摘要
航天器及其部件的热真空试验是航天器研制过程保证其可靠性的重要环节。由于复杂的物理和边界条件,单纯从传热的角度得到的航天器传热模型与真实情况存在差别。基于传热理论的基本方法,文章提出结合系统辨识的方法得到航天器热真空试验传热数学模型。这种方法可以推广到相似的试验中去,将加快试验进程和节省大量的试验经费。
Thermal vacuum test of spacecrafts or their parts is one of the crucial processes during spacecraft design.Due to the complexity of thermal boundary conditions and physical features,however,thermal model solely obtained from heat analysis aspect is somehow not as precise as expected by comparison with real test data.Based on basic thermal analysis,a new thermal model is obtained by means of system identification.In addition,thermal test process will be shortened and expenses will be decreased with the similar thermal test requirements.
出处
《航天器环境工程》
2005年第4期202-203,共2页
Spacecraft Environment Engineering
关键词
航天器
热真空试验
系统辨识
传热模型
spacecraft
thermal vacuum test
system identification
thermal model
