• Journal of Aerospace System Engineering
• /
• v.14 no.spc
• /
• pp.1-6
• /
• 2020

The flaw tolerance evaluation requirement prescribed in Federal Aviation Regulation (FAR) §29.571 Amendment 55 was established in 2012. As a result, there are not many datas of flaw tolerance evaluation. This paper introduces the series of processes and evaluation methods carried out for certification based on the flaw tolerance evaluation. An initial flaws were artificially formed on the main rotor actuator and then the damage tolerance test was performed, which was twice life time of design requirements, to demonstrate that the main rotor actuator of the rotorcraft is sufficiently capable of flaw tolerance.

• Journal of Energy Engineering
• /
• v.20 no.2
• /
• pp.90-95
• /
• 2011

This study was conducted to judge requalification of cylinders by assessing composite flaws such as scratches, cuts, and gouges damaging on the composite of Type III cylinders for compressed natural gas vehicles. As a result of the flaw tolerance test, all specimens have satisfied with minimum requirement cycles according to damage levels based on ISO 19078 and cyclic performance for pressure showed beyond twenty thousands in damage level 1 and 2, and did eighteen thousands to twenty-one thousands in damage level 3. Eight of twelve specimens failed the test due to composite flaws and the rest of the cylinders failed regardless of flaws. The results of Finite Element Method followed by the computer simulation indicated that the stress of 79.5 MPa calculated on the flaw model of $1.25\;mm{\times}200\;mm$ and the stress of 66.6 MPa on the non-flaw model when the service pressure applied to inside of cylinder. The difference between the models is about 19.37%. We concluded that this difference influences fatigue life and this flaw model is a critical value affecting cyclic performance of cylinders.

• Journal of the Korean Ceramic Society
• /
• v.35 no.8
• /
• pp.807-812
• /
• 1998

Mechanical properties of two types of polycrystlline {{{{ { { Ti}_{3 }SiC }_{2 } }} with different grain size were investigated. A fine grain {{{{ { { Ti}_{3 }SiC }_{2 } }} has a higher fracture strength and hardness. Plot of strength versus Vickers indentation load indicated that {{{{ { { Ti}_{3 }SiC }_{2 } }} has a high flaw tolerance. Hertzian indentation test using a spherical indenter was used to study elastic and plastic behavior in {{{{ { { Ti}_{3 }SiC }_{2 } }}. Indentation stress-strain curves of each material are made to evaluate the plasticity of {{{{ { { Ti}_{3 }SiC }_{2 } }} Both find and coarse grain {{{{ { { Ti}_{3 }SiC }_{2 } }} showed high plasticity. In-dentation stress-strain curve of coarse grain {{{{ { { Ti}_{3 }SiC }_{2 } }} deviated even more from an ideal elastic limit in-dicating exceptional plasticity in this material. Deformation zones were formed below the contact as well as around the contact area in both materials but the size of deformation zone in coarse grain {{{{ { { Ti}_{3 }SiC }_{2 } }} was much larger than that in fine grain {{{{ { { Ti}_{3 }SiC }_{2 } }} Intragrain slip and kink would account for high plasticity. Plastic behavior of {{{{ { { Ti}_{3 }SiC }_{2 } }} was strongly influenced by grain size.

• Transactions of the Korean Society of Mechanical Engineers A
• /
• v.36 no.10
• /
• pp.1275-1282
• /
• 2012

Helicopter rotor systems are dynamically loaded structures with many composite components such as the main and the tail rotor blades. The fatigue properties of composite materials are extremely important to design durable and reliable helicopter rotor blades. The safe-life methodology has generally been used in the helicopter industry to substantiate dynamically loaded composite components. However, it cannot be used to evaluate the strength reducing effects of flaws and defects that may occur during manufacturing and operational usage. The damage tolerance methodology provides a proper means to overcome this shortcoming; however, it is difficult to economically apply it to every composite component. The flaw tolerant methodology is an equivalent option to the damage tolerance methodology for civil and military rotorcraft. In this study, the flaw tolerant safe-life evaluation is described and illustrated by means of successful application to substantiate the retirement time of composite rotor blades.