航天器铷钟的一种精密控温系统  

A Precise Temperature Control System for Spacecraft Rubidium Atomic Clock

作　　者：李国强[1] 耿利寅[1] 童叶龙[1] 

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器工程》2011年第4期93-98,共6页Spacecraft Engineering

摘　　要：研究了一种应用于航天器的高精度、高稳定度的温度控制系统:使用热敏电阻作为温度传感器;采用多级控温策略,核心级采用基于径向基函数(Radial Basis Function,RBF)神经网络比例、积分、微分(PID)控制算法,非核心级采用积分分离式PID算法;采用脉宽调制(PWM)控制作为控制方式。以航天器铷钟作为控制对象,通过铷钟模拟件的热平衡试验,验证了高精度控温系统的控制效果。试验结果表明:核心级施加RBF神经网络PID控制时,稳态控温精度优于±0.08℃;内热源阶跃冲击或外热流正弦扰动下,其温度波动小于±0.1℃,控温稳定度优于0.1℃/d。此精密控温系统可应用于有高精度控温需求的航天器星钟和高分辨率光学相机。The paper shows a high-precision and high-stability temperature control system for spacecraft,which uses thermistor as sensor.The system control strategy is step-by-step,using RBF-based nenral network PID control for core stage,using integral separation PID control for others;and using pulse width modulation（PWM） as control mode.The system＇s performance is verified through thermal balance test of rubidium atomic clock simulator.Test results are shown as follows.When the core stage is controlled by nerval network PID control,its temperature change can be within ±0.08℃ in steady case;when it is disturbed by internal heat source or orbit heat flux,the core stage＇s temperature change can be within ±0.1℃ and the temperature stability is ±0.1℃/day.The temperature control system can be applied in precision temperature control for spacecraft atomic clock and high-resolution camera.

关 键 词：航天器 多级控温 神经网络 比例、积分、微分控制 热平衡试验 

分 类 号：V444.3[航空宇航科学与技术—飞行器设计]