低轨通信卫星箱式构型设计与散热能力分析

为提高低轨通信卫星散热效率,降低卫星平台质量,通过分析卫星在轨飞行时各个蜂窝板外热流特点,提出一种以热管为传导网络的倒梯形延展板箱式构型。首先,根据低轨通信卫星在轨外热流积分平均值,通过数值计算得到各蜂窝板平均散热能力,并对比两种箱式构型散热能力。其次,为保证各蜂窝板温度均匀,设计了由预埋热管和外敷热管组成的热管网络,强化蜂窝板内和蜂窝板间热耦合特性。最后,某型低轨通信卫星采用倒梯形延展板构型方案,并对卫星进行高低温热平衡试验验证。研究结果表明:在相同面积条件约束下,与正梯形构型相比,倒梯形延展板构型+X蜂窝板散热能力提升36.3%,-X蜂窝板散热能力提升36.4%,+Z蜂窝板散热能力提升10.2%,-Z蜂窝板散热能力提升98.6%,整星散热能力提升34.6%；热平衡试验结果表明,在高低温工况下所有设备满足温度指标要求,整星满足2 200 W热耗散热能力需求,其中+Z板相控阵天线峰值热耗为870 W,证实了基于热管网络的倒梯形延展板箱式构型的可行性。

Box-type configuration design and heat rejection analysis for LEO communication satellite

To improve the heat rejection efficiency of low Earth orbit (LEO) communication satellite and reduce the platform mass, through the analysis of the orbital heating flux of each honeycomb panel of in-orbit satellite, this paper proposes an inverted trapezoidal extension panel with heat pipes as conduction network. First, according to the integral average values of orbital heating flux of LEO communication satellite in orbit, the average heat rejection capacity of each honeycomb panel was obtained through numerical calculation, and the heat rejection performance of two box-type configuration schemes was compared. Then, in order to ensure the uniform temperature of honeycomb panels, a heat pipe network consisting of embedded heat pipes and external heat pipes was designed, so as to enhance the thermal coupling characteristics within and between honeycomb panels. Finally, the inverted trapezoidal extension panel configuration scheme was adopted for a LEO communication satellite, and hot and cold thermal balance tests were carried out. Research results showed that with the same area constraint, by using the inverted trapezoidal extension panel configuration, the heat rejection capacity of +X honeycomb panel was improved by 36.3%, -X honeycomb panel by 36.4%, +Z honeycomb panel by 10.2%, -Z honeycomb panel by 98.6%, and the heat rejection capacity of the whole satellite was improved by 34.6%, compared with the positive trapezoidal configuration. The thermal balance test results showed that the satellite platform met all temperature requirements under hot and cold cases. The whole satellite met the heat rejection requirement of 2 200 W, and the peak heat rejection was 870 W for the +Z panel phased array, indicating the feasibility of the inverted trapezoidal extension panel configuration based on the heat pipe network.