火箭增压输送系统减压阀出口压力性能改进研究

doi:10.11832/j.issn.1000-4858.2022.12.023

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液压与气动 ›› 2022, Vol. 46 ›› Issue (12) : 168-176. DOI: 10.11832/j.issn.1000-4858.2022.12.023

综合应用

火箭增压输送系统减压阀出口压力性能改进研究

张明¹, 臧辉¹, 郭志海¹, 杨丽曼², 石玉鹏¹

作者信息 +

Improvement of Rocket Pressurization System Pneumatic Reducing Valve Pressure Performance

ZHANG Ming¹, ZANG Hui¹, GUO Zhi-hai¹, YANG Li-man², SHI Yu-peng¹

Author information +

History +

摘要

为解决液体火箭增压输送系统气体减压阀在生产和飞行试验中出现的出口压力长时间持续下降问题,基于实测摩擦力提出了O形圈黏弹摩擦特性对减压阀出口压力的影响机理。使用修正摩擦力后的减压阀仿真模型复现了该减压阀出口压力长时间持续下降现象,并提出改进方案。样机验证试验表明,改进后减压阀出口压力长时间下降现象明显改善,减压阀精度提高约30%,验证了改进方案的有效性和O形圈黏弹摩擦特性对减压阀出口压力影响机理的正确性。

Abstract

The effects of rubber O-rings viscous friction characteristics on pneumatic reducing valve pressure performance were put forward based on experiment measured friction to solve the valve outlet pressure long-term decreasing problem during production and flight testing, which pneumatic reducing valve that was used in liquid rocket pressurization system. Based on the valve simulation model using the modified friction force, the outlet pressure long-term decreasing phenomenon was repeated and improved scheme was proposed. The prototype experiments show that, the valve outlet pressure long-term decreasing phenomenon was obviously improved and the valve accuracy was increased by about 30%. Finally, the effectiveness of the improved schemes and the theory correctness of the effects of rubber O-rings viscous friction characteristics on pneumatic reducing valve outlet pressure performance were validated.

导出引用

张明, 臧辉, 郭志海, 杨丽曼, 石玉鹏. 火箭增压输送系统减压阀出口压力性能改进研究[J].液压与气动, 2022, 46(12): 168-176. https://doi.org/10.11832/j.issn.1000-4858.2022.12.023

ZHANG Ming, ZANG Hui, GUO Zhi-hai, YANG Li-man, SHI Yu-peng. Improvement of Rocket Pressurization System Pneumatic Reducing Valve Pressure Performance[J]. CHINESE HYDRAULICS & PNEUMATICS, 2022, 46(12): 168-176. https://doi.org/10.11832/j.issn.1000-4858.2022.12.023

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Received	Revised	Published
2022-05-11	2022-06-25	2022-12-15
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2022-12-21

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