国防科技大学学报
國防科技大學學報
국방과기대학학보
Journal of National University of Defense Technology
2015年
5期
91-96
,共6页
平流层长航时气球%上升过程%超冷现象%热模型
平流層長航時氣毬%上升過程%超冷現象%熱模型
평류층장항시기구%상승과정%초랭현상%열모형
stratospheric long duration balloon%ascent stage%supercooling phenomenon%thermal model
平流层长航时气球超冷现象是指内部浮升气体温度低于外界大气温度,超冷会引起浮力损失进而阻碍气球上升过程。建立了长航时气球辐射、对流等热模型和上升过程动力学模型,仿真分析了初始净浮力、蒙皮热物性参数、放飞时间和放飞日期等因素对超冷现象的影响规律。研究结果表明,上升过程内外温差随初始净浮力增大而增大且变化显著,可见光吸收率和红外吸收率增大时,内外温差值总体上呈减小趋势;放飞时刻和放飞日期对超冷现象影响较小,但放飞时间不同,气球上升至设计驻空高度的时间差别较大。该结论可为平流层浮空器总体方案设计和放飞试验提供有益参考。
平流層長航時氣毬超冷現象是指內部浮升氣體溫度低于外界大氣溫度,超冷會引起浮力損失進而阻礙氣毬上升過程。建立瞭長航時氣毬輻射、對流等熱模型和上升過程動力學模型,倣真分析瞭初始淨浮力、矇皮熱物性參數、放飛時間和放飛日期等因素對超冷現象的影響規律。研究結果錶明,上升過程內外溫差隨初始淨浮力增大而增大且變化顯著,可見光吸收率和紅外吸收率增大時,內外溫差值總體上呈減小趨勢;放飛時刻和放飛日期對超冷現象影響較小,但放飛時間不同,氣毬上升至設計駐空高度的時間差彆較大。該結論可為平流層浮空器總體方案設計和放飛試驗提供有益參攷。
평류층장항시기구초랭현상시지내부부승기체온도저우외계대기온도,초랭회인기부력손실진이조애기구상승과정。건립료장항시기구복사、대류등열모형화상승과정동역학모형,방진분석료초시정부력、몽피열물성삼수、방비시간화방비일기등인소대초랭현상적영향규률。연구결과표명,상승과정내외온차수초시정부력증대이증대차변화현저,가견광흡수솔화홍외흡수솔증대시,내외온차치총체상정감소추세;방비시각화방비일기대초랭현상영향교소,단방비시간불동,기구상승지설계주공고도적시간차별교대。해결론가위평류층부공기총체방안설계화방비시험제공유익삼고。
Supercooling phenomenon of stratospheric long duration balloons means that the temperature of helium gas inside is lower than that of atmosphere outside,this will cause the loss of buoyancy and affect ascent process of the balloon as a result.Radiation and convection thermal models and the vertical dynamic model of long duration balloons were established,and the influence regularity of some important factors,including initial net buoyancy,skin thermal physical parameters,launch time and launch date,on supercooling phenomenon was analyzed.Simulation results show that the temperature difference between helium gas and outside atmosphere enlarges remarkably along with the increase of initial net buoyancy, and the temperature difference decreases when the absorptivity for visible light and infrared radiation increases.Simulation results also show that the influence of launch time and launch date on supercooling phenomenon is much smaller,while flight time from ground to designed altitude displays great difference when the launch time is different.The research results can provide theoretical reference for conceptual design and flight test.