摘要
随着航天器轻量化以及微型化发展趋势,微小飞行器作为一种高功能性、低成本的航天器得到了广泛的关注,同时微小飞行器电子设备集成化以及轻量化会给热控系统带来设计难度。针对某微小飞行器的轨道参数和结构性能,提出了采取等温化以及机-电-热一体化的热设计方案,并通过Thermal Desktop软件建立飞行器在轨状态的热模型,仿真分析飞行器的高温和低温极端外热流工况以及瞬态温度分布。仿真结果表明,采取的热控方案能够解决该类微小飞行器的热设计难题。
With the development trend of lightweight and miniaturization of spacecraft,micro spacecraft as a kind of high functionality and low cost spacecraft has been widely concerned,meanwhile the advantage will bring some difficulties for the design of the thermal control system.Firstly,this paper put forward the thermal control measures according to a micro spacecraft orbit parameters and structure performance to solve the thermal control problems. Then,the in-orbit thermal model of micro spacecraft is established by Thermal Desktop software which can simulate the high and low temperature extreme heat flux conditions and the transient temperature distribute. The simulation results show that the thermal control scheme can solve the problems of thermal design.
出处
《微型机与应用》
2017年第7期91-94,共4页
Microcomputer & Its Applications
关键词
微小飞行器
热模型
外热流
瞬态温度分布
micro spacecraft
thermal model
heat flux
transient temperature distribute
