基于多轴联动的航天器带动力风洞实验控制系统设计

Design of control system for spacecraft with power wind tunnel experiment based on multi-axis linkage

摘要:

针对当前航天器带动力风洞实验控制系统受动态性能和稳态精度的影响，导致航天器中心偏离风洞轴心距离控制误差较大，上旋翼所能承受压力与实际值不符的问题，设计基于多轴联动的航天器带动力风洞实验控制系统。采用PROFIBUS现场总线方式，设计控制系统总体结构。使用伺服电机模块，控制启停指令，以西门子57-300 PLC为主站设计现场控制器，研制一种航天器风洞测试支撑装置，并将迎角机构安装在模块化分层结构中。利用多轴联动控制器，采用RS-232串行通信原理，根据负载惯量选择2kW伺服驱动器，实现伺服电机紧急停车，完成控制系统硬件设计。计算多轴联动随动目标动态，使用柔性bang-bang控制，消除系统动态性能和稳态精度的影响，在误差数据支持下，设计实验控制流程，完成控制系统软件设计。实验结果表明，该系统控制航天器中心偏离风洞轴心最大偏离距离为0.32mm，最小为0.1mm，且上旋翼所能承受压力与实际值一致，控制误差较小，具有精准控制效果。

Abstract:

Due to the influence of the dynamic performance and steady-state accuracy of the current spacecraft wind tunnel test control system, the control error of the spacecraft center deviation from the wind tunnel axis is large, and the pressure of the upper rotor is inconsistent with the actual value. The overall structure of the control system is designed based on PROFIBUS. The servo motor module is used to control the start stop command, and the Siemens 57-300 PLC is used as the master station to design the field controller. A kind of support device for spacecraft wind tunnel test is developed, and the angle of attack mechanism is installed in the modular hierarchical structure. Using multi axis linkage controller, RS-232 serial communication principle, 2kW servo driver is selected according to the load inertia to realize the emergency stop of servo motor, and the hardware design of control system is completed. The flexible bang bang control is used to eliminate the influence of system dynamic performance and steady-state accuracy. With the support of error data, the experimental control process is designed and the control system software is designed. The experimental results show that the maximum deviation distance of the spacecraft center from the wind tunnel axis is 0.32mm, and the minimum is 0.1mm. The pressure of the upper rotor is consistent with the actual value, the control error is small, and the system has accurate control effect.