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设计开发了一种星载微波辐射计热定标源,运用有限元分析(Finite Element Analysis,FEA)软件对其进行热特性仿真分析,并通过热真空环境模拟试验对其进行验证。仿真表明,热定标源温度随着传递距离的增大(从源体底部向尖劈顶部、从中心向四周)而线性减小;尖劈高度方向的温度梯度d T/dh大于半径方向的温度梯度d T/dr,两者随着空间环境温度的增加(2.7 K→293 K)而逐渐减小。通过试验考核,热定标源温度精度在±0.15 K/16 s范围内,温度均匀性≤0.15 K,具有良好的温度稳定性和均匀性,验证了热定标源热设计的合理性与可行性。
A thermal calibration source of a spaceborne microwave radiometer was designed and developed. Its thermal characteristics were simulated by Finite Element Analysis (FEA) software and verified by thermal vacuum environment simulation. The simulation shows that the temperature of the thermal calibration source decreases linearly with the increase of the transmission distance (from the bottom of the source body to the top of the wedge, from the center to the periphery), and the temperature gradient d T / dh in the wedge height direction is larger than that in the radial direction The temperature gradient, d T / dr, decreases with increasing ambient temperature (2.7 K → 293 K). Through the test evaluation, the thermal calibration source temperature accuracy within ± 0.15 K / 16 s, temperature uniformity ≤ 0.15 K, with good temperature stability and uniformity, verify the thermal calibration heat source design is reasonable and feasible Sex.