The Effect of Thermal Exposure on the Mechanical Properties of Aluminum-graphite Composites PDF Download
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Category :
Languages : en
Pages : 70
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Author:
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ISBN:
Category :
Languages : en
Pages : 70
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Author: M. P. Hanson
Publisher:
ISBN:
Category : Composite materials
Languages : en
Pages : 20
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Composites were exposed in circulating and static air environments up to 589 K for a maximum of 1000 hours. Composites of HT-S, HM-S, Thornel 50S, and Fortafil 5-Y fiber and a new addition type polyimide resin were laminated in a matched-die mold. Flexural strengths, flexural modulus, and interlaminar shear strengths were determined at 297, 533, and 598 K after various durations of exposure. Composite and fiber weight loss characteristics were determined by isothermal gravimetric analysis in air. Properties of composites exposed and tested at the environment temperatures were compared with those determined under short-term exposure. A new short beam interlaminar shear fixture is described. Environmental effects of long-term ambient temperature exposure on the elevated temperature mechanical properties of graphite/polyimide composites are presented.
Author: William C Harrigan (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 21
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Room temperature tensile tests were conducted on specimens of 6061 aluminum-Thornel 50 graphite composite after thermal exposure for up to 3000 hours at 465C and thermal cycling between room temperature and 485C or 400C for up to 5000 cycles. These tests demonstrate that the ultimate strength of the composite is not affected by thermal exposure at 465C for 3000 hours or by thermal cycling between room temperature and 400C for 5000 cycles. The tensile modulus is also unaffected by exposure at 465C or cycling to 400C. Cycling between room temperature and 485C for 5000 cycles causes a 9% decrease in the strength with no decrease in modulus. (Author).
Author: Morgan P. Hanson
Publisher:
ISBN:
Category :
Languages : en
Pages : 13
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Author: M. P. Hanson
Publisher:
ISBN:
Category : Composite materials
Languages : en
Pages : 13
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Book Description
Composites were exposed in circulating and static air environments up to 589 K (600 deg F) for a maximum of 1000 hours. Composites of HT-S, HM-S, Thornel 50S, and Fortafil 5-Y fiber and a new addition type polyimide resin were laminated in a matched-die mold. Flexural strength, flexural modulus, and interlaminar shear strengths were determined at 297, 533, and 598 K (75 deg, 500 deg, and 600 deg F) after various durations of exposure. Composite and fiber weight loss characteristics were determined by isothermal gravimetric analysis in air. Properties of composites exposed and tested at the environment temperatures are compared with those determined under short-term exposure. A new short beam interlaminar shear fixture is described. Environmental effects of long-term (up to 1 year) ambient temperature exposure on the elevated temperature mechanical properties of graphite/polyimide composites are presented.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725555655
Category :
Languages : en
Pages : 36
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An experimental investigation of the mechanical properties and microstructure of an aluminum matrix/polycrystalline alumina fiber composite material is discussed. The effects of fabrication, isothermal exposure (up to 10,000 hours at 590 K), thermal cycling (6000 cycles between 200 K and 590 K), fatigue (1,000,000 tension-tension cycles) were determined by mechanical testing and metallurgical analysis. The fabrication process severely degraded the fiber strength by reducing the alumina to a nonstoichiometric form and quenching in the resultant vacancies and stress fields. However, isothermal exposure, thermal cycling, and fatigue cycling all restored the fiber strength by enhancing vacancy annihilation. Comparison of the as-fabricated material with other aerospace materials shows that it is an attractive candidate for select applications. Long duration isothermal exposure weakened the matrix by overaging and through the diffusional loss of lithium to a surface reaction forming lithium carbonate. Thermal cycling initiated cracks in the matrix and fibers. Tension-tension fatigue cycling caused no apparent damage to the as-fabricated material but in fact, strengthened it to the rule-of-mixtures value. Fatigue cycling after thermal exposure did have a cumulative damage effect. Olsen, G. C. Langley Research Center NASA-TP-1795, L-14074 RTOP 506-53-23-01...
Author:
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ISBN:
Category :
Languages : en
Pages : 40
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Author: Martha E. Meaney
Publisher:
ISBN:
Category : Metallic composites
Languages : en
Pages : 108
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Author: George C. Olsen
Publisher:
ISBN:
Category : Aluminum
Languages : en
Pages : 40
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721139576
Category :
Languages : en
Pages : 106
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Book Description
Tensile properties were evaluated for four aluminum alloys that are candidates for airframe applications on high speed transport aircraft. These alloys included the Al-Cu-Mg-Ag alloys C415 and C416 and the Al-Cu-Li-Mg-Ag alloys RX818 and ML377. The Al-Cu-Mg alloys CM001, which was used on the Concorde SST, and 1143, which was modified from the alloy used on the TU144 Russian supersonic aircraft, were tested for comparison. The alloys were subjected to thermal exposure at 200 F, 225 F and 275 F for times up to 30,000 hours. Tensile tests were performed on thermally-exposed and as-received material at -65 F, room temperature, 200 F, 225 F and 275 F. All four candidate alloys showed significant tensile property improvements over CM001 and 1143. Room temperature yield strengths of the candidate alloys were at least 20% greater than for CM001 and 1143, for both the as-received and thermally-exposed conditions. The strength levels of alloy RX818 were the highest of all materials investigated, and were 5-10% higher than for ML377, C415 and C416 for the as-received condition and after 5,000 hours thermal exposure. RX818 was removed from this study after 5,000 hours exposure due to poor fracture toughness performance observed in a parallel study. After 30,000 hours exposure at 200 F and 225 F, the alloys C415, C416 and ML377 showed minor decreases in yield strength, tensile strength and elongation when compared to the as-received properties. Reductions in tensile strength from the as-received values were up to 25% for alloys C415, C416 and ML377 after 15,000 hours exposure at 275 F. Edahl, Robert A., Jr. and Domack, Marcia Langley Research Center WU 703-63-61-01; 23-762-55-LD
