摘要
基于临近空间浮空器动力学与热力学耦合关系,研究分析上升过程飞行航迹与内部气体热性能。建立临近空间浮空器初始充气量模型、热模型和上升过程动力学模型,通过飞行试验验证了数学模型的准确性。仿真计算了某高空科学气球的上升航迹,得到了气球净升力对爆破高度、速度等飞行航迹性能参数的影响,分析了参数变化规律与变化原因。研究结果表明,随着净升力的增加,爆破高度迅速降低,而气球上升速度逐渐上升,且上升速度的增大比爆破高度的减小相对于净升力的变化更加敏感,表明气球的净升力对航迹性能参数存在重要影响。研究结果可为临近空间浮空器设计、试验和应用提供理论参考。
Based on the coupling relation between dynamics and thermodynamics of near-space aerostat,the trajectory of ascent process and the thermal performance of internal gas are studied.Initial inflation model,thermal model and ascend⁃ing dynamic model of near-space aerostat are established.Accuracy of models is verified by flight tests.The effect of the net lift of a balloon on blasting altitude,ascent velocity and other trajectory performances is obtained through simulation.Simultaneously,variation regularity and variation reason of parameters are analyzed.Research results show that with the increasing of net lift,the blasting altitude decreases rapidly,the ascent velocity increases gradually.With the net lift vary⁃ing,the increase of ascent velocity is more sharp than the decrease of blasting altitude,which shows that the effect of net lift on ascent trajectory performance parameters is significant.All those can provide a theoretical reference for the design,test and application of near-space aerostat.
作者
陈雪
赵新路
杨涵
CHEN Xue;ZHAO Xinlu;YANG Han(Chengdu Aeronautic Polytechnic,Chengdu 610100,China;Research Institute of Sichuan Aerospace System Engineering,Chengdu 610100,China)
出处
《海军航空工程学院学报》
2020年第6期433-438,470,共7页
Journal of Naval Aeronautical and Astronautical University
基金
国防科学技术基金资助项目(414110×0×01)。
关键词
临近空间
浮空器
上升过程
净升力
航迹性能
near-space
aerostat
ascent process
net lift
trajectory performance
