Multidisciplinary Integrated Framework for the Optimal Design of a Jet Aircraft Wing

Table 5

Level 3, structural sizing loop results summary.

(a) Structural Sizing Optimization

Sizing data
Stringer section	L section
Spar cap material	Aluminium
Stringer material	Aluminium
Sizing variables	Best
Spar caps (Figure 12  shows the legend for element position)
h13	21,24 mm
h24	22,29 mm
Base13	22,19 mm
Base24	22,08 mm
Thickness h13	1,72 mm
Thickness h24	2,34 mm
Thickness base13	1,62 mm
Thickness base24	2,64 mm
Stringers	L section
h top	22,02 mm
h bottom	15,86 mm
Base top	21,41 mm
Base bottom	20,30 mm
Thickness h top	2,98 mm
Thickness h bottom	2,57 mm
Thickness base top	1,86 mm
Thickness base bottom	2,66 mm
Number of stringers	3
Spars position
1	25,98% chord
2	62,11% chord
Ribs position
1	0% span
2	5% span
3	10% span
4	15% span
5	20% span
6	25% span
7	30% span
8	35% span
9	40% span
10	45% span
11	50% span
12	55% span
13	60% span
14	65% span
15	70% span
16	75% span
17	80% span
18	100% span

(b) Composites stacking sequence characteristics

Layers thickness
Leading edge	0,3 mm
Top surface	0,3 mm
Bottom surface	0,3 mm
Trailing edge	0,3 mm
Spars	0,3 mm
Ribs	0,3 mm
Layers orientation [ ° ]	1	2	3	4	5	6	7	8	9	10
Leading edge	45	45	90	45	90	90	45	90	45	45
Top surface	90	45	45	90	45	0	90	90	0	45
Bottom surface	90	45	90	90	0	45	0	90	45	90
Trailing edge	90	0	45	0	45	45	45	45	90	0
Spars	45	45	90	90	90	45	45	45	90	0
Ribs	45	45	90	45	45	0	0	0	0	0

(c) Optimum objective variables

Manufacturing cost	4,35E + 07
Structural mass	2077 kg
Maximum displacement	1603 mm