摘要
高空长航时飞行器由于长时间处于低温使用环境中,飞行器的燃料及其供给系统需进行温度控制功能设计,以保障飞行器长时间正常运行,以免造成飞行器损坏;飞行器燃料所处的低温环境受到内外部多种热源影响,且与飞行器的飞行任务剖面密切相关,温度环境复杂且难以有效计算仿真;针对飞行器在复杂低温环境中对燃料进行温度控制功能的需求,以及飞行器对温控系统高可靠性要求、资源条件限制苛刻等限制条件,开展了温控系统设计和优化,并完成了硬件设计和系统仿真;由于地面试验和真实环境差异较大,单一地面试验很难模拟真实热环境,对系统优化设计造成困难,针对性开展热环境分析,系统方案设计、地面试验和飞行试验联合验证,优化系统方案,实现了一种高效可靠,且易于工程应用的燃料贮箱温控功能,取得了良好的工程应用效果,同时该优化设计方法具有一定的扩展性。
High altitude long endurance unmanned air vehicle has been in low temperature environment for a long time.For the demands of thermal control for flight vehicle’s propellant tank,this project focus on the optimal design of thermal control system.Due to the high emphasis paying on reducing vehicle weight,and highly reliability level,environmental adaptability requirements,the thermal control system is designed under difficulty.The heat transfer analysis model was established for the structure and the heater efficiency.The calculation and analysis of heat rate were conducted with different schemes and configurations,the functional optimization design method in this paper can be applied in propellant tank thermal control system.
作者
张素明
Zhang Suming(Beijing Institute of Astronautical Systems Engineering,Beijing 100076)
出处
《计算机测量与控制》
2021年第3期157-160,170,共5页
Computer Measurement &Control
