摘要
根据高空飞艇的定点运行区域地球纬度、定点运行时域的太阳运行规律,以及高空飞艇的飞行姿态,对高空飞艇囊体及所包容的氦气建立有限元物理模型并进行有限元热分析,得到高空飞艇艇内氦气平均温度在太阳辐射情况下随时间变化的规律及温差范围。同时,与不包括飞艇囊体热容量的飞艇氦气热分析进行了比较,得到了高空飞艇热分析中加入囊体材料热容及忽略囊体热容的差异。研究证明高空飞艇的热分析必须考虑囊体的质量和热容及薄膜电池的质量和热容。
According to the latitude and the sun running rules at the fixed-pointed time zone, as well as flying posture of the high-altitude airship, the finite element modeling of the envelope and the Helium in- flated of the airship are established, and the temperature calculation is carried out by FEM. The rules of the average temperature of the Helium inflated in the airship are obtained in relation to the time chan- ging, and also the temperature range of Helium is obtained. As to comparing the result of the temperature calculation of Helium without the thermal capacity of the airship envelope, the difference of the analysis result of the Helium with and without the thermal capacity of the airship envelope has been found. The necessity of the accounting of the thermal capacity, the weight of the envelope and the solar cell is indica- ted by the analysis of the calculation results.
出处
《中国电子科学研究院学报》
2012年第5期502-505,共4页
Journal of China Academy of Electronics and Information Technology
关键词
平流层
高空飞艇
抗热能力
气压差
stratosphere
high-altitude airship
heatproof ability
pneumatic pressure difference
