多飞行状态倾转旋翼气动优化设计

doi:10.7527/S1000-6893.2023.29024

Abstract

Abstract:

A calculation model for the aerodynamic performance of tiltrotors was established based on the blade element momentum theory. The calculation model was combined with the NSGA-II multi-objective genetic algorithm to optimize the efficiency of the tiltrotor in hover， tilt forward flight， and high-speed cruise flight conditions. Parameters such as blade airfoil selection distribution， chord length and twist angle were used as optimization variables to design a tiltrotor. The rotor flow field was simulated by using the Delayed Detached Eddy Simulation （DDES） method improved from the classical Detached Eddy Simulation （DES）. The flow wake with high accuracy was captured， and the induced velocity distribution of the tiltrotor flow field was analyzed. At the same time， the high accuracy and reliability of the blade element momentum theory theoretical calculation model were verified. The calculation results show that under the same flight conditions， compared with the original tiltrotor model， the hovering efficiency increases from 71.78% to 75.34%， and the cruising efficiency increases from 62.93% to 71.32%.

Key words: tiltrotor, blade element momentum theory, NSGA-II algorithm, flight efficiency, delayed detached eddy simulation

CLC Number:

V211.52

Zonghui WANG, Yunjun YANG, Hongrui ZHAO, Xuechen WANG. Aerodynamic optimization design of tiltrotor under multiple flight conditions[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 529024-529024.

Figures/Tables 20

Fig.1

Fig.2

Fig.3

Fig.4

Table 1

Verification of hover and cruise flight condition

模型	拉力 $T$ /N	拉力系数 $C T / 10 - 3$	扭矩 $Q$ /（N·m）	功率系数 $C P / 10 - 3$	悬停效率 $f F M / %$	巡航效率 $η c r u i s e / %$
文献［26］	90 880	7.19	61 541	0.60	72.45
本文模型	90 627	7.17	61 024	0.59	72.73
文献［14］悬停	2 413	8.73	359	0.81	71.03
本文模型	2 394	8.66	344	0.78	73.22
文献［14］巡航	233	1.37	169	0.41		63.11
本文模型	231	1.35	166	0.40		63.59

Table 1

Table 2

Blade geometry parameters in Ref.［14］

$r / R$	弦长 $c$ /m	扭转角 $θ$ /（°）	翼型
0.20	0.292 5	25.44	xx1-mod
0.50	0.235 5	14.35	过渡翼型
0.75	0.188 0	7.60	过渡翼型
1.00	0.140 4	2.75	xx1

Table 2

Fig.5

Table 3

Fig.6

Fig.7

Table 4

Optimal blade geometry parameters

$r / R$	弦长 $c$ /m	扭转角 $θ$ /（°）	翼型
0.20	0.328 5	25.99	NACA64118
0.50	0.243 7	16.60	NACA64118
0.75	0.147 8	11.05	OA212
1.00	0.109 8	8.26	OA212

Table 4

Table 5

Optimal blade flight efficiency

悬停

桨距角

$θ 0.75 R$ /（°）

斜飞

桨距角

$θ 0.75 R$ /（°）

巡航

桨距角

$θ 0.75 R$ /（°）

f F M

η 30 °

η c r u i s e

11.05

14.05

23.00

77.41

54.57

73.73

Table 5

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Table 6

Comparison of rotor mechanical performance

模型	旋翼飞行状态	拉力 $T$ /N	扭矩 $Q$ /（N·m）	功率 $P$ /kW	效率/%
最优个体 $S$ （CFD）	悬停	2 297	314	32.9	75.34
	巡航	245	157	14.3	71.32
	倾斜前飞	1 850	403	36.7	50.34
最优个体 $S$ （BEMT）	悬停	2 389	325	34.0	77.41
	巡航	218	135	12.3	73.73
	倾斜前飞	1 722	301	31.6	54.57
文献［14］（CFD）	悬停	2 502	375	39.2	71.78
文献［14］（CFD）	巡航	253	184	16.8	62.93

Table 6

Fig.13

Fig.14

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参数	悬停	倾斜前飞	高速巡航
飞行高度/km	0	2	2
飞行速度/（m·s^-1）	0	20	41.7
拉力/N	≥2 352	≥1 600	≥147
功率/kW	≤37.7
转速/（r·min^-1）	1 000	1 000	870
效率/%			≥60

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Aerodynamic optimization design of tiltrotor under multiple flight conditions

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