Furniture Design Ideas

This section discusses the ratio of static OH strength to static NH strength and its temperature dependence, where this ratio is calculated from the mean strength based on the test results in Table2 or Fig. 3. Since the cross section of OH specimens was equal to that of NH specimens and the static strength was […]

1.1 Fiber-dominant strength, matrix-dominant strength, and failure modes As described above, static tensile strength and tension fatigue strength are predominantly fiber-dominant, and static compressive strength and compression and tension-compression fatigue strengths are matrix-dominant. This section discusses the fiber-dominant and matrix-dominant characteristics of static and fatigue strengths based on observations of specimen failure and failure modes. […]

Fig. 6 shows the static OHC strength and S-N relationship obtained from tension – compression fatigue tests for R=-1 at RT and 150°C. Since compression load repetition greatly influences fatigue life in tension-compression fatigue tests, as described later, static OHC strength was plotted at N=1 as in the case of compression fatigue. According to the […]

Fig. 5 presents the static OHC strength and S-N relationships obtained from compression fatigue tests for R=10 at RT and 150°C. From the two S-N lines in this figure and the Ъ or Ъ/a values in Table 4, compression fatigue strength Smin at RT and 150°C drops considerably with the increase in the number of […]

Let us examine S-N (stress-life) relationships on semi-logarithmic graph paper based on net section stress, placing the maximum stress Smax on the ordinate and the logarithm of fatigue life logN on the abscissa, where N is the number of load cycles to failure. In compression fatigue, the minimum stress Smin is used instead of Smax […]

Fig. 3 shows non-hole tensile (NHT) strength, non-hole compressive (NHC) strength, open – hole tensile (OHT) strength, and open-hole compressive (OHC) strength at RT and high temperatures, where OH strength is represented by net section stress, as described above. Since these tests were carried out to determine their temperature dependence, only a few specimens were […]

Table 2 presents the numerical data of static strength Su and its mean Su, while Table 3 presents fatigue life data. These data were systematically obtained as described above and are expected to be used for the reference or comparison data for conventional CF/BMI composite materials and new CF/BMI materials recently developed for low-cost and […]

The prepreg system used is a combination of G40-800 CF and 5260 toughened BMI resin made by CYTEC Co. The lamination has a quasi-isotropic (QI) stacking sequence, 32 plies [45/0/-45/90]^. The nominal thickness of 4.29 mm (0.134 mm x 32) was used in calculating stress on specimens. Laminate panels were cured in an autoclave at […]

Toshiyuki Shimokawa1, Yoshiaki Kakuta2 and Takenori Aiyama3 formerly Tokyo Metropolitan Institute of Technology, 2Japan Aerospace Exploration Agency, 3Toyota Motor Corporation Japan 1. Introduction A lot of polymer composite materials are being used in the structures of civil transport aircraft currently under development, such as the Boeing 787, Airbus A350, and Bombardier C Series. Their percentages […]

Laricheva V. P. Branch of FSUE "Karpov Institute of Physical Chemistry" Obninsk, Kaluga Region, Russia 1. Introduction In this article it is discussed the compact-packed materials, which acquire rigidity under the exposure to ionizing radiation. The prepreg materials, additionally curable under the irradiation exposure, can be used for the fabrication of large-size products (for example, […]