大推力氢氧补燃发动机推力闭环控制设计

Thrust closed-loop control and HIL test of the large scale expendable liquid rocket propulsion

摘要:

提出了大推力氢氧补燃发动机推力闭环控制系统的软硬件平台,为建立液体火箭发动机综合控制系统奠定了坚实的基础。首先,建立了氢氧补燃发动机实时动态非线性模型,在此基础上得到了设计点线性化模型并验证；其次,在线性模型的基础上采用根轨迹法设计了推力闭环控制器,将控制器与非线性模型联合仿真验证了算法的有效性；最后,介绍了发动机硬件在回路系统的软硬件配置,并进行了控制器的平台验证,从操作和实现方式上验证了软硬件平台。该设计满足算法需求且界面人性化,易于操作。

Abstract:

The principle of large scale expendable liquid rocket engine thrust closed-loop control was proposed and tested. This part is critical to the liquid rocket propulsion control system. Firstly, the real-time dynamic model was set up here, based on this model we got the linear model at the design point . Secondly, the root locus method was used to design the controller, then the simulation of real-time dynamic model combined with the controller was carried out. At last, the hardware-in-the -loop platform containing software and hardware was set up for the engine control. The results show that the controller and the platform work well and easy to operate.