摘要
火星表面起飞上升热控技术是火星取样返回探测的关键技术,涉及探测器在火星表面存储控温、火星表面起飞上升控温及火星在轨飞行控温等,具有温度指标要求高、控温维度大、资源紧张的特点。本文对国内外主要火星车及美国航空航天局(NASA)火星上升器的热控方案进行了调研和总结。分析表明火星表面探测器热控技术根据资源分配情况主要采用2种方式:当热控质量受限不明显时,可采用机械泵驱动流体回路技术配合常规热控措施,对大热耗单机进行热量收集和传输,实现废热的再利用;当热控质量受限严重时,需采用轻量化低功耗的控温措施,可采用复合纳米气凝胶隔热技术配合常规热控措施,高效隔绝火星表面低温对流环境,实现低功耗控温。随后提出了火星表面起飞上升的热控关键技术,主要包括纳米气凝胶隔热技术、火星原位资源隔热技术、机械泵驱动两相流体回路技术、气动热防护技术及热试验模拟技术等,可为后续火星探测提供一定的参考。
The thermal control technology for Mars surface takeoff and ascent is a key technology for Mars samplereturn exploration,involving the temperature control for storage,the temperature control for Mars surface takeoff and ascent,andthe temperature control for Mars in-orbit flight.It has the characteristics of high temperature index requirements,large temperature control dimensions,and scarce resources.In this paper,the thermal control schemes of major Mars roversat home and abroad and the Mars ascenders ofthe National Aeronautics and Space Administration(NASA)are investigated and summarized.The results show that,according to the resource allocation,the thermal control technology of Mars surface probes mainly adopts two strategies.When the thermal control weight is not significantly limited,aiming at the reuse of waste heat,the mechanical pump driven fluid circuit technology is adopted to collect and transfer the heat of high heat consumption devices,in conjunction with conventional thermal control measures.When the thermal controlweight is severely limited,lightweight and low-power thermal control measures should be adopted.At this time,aiming at the lowest power consumption,the composite nano-aerogel thermal insulation technology is usually adopted to efficiently isolate the low-temperature convective environment on the surface of Mars,in combination with conventional thermal control measures.Subsequently,the key thermal control technologies for Mars surface takeoff and ascent are proposed,mainly includingthe nano-aerogel thermal insulation technology,the thermal insulation technology for in-situ resources on Mars,the mechanically pumped two-phase loop(MPTL)technology,the atmospheric dynamic thermal protection technology,and the thermal test simulation technology,which can provide some reference for subsequent Mars exploration.
作者
杨金
刘彤杰
徐亮
盛松
倪浩伟
杜艾
缪洪康
徐涛
王伟
吴志亮
朱虹
YANG Jin;LIU Tongjie;XU Liang;SHENG Song;NI Haowei;DU Ai;MIAO Hongkang;XU Tao;WANG Wei;WU Zhiliang;ZHU Hong(Shanghai Institute of Satellite Engineering,Shanghai 201109,China;Shanghai Academy of Spaceflight Technology,Shanghai 201109,China;School of Physics Science and Engineering,Tongji University,Shanghai 200092,China;Shanghai Aerospace Engineering Research Institute,Shanghai 201109,China)
出处
《上海航天（中英文）》
CSCD
2024年第5期90-98,120,共10页
Aerospace Shanghai（Chinese&English）
基金
国家级项目
行星探测重大工程资助项目。
关键词
火星车
起飞上升
热控
温度场
Mars rover
takeoff and ascent
thermal control
temperature field
