宇航计测技术 ›› 2023, Vol. 43 ›› Issue (2): 20-26.doi: 10.12060/j.issn.1000-7202.2023.02.04

• 量值传递技术 • 上一篇    下一篇

液体火箭发动机推力自动校准系统仿真

赵恒,朱子环   

  1. 北京航天试验技术研究所,北京 100074
  • 出版日期:2023-04-21 发布日期:2023-06-21
  • 作者简介:赵恒(1998-),男,在读硕士研究生,主要研究方向:液体火箭发动机试验推力测量技术及仿真。

Simulation of Automatic Calibration Process for Thrust of Liquid Rocket Engines

ZHAO Heng,ZHU Zi-huan   

  1. Beijing Institute of Aerospace Experiment Technology,Beijing 100074,China
  • Online:2023-04-21 Published:2023-06-21

摘要: 针对液体火箭发动机原位校准高准确度的要求,介绍了一种以伺服电机为执行部件,基于液压传动力值自动加载装置,阐述了该系统的结构和工作原理。建立系统数学模型,通过Matlab和AMEsim搭建了系统的仿真模型,在分析影响模拟推力加载准确度和稳定性的基础上,设计了模糊PID控制器。仿真结果表明:所设计的力值加载系统能够完成力值精确加载,(0~6) kN力值加载时间小于30 s,加载力的示值最大误差为±0.05%,满足校准力值加载需求。证明了在力值加载系统中引入模糊PID控制算法,可以有效补偿系统中的不确定性扰动,增强系统的鲁棒性。

关键词: 推力, 自动校准, 力值加载, 建模, 模糊PID控制

Abstract: Aiming at the requirement of high accuracy of in-situ calibration of liquid rocket engines,an automatic force loading device based on hydraulic transmission with servo motor as the execution component was introduced,and the structure and working principle of the system was expounded.The mathematical model of the system was established,the simulation model of the system was built through Matlab and AMEsim,and the fuzzy PID controller was designed on the basis of analyzing the accuracy and stability of thrust loading.The simulation results show that the designed force value loading system can complete the accurate force value loading,the (0~6) kN force value loading time is less than 30 s,and the maximum error of the loading force indication value is ±0.05%,which meets the calibration force value loading requirements.It is proved that the introduction of the fuzzy PID control algorithm into the force loading system can effectively compensate the uncertain disturbance in the system and enhance the robustness of the system.

Key words: Thrust, Automatic calibration, Force value loading, Modeling, Fuzzy PID control

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