Mechanical properties
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Hardness refers to a material's ability to resist abrasion, penetration and permanent distortion. It is measured by indenting a material with an indenter under a known load and measuring the indentation size. Hardness is important for piston engine cases as they must withstand high pressures. Malleability allows a material to be hammered, rolled or pressed into shapes without damage and is necessary for aircraft sheet metal like turbine engine cowlings. Toughness is the ability to withstand tearing or shearing without breaking and is desirable in aircraft metals like carbon brakes which require high performance. Ductility permits drawing, bending or twisting without breaking and is essential for aircraft wing structures. Conductivity enables heat or electricity transfer in a material and is
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used, 1-concentrated force, 2-concentrated forces and partial uniformly distributed
load. It is also seen that, when reinforcing ratio increases from minimum to
maximum, in case of 1-concentrated force, ultimate capacity increases by about 280%
and deflection decreases by about 33%, respectively. Whereas, in case of 2-
concentrated forces, ultimate capacity increases by about 258% and deflection
decreases by about 50%, respectively. Finally, in case of uniformly distributed load,
ultimate capacity increases by about 289% and deflection decreases by about 28%,
respectively.
SUGGESTING DEFLECTION EXPRESSIONS FOR RC BEAMS
This experimental work aims at presenting load-deflection expressions for the concrete beams that reinforced with three different reinforcement ratios of ACI 318-14, which are minimum, maximum and the average of them. Three groups of beams were cast, each group contained three beam specimens. Three types of loading are used, 1-concentrated force, 2-concentrated forces and partial uniformly distributed load. It is also seen that, when reinforcing ratio increases from minimum to maximum, in case of 1-concentrated force, ultimate capacity increases by about 280% and deflection decreases by about 33%, respectively. Whereas, in case of 2-concentrated forces, ultimate capacity increases by about 258% and deflection decreases by about 50%, respectively. Finally, in case of uniformly distributed load, ultimate capacity increases by about 289% and deflection decreases by about 28%, respectively.
SUGGESTING DEFLECTION EXPRESSIONS FOR RC BEAMS
This experimental work aims at presenting load-deflection expressions for the
concrete beams that reinforced with three different reinforcement ratios of ACI 318-
14, which are minimum, maximum and the average of them. Three groups of beams
were cast, each group contained three beam specimens. Three types of loading are
used, 1-concentrated force, 2-concentrated forces and partial uniformly distributed
load. It is also seen that, when reinforcing ratio increases from minimum to
maximum, in case of 1-concentrated force, ultimate capacity increases by about 280%
and deflection decreases by about 33%, respectively. Whereas, in case of 2-
concentrated forces, ultimate capacity increases by about 258% and deflection
decreases by about 50%, respectively. Finally, in case of uniformly distributed load,
ultimate capacity increases by about 289% and deflection decreases by about 28%,
respectively.
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Hy3613901394
This document discusses the processing and synthesis of an Al 6063/Al2O3 metal matrix composite using stir casting. Al 6063 plates were cast with 3%, 6%, and 9% Al2O3. Microstructure, hardness, and tensile strength tests were conducted. Tensile strength increased with Al2O3 content up to 6% but decreased from 6% to 9% due to increased porosity. Hardness also increased with Al2O3 content due to grain refinement and particle strengthening. The composite showed improved properties over the base Al 6063 alloy. Microstructure analysis found loosely formed grains and silicon segregation.
Hy3613901394
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- 1. UNIVERSITI KUALA LUMPUR MALAYSIAN INSTITUTE OF AVIATION TECHNOLOGY PHYSICS AND AERODYNAMICS 1 ( AAB20103 ) ASSIGNMENT MECHANICAL PROPERTIES 1BME 2 NATASHA NABILA BINTI RANI 53259313224 MDM SHARIFAH FATHIN ADLINA
- 2. Choose 5 out of 8 of the mechanical properties. Define the term, give formula related, give example related to an aircraft and give reason why it is important to the aircraft. HARDNESS DEFINITION Hardness refers to the ability of a material to resist abrasion, penetration, cutting action, or permanent distortion. It can withstand shape change, scratches and wear. FORMULA Measure the size of an indentation made by some indenter under a known load and the depth to which an indenter penetrates under specified conditions. Example formula using Microhardness Test KHN = F/A = 𝑃 𝐶𝐿2⁄ F = applied load in kgf A = the unrecovered projected area of the indentation in 𝑚𝑚2 L = measured length of long diagonal of indentation in mm C = 0.07028 = Constant of indenter relating projected area of the indentation to the square of the length of the long diagonal. EXAMPLE piston engine case for small aircraft REASON It can resist stress without breaking. Engine is high pressure part, thus it have to withstand stress on it by using material that have hardness properties.
- 3. MALLEABILITY DEFINITION Malleability refers to the ability of a material which can be hammered, rolled, or pressed into various shapes without cracking, breaking, or leaving some other detrimental effect. FORMULA Tensile Stress Formula EXAMPLE Turbine engine cowling REASON This property is necessary in sheet metal use on aircraft because it can be worked into curved shapes without give any damage to it.
- 4. TOUGHNESS DEFINITION Toughness refers to the ability of a material which can withstand tearing or shearing and may be stretched or otherwise deformed without breaking or cracking. FORMULA Young Modulus Formula F = applied axial force lo = original length A = area of cross-section Δ l = change in length E = modulus of elasticity EXAMPLE Carbon brake REASON aircraft requires far tougher material and offer much higher performance. Toughness is a desirable property in aircraft metals.
- 5. DUCTILITY DEFINITION Ductility refers to the ability of a material which permits it to be permanently drawn, bent, or twisted into various shapes without breaking. FORMULA Strain Formula x = Change in dimension, L = Original dimension. Percent Elongation = Final length (in) - Initial Length (in) x 100 Initial Length (in) EXAMPLE Skin, ribs and spar on aircraft wing REASON This property is essential for metals used in making wire and tubing. Ductile metals are greatly preferred for aircraft use because of their ease of forming and resistance to failure under shock loads.
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