Composite model predictive control technology for exhaust environment pressure in high-altitude chamber
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摘要:
针对高空舱飞行环境模拟试验过程中排气环境压力控制系统存在的动态优化、流量变化干扰以及安全运行约束保障问题，提出了一种结合扩张状态观测器（ESO）与控制障碍函数（CBF）约束的复合模型预测控制（MPC）策略（MPC-ESO-CBF）。分析高空舱排气环境模拟系统核心设备的综合特性与动态过程；针对排气环境压力的动态跟踪控制需求，设计MPC以实现最优控制；考虑系统中存在的未建模动态与外部扰动，构造ESO以实现实时估计与补偿。为保障系统运行的安全性，引入CBF，确保关键状态变量始终处于安全区间内。最后，依托构建的高置信度高空舱排气压力控制系统半实物数字化仿真平台，对所提出的控制策略开展了系统性验证，并与线性自抗扰控制器（LADRC）进行对照评估。验证结果显示，相较于LADRC，基于MPC-ESO-CBF的控制策略，在推力瞬变的过渡态工况下展现出更优的动态性能：排气环境压力的调节时长缩短约38.7%，瞬态峰值扰动幅度降低约33.7%，且稳态阶段的平均误差减少约49.1%。
Abstract:To address the challenges of dynamic optimization, flow-rate disturbances, and safety-operation constraints in the exhaust environment pressure control system during high-altitude chamber flight-environment simulation tests, a composite model predictive control (MPC) strategy incorporating an extended state observer (ESO) and a control barrier function (CBF), referred to as MPC-ESO-CBF, was proposed. The integrated characteristics and dynamic processes of the core equipment in the high-altitude chamber exhaust environment simulation system were analyzed. To meet the demand for dynamic tracking control of exhaust environment pressure, an MPC controller was designed to achieve optimal control performance. Considering unmodeled dynamics and external disturbances in the system, an ESO was constructed to enable real-time estimation and compensation. To ensure safe system operation, a CBF was introduced to strictly confine key state variables within a prescribed safe region. A high-fidelity digital simulation platform for exhaust pressure control in high-altitude chambers was developed, and the proposed control strategy was systematically validated and compared with a linear active disturbance rejection controller (LADRC). The validation results showed that, compared with LADRC, the MPC-ESO-CBF strategy exhibited superior dynamic performance under transient thrust-variation conditions: the adjustment time of exhaust-environment pressure was reduced by approximately 38.7%, the transient peak disturbance magnitude decreased by about 33.7%, and the steady-state average error was reduced by roughly 49.1%.
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图 1 高空舱排气压力控制系统结构示意图
Figure 1. Structural schematic of the high-altitude chamber exhaust pressure control system
图 2 高空舱排气扩压器结构示意图
Figure 2. Schematic diagram of the high-altitude chamber exhaust diffuser structure
图 8 参数摄动下ESO扰动估计
Figure 8. Disturbance estimation via the ESO under parameter perturbations
表 1 控制器参数整定
Table 1. Controller parameter tuning
控制参数 数值 $ {\omega }_{0} $ 7 $ {N}_{{\mathrm{p}}} $ 20 S diag（2 000,1） Q diag（2 000,1） R 10 $ \alpha $ 0.8 
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表 2 仿真工况下排气环境压力控制性能
Table 2. Control performance of the exhaust environment pressure simulation
控制器 阶段 环境压力
瞬态峰值
扰动/kPa环境压力
稳态平均
误差/kPa调节
时长/sLADRC 子阶段1 0.0800 0.0139 62.0 子阶段2 0.7969 0.0306 9.4 子阶段3 1.1135 0.1330 7.5 MPC-ESO-
CBF子阶段1 0.0466 0.0034 4.1 子阶段2 0.5274 0.0132 5.5 子阶段3 0.7383 0.0677 4.6
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