The copolymerization of maleic anhydride (MA), N‐2‐chlorophenyl maleimide (2‐CMI) and N‐α‐naphthyl maleimide (α‐NMI) with styrene (ST) initiated by α‐radiation has been studied. The initial rate of copolymerization depends on the total concentration of the comonomers, and the rate decreases in the series ST/MA > ST/α‐NMI > ST/2‐CMI. The maximum rate occurred at a ratio for which [M2] > [ST]. The rate of formation and the reaction of m 1˙ is greater than m 2˙. The monomer reactivity ratios indicate that the ratio of alternating units decreases in the order ST/MA > ST/α‐NMI > ST/2‐CMI.
Acta Polymericr 42 (1W1) Nr. 5 210 MOHAMED ;itid AHMED: Tha molecular int.eract.ion of N-cliloroplienyl ninleimiilcs with styrcne and nict.liyl rnetliacryla tcThe molecular interactions of N-2-, N-3-, and N-4-chlorophenyl maleimidus with styrcne and mcthyl niethacrylate, respectively, were investigated by 1H-NMR spectroscopy. A considerable upfield shift in the maleimide-styrene systems and a small downfield shift in the maleimide-methyl methacrylate systems are found. The results are discussed with respect to the stability of the monomer complexes.
Die mvlekularen VVechselwirkungen vvn N-Chlvrphenylmaleinirniden mil Styren und Melhylrnethacnjlal Die molekularen Ivechselwirkungen von N-2-, N-3-sowie N-4-Chlorphenylmaleinimiden mit Styren beziehungsweiseMethylmethacrylat wurden mit der 'H-NMR-Spektroskopie untersucht. Bei den Maleinimid-Styren-Systemen wurde eine betrachtliche Verschiebung zu hoherem Feld und bei den Maleinimid-Mcthylmethacrylat-Systemen eine geringe Verscliiebung zu niedrigerem Feld gefunden. Die Ergebnisse werden hinsiclitlich der Stabilittit der Monomerkomplese diskuticrt.
The high strength fiber composite parts are made up of several plies with different fiber orientations with a designed balanced layup sequence, however the destructive tests are carried only on the test laminates which are fabricated and cured along with the actual parts. The (ILSS) inter laminar shear strength is a vital destructive test carried on the test laminates as per the ASTM D2344 standards, based on these test results the actual parts are qualified for final assembly. Hence there is a need to find an accurate ILSS value of the actual part to predict its quality and strength. Earlier researchers stated that the ILSS values vary on the layer orientations and on the layup sequence, hence the apparent ILSS values obtained from these test coupons may vary with the actual part since the layer orientations followed to manufacture the part and test laminates are different. It is essential to find the strength of the actual part based on the values obtained from the test laminates and to analyze its properties. Efforts were made in this work to obtain the ILSS values of the test laminates fabricated with [0/45]s, [90/45]s, [0/90]s [0/45/90]s orientations and to find a correction factor to evaluate apparent ILSS for the actual part. This work will help composite materials designers and manufacturers to design high strength composite parts for aerospace.
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