固体火箭技术2026，Vol.49Issue(4)：491-500,10.DOI:10.7673/j.issn.1006-2793.2026.04.001
基于LADRC的喉栓式固体火箭发动机压强控制
Pressure control of pintle solid rocket motor based on LADRC
陈施吉 1石峰 2强洪夫 1戴陈超 1刘舜 1彭永康 1王学仁1
作者信息
- 1. 火箭军工程大学,固体推进全国重点实验室,西安 710025
- 2. 航天动力技术研究院,西安 710025
- 折叠
摘要
Abstract
To address the strong nonlinearity,strong time-varying characteristics,geometric boundary variations,and parameter perturbations in pressure regulation of pintle solid rocket motors,a pressure dynamic model considering free-volume variation,nozzle-throat area constraints,and linear ablation was established.Based on equilibrium-point calculation and local linearization analysis,a linear active disturbance rejection control(LADRC)method incorporating equilibrium-displacement feedforward,dynamic incremental compensation,and constraint quantification was proposed,with key control parameters tuned by the differential evolution(DE)algorithm.DE-optimized PID controller(DE-PID)and fixed-parameter PID controller(F-PID)were used for comparison.Results show that LADRC performs well in step tracking,noisy sinusoidal tracking,free-volume variation,and time-varying nozzle-throat ablation,with low overshoot and fast response.Under the tested conditions,the overshoot of the LADRC remains below 0.47%,while the settling time is limited to less than 0.92 s.Its regulation speed is 2.17～6.44 times that of the F-PID.While maintaining an error level comparable to that of the DE-PID,the LADRC provides more stable overshoot suppression,waveform tracking continuity,and disturbance-recovery capability.关键词
喉栓/固体火箭发动机/压强控制/线性自抗扰控制/差分进化/烧蚀时变Key words
pintle/solid rocket motor/pressure control/linear active disturbance rejection control/differential evolution/time-varying ablation分类
航空航天引用本文复制引用
陈施吉,石峰,强洪夫,戴陈超,刘舜,彭永康,王学仁..基于LADRC的喉栓式固体火箭发动机压强控制[J].固体火箭技术,2026,49(4):491-500,10.
