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机载液氢储罐对静态日蒸发率、结构强度、储氢质量密度等要求较高。针对特殊的绝热要求和工作环境,对无人机机载液氢储罐绝热结构进行创新设计。选取高真空多层绝热的绝热方式;首次提出一种组合式点接触绝热支撑结构,与普通支撑结构从理论计算和仿真两方面对比说明新型结构的优异性能;采用增加气液盘管长度的方法,增加结构热阻。分别建立机载液氢储罐的一维和三维整体传热模型,并对模型进行理论计算和仿真。研究和分析结果表明:通过组合式点接触绝热支撑结构的热流量比一般支撑结构减少90%以上;具有高真空多层绝热、组合式点接触支撑结构和气液加长盘管的设计方案的漏热量比目前同规格普通低温液氢容器的漏热量低24.6%~35.2%。
On-board liquid hydrogen storage tanks have higher requirements on static daily evaporation rate, structural strength and hydrogen storage mass density. In view of the special adiabatic requirements and working environment, an innovative design of the thermal insulation structure of UAV tank for UAVs is designed. Select the adiabatic way of high-vacuum multi-layer insulation; Propose a combined point-contact adiabatic support structure for the first time, and compare with the common support structure to demonstrate the excellent performance of the new structure from the theoretical calculation and simulation; , Increase the structural resistance. The one-dimensional and three-dimensional integral heat transfer models of airborne liquid hydrogen storage tank are established, and the model is calculated and simulated. The results of research and analysis show that the heat flux through the combined point-contact adiabatic support structure is reduced by more than 90% compared with that of the general support structure. The heat leakage of the design with high vacuum multi-layer insulation, combined point contact support structure and gas-liquid extension coil Than the current specifications of the ordinary low temperature liquid hydrogen container leakage heat is low 24.6% ~ 35.2%.