基于LADRC的喉栓式固体火箭发动机压强控制OA

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.