Rapid Application TechnologyAircraft Battle Damage Repairs

Bartholomeusz, R.A.; Pearce, P. J.; Vodicka, Roger

doi:10.1016/b978-008042699-0/50027-9

Cited by 4 publications

(3 citation statements)

References 8 publications

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“…A certain aircraft battle damage information once was described as "disconnected to the automatic flight control system was found during air combat." Through the analysis of the damage, it is concluded that the source of the problem is not the failure of the automatic flight control system, but the damage of the angle of attack sensor of the avionics system [26][27][28]. Therefore, the damage mode should actually be "equipment damageabnormal electronic equipment -abnormal operation of flight control equipment -abnormal response -unstable operation -data jumping" instead of "abnormal responseabnormal disconnection" [29].…”

Section: Casementioning

confidence: 99%

Research on Standardization of Aircraft Battle Damage Description

Jia

Zhao

Guo³

2021

E3S Web Conf.

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Rapid and accurate description of battle damage is the first step in aircraft battle damage repair (ABDR). The standardized description of damage information is the basis of the construction of aircraft battle damage data model. This paper studies and analyses the statistical description of battle damage in the view of definition, damage mode and cause classification of battle damage, so as to obtain the basis for standardized description of battle damage information.

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Section: Casementioning

confidence: 99%

Research on Standardization of Aircraft Battle Damage Description

Jia

Zhao

Guo³

2021

E3S Web Conf.

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“…2 Composite patch repairs have several advantages over the more traditional methods of bolting or welding of metal plates onto metallic structures: fibers may be arranged in position, density, and orientation within the matrix to achieve unique performance requirements; per unit volume, composite materials typically weigh much less than metal and have higher strength and stiffness; composites have high failure strain, durability, and corrosion resistance; and adhesive bonding eliminates stress concentrations at bolt holes. 3,4 A select few of the many examples of composite patch repair in the aerospace industry include: the reinforcement of the Royal Australian Air Force F-111 wing pivot fitting with a boron/epoxy composite, reducing strain in that part by 30%; 5 and a rapid repair technique developed by Bartholomeusz et al 6 using carbon/vinyl ester patches to quickly restore the airworthiness of battle damaged aircraft in times of conflict which demonstrated the superior performance of bonded composite repairs to battle damaged aircraft versus traditional fastened repairs under both static and fatigue loading through experimental damage.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Composite Patch Performance Under Low-Velocity Impact Loading

Goodmiller

TerMaath

2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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A finite element model to investigate the performance of hybrid structure under lowvelocity impact loading was developed and validated using a building-block approach. The hybrid structure consisted of a composite patch adhesively bonded to a metal substrate. Each component of the model was validated individually to accurately capture the behavior and damage mechanisms of each material. Interlaminar composite damage and adhesive damage were modeled with cohesive zone theory. Hashin failure criteria with energy dissipation based damage evolution modeled intralaminar damage in the composite. The Johnson-Cook plasticity model captured the metal substrate's behavior. Each component was assembled into a hybrid structure model that captured the interactions between the damage modes. Once the hybrid model was validated with experimental results, a sensitivity study was performed on various input parameters to provide guidance for optimized design of composite patches subjected to low-velocity impact loading. NomenclatureA, B, C, m, n = Johnson-Cook material constants a 0 = initial crack length BK = Benzeggagh-Kenane C v = empirical variable adjusting for void content CDM = continuum damage mechanics CFRP = carbon-fiber reinforced polymer CZT = cohesive zone theory d = length of the lever arm in MMB test D = damage variable DCB = double cantilever beam E m = Young's Modulus of matrix E 1 , E 1f = Young's Modulus of ply or fiber, longitudinal orientation E 2 , E 2f = Young's Modulus of ply or fiber, transverse orientation E 3 = Young's Modulus of ply, out-of-plane orientation ENF = end-notched flexure F = applied load FRP = fiber reinforced polymer G c = critical fracture energy G f c , G f t = energy dissipation rate, longitudinal (fiber) compressive or tensile G I , G II = Mode I or II fracture energy G Ic , G IIc = Mode I critical fracture energy G m = shear modulus, matrix G m c , G m t = energy dissipation rate, transverse (matrix) compressive or tensile G shear = total shear fracture energy G T = total fracture energy G 12 , G 12f 2 G 13 = transverse shear modulus G 23 , G 23f = out-of-plane shear modulus of ply or fiber GFRP = glass-fiber reinforced polymer h = thickness of adhered plies K = penalty stiffness , = fiber or matrix bulk modulus L = length of half span for DCB, ENF, MMB tests , = Mode I or II cohesive zone length L e = length of each element LEFM = linear elastic fracture mechanics M = length of cohesive zone parameter MMB = mixed mode bending N e = number of elements in the cohesive zone S L , S Lm = longitudinal shear strength of ply or matrix S T = transverse shear strength S 0 , S a = maximum traction, Mode II; max. traction from coarse mesh refinement, Mode II t, t n , t s , t t = traction, Mode I, Mode II, or Mode III traction T = homologous temperature T c = thickness of adhesive layer ̅ = traction without damage application, Mode I T 0 , T a = maximum traction, Mode I; max. traction from coarse mesh refinement, Mode I = effective traction at damage inititiation V f = fiber volume ratio V m = ma...

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“…1 Bonding composite patches to damaged areas is a widely used repair technique in the industry. Studies differ according to engineering and industry needs such as aerospace industry, [1][2][3][4] civil engineering, [5][6][7][8][9] and naval applications. [10][11][12] A number of researchers [13][14][15] have concluded that the effect of repairing a patch depends on the bonding process and patch design.…”

Section: Introductionmentioning

confidence: 99%

Numerical model for composite patch repair of notched aluminum plates under impact loading

Çalışkan

Ekici

Bayazit

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part L:

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The damaged area for various structures can be effectively repaired using composite materials. With the effect of impact, damage can occur that cannot be clearly seen in the inner structure of a laminated composite. This can cause delamination and other damage modes in layered composite structures. In this study, three-dimensional dynamic progressive damage analysis was performed in adhesively bonded composite patch-repaired metal notched plates under impact loads to investigate the effect of external composite patch material and thickness. Three-dimensional Hashin damage models were used for the progressive damage model. A user-defined subroutine, VUMAT was written to transfer the damage models to finite element code. By writing a separate script in Python language that relates to the damage models, the weakness in the laminate of the composite patch was transferred to the finite element model with a different degradation model proposed. It was found that plastic deformations occurring after impact damage in the notched metal plates was prevented by the use of composite patches. While glass and carbon fiber exhibit similar behavior at lower impact velocities, the progress of damage is prevented by increasing patch thickness. These behaviors were confirmed by the numerical model and showed an advanced agreement with experimental results.

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Rapid Application TechnologyAircraft Battle Damage Repairs

Cited by 4 publications

References 8 publications

Research on Standardization of Aircraft Battle Damage Description

Research on Standardization of Aircraft Battle Damage Description

Investigation of Composite Patch Performance Under Low-Velocity Impact Loading

Numerical model for composite patch repair of notched aluminum plates under impact loading

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