Modeling and analysis of stratospheric airship's energy storage battery considering rate
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摘要:
准确掌握储能电池的实际电量是确保平流层飞艇实现长航时飞行的关键因素之一。首先,建立了平流层飞艇能源系统仿真模型,对能量输入和消耗进行动态分析。随后,对储能电池进行不同电流倍率的充放电测试,采用多项式拟合的方法,根据测试数据建立了储能电池充放电过程中荷电状态(SOC)、剩余放电时间(RDT)、剩余充电时间(RCT)的分析模型。最后,结合能源系统能量输入、消耗模型和储能电池模型进行飞行模拟仿真,获取各部分变化数据,与已有试验数据进行量化对比分析。结果表明:所构建储能电池模型在SOC、RDT、RCT的计算误差分别小于3%、1.5%、1.5%,能够准确反映电池工作过程中SOC、RDT、RCT的变化,可为平流层飞艇平台制定优化的飞行策略提供量化支撑。
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关键词:
- 平流层飞艇 /
- 储能电池模型 /
- 荷电状态(SOC) /
- 剩余放电时间(RDT) /
- 剩余充电时间(RCT)
Abstract:Accurately grasping the actual power of energy storage battery is one of the key factors for the stratospheric airship to realize long-time flight. First, a simulation model of a stratospheric airship energy system was established to analyze the energy input and consumption dynamically. Then, charging and discharging tests of energy storage batteries with different electric current ratios were carried out. The polynomial fitting method was adopted to establish an analysis model of state of charge (SOC), remaining discharging time (RDT) and remaining charging time (RCT) in the process of charging and discharging of energy storage batteries. Finally, the flight simulation was carried out by combining the energy input and consumption models of the energy system and the battery model to obtain the variation data of each part. And the quantitative comparison and analysis with the existing experimental data were conducted. The results show that the calculated errors of the established energy storage battery model in SOC, RDT and RCT are less than 3%, 1.5% and 1.5% respectively, which can accurately reflect the changes of SOC, RDT and RCT during the battery working process, and can provide quantitative support for the formulation of optimal flight strategies for the stratospheric airship platform.
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表 1 测试电池的基本参数
Table 1. Basic parameters of test batteries
参数 参数值 标称容量/mAh 3 400 电压范围/V 2.75~4.25 放电温度范围/℃ -20~50 充电温度范围/℃ -20~50 表 2 线性拟合8次多项式系数与电流倍率的结果
Table 2. Results of linear fitting of eighth-degree polynomial coefficients and discharging rate
系数 Bj1 Bj0 A8i 5.245×102 -1.888×103 A7i -1.456×104 5.150×104 A6i 1.762×105 -6.122×105 A5i -1.215×106 4.143×106 A4i 5.213×106 -1.746×107 A3i -1.427×107 4.690×107 A2i 2.432×107 -7.846×107 A1i -2.360×107 7.474×107 A0i 9.984×106 -3.103×107 表 3 不同电流倍率恒流放电的总放电时间
Table 3. Total duration of constant-current discharging at different discharging rates
电流倍率/C T0i/min 0.05 1 343 0.1 675 0.15 448 0.2 334 0.25 266 0.3 220 0.35 187 0.4 162 0.5 129 表 4 快速升压段充电时间与充电容量所占百分比
Table 4. Percentage of charging time and charging capacity at the stage of voltage rising rapidly
电流倍率/C 时间占比/% 电量占比/% 0.05 0.98 0.99 0.1 1.36 1.39 0.15 1.87 1.97 0.2 2.29 2.49 0.25 2.19 2.49 0.3 1.96 2.32 表 5 缓慢升压段多项式系数与电流倍率拟合的结果
Table 5. Fitting results of polynomial coefficients and charging rates at the stage of voltage rising slowly
系数 Ej2 Ej1 Ej0 D2i -0.471 4 -0.300 9 -0.283 9 D1i 3.367 3 2.576 2 3.287 1 D0i -5.678 4 -5.859 7 -7.797 9 表 6 缓慢升压段系数pjI与电流倍率拟合结果
Table 6. Fitting results of coefficient pjI and charging rates at the stage of voltage rising slowly
系数 aji bji cji G2i 1 309 -0.932 9 1 327 G1i -14 407 -0.955 6 -10 967 G0i 36 678 -0.973 6 28 329 表 7 飞艇参数
Table 7. Airship parameters
几何参数 数值 能源相关参数 数值 长度/m 220 储能电池容量/(kW·h) 700 直径/m 54 电池能量密度/(Wh·kg-1) 330 浸润面积/m2 33 000 电机效率 0.93 体积/m2 380 000 螺旋桨效率 0.77 飞行高度/m 20 000 太阳能电池效率(273 K) 0.2 PV阵列面积/m2 2 200 PV阵列圆心角/(°) 90 表 8 两个飞行方案的参数设置
Table 8. Parameter setting for two flight schemes
参数 方案A 方案B 风速/(m·s-1) 15 20 白天空速/(m·s-1) 27 25 夜晚空速/(m·s-1) 15 15.5 纬度/(°N) 109.50 109.50 经度/(°E) 18.25 18.25 表 9 储能电池工作阶段划分(方案A)
Table 9. Work stage division of energy storage battery (Plan A)
阶段 时刻 电流倍率/C 1 18:00~18:40 0~ -0.066 2 18:40~06:40 -0.066 3 06:40~07:20 -0.066~0 4 07:20~08:40 0 5 08:40~11:32 0~0.268 6 12:32~13:24 0.268~0 7 13:24~18:00 0 表 10 储能电池工作阶段划分(方案B)
Table 10. Work stage division of energy storage battery(Plan B)
阶段 时刻 电流倍率/C 1 18:00~18:40 0~-0.072 2 18:40~06:40 -0.072 3 06:40~07:20 -0.072~0 4 07:20~08:10 0 5 08:10~11:52 0~0.339 6 11:52~12:55 0.339~0 7 12:55~18:00 0 -
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