氢能飞机及航空动力多学科总体耦合设计

doi:10.7527/S1000-6893.2025.31712

Abstract

Abstract:

Compared with traditional aircraft， hydrogen-powered aircraft undergo significant changes in aspects such as propulsion systems， fuel storage and transportation systems， and airframe structure. Firstly， a fuel cell hybrid power system model is established， integrating the polarization losses of the fuel cell with the overall performance of the electric-driven fan engine. Then， liquid hydrogen storage tank and hydrogen supply models are developed， and the pressure and temperature variations inside the tank during the hydrogen supply process are evaluated. Next， three-dimensional geometric modeling of the aircraft is performed， along with rapid aerodynamic assessment， and the impact of integrating the liquid hydrogen tank on the overall aerodynamic characteristics of the aircraft is analyzed. The variation of the aircraft’ s lift-to-drag ratio with the external shape is obtained. By considering fuel storage energy， propulsion system power， and tank structural design， as the aircraft carries more energy， the weight efficiency of the liquid hydrogen storage tank can reach up to 80%. Considering both the fuel consumption rate and mass of the fuel cell hybrid power system， the layout of the hydrogen fuel tank is optimized， and a multi-dimensional match of fuel storage and transportation systems， propulsion systems， and aircraft airframe structure for the liquid hydrogen-powered aircraft is achieved，resulting in an integrated airframe-propulsion matching scheme. The study further shows that simply increasing the fuselage length results in a small change in the lift-to-drag ratio. The reduction in carbon emissions and the weight efficiency of the hydrogen tank are positively correlated with the increase in fuselage length. When the fuselage length is extended by 5%， the carbon emission can be reduced by 714 kg， corresponding to a 1.56% reduction rate. When the fuselage length is extended by 20%， the carbon emission can be reduced by 45 709 kg， achieving a 100% reduction rate， and the cruising time exceeds that of traditional aircraft by 10.04%.

Key words: hydrogen-powered aircraft, multidisciplinary coupling, fuel cell, aviation propulsion, engine characteristics

CLC Number:

V272

Zhixing JI, Yanzhe WANG, Xiaoxue MEI, Liwen CHENG, Zibo XU, Zhanxue WANG. Multidisciplinary coupling design of hydrogen-powered aircraft and aviation propulsion[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(17): 231712.

Figures/Tables 22

Fig.1

Fig.2

Fig.3

Table 1

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Table 2

Table 3

Table 4

Fig.11

Table 5

Additional weight brought to aircraft by a single hydrogen tank and corresponding energy contained in hydrogen

机身长度增加比例/%	r/m	增加空间的体积V₁/m³	氢罐的体积V₂/m³	液氢的质量 $m H 2$ /kg	罐体的总质量m_tank/kg	质量效率/%	氢含有的能量Q/（10⁹ J）
5	0.42	21.9	0.96	67.8	525	14.0	9.62
10	0.85	43.8	7.67	543	1 198	49.6	77
15	1.27	65.7	25.9	1 832	2 940	67.9	260
20	1.70	87.7	61.3	4 342	6 243	75.4	616

Table 5

Fig.12

Table 6

Fuel system parameters corresponding to different fuselage lengths

机身长度增加比例/%	液氢的质量 $m H 2$ /kg	氢含有的能量Q/（10⁹ J）	仍需携带的航空煤油质量/kg	飞机在燃料部分减轻的质量/kg	碳排放减少量/kg	减碳比例 /%
5	67.8	9.62	14 437	-3 640	714	1.56
10	542	77	12 833	91.9	5 713	12.5
15	1 832	260	8 479	1 415	19 283	42.2
20	4 342	616	0	4 081	45 709	100

Table 6

Table 7

Table 8

Table 9

Table 10

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燃料	单位质量所含能量/（MJ·kg^-1）	单位体积所含能量/（MJ·L^-1）
氢（液态）	121	8.50
氢（标准大气压）	121	0.01
氢（被压缩状态，700 bar）	121	5.60
航空煤油	43.1	34.4
汽油	44.4	32.5
柴油	45.6	38.6
天然气（液态）	53.6	22.2

飞机几何参数	数值
飞机长度/m	39.5
翼展/m	35.8
机身高度/m	4.01
机身宽度/m	3.76

设计点参数	数值
迎角/（°）	1~16
巡航马赫数	0.79
雷诺数/10⁹	4.67
飞行高度/m	12 500
巡航速度/（km·h^-1）	828

机身长度增加比例/%	增加长度/m
5	1.97
10	3.95
15	5.92
20	7.89

参数	数值
风扇压比	1.50
风扇效率	0.86
压气机压比	1.33
压气机效率	0.86
空气流量/（kg·s^-1）	12.8
发动机耗油率/（10^-6 kg·（N∙s）^-1）	5.40
巡航马赫数	0.85
涵道比	12.9
推力/（10⁴ N）	2.18
热效率	0.49
推进效率	0.80
总效率	0.39
燃料电池阳极进口温度/K	325
燃料电池阴极进口温度/K	299
阳极厚度/μm	190
阴极厚度/μm	190
燃料电池总功率/MW	6.80
燃料电池活化面积/（10³ m²）	3.51
单个发动机燃料电池堆数	4
燃料电池堆长度/m	0.70
燃料电池堆宽度/m	0.70
燃料电池堆高度/m	0.34
燃料电池堆层数	942
外涵散热量与电功率之比	0.94

Multidisciplinary coupling design of hydrogen-powered aircraft and aviation propulsion

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机身长度增加比例/%	sfc（液氢）/（10^-6 kg/（N∙s）^-1）	sfc（煤油）/（10^-5 kg/（N∙s）^-1）	升阻比
0	5.40	1.60	18.9
5	5.40	1.60	16.8
10	5.40	1.60	16.5
15	5.40	1.60	16.3
20	5.40	1.60	16.0

机身长度增加比例/%	使用航空煤油阶段		使用液氢阶段
机身长度增加比例/%	M₁/kg	M₂/kg	M₁/kg	M₂/kg
0	61 865	41 000	41 000	41 000
5	59 076	44 639	44 639	44 571
10	58 444	45 611	45 611	45 068
15	56 055	47 396	47 396	45 564
20	50 403	50 403	50 403	46 061

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机身长度增加比例/%	巡航时间/h
0	6.87
5	4.29
10	4.65
15	5.79
20	7.56