期刊文献+

火星车有风热平衡试验环境模拟技术 被引量:2

Thermal environment simulation technology of Mars rover wind thermal balance test
下载PDF
导出
摘要 为了保证火星车在火星表面能够正常工作,需要在地面模拟火星表面的有风热环境,包括风速、风向、气体温度、气体成分和压力等,完成火星车在火星表面有风热环境下的热平衡试验。针对火星表面有风热环境特点,开展低压风速模拟、低压风速测量、压力控制、温度控制等研究,利用现有的KM3E真空容器,在其内部增加特殊设计的风扇、导流装置、压力控制系统、气体温度控制系统、火星车姿态调整系统等,使KM3E具备火星表面有风热环境模拟条件。该模拟技术成功应用于火星车有风热平衡试验,充分验证了火星车热控系统设计,为火星车热分析模型提供了重要参考。 To ensure the operation of the Mars rover on the Mars’surface,it is necessary to simulate on the ground the thermal environment with wind on the Mars surface,such as the speed and the direction of the wind,as well as the gas temperature,composition,and the pressure of the gas.The simulation and the measurement are carried out for the low-pressure wind speed,the pressure control,and the temperature control.With the existing KM3E chamber as a basic configuration,we add the specially designed fans,the runners,the pressure control systems,the gas temperature control system,and the attitude adjustment system for the Mars rover sample,for the thermal environment simulation of the Mars surface.The wind thermal balance test of the Mars rover is successfully conducted,and the performance of the Mars thermal control system is verified,to support the modification of the thermal analysis model of the Mars rover.
作者 高庆华 李鹏 刘佳彬 金翠玲 王辰星 GAO Qinghua;LI Peng;LIU Jiabin;JIN Cuiling;WANG Chenxing(Beijing Institute of Spacecraft Environment Engineering;China Academy of Space Technology,Beijing 100094,China)
出处 《航天器环境工程》 2019年第6期594-600,共7页 Spacecraft Environment Engineering
关键词 火星车 风场 热平衡试验 风速模拟 风速测量 Mars rover wind field thermal balance test wind speed simulation wind speed measurement
  • 相关文献

参考文献3

二级参考文献24

  • 1邱玉鑫,程娅红,胥家常.浅析高空长航时无人机的气动研究问题[J].流体力学实验与测量,2004,18(3):1-5. 被引量:17
  • 2White B R,Benzit M. Wind tunnel measurements of the coefficient of restitution and kinetic energy of quartz sand for Mars and Earth impacting on a basalt rock with numerical simulation,AIAA 2006-270[R].
  • 3White B R. A low-density boundary-layer wind tunnel facility,AIAA 1987-0291[R].
  • 4Soriano J F,Coouilla R V,Wilson G R. A wind tunnel study on the Mars Pathfinder(MPF)lander descent pressure sensor,NASA TM-2001-210253[R].
  • 5Anyoji M,Nagai H,Asai K. Development of low density wind tunnel to simulate atmospheric flight on Mars,AIAA 2009-1517[R].
  • 6Anyoji M,Ida S,Nose K. Characteristics of the Mars wind tunnel at Tohoku university in CO2 operation mode, AIAA 2010-1490[R].
  • 7Hiroki N,Keisuke A,Daiju N. Characteristics of low-Reynolds number airfoils in a Mars wind tunnel,AIAA 2013-0073[R].
  • 8Arrighi R S. Revolutionary atmosphere:the story of the altitude wind tunnel and the space power chambers[M].Washington:National Aeronautics and Space Administration,2010.
  • 9Blaha B J,Shaw R J. The NASA altitude wind tunnel:its role in advanced icing research and development,AIAA 1985-0090[R].
  • 10Chamberlin R. The altitude wind tunnel(AWT):a unique facility for propulsion system and adverse weather testing,AIAA 1985-0314[R].

共引文献52

同被引文献32

引证文献2

二级引证文献5

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部