Influence of secondary damage on flight cycles and inspection interval for an aircraft wing panel

Abstract

The present paper discusses the methodology for analytical estimation of an aircraft wing bottom panel flight cycles (FC) and inspection interval (II) at primary damage location based on critical value of FC due to secondary damage. The repeated type of fatigue spectrum is generated using the Air Force Fracture Mechanics and Fatigue Crack Growth Analysis software, which is further used for prediction of FC, and II of a finite Aluminum alloy plate (Al alloy: 2014 T-351) using Nasgro model. The influence of combined load, compressive load, composite reinforcement and delamination on critical FC, and II at primary damage location of wing bottom panel are investigated based on critical flight cycle due to secondary damage. The present methodology for estimation of FC and II is validated w.r.t. analytical estimation and published experimental results.

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Abbreviations

L′ and D′:

Lift and drag force

M, xcp :

Moment and aerodynamic center

W :

Width of plate, mm

B :

Hole offset distance, mm

T :

Panel thickness, mm

c, a :

Corner flaw length on surface and thickness, mm

c 2 :

Through crack length, mm

2a :

Total though crack length, mm

σ :

Nominal or applied stress, MPa

K 1 :

Mode-I stress intensity factor

c 3 :

Edge crack length, mm

n 1 :

Paris exponent

C1 :

Paris coefficient

f :

Crack closure parameter

p, q :

NASGRO equation exponents

W p :

Width of composite patch, mm

ΔKth :

Crack propagation threshold value of the stress intensity factor range, MPa(m)1/2

II:

Inspection interval

SF:

Scatter factor

D :

Diameter of bolt, mm

K max :

Maximum stress intensity factor, MPa(m)1/2

K min :

Minimum stress intensity factor, MPa(m)1/2

ΔK :

Difference in stress intensity factor, MPa(m)1/2

K :

Stress intensity factor

K d :

Stress intensity factor of composite patch with disbond, MPa(m)1/2

D h :

Disbond height

Ep, Er :

Modulus of elasticity for plate and reinforcement

tp, tr :

Thickness of plate and reinforcement

K r :

Stress intensity factor of composite patch without disbond

N 1 :

Corner crack flight cycles

N 2 :

Through crack flight cycles

N 3 :

Edge crack flight cycles

N crit :

Critical crack flight cycle

a crit :

Critical crack length

N det :

Detectable crack cycle

a det :

Detectable crack length

σ F :

Axial stress, MPa

Seq:

Equivalent stress

β :

Normalized stress intensity factor

σ b :

Bearing or pin stress, MPa

K c :

Plane stress fracture toughness, MPa(m)1/2

K IC :

Plane strain fracture toughness, MPa(m)1/2

t l :

Laminate thickness, mm

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Correspondence to Amit Kumar Srivastava.

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Srivastava, A.K., Arora, P.K. & Srivastava, S.C. Influence of secondary damage on flight cycles and inspection interval for an aircraft wing panel. J Braz. Soc. Mech. Sci. Eng. 42, 337 (2020). https://doi.org/10.1007/s40430-020-02425-z

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Keywords

  • Flight cycles
  • Corner flaws
  • Through crack
  • Inspection interval