面向eVTOL/eSTOL的分布式动力能源系统高精度建模与仿真

doi:10.7527/S1000-6893.2025.31513

Abstract

Abstract:

Addressing the challenges posed by drastic power load variations and high losses in complex transmission systems for distributed electric propulsion aircraft such as electric Vertical Take-Off and Landing/ electric Short Take-Off and Landing（eVTOL/eSTOL）， this paper proposes a high-precision power and energy system modeling and evaluation method applicable to the entire flight process of unmanned aerial vehicles （UAVs）. We first establish an energy system model based on a second-order RC battery model， identifying key parameters through a particle swarm algorithm using battery discharge experimental data， and construct a propulsion system model including propellers， motors， Electronic Speed Controllers （ESCs）， and transmission cables. Subsequently， a working state calculation framework for the UAV power and energy system based on an implicit function equation system is introduced and validated against experimental data. Finally， a simulation assessment of the power and energy system is conducted for a specific project involving a distributed electric propulsion UAV， alongside the optimization design of the transmission cable layout. The results indicate that both the voltage prediction error of the energy system and the errors in the system state calculation framework are smaller than 2%. The model accurately reflects the operational state changes of each component throughout the entire flight process， and the optimized transmission cable layout reduces voltage loss by 17.2% and average power loss by 16.36%， thereby verifying the accuracy and validity of the proposed method.

Key words: distributed electric propulsion, power and energy system modeling, second-order RC battery model, working state calculation framework modeling, transmission cable layout optimization

CLC Number:

V228

Sanya SUN, Zhuang SHAO, Zhou ZHOU, Kelei WANG, Jia ZONG. High-precision modeling and simulation of distributed propulsion energy systems for eVTOL/eSTOL[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(15): 131513.

Figures/Tables 26

Fig.1

Fig.2

Fig.3

Fig.4

Table 1

Battery parameter identification results

SOC	$R 1$ / $m Ω$	$R 2$ / $m Ω$	$C 1$ / $F$	$C 2 / F$	$R 0$ / $m Ω$	$U O C$ /V
1.0	7.54	22.92	62.12	454.25	18.3	25.2
0.9	7.74	21.54	59.04	516.13	18.4	24.77
0.8	7.41	19.77	81.39	572.66	18.2	24.2
0.7	6.54	16.04	165.77	942.20	17.8	23.64
0.6	6.18	16.49	128.11	667.26	18.1	23.31
0.5	6.36	18.33	133.80	614.55	15.8	23.13
0.4	5.76	16.67	131.78	659.16	13.9	22.94
0.3	5.40	14.41	46.30	798.22	15.1	22.76
0.2	5.49	15.61	34.31	627.63	16.2	22.74
0.1	5.64	16.31	24.22	193.45	16.7	22.36

Table 1

Fig.5

Table 2

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Fig.13

Table 3

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Table 4

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Fig.22

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放电工况		模型类型	MAE	归一化误差/%	RMSE
恒流放电	1倍率	二阶RC电路	0.059 6	0.85	0.078 1
	1倍率	Shepherd	0.713 8	10.20	0.772 4
	3倍率	二阶RC电路	0.139 8	1.99	0.159 0
	3倍率	Shepherd	0.843 5	12.05	0.936 7
	6倍率	二阶RC电路	0.165 4	2.36	0.207 1
	6倍率	Shepherd	1.477 9	21.11	1.550 7
恒功率放电	400 W	二阶RC电路	0.065 9	0.94	0.083 1
恒功率放电	400 W	Shepherd	0.823 5	11.70	0.903 8

参数	取值	参数	取值	参数	取值
ρ/（kg·m^-3）	1.188	C_M	0.006 4	I_m0/A	1.2
D/m	0.279 4	C_T	0.106 8	K_V₀	900
R_m/Ω	0.033 6	U_m0/V	10	R_e/Ω	0.025

参数	数值
总线长度L_bus/m	［1.748， 0.874］
分线长度L_div/m	［2.476， 1.636， 1.636， 2.476］［1.946， 0.718， 0.718， 1.946］
总线截面积S_bus/（10^-5 m²）	1.42
分线截面积S_div/（10^-6 m²）	6.99
总线有效导电面积占比K_bus	0.28
分线有效导电面积占比K_div	0.21
铜电阻率ρ_cu/（10^-8 Ω·m）	1.78
铜密度ρ_mcu/（kg·m^-³）	8 900
绝缘层密度ρ_mvs/（kg·m^-³）	932

High-precision modeling and simulation of distributed propulsion energy systems for eVTOL/eSTOL

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