PSI - Issue 71

M. Mohan Kumar et al. / Procedia Structural Integrity 71 (2025) 333–339

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3.2 Loads and Boundary condition details The wing was subjected to testing under the critical One-Wheel Landing load case, which is considered for the Design Limit Load test. In this scenario, both Z and X loads were applied at the landing gear attachment brackets on all four landing gear attachment points of the wing, aligned with the global X and Z directions. These loads are crucial as they determine most of the design parameters. Y-direction loads were not applied during the test, as their impact on the structure is negligible. The structural loads applied at the landing gear attachment points are outlined in Table 1, while the details of the boundary conditions are illustrated in Fig. 3.

Fig. 3. Load application points on MLG for One-wheel landing case.

Table 1. Load chart for One-wheel landing load case Location

Global

Coordinates

Loads at MLG (kg)

X

Y

Z

Fx

Fy

Fz

A B C D E

1415 1415 1415 1415 1285 1285 1285 1285 1285 1285 1285 1285 1415 1415 1415 1415

-520 -441 -520 -440 -520 -440 -520 -440

-460 -460 -510 -510 -460 -460 -510 -510 -460 -460 -510 -510 -460 -460 -510 -510

68.9 68.9 68.9 68.9 68.9 68.9 68.9 68.9 -27.1 -27.1 -27.1 -27.1 -27.1 -27.1 -27.1 -27.1

0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0

690.3 690.3 690.3 690.3 -242.3 -242.3 -242.3 -242.3

Left MLG rear

F

Left MLG front

G H

I J

440 520 440 520 440 520 440 520

-88 -88 -88 -88 -88 -88 -88 -88

Right MLG front

K L

M

N O

Right MLG rear

P