高空高速无人飞行器热控制系统设计

Design of thermal control system for high-altitude and high-speed unmanned vehicle

针对飞行时间短、速度和高度变化快、表面温度波动大的无人飞行器UAV(UnmannedAerialVehicles)热控制系统设计难题,提出了一种可解决实际工程问题的热分析计算方法.即把热天工况、冷天工况和标准天工况作为设计试验工况;采用参考温度法、高超音速工程预测法或计算流体动力学CFD(ComputationalFluidDynamics)数值模拟法,确定了飞行器表面温度分布,并把其作为后续热分析数学模型的外边界条件;分析结构热容量对瞬态热载荷的影响,建立与之相应的边值问题方程,并采用有限差分法求解;根据高空高速飞行特点及瞬态热载荷值,确定仪器设备舱调温系统方案.

According to design of thermal control system for UAV（ unmanned aerial vehicles）, which is characterized by small flight time-consumption, high speed, and quick change in altitude, thermal analysis and calculation methods which can be applied to practice engineering were put forward. Hot atmosphere, standard atmosphere and cold atmosphere were referred to as design conditions. In virtue of referring temperature, hypersonic engineering prediction or CFD（computational fluid dynamics） numerical simulation, surface temperature of vehicle was attained and taken as outer boundary conditions of thermal analysis mathematics model. Structure thermal capacity＇ s influence of the transitional thermal load was analyzed, and boundary equation was set up and solved by finite difference method. According to flight feature and transitional thermal load value, scheme of temperature adjusting system of electronic equipment cabin was presented.