract:
In order to study the effect of the valve opening time difference on the working process of the space liquid rocket engine using hypergolic propellants, the high-altitude simulated thermal test of a 150 N engine was carried out. The engine working stability, ignition thrust peak and response time were investigated when the oxidant valve and fuel valve were opened 40, 100, 500, 1000 ms in advance, respectively. The test results showed that the engine can be successfully ignited, and the thrust after stabilization was basically unchanged. When the oxidant valve and the fuel valve were opened first, the ignition thrust peak of the engine was about 1.01—1.05 times and 1.04—1.07 times of the stable thrust, respectively, which was equivalent to the opening of the two-way valve synchronous signal. When the fuel valve was opened first, the startup response time was extended by about 16 ms. When the valve was opened alone, the oxidant was fully vaporized, the ice particles were ejected in the middle area of the flow field, and the fuel was partially vaporized. When the valve opening time difference reached 500 and 1000 ms, while the oxidant valve and the fuel valve were opened separately, the output thrust of the engine was about 11 N and 6 N, respectively, accounting for 7% and 4% of the stable thrust respectively, and the output thrust of the latter fluctuated and kept falling.
- liquid rocket engine /
- valve opening time difference /
- working stability /
- ignition thrust peak /
- starting response time /
- propellant gasification

HTML

图 1 发动机高空模拟热试车系统图

Figure 1. Schematic of high-altitude simulated thermal test system

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图 2 发动机工作曲线（阀门同步信号开启）

Figure 2. Curves of engine working parameters（valves open synchronously）

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图 3 发动机在试车台上点火照片

Figure 3. Photo of the engine igniting on the test bench

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图 4 发动机推力参数变化曲线（阀门先开1 000 ms）

Figure 4. Curves of engine thrust parameters （valve opens 1 000 ms in advance）

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图 5 阀门先开1000 ms时发动机单路推进剂喷出状态

Figure 5. Engine state of ejecting single-channel propellant when valve opens 1000 ms in advance

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图 6 不同阀门开启时差下发动机点火推力峰变化曲线

Figure 6. Curves of engine ignition thrust peak under different valve opening time differences

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图 7 氧阀先开时发动机工作参数曲线

Figure 7. Curves of engine working parameters when oxygen valve opens in advance

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图 8 燃阀先开时发动机工作参数曲线

Figure 8. Curves of engine working parameters when fuel valve opens in advance

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图 9 发动机启动段推力变化曲线

Figure 9. Curves of thrust variation during engine start-up

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图 10 氧阀先开1 000 ms时发动机温度参数变化

Figure 10. Variation of engine temperature parameters with oxygen valve opens 1 000 ms in advance

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表 1 150 N发动机理论设计参数

Table 1. Theoretical design parameters of 150 N engine

真空推力/N	氧化剂质量流量/（g/s）	燃料质量流量/（g/s）
150	32.15	19.48

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表 2 高空模拟热试车工况

Table 2. Condition of high-altitude simulated thermal test

序号	工况	真空推力/N	氧化剂入口压力/MPa	燃料入口压力/MPa	试车程序
1#	正常同步开启	150	1.36	1.30	30 s
2#	氧阀先开40 ms	150	1.36	1.30	2 s×100
3#	氧阀先开100 ms	150	1.36	1.30	2 s×100
4#	氧阀先开500 ms	150	1.36	1.30	2 s×100
5#	氧阀先开1000 ms	150	1.36	1.30	2 s×100
6#	燃阀先开40 ms	150	1.36	1.30	2 s×100
7#	燃阀先开100 ms	150	1.36	1.30	2 s×100
8#	燃阀先开500 ms	150	1.36	1.30	2 s×100
9#	燃阀先开1000 ms	150	1.36	1.30	2 s×100

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表 3 不同阀门开启时差下发动机工作参数

Table 3. Engine operating parameters under different valve opening time differences

序号	工况	推力均值/N	推力峰均值/MPa	推力峰最大值/MPa	发动机启动时间/ms	发动机关闭时间/ms	试车程序
1#	正常同步开启	152.4	160.5	160.5	68	81	30 s
2#	氧阀先开40 ms	151.3	158.4	159.9	71	82	2 s×100
3#	氧阀先开100 ms	152.6	154.1	155.5	67	82	2 s×100
4#	氧阀先开500 ms	153.7	157.9	158.8	68	82	2 s×100
5#	氧阀先开1000 ms	153.8	158.5	159.6	71	74	2 s×100
6#	燃阀先开40 ms	152.0	159.8	162.0	87	82	2 s×100
7#	燃阀先开100 ms	153.2	160.4	162.1	89	83	2 s×100
8#	燃阀先开500 ms	153.8	160.5	161.7	86	76	2 s×100
9#	燃阀先开1 000 ms	153.4	164.1	164.9	81	72	2 s×100

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表 4 不同工况下发动机身部温度变化结果

Table 4. Results of engine body temperature under different working conditions

序号	工况	温度/℃		试车程序
序号	工况	直线段	喉部	试车程序
1#	正常同步开启	1165	1096	30 s
2#	氧阀先开40 ms	1009	832	2 s×100
3#	氧阀先开100 ms	1017	831	2 s×100
4#	氧阀先开500 ms	947	832	2 s×100
5#	氧阀先开1000 ms	872	831	2 s×100
6#	燃阀先开40 ms	1051	831	2 s×100
7#	燃阀先开100 ms	1003	830	2 s×100
8#	燃阀先开500 ms	970	830	2 s×100
9#	燃阀先开1000 ms	888	830	2 s×100

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