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星上控温策略的地面模拟与验证
引用本文:吴东亮, 朱琳, 童叶龙, 等. 星上控温策略的地面模拟与验证[J]. 航天器环境工程, 2018, 35(3): 270-276doi:10.12126/see.2018.03.012
作者姓名:吴东亮  朱琳  童叶龙  王擎宇  柳晓宁
作者单位:北京卫星环境工程研究所,北京 100094
摘    要:
为充分验证卫星在轨温度控制策略的适用性和效果,针对航天器在轨温度控制的特点及方式,提出一种在地面模拟星上控温策略的方法。该方法包含:设计开发一套适用于航天器真空热试验的星上控温模拟系统及基于比例开关控制算法的星上控温模拟软件;采用并行驱动技术实现单个控温时间片为1 s的时间控制精度,工况稳定后温度控制误差不超过±0.3 ℃。该方法已成功应用于某型号卫星真空热试验过程,系统配置灵活、操作简单、控温周期短、控温精度高,实现了星上控温策略的有效验证。

关 键 词:航天器   温度控制   真空热试验   模拟软件   比例开关控制   并行驱动
收稿时间:2017-10-27
修稿时间:2018-05-04

A ground-based method for simulating the temperature control strategy onboard satellite
WU D L, ZHU L, TONG Y L, et al. A ground-based method for simulating the temperature control strategy onboard satellite[J]. Spacecraft Environment Engineering, 2018, 35(3): 270-276doi:10.12126/see.2018.03.012
Authors:WU Dongliang  ZHU Lin  TONG Yelong  WANG Qingyu  LIU Xiaoning
Affiliation:Beijing Institute of Spacecraft Environment Engineering, Beijing 100094, China
Abstract:
In order to verify the feasibility and the effect of the satellite on-orbit temperature control strategy on the ground, a method for simulating the strategy based on the characteristics and manners of spacecraft temperature control is proposed, including the design of a satellite temperature control simulation system for the spacecraft thermal vacuum test, and the development of a temperature control simulation software based on the proportional switch control algorithm. The simulation results show that the time control precision of the single slice of the temperature control time is 1 s, and the temperature control error is within the range of ±0.3 ℃. The system is successfully applied in the vacuum thermal test of a certain type of satellite, featuring flexibility, simple operation, short temperature control cycle, high temperature control accuracy, and an effective verification is made for the temperature control strategy onboard the satellite.
Keywords:spacecrafts  temperature control  vacuum thermal test  simulation software  proportional switch control  parallel drive
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