Repair of mirage III aircraft using the BFRP crack-patching technique

A. A. Baker; R. J. Callinan; M. J. Davis; R. Jones; J. G. Williams

doi:10.1016/0167-8442(84)90035-1

Repair of mirage III aircraft using the BFRP crack-patching technique

A. A. Baker, R. J. Callinan, M. J. Davis, R. Jones, J. G. Williams

Research output: Contribution to journal › Article › Research › peer-review

116 Citations (Scopus)

Abstract

The BFRP crack-patching technique has been applied to the field repair of fatigue cracks in the aluminium alloy wing skins of Mirage III fighter aircraft. Finite-element procedures were used in patch design. The repair was qualified using fatigue-crack propagation studies on panels simulating the cracked and repaired area. A field support unit was designed to allow repairs to be carried out by air force personnel during routine maintenance of the aircraft. To date over 150 patches have been applied and nearly three years of operational history gained. While some crack growth was observed after repair of a few wings, the patch stopped further growth and no wing skin has required further repair.

Original language	English
Pages (from-to)	1-15
Number of pages	15
Journal	Theoretical and Applied Fracture Mechanics
Volume	2
Issue number	1
DOIs	https://doi.org/10.1016/0167-8442(84)90035-1
Publication status	Published - Oct 1984
Externally published	Yes

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abstract = "The BFRP crack-patching technique has been applied to the field repair of fatigue cracks in the aluminium alloy wing skins of Mirage III fighter aircraft. Finite-element procedures were used in patch design. The repair was qualified using fatigue-crack propagation studies on panels simulating the cracked and repaired area. A field support unit was designed to allow repairs to be carried out by air force personnel during routine maintenance of the aircraft. To date over 150 patches have been applied and nearly three years of operational history gained. While some crack growth was observed after repair of a few wings, the patch stopped further growth and no wing skin has required further repair.",

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AU - Williams, J. G.

PY - 1984/10

Y1 - 1984/10

N2 - The BFRP crack-patching technique has been applied to the field repair of fatigue cracks in the aluminium alloy wing skins of Mirage III fighter aircraft. Finite-element procedures were used in patch design. The repair was qualified using fatigue-crack propagation studies on panels simulating the cracked and repaired area. A field support unit was designed to allow repairs to be carried out by air force personnel during routine maintenance of the aircraft. To date over 150 patches have been applied and nearly three years of operational history gained. While some crack growth was observed after repair of a few wings, the patch stopped further growth and no wing skin has required further repair.

AB - The BFRP crack-patching technique has been applied to the field repair of fatigue cracks in the aluminium alloy wing skins of Mirage III fighter aircraft. Finite-element procedures were used in patch design. The repair was qualified using fatigue-crack propagation studies on panels simulating the cracked and repaired area. A field support unit was designed to allow repairs to be carried out by air force personnel during routine maintenance of the aircraft. To date over 150 patches have been applied and nearly three years of operational history gained. While some crack growth was observed after repair of a few wings, the patch stopped further growth and no wing skin has required further repair.

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Repair of mirage III aircraft using the BFRP crack-patching technique

Abstract

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