飞行器能源与热管理系统中多能流统一建模与分析方法

doi:10.7527/S1000-6893.2023.28427

Abstract

Abstract:

The integrated optimization of energy and thermal management system is one of the key technologies in aircraft performance improvement. However， due to the differences in traditional analysis methods of thermal management， power supply and other subsystems， the overall integration analysis is too complicated to conduct. Based on the heat current method of thermal system analysis， this paper establishes the standardized transmission network model of electric， heat and working medium， and proposes the data interaction method between the subsystems of thermal management and power supply， forming an overall modeling and analysis method for the energy and thermal management system of aircraft. The same system is also computationally tested on AMESim. Calculation results show that the calculation time of the newly proposed method is nearly 2 orders of magnitude lower than that of the commercial software AMESim on the premise of ensuring the accuracy. Through the variable condition simulation of the system with a given flight profile， it is calculated that under the requirement of temperature control， the carrying capacity of the phase change working medium required by a single mission target is calculated to be 348.8 kg， and the minimum initial power and capacity required by the airborne battery are 1 837 and 3 158 W∙h， repsectively. In conclusion， the proposed method can be used for quantitative lightweight optimization of aircraft.

Key words: energy and thermal management system, overall analysis, graph theory, transmission network model, heat current method

CLC Number:

V245

Runhang TENG, Kelun HE, Tian ZHAO, Xiaoxiao YU, Xikui YU, Xianghua XU, Xingang LIANG, Qun CHEN. Unified modeling and analysis method of multi-energy flow for aircraft energy and thermal management system[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(19): 128427-128427.

Figures/Tables 17

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Table 1

Coefficient matrix in constraint equations of each physical process

系数矩阵	电机	管道	离心泵	换热器换热过程	两股流混合过程	单股流加热过程
$F$	$1$	$1$	$1$	$100010001$	$1001$	$1000$
$H$	$- r + P i k 2$	$- 12 f m ˙ k ρ A 2 ⋅ L D + ζ$	$- a 1 ω ρ g ρ + a 2 g m ˙ k ρ$	$00 - 1 G 1 00 1 G 2 00 - R h$	$0 2 × 2$	$0 1 G 1 01$
$J$	$0 1 × 2$	$0 1 × 2$	$0 1 × 2$	$0 3 × 4$	$- G 1 G 1 + G 2 G 2 G 1 + G 2 0 G 1 G 1 + G 2 - G 1 G 1 + G 2 0$	$0 2 × 2$
$Ω s$	$2 P i k$	$0$	$0$	$0 1 × 3$	$0 1 × 2$	$0 Q s$
$Φ s$	$0$	$0$	$a 0 ω 2 ρ g$	$0 1 × 3$	$0 1 × 2$	$0 1 × 2$

Table 1

Fig.9

Table 2

Table 3

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

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部件类型	能量流模型	AMESim对比模型
换热器	通过热阻计算，考虑了两侧流体的流速变化对传热的影响。	采用ε-NTU法并固定换热器效能，忽略两侧流体流速变化的影响。
离心泵	压差表示为体积流量、泵转速和流体密度的函数；考虑机械效率引起的发热。	压差表示为体积流量、泵转速的函数；忽略机械效率引起的发热。
容积泵	考虑机械效率引起的发热。	忽略机械效率引起的发热。
调节阀	压差表示为阀门开度、体积流量和流体密度的函数。	体积流量表示为阀门开度、压差的函数。
压气机/涡轮	基于弗留格尔公式^［30］的通流系数模型。	构建增压比、相对内效率（绝热效率）与修正质量流量、修正转速函数关系的模型。
多支路连接节点	节点连接的各条支路相互等价，后续通过整体迭代计算节点变量。	需要事先指定一条主要支路，该支路在流程中的计算结果作为节点变量的计算结果。

计算参数	数值		偏差/%
计算参数	多能流整体求解算法	AMESim	偏差/%
计算时间/s	19.14	6 185
燃烧室供油量（p13）/（kg·s^-1）	1.02	1.00	2.0
加力燃烧室供油量（p19）/（kg·s^-1）	2.33	2.41	3.4
液冷循环流量（pm7）/（kg·s^-1）	2.45	2.39	2.5
滑油循环1流量（pm5）/（kg·s^-1）	6.53	6.50	0.5
滑油循环2流量（pm6）/（kg·s^-1）	6.53	6.50	0.5
加力燃烧室回油支路1流量（v8）/（kg·s^-1）	2.03	2.05	-1.0
加力燃烧室回油支路2流量（v6）/（kg·s^-1）	1.02	0.98	4.9
燃烧室油路出口温度/K	367.3	369.6	-0.6
加力燃烧室油路出口温度/K	339.8	335.3	0.6
换热器（hex1）热流体入口温度/K	407.8	405.7	1.3
换热器（hex1）冷流体入口温度/K	329.8	327.0	0.8
换热器（hex2）热流体入口温度/K	410.3	406.3	1.0
换热器（hex2）冷流体入口温度/K	320.3	316.3	1.3
换热器（hex3）热流体入口温度/K	316.5	314.5	0.6
换热器（hex4）热流体入口温度/K	355.9	352.0	1.1
换热器（hex4）冷流体入口温度/K	317.9	315.1	0.9

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Unified modeling and analysis method of multi-energy flow for aircraft energy and thermal management system

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