摘要
载荷分系统为航天器实现功能的重要组成部分,随型号设计难度的提高,载荷分系统一般通过提高行波管放大器输出功率来实现性能达标,由此必然导致多工器后级公共端波导热耗过高,对系统级热设计提出更高要求。首先对系统级波导组件热设计方法进行介绍,在此基础上对高热耗波导组件的热分析方法、散热设计及试验验证情况等进行描述。结果表明,在系统热设计无法保证波导使用温度时,需在波导组件上实施散热措施,使用的通用化散热翅片设计简单,安装灵活,利于产品化,经试验验证,最高可将波导温度降低25℃左右。
As an important part of spacecraft,the design of load subsystem is becoming more and more difficult,most load subsystems achieve performance standards by increasing the output power of TWT amplifier,which will inevitably lead to high heat consumption of common end waveguide at the rear stage of multiplexer,and put forward higher requirements for system level thermal design.Firstly,the system level thermal design method is introduced.On this basis,the thermal analysis method,heat dissipation design and experimental verification of high heat consumption waveguide components are described.The results show that when the system level design can not guarantee the service temperature of the waveguide,it is necessary to implement heat dissipation measures on the waveguide assembly.The universal heat dissipation fin used in this paper has the advantages of simple design,flexible installation and product use.At the same time,it is verified by experiments that the waveguide temperature can be reduced 20℃at the highest.
作者
王峻
涂冰怡
萧鑫
WANG Jun;TU Bingyi;XIAO Xin(China Academy of Space Technology(Xi’an),Xi’an 710000,China)
出处
《空间电子技术》
2023年第1期82-87,共6页
Space Electronic Technology
关键词
波导组件
系统级热设计
散热措施
waveguide
subsystem thermal design
heat dissipation measures
