Topic
Ammonium perchlorate
About: Ammonium perchlorate is a research topic. Over the lifetime, 2359 publications have been published within this topic receiving 33412 citations. The topic is also known as: AP.
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TL;DR: In this article, the authors investigated the thermal decomposition of AP/GA nanocomposites and found that the high temperature decomposition peak temperature decreases by 83.7℃ and the total heat release reaches 2 110 J/g.
Abstract: Ammonium perchlorate / graphene aerogels(AP/GA) nanocomposites were prepared by sol-gel method and characterized by scanning electron microscope(SEM),elemental analysis and X-ray diffraction(XRD).Their thermal decomposition behaviours were investigated by TG-DSC-IR.The results indicate that AP is presented in the AP/GA nanocomposites with an average particle size of 69.41 nm and occupied 94.4% of total mass.GA shows an obvious catalytic effect on the thermal decomposition of AP/GA.Compared to pure AP,the low temperature decomposition peak of AP/GA nanocomposites disappears,the high temperature decomposition peak temperature decreases by 83.7℃,and the total heat release reaches 2 110 J/g.
9 citations
TL;DR: A 100-microliter volume of urine was chromatographed on a 50 X 0.4 cm I.D. column packed with a macroreticular anion-exchange resin and the effect of the addition of ethanol or acetonitrile to the ammonium perchlorate solution was investigated.
9 citations
TL;DR: In this article, a charge separation process involving protons, rather than the usual dipole orientation process, was used to determine the depolarization of ammonium perchlorate and NH 4 ClO 4 doped with SO 4 2− and CrO 4 O 2− ions.
9 citations
TL;DR: In this article, the effects of ammonium perchlorate on burning behavior of a solid rocket propellant system containing nitramine were studied, and it is possible to reduce the burning exponent by adding ammonium permachlorate from n ≥ 0.9 to n ≤ 0.65.
Abstract: Solid rocket propellants containing nitramine are considerably superior to doublebase propellants, both as regards their performance and mechanical properties. The pressure exponent of non-modified nitramine propellants is n ≥ 0.9. The possibility of changing the burning rate or, respectively, the pressure exponent has, however, only been realisable to a restricted extent up till now in propellants with an increased nitramine content. In the following propellant system containing nitramine, the effects of ammonium perchlorate on burning behaviour are studied:
ammonium perchlorate (AP)
hexogen (RDX)
nitroglycerin (NG), or trimethylolethane trinitrate (TMETN)
polyurethane binder (PU)
AP concentrations already as great as 10% produce considerable changes in the burning behaviour of the propellants described above. It is possible to reduce the pressure exponent by the addition of ammonium perchlorate from n ≥ 0.9 to n ≤ 0.65. The burning rates may also be influenced with AP concentrations ≤ 20% and by varying the AP particle size by the factor of 2. All the propellants prepared were easily castable and showed exceptionally good viscoelastic properties (strain at break eR > 200%) in the temperature range between −40 °C to + 50 °C. The thermal chemical stability is not influenced negatively in any way by the combination of nitric acid esters and ammonium perchlorate.
9 citations
TL;DR: In this article, the rate of exchange of ammonia between tetraammineplatinum(II) and solution ammonia in aqueous ammonia/ammonium perchlorate buffers of unit ionic strength has been determined in the temperature range 81-100 o C using nitrogen-15 labeling and optical emission isotopic distribution analysis.
Abstract: The rate of exchange of ammonia between tetraammineplatinum(II) and solution ammonia in aqueous ammonia/ammonium perchlorate buffers of unit ionic strength has been determined in the temperature range 81-100 o C using nitrogen-15 labeling and optical emission isotopic distribution analysis
9 citations