基于蜻蜓翅几何及刚度相似性的仿生扑翼结构

doi:10.7527/S1000-6893.2022.27987

Abstract

Abstract:

At present， the research on flapping wing and flapping wing rotor micro aerial vehicles is mainly focused on the flapping mechanism design and aerodynamic characteristics analysis. The research on insect wings is mainly focused on the biological composition in micro scale， the material and mechanics. In the present study， the principal component analysis method is used to establish the relationship between the spanwise bending stiffness and the geometric parameters of insect wings. Taking the dragonfly-like flapping wing design as an example， a bionic flapping wing of geometric similarity to the structure layout of a dragonfly wing was designed. In addition， a stiffness similarity criterion for the dragonfly-like flapping wing design was established based on the experimental results of the spanwise bending stiffness of the dragonfly wings. The flapping wing structure was then optimized by using the stiffness similarity criteria as a design constraint. Test samples of a flapping wing （JX-wing） of rectangular shape and only stiffness similarity to dragonfly wings， a flapping wing （JH-wing） with only geometric similarity to dragonfly wings and a flapping wing （GD-wing） of both geometric and stiffness similarity to dragonfly wings were manufactured. Aerodynamic lift forces of those flapping wings were measured in the flapping frequency range of 5-15 Hz based on a flapping wing rotor test platform. The test results show that the GD-wing of both geometric and stiffness similarity can generate 25% higher lift than the rectangular JX-wing of only stiffness similarity at 12.5 Hz flapping frequency. The lift produced by the GD-wing of both geometric and stiffness similarity is close to the JH-wing of only geometric similarity when the flapping frequency is below 6.5 Hz， but increased to at least twice larger than the JH-wing when the flapping frequency is above 8 Hz. The flapping wing structure design method based on both geometric similarity and stiffness similarity provides a pass-way to improve the aerodynamic lift and efficiency of flapping wing and flapping wing rotor.

Key words: principal component analysis, geometry similarity, stiffness similarity, flapping wing structure model, flapping wing rotor experiment

CLC Number:

V276

Yuanyuan HE, Xuan YANG, Hui HAN, Qichen WANG, Hang ZHANG. A dragonfly-like flapping wing structure based on geometry and stiffness similarity[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(14): 227987-227987.

Figures/Tables 36

Table 1

Table 2

Eigenvalues and principal component contribution

主成分	特征值	贡献率/%	累计贡献率/%
$z 1$	3.884 6	97.11	97.11
$z 2$	0.114 5	2.86	99.98
$z 3$	9.379 4×10^-4	0.02	100
$z 4$	-1.908 2×10^-5	0	100

Table 2

Fig. 1

Table 3

Fig. 2

Table 4

Table 5

Table 6

Table 7

Table 8

Table 9

Fig. 3

Fig. 4

Fig. 5

Fig. 6

Fig. 7

Fig. 8

Fig. 9

Table 10

Bending stiffness along span of flapping wing

$i$	展向位置/%	展向抗弯刚度/（10^-3 N·m²）
0	0	6.526 0
1	10	5.938 4
2	20	5.350 8
3	30	4.763 2
4	40	4.175 6
5	50	3.588 0
6	60	3.000 4
7	70	2.412 8
8	80	1.825 2
9	90	1.237 6
10	100	0.650 0

Table 10

Fig. 10

Table 11

Parameters of partial beam line-width function of flapping wing model

脉络编号 $j$	$a j$	$b j$
1	-2.7	3.0
2	-0.5	2.0
3	-2.7	3.0
4	-1.2	1.5
5	-0.6	1.1
6	-0.9	1.2
7	-0.7	1.0

Table 11

Fig. 11

Fig. 12

Fig. 13

Fig. 14

Fig. 15

Fig. 16

Table 12

Table 13

Fig. 17

Table 14

Fig. 18

Table 15

Table 16

Fig. 19

Table 17

References 29

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翅长l/mm	弦长b/mm	翼面积S/mm²	重量m/g	抗弯刚度EI/（N·mm²）
8	2.254	15.42	0.006 049	0.711 50
9	2.573	19.47	0.008 885	1.009 50
10	2.897	23.99	0.012 530	1.380 40
20	6.319	94.63	0.120 382	10.815 8
30	9.972	211.20	0.452 193	36.062 0
40	13.782	373.30	1.156 442	84.745 8
50	17.715	580.70	2.395 731	164.400
60	21.748	833.18	4.343 959	282.559
70	25.866	1 130.56	7.184 557	446.626
80	30.059	1 472.70	11.109 275	664.000

参数	蜻蜓编号
参数	1	2	3
体重/mg	330	380	250
体长/mm	50	50	49
体宽/mm	7	6	6
前翅翼展/mm	90	90.5	85
前翅长度/mm	44	43.5	41.5
前翅最大弦长/mm	10	10.5	9.5

加载位置/mm	加载重量/mg	加载处位移/mm	抗弯刚度/（N·mm²）
31（展向70%处）	250	4	6.69
31（展向70%处）	350	5.5	6.81
31（展向70%处）	450	7	6.88
40（展向90%处）	250	14	4.02

加载位置/mm	加载重量/mg	加载处位移/mm	抗弯刚度/（N·mm²）
31（展向70%处）	150	1	16.4
31（展向70%处）	250	2	13.4
31（展向70%处）	350	3	12.5
31（展向70%处）	450	4	12.0

加载位置/mm	加载重量/mg	加载处位移/mm	抗弯刚度/（N·mm²）
22（展向50%处）	350	1	12.2
26（展向60%处）	150	1	8.61
26（展向60%处）	250	2	7.18

A dragonfly-like flapping wing structure based on geometry and stiffness similarity

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Figures/Tables 36

References 29

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加载位置/mm	加载重量/mg	加载处位移/mm	抗弯刚度/（N·mm²）
30（展向70%处）	200	2	8.82
30（展向70%处）	250	3	7.35
30（展向70%处）	300	4	6.62
36（展向83%处）	150	8	2.86

加载位置/mm	加载重量/mg	加载处位移/mm	抗弯刚度/（N·mm²）
20（展向48%处）	450	1	11.8
30（展向72%处）	150	1	13.2
30（展向72%处）	200	1.5	11.8
30（展向72%处）	250	2	11.0
35（展向84%处）	80	2	5.60
35（展向84%处）	150	3	7.00
35（展向84%处）	200	3.5	8.00
35（展向84%处）	250	4	8.75

加载位置/mm	加载重量/mg	加载处位移/mm	抗弯刚度/（N·mm²）
25（展向60%处）	200	1	10.2
25（展向60%处）	250	1.2	10.6
25（展向60%处）	300	1.4	10.9
25（展向60%处）	350	1.6	11.2
25（展向60%处）	400	1.8	11.3
25（展向60%处）	450	2	11.5
30（展向72%处）	250	2	6.62
30（展向72%处）	80	2	7.10
30（展向72%处）	150	3	7.35
30（展向72%处）	200	3.5	7.56
30（展向72%处）	250	4	7.72

电压/V	频率/Hz	最大升力/gf	最大负升力/gf	平均升力/gf
0.6	4.1	19.5	-18.9	0.7
1.0	4.6	33.1	-33.6	1.6
1.4	5.3	45.0	-46.2	3.5
1.8	6.6	64.1	-56.4	4.4
2.2	8.0	85.6	-75.4	5.8
2.6	9.3	114.1	-82.1	8.5
3.0	10.8	123.9	-90.2	11.1
3.2	12.5	136.3	-91.6	12.9
3.4	14.3	161.5	-128.7	14.7

拍动频率/Hz	最大升力/gf	最大负升力/gf	平均升力/gf
4.6	22.2	-15.8	1.8
6.6	30.1	-17.2	3.9
8.3	31.1	-26.8	3.0
9.3	38.4	-28.8	2.2

拍动频率/Hz	4.6	6.6	8.3	9.3
JH翼平均升力/gf	1.8	3.9	3.0	2.2
GD翼平均升力/gf	1.6	4.4	6.9	8.5
升力提升比/%	-11.11	12.80	130.00	286.36

拍动频率/Hz	最大升力/gf	最大负升力/gf	平均升力/gf
9.3	50.8	-36.7	8.1
10.8	57.5	-38.4	9.5
12.5	64.0	-40.1	10.3
14.3	72.3	-47.7	12.3

拍动频率/Hz	9.3	10.8	12.5	14.3
JX翼平均升力/gf	8.1	9.5	10.3	12.3
GD翼平均升力/gf	8.5	11.1	12.9	14.7
升力提升比/%	4.9	16.8	25.2	19.5

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梁名称	主梁	次梁	斜次梁
长度/mm	140	35	144
直径/mm	0.85	0.68	0.78