F-5M DTA Program

Mattos, Daniel Ferreira V.; Mello Junior, Alberto W. S.; Ribeiro, Fabrício N.

doi:10.5028/jatm.2009.0101113120

Abstract:

The Brazilian F-5 was submitted to avionics and weapons upgrade. This "new" aircraft has proven to be heavier and more capable. A comprehensive damage tolerance analysis is being performed to evaluate how the new mission profiles and weight distribution may affect the airframe structural integrity. Operational data were collected at the Brazilian Air Force Bases where the fighter is flown. Software was developed in order to acquire, filter and anafyze flight data. This data was used for comparison between the pre and post modernization mission profiles and to determine the stress level in each of the known aircraft fatigue critical locations (FCL). The results show that the change in aircraft weight and balance and the new operational profile can significantly change the inspection intervals of certain fatigue critical locations of the structure. A preliminary result for the horizontal tail has shown that this component will have a much more restrictive maintenance schedule to assure flight safety.

Key words:
Fatigue; Damage tolerance; Structure; F-5; Flight data analysis; Crackgrowth

Full text is available only in PDF.

REFERENCES

AFWAL-TR-82-3073, 1984, "USAF Damage Tolerant Design Handbook: Guidelines for the Analysis and Design of Damage Tolerant Aircraft Structures". Wright-Patterson AFB Ohio, Final Report.
Bumside, H., 1993, "Flying Longer: With Confidence", Technology Today.
Mattos, D.F.V., 2008, "Análise de Dados de Vôo das Aeronaves F-5M Para Cálculo de Vida em Fadiga", pp.18-74, Graduation Work, ITA, São José dos Campos.
Mello Jr., A.W.S., 1998, "Crack 2000 Program: Software for Practical Fracture Mechanics and Damage Tolerance Analysis", User's Manual, IAE, São José dos Campos.
Mello Jr., A.W.S. et al. , 2008, "Edição e Pré-Análise de Dados Operacionais do Projeto DTA F-5M: Software EPAD F-5M", IAE, São José dos Campos (RENG ASA-I 03/08).
Mello Jr., A.W.S. et al., 2009, "Geração de Ciclo de Tensões para Análise de Fadiga. Software GCTAF F-5M", IAE, São José dos Campos (Submitted for approval).
Northtrop Corporation, 1977, "F-5E/F Fatigue Loads for the Damage Tolerance Assessment", Hawthome, CA, (NOR 76-164)
RIBEIRO, F. N., 2008, "Procedimentos a respeito da Coleta de Dados de Vôo das Aeronaves F-5EM e F-5FM utilizando o Programa F5DACOM", IAE, São José dos Campos (RENG ASA-102/08).
RIBEIRO, F. N., 2009, "Procedimentos para a Seleção de Dados de Fadiga das Aeronaves F-5EM e F-5FM utilizando o Programa SEDAF", IAE, São José dos Campos (Submitted for approval).
USAF, 1975,'Aircraft Struetural Integrity Program: Airplane Requirements". Wright-Patterson AFB Ohio, FSG-15GP, (MIL-STD-1530).
USAF, 1974, "Airplane Damage Tolerance Requirements". Wrigth-Patterson AFB. Ohio, (MIL-A-83444).
USAF, 1975, "Airplane Strength and Rigidity Realibility Requirements, Repeated Loads and Fatigue", Wrigth-Patterson AFB Ohio,045433, (MIL-STD-A-886B).
Wieland, David H. et al., 1995, " F-5 FMS Durability and Damage Tolerance Update Final DADTA Report F-5", E. Southwest Research Institute, San Antonio, Texas.

Publication Dates

Publication in this collection
Jan-Jun 2009

History

Received
05 May 2009
Accepted
27 May 2009

This is an Open Access article distributed under the terms of the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

[1] AFWAL-TR-82-3073, 1984, "USAF Damage Tolerant Design Handbook: Guidelines for the Analysis and Design of Damage Tolerant Aircraft Structures". Wright-Patterson AFB Ohio, Final Report.

[2] Bumside, H., 1993, "Flying Longer: With Confidence", Technology Today.

[3] Mattos, D.F.V., 2008, "Análise de Dados de Vôo das Aeronaves F-5M Para Cálculo de Vida em Fadiga", pp.18-74, Graduation Work, ITA, São José dos Campos.

[4] Mello Jr., A.W.S., 1998, "Crack 2000 Program: Software for Practical Fracture Mechanics and Damage Tolerance Analysis", User's Manual, IAE, São José dos Campos.

[5] Mello Jr., A.W.S. et al. , 2008, "Edição e Pré-Análise de Dados Operacionais do Projeto DTA F-5M: Software EPAD F-5M", IAE, São José dos Campos (RENG ASA-I 03/08).

[6] Mello Jr., A.W.S. et al., 2009, "Geração de Ciclo de Tensões para Análise de Fadiga. Software GCTAF F-5M", IAE, São José dos Campos (Submitted for approval).

[7] Northtrop Corporation, 1977, "F-5E/F Fatigue Loads for the Damage Tolerance Assessment", Hawthome, CA, (NOR 76-164)

[8] RIBEIRO, F. N., 2008, "Procedimentos a respeito da Coleta de Dados de Vôo das Aeronaves F-5EM e F-5FM utilizando o Programa F5DACOM", IAE, São José dos Campos (RENG ASA-102/08).

[9] RIBEIRO, F. N., 2009, "Procedimentos para a Seleção de Dados de Fadiga das Aeronaves F-5EM e F-5FM utilizando o Programa SEDAF", IAE, São José dos Campos (Submitted for approval).

[10] USAF, 1975,'Aircraft Struetural Integrity Program: Airplane Requirements". Wright-Patterson AFB Ohio, FSG-15GP, (MIL-STD-1530).

[11] USAF, 1974, "Airplane Damage Tolerance Requirements". Wrigth-Patterson AFB. Ohio, (MIL-A-83444).

[12] USAF, 1975, "Airplane Strength and Rigidity Realibility Requirements, Repeated Loads and Fatigue", Wrigth-Patterson AFB Ohio,045433, (MIL-STD-A-886B).

[13] Wieland, David H. et al., 1995, " F-5 FMS Durability and Damage Tolerance Update Final DADTA Report F-5", E. Southwest Research Institute, San Antonio, Texas.

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