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蓄电池发热量是航天器蓄电池热控设计的重要参数,其测试准确度直接影响热控设计状态和在轨工作温度。文章采用真空绝热量热法对蓄电池发热量测试系统进行了漏热分析,并给出了修正方法;以模拟蓄电池为研究对象,分析了蓄电池发热量测试误差,并提出了改善系统测量准确度的解决方案。结果表明,当放电时间大于1 h,航天器蓄电池发热功率在2~25 W范围内时,测试误差不超过6%,且发热功率越大误差越小;当发热功率大于10 W时,测试误差不超过3%,可以满足工程要求;对于发热功率较小(绝对值小于0.5 W)的小电流放电或充电,测试误差较大,但绝对值仍然较小,对实际工程影响不大。
The battery heat is an important parameter in the thermal control design of spacecraft battery. The test accuracy directly affects the thermal control design status and on-orbit operating temperature. In this paper, the leakage heat analysis of battery calorific value test system is carried out by vacuum adiabatic calorimetry, and the correction method is given. Taking the simulated battery as the research object, the test error of the calorific value of the battery is analyzed, and the measurement accuracy of the system is improved solution. The results show that the test error is less than 6% when the discharge time is more than 1 h and the heating power of the spacecraft battery is in the range of 2 ~ 25 W. The error of the test result is smaller when the heating power is greater than 10 W. Less than 3% can meet the project requirements. For small current with small heating power (less than 0.5 W in absolute value), the test error is large but the absolute value is still small, which has little effect on the actual project.