Modelling of stable tearing in aircraft structures (2005)
Liu, Q., Hamel, P., Hu, W., Sharp, P.K., Lahousse, A., Clark, G.
Fatigue crack growth in metallic structures remains one of the main threats to aircraft structural integrity, and is the subject of extensive research worldwide in an attempt to assess existing...
Modelling of stable tearing in aircraft structures (2005)
Liu, Q., Hamel, P., Hu, W., Sharp, P.K., Lahousse, A., Clark, G.
Fatigue crack growth in metallic structures remains one of the main threats to aircraft structural integrity, and is the subject of extensive research worldwide in an attempt to assess existing...
Modelling of stable tearing in aircraft structures (2005)
Liu, Q., Hamel, P., Hu, W., Sharp, P.K., Lahousse, A., Clark, G.
Fatigue crack growth in metallic structures remains one of the main threats to aircraft structural integrity, and is the subject of extensive research worldwide in an attempt to assess existing...
Modelling of stable tearing in aircraft structures (2005)
Liu, Q., Hamel, P., Hu, W., Sharp, P.K., Lahousse, A., Clark, G.
Fatigue crack growth in metallic structures remains one of the main threats to aircraft structural integrity, and is the subject of extensive research worldwide in an attempt to assess existing...
The Effect Of Pitting Corrosion On The Position Of Aircraft Structural Failures (2004)
Crawford, B. R., Loader, C., Sharp, P. K.
Corrosion has been shown over the last decade to significantly reduce the structural integrity of aircraft as they age. Previous work at DSTO has shown that pitting and exfoliation corrosion are...
Liu, Q., Ding, K., Ye, L., Rey, C., Barter, S. A., Sharp, P. K., ...
Laser shock peening (LSP) is a promising surface treatment for fatigue life extension of metallic materials. The benefits include deeper residual stresses (>1 mm) and a smoother surface finish than...
The Effectiveness Of Repairing Fatigue Damaged 7050 Aluminium Alloy Using Shot Peening (2004)
Liu, Q., Hu, W., Barter, S. A., Sharp, P. K.
Shot peening is an effective life extension surface treatment process. In this study, experiments were performed to investigate whether shot peening could be used to recover the fatigue resistance of...
The Effectiveness Of Repairing Fatigue Damaged 7050 Aluminium Alloy Using Shot Peening (2004)
Liu, Q., Hu, W., Barter, S. A., Sharp, P. K., Atrens, A., Boland, J. N., ...
Shot peening is an effective life extension surface treatment process. In this study, experiments were performed to investigate whether shot peening could be used to recover the fatigue resistance of...
Liu, Q., Ding, K., Ye, L., Rey, C., Barter, S. A., Sharp, P. K., ...
Laser shock peening (LSP) is a promising surface treatment for fatigue life extension of metallic materials. The benefits include deeper residual stresses (>1 mm) and a smoother surface finish than...
The Effect Of Pitting Corrosion On The Position Of Aircraft Structural Failures (2004)
Crawford, B. R., Loader, C., Sharp, P. K., Atrens, A., Boland, J. N., Clegg, R., ...
Corrosion has been shown over the last decade to significantly reduce the structural integrity of aircraft as they age. Previous work at DSTO has shown that pitting and exfoliation corrosion are...
The effect of retrogression and reaging treatments on residual stress in AA7075 (2004)
Grosvenor, A., Davies, C.H.J., Sharp, P.K.
Aging aircraft is a significant problem to the Australian Defence Force and aircraft fleets world wide--in particular corrosion of peak aged 7xxx series aluminium alloys. It is well documented that...
Brandt, Milan, Durandet, Yvonne C., Liu, Qianchu, Sharp, P. K.
Abstract not available.
Brandt, Milan, Durandet, Yvonne C., Liu, Qianchu, Sharp, P. K.
Abstract not available.
The Effect Of Pitting Corrosion On The Position Of Aircraft Structural Failures (2004)
Crawford, B. R., Loader, C., Sharp, P. K.
Corrosion has been shown over the last decade to significantly reduce the structural integrity of aircraft as they age. Previous work at DSTO has shown that pitting and exfoliation corrosion are...
Liu, Q., Ding, K., Ye, L., Rey, C., Barter, S. A., Sharp, P. K., ...
Laser shock peening (LSP) is a promising surface treatment for fatigue life extension of metallic materials. The benefits include deeper residual stresses (>1 mm) and a smoother surface finish than...
The Effectiveness Of Repairing Fatigue Damaged 7050 Aluminium Alloy Using Shot Peening (2004)
Liu, Q., Hu, W., Barter, S. A., Sharp, P. K.
Shot peening is an effective life extension surface treatment process. In this study, experiments were performed to investigate whether shot peening could be used to recover the fatigue resistance of...
Brandt, Milan, Durandet, Yvonne C., Liu, Qianchu, Sharp, P. K.
Abstract not available.
Brandt, Milan, Durandet, Yvonne C., Liu, Qianchu, Sharp, P. K.
Abstract not available.
The Effect Of Pitting Corrosion On The Position Of Aircraft Structural Failures (2004)
Crawford, B. R., Loader, C., Sharp, P. K.
Corrosion has been shown over the last decade to significantly reduce the structural integrity of aircraft as they age. Previous work at DSTO has shown that pitting and exfoliation corrosion are...
Liu, Q., Ding, K., Ye, L., Rey, C., Barter, S. A., Sharp, P. K., ...
Laser shock peening (LSP) is a promising surface treatment for fatigue life extension of metallic materials. The benefits include deeper residual stresses (>1 mm) and a smoother surface finish than...
The Effectiveness Of Repairing Fatigue Damaged 7050 Aluminium Alloy Using Shot Peening (2004)
Liu, Q., Hu, W., Barter, S. A., Sharp, P. K.
Shot peening is an effective life extension surface treatment process. In this study, experiments were performed to investigate whether shot peening could be used to recover the fatigue resistance of...
The effect of retrogression and reaging treatments on residual stress in AA7075 (2004)
Grosvenor, A., Davies, C.H.J., Sharp, P.K.
Aging aircraft is a significant problem to the Australian Defence Force and aircraft fleets world wide--in particular corrosion of peak aged 7xxx series aluminium alloys. It is well documented that...
Brandt, Milan, Durandet, Yvonne C., Liu, Qianchu, Sharp, P. K.
Abstract not available.
The effect of retrogression and reaging treatments on residual stress in AA7075 (2004)
Grosvenor, A., Davies, C.H.J., Sharp, P.K.
Aging aircraft is a significant problem to the Australian Defence Force and aircraft fleets world wide--in particular corrosion of peak aged 7xxx series aluminium alloys. It is well documented that...
The effect of retrogression and reaging treatments on residual stress in AA7075 (2004)
Grosvenor, A., Davies, C.H.J., Sharp, P.K.
Aging aircraft is a significant problem to the Australian Defence Force and aircraft fleets world wide--in particular corrosion of peak aged 7xxx series aluminium alloys. It is well documented that...
Investigation into the application of laser cladding to repair damaged 7075 aluminium alloy (2003)
Brandt, Milan, Durandet, Yvonne C., Liu, Qianchu, Sharp, P. K.
Not available.
Investigation into the application of laser cladding to repair damaged 7075 aluminium alloy (2003)
Brandt, Milan, Durandet, Yvonne C., Liu, Qianchu, Sharp, P. K.
Not available.
Investigation into the application of laser cladding to repair damaged 7075 aluminium alloy (2003)
Brandt, Milan, Durandet, Yvonne C., Liu, Qianchu, Sharp, P. K.
Not available.
Investigation into the application of laser cladding to repair damaged 7075 aluminium alloy (2003)
Brandt, Milan, Durandet, Yvonne C., Liu, Qianchu, Sharp, P. K.
Not available.
Investigation into the application of laser cladding to repair damaged 7075 aluminium alloy (2003)
Brandt, Milan, Durandet, Yvonne C., Liu, Qianchu, Sharp, P. K.
Not available.
The incorporation of pitting corrosion damage into F-111 fatigue life modelling (2002)
Mills, T., Sharp, P.K., Loader, C.
The ageing of the F-111 fleet in conjunction with a significant increase in planned retirement date has presented a new challenge to the RAAF, namely: maintaining the level of safety from...
The incorporation of pitting corrosion damage into F-111 fatigue life modelling (2002)
Mills, T., Sharp, P.K., Loader, C.
The ageing of the F-111 fleet in conjunction with a significant increase in planned retirement date has presented a new challenge to the RAAF, namely: maintaining the level of safety from...
Fatigue life recovery in aluminium alloy aircraft structure (2002)
Sharp, P.K., Liu, Q., Barter, S.A., Baburamani, P., Clark, G.
Abstract This paper presents the results of several DSTO research programmes which investigated the effectiveness of the fatigue life enhancement method used on RAAF F/A-18 aircraft – glass bead...
Initiation and early growth of fatigue cracks in an aerospace aluminium alloy (2002)
Barter, S.A., Sharp, P.K., Holden, G., Clark, G.
Material imperfections usually play a substantial role in the early stages of fatigue cracking. This article presents some observations concerning fatigue crack initiating flaws and early crack...
The incorporation of pitting corrosion damage into F-111 fatigue life modelling (2002)
Mills, T., Sharp, P.K., Loader, C.
The ageing of the F-111 fleet in conjunction with a significant increase in planned retirement date has presented a new challenge to the RAAF, namely: maintaining the level of safety from...
Fatigue life recovery in aluminium alloy aircraft structure (2002)
Sharp, P.K., Liu, Q., Barter, S.A., Baburamani, P., Clark, G.
Abstract This paper presents the results of several DSTO research programmes which investigated the effectiveness of the fatigue life enhancement method used on RAAF F/A-18 aircraft – glass bead...
Initiation and early growth of fatigue cracks in an aerospace aluminium alloy (2002)
Barter, S.A., Sharp, P.K., Holden, G., Clark, G.
Material imperfections usually play a substantial role in the early stages of fatigue cracking. This article presents some observations concerning fatigue crack initiating flaws and early crack...
The incorporation of pitting corrosion damage into F-111 fatigue life modelling (2002)
Mills, T., Sharp, P.K., Loader, C.
The ageing of the F-111 fleet in conjunction with a significant increase in planned retirement date has presented a new challenge to the RAAF, namely: maintaining the level of safety from...
Fatigue life recovery in aluminium alloy aircraft structure (2002)
Sharp, P.K., Liu, Q., Barter, S.A., Baburamani, P., Clark, G.
Abstract This paper presents the results of several DSTO research programmes which investigated the effectiveness of the fatigue life enhancement method used on RAAF F/A-18 aircraft – glass bead...
Initiation and early growth of fatigue cracks in an aerospace aluminium alloy (2002)
Barter, S.A., Sharp, P.K., Holden, G., Clark, G.
Material imperfections usually play a substantial role in the early stages of fatigue cracking. This article presents some observations concerning fatigue crack initiating flaws and early crack...
Fatigue life recovery in aluminium alloy aircraft structure (2002)
Sharp, P.K., Liu, Q., Barter, S.A., Baburamani, P., Clark, G.
Abstract This paper presents the results of several DSTO research programmes which investigated the effectiveness of the fatigue life enhancement method used on RAAF F/A-18 aircraft – glass bead...
Initiation and early growth of fatigue cracks in an aerospace aluminium alloy (2002)
Barter, S.A., Sharp, P.K., Holden, G., Clark, G.
Material imperfections usually play a substantial role in the early stages of fatigue cracking. This article presents some observations concerning fatigue crack initiating flaws and early crack...
The effect of peening on the fatigue life of 7050 aluminium alloy (2001)
Many changes in the design and manufacture of high-performance military aircraft - for example, the use of highly optimised design and the use of higher-strength materials have led to an...
Review of F-111 structural materials (2001)
Mills, T., Clark, G., Loader, C., Sharp, P.K., Schmidt, R.
Safety by inspection has been the key to protecting the F-111 fleet since the early 1970s. The ageing of the F-111 fleet in conjunction with a significant increase in planned retirement date has...
The effect of peening on the fatigue life of 7050 aluminium alloy (2001)
Many changes in the design and manufacture of high-performance military aircraft - for example, the use of highly optimised design and the use of higher-strength materials have led to an...
Review of F-111 structural materials (2001)
Mills, T., Clark, G., Loader, C., Sharp, P.K., Schmidt, R.
Safety by inspection has been the key to protecting the F-111 fleet since the early 1970s. The ageing of the F-111 fleet in conjunction with a significant increase in planned retirement date has...
Russo, S., Sharp, P.K., Dhamari, R., Mills, T.B., Hinton, B.R.W., Shankar, K.
Fatigue test results of jointed specimens manufactured from 7075-T6 aluminium alloy indicated that the application of Corrosion preventative Compounds (CPCs) at the faying surfaces decreased the...
The effect of peening on the fatigue life of 7050 aluminium alloy (2001)
Many changes in the design and manufacture of high-performance military aircraft - for example, the use of highly optimised design and the use of higher-strength materials have led to an...
Review of F-111 structural materials (2001)
Mills, T., Clark, G., Loader, C., Sharp, P.K., Schmidt, R.
Safety by inspection has been the key to protecting the F-111 fleet since the early 1970s. The ageing of the F-111 fleet in conjunction with a significant increase in planned retirement date has...
Russo, S., Sharp, P.K., Dhamari, R., Mills, T.B., Hinton, B.R.W., Shankar, K.
Fatigue test results of jointed specimens manufactured from 7075-T6 aluminium alloy indicated that the application of Corrosion preventative Compounds (CPCs) at the faying surfaces decreased the...
The effect of peening on the fatigue life of 7050 aluminium alloy (2001)
Many changes in the design and manufacture of high-performance military aircraft - for example, the use of highly optimised design and the use of higher-strength materials have led to an...
Review of F-111 structural materials (2001)
Mills, T., Clark, G., Loader, C., Sharp, P.K., Schmidt, R.
Safety by inspection has been the key to protecting the F-111 fleet since the early 1970s. The ageing of the F-111 fleet in conjunction with a significant increase in planned retirement date has...
Russo, S., Sharp, P.K., Dhamari, R., Mills, T.B., Hinton, B.R.W., Shankar, K.
Fatigue test results of jointed specimens manufactured from 7075-T6 aluminium alloy indicated that the application of Corrosion preventative Compounds (CPCs) at the faying surfaces decreased the...
Russo, S., Sharp, P.K., Dhamari, R., Mills, T.B., Hinton, B.R.W., Shankar, K.
Fatigue test results of jointed specimens manufactured from 7075-T6 aluminium alloy indicated that the application of Corrosion preventative Compounds (CPCs) at the faying surfaces decreased the...
Russo, S.G., Sharp, P.K., Dharma, R., Hinton, B.R.W., Shankar, K., Clark, G.
Corrosion and fatigue are major factors in determining the structural integrity and life expectancy of aging aircraft. The presence of corrosion on airframe structures can have a detrimental effect...
Russo, S.G., Sharp, P.K., Dharma, R., Hinton, B.R.W., Shankar, K., Clark, G.
Corrosion and fatigue are major factors in determining the structural integrity and life expectancy of aging aircraft. The presence of corrosion on airframe structures can have a detrimental effect...
Russo, S.G., Sharp, P.K., Dharma, R., Hinton, B.R.W., Shankar, K., Clark, G.
Corrosion and fatigue are major factors in determining the structural integrity and life expectancy of aging aircraft. The presence of corrosion on airframe structures can have a detrimental effect...
Russo, S.G., Sharp, P.K., Dharma, R., Hinton, B.R.W., Shankar, K., Clark, G.
Corrosion and fatigue are major factors in determining the structural integrity and life expectancy of aging aircraft. The presence of corrosion on airframe structures can have a detrimental effect...
Review of F-111 Structural Materials (1998)
Mills, T., Clark, G., Loader, C., Sharp, P. K., Schmidt, R.
The RAAF is now the sole operator of the F-111 and current plans for the fleet will keep the aircraft in service until 2020. The F-111 is a structurally complex aircraft, and its swing-wing geometry...
The Incorporation of Pitting Corrosion Damage into F-111 Fatigue Life Modelling (1998)
Mills, T., Sharp, P. K., Loader, C.
In this report, an Equivalent Crack Size (ECS) approach is assessed and implemented for corrosion pittIng in D6ac steel. Relationships between physical corrosion morphology and fatigue life of...
Modelling of Stable Tearing in Aircraft Structures (1998)
Liu, Q., Hamel, P., Hu, W., Sharp, P. K., Lahousse, A., Clark, G.
This report summarises the cooperative research program on stable tearing between DSTO and CEAT. The main objective was to study the conditions under which aircraft materials fracture by stable...
Sharp, P. K., Clayton, J. Q., Clark, G.
This paper concerned metals in some important way and contained information about, utilized, or discussed these subjects: basic topics: experimental materials and material types: aa 7050-t7451...
Evaluation of Innovative NDI Methods for Detection of Widespread Fatigue Damage. (1997)
Sharp, P. K., Rowlands, D. E., Clark, G.
High-performance high-strength aircraft components such as the F/A-18 FS488 bulkhead can experience catastrophic failure in fatigue tests from very small cracks. At the same time, the efficiency of...
The Implications of Corrosion with respect to Aircraft Structural Integrity. (1997)
Cole, G. K., Clark, G., Sharp, P. K.
This report discusses the influence of corrosion on aircraft structural integrity. Brief introductions to corrosion in aircraft and aircraft structural integrity are provided and the literature...
The implications of corrosion with respect to aircraft structural integrity (1997)
Cole, G.K., Clark, G., Sharp, P.K.
Increasing economic pressure has encouraged extension of the service lives of many civil and military aircraft fleets beyond their original design goals. Consequently, since the incidence of...
The implications of corrosion with respect to aircraft structural integrity (1997)
Cole, G.K., Clark, G., Sharp, P.K.
Increasing economic pressure has encouraged extension of the service lives of many civil and military aircraft fleets beyond their original design goals. Consequently, since the incidence of...
Retardation and repair of fatigue cracks by adhesive infiltration (1997)
Sharp, P.K., Clayton, J.Q., Clark, G.
This paper presents results which demonstrate that polymeric filler materials, such as low-viscosity epoxies, can be vacuum-infiltrated into fatigue cracks in 7050 aluminium alloy to produce...
The implications of corrosion with respect to aircraft structural integrity (1997)
Cole, G.K., Clark, G., Sharp, P.K.
Increasing economic pressure has encouraged extension of the service lives of many civil and military aircraft fleets beyond their original design goals. Consequently, since the incidence of...
Retardation and repair of fatigue cracks by adhesive infiltration (1997)
Sharp, P.K., Clayton, J.Q., Clark, G.
This paper presents results which demonstrate that polymeric filler materials, such as low-viscosity epoxies, can be vacuum-infiltrated into fatigue cracks in 7050 aluminium alloy to produce...
The implications of corrosion with respect to aircraft structural integrity (1997)
Cole, G.K., Clark, G., Sharp, P.K.
Increasing economic pressure has encouraged extension of the service lives of many civil and military aircraft fleets beyond their original design goals. Consequently, since the incidence of...
Retardation and repair of fatigue cracks by adhesive infiltration (1997)
Sharp, P.K., Clayton, J.Q., Clark, G.
This paper presents results which demonstrate that polymeric filler materials, such as low-viscosity epoxies, can be vacuum-infiltrated into fatigue cracks in 7050 aluminium alloy to produce...
Retardation and repair of fatigue cracks by adhesive infiltration (1997)
Sharp, P.K., Clayton, J.Q., Clark, G.
This paper presents results which demonstrate that polymeric filler materials, such as low-viscosity epoxies, can be vacuum-infiltrated into fatigue cracks in 7050 aluminium alloy to produce...
Evaluation of innovative NDI methods for detection of widespread fatigue damage (1996)
Sharp, P.K., Rowlands, D.E., Clark, G.
In a fatigue test on a stand-alone F / A-18 FS488 wing carry-through bulkhead, the final failure occurred in a large cross-section, from a fatigue crack size only 6 mm deep. Further evaluation of...
Evaluation of innovative NDI methods for detection of widespread fatigue damage (1996)
Sharp, P.K., Rowlands, D.E., Clark, G.
In a fatigue test on a stand-alone F / A-18 FS488 wing carry-through bulkhead, the final failure occurred in a large cross-section, from a fatigue crack size only 6 mm deep. Further evaluation of...
Evaluation of innovative NDI methods for detection of widespread fatigue damage (1996)
Sharp, P.K., Rowlands, D.E., Clark, G.
In a fatigue test on a stand-alone F / A-18 FS488 wing carry-through bulkhead, the final failure occurred in a large cross-section, from a fatigue crack size only 6 mm deep. Further evaluation of...
Evaluation of innovative NDI methods for detection of widespread fatigue damage (1996)
Sharp, P.K., Rowlands, D.E., Clark, G.
In a fatigue test on a stand-alone F / A-18 FS488 wing carry-through bulkhead, the final failure occurred in a large cross-section, from a fatigue crack size only 6 mm deep. Further evaluation of...
Sharp, P.K., Clayton, J.Q., Clark, G.
Metal and glass-bead peening treatments, widely used throughout the aircraft industry to enhance the fatigue performance of many steels and titanium alloys, are now being routinely applied to...
Sharp, P.K., Clayton, J.Q., Clark, G.
Metal and glass-bead peening treatments, widely used throughout the aircraft industry to enhance the fatigue performance of many steels and titanium alloys, are now being routinely applied to...
Sharp, P.K., Clayton, J.Q., Clark, G.
Metal and glass-bead peening treatments, widely used throughout the aircraft industry to enhance the fatigue performance of many steels and titanium alloys, are now being routinely applied to...
Sharp, P.K., Clayton, J.Q., Clark, G.
Metal and glass-bead peening treatments, widely used throughout the aircraft industry to enhance the fatigue performance of many steels and titanium alloys, are now being routinely applied to...