一种航天器热平衡试验温度稳定判据确定方法

A Thermal Stabilization Criterion Determination Method for Spacecraft Thermal Balance Test

针对典型航天器热控设计与传热过程特点,建立了设备与舱体动态耦合换热集总参数模型。提出了一种基于热时间常数的航天器热平衡试验温度稳定判据确定方法,给出了双节点耦合换热型航天器系统的热时间常数定义,建立了热平衡温差与温度变化率的对应关系。提出了基于Levenberg-Marquardt最小二乘法温度曲线拟合的热时间常数实时修正方法,该实时修正方法可用于多节点耦合换热航天器热平衡温度稳定判据确定。讨论了目前广泛采用的航天器热平衡试验温度稳定判据的适用性,研究结果可用于指导航天器热平衡试验中温度稳定判据确定。

A transient coupling lumped heat transfer model is proposed for the internal avionics and external spacecraft structure, which is consistent with the heat transfer characteristics of a general spacecraft thermal control system. The determination method for thermal stabilization criterion is developed, which is based on the thermal time constant. The spacecraft thermal time constant is achieved analytically for dual-node coupling heat transfer process. The relation between the thermal stabilization temperature difference and the temporal change rate of the temperature is derived. The real-time correction method for the thermal time constant is proposed, which is based on the temperature curve fitting technology by using the Levenberg-Marquardt algorithm and least squares method. Furthermore, the real-time correction method is able to meet the demand of the thermal stabilization criterion determination for the multi-node coupling heat transfer spacecraft system. The validity of the actual thermal stabilization criterions is discussed. The determination method of the thermal stabilization proposed in this paper can be applied to the spacecraft thermal balance tests.