Showing papers on "Ammonium perchlorate published in 1978"
16 Jan 1978
36 citations
TL;DR: In this article, transition metal oxides are known to promote the thermal decomposition of ammonium perchlorate (AP) and the combustion of AP based on composite solid propellants, but no clearcut picture has emerged so far particularly on the latter process.
34 citations
TL;DR: In this paper, the effect of additives on the flame structures and the burning rates of double-base propellants have been examined by means of photographic observations and temperature profile measurements, and it was found that the addition of Ni or AP significantly increased the flame temperature at pressures below 30 atm and the stable combustion limit was lowered to below 3 atm.
Abstract: The effect of additives on the flame structures and the burning rates of double-base propellants have been examined by means of photographic observations and temperature profile measurements. The additives used for this study are lead salicylate (PbSa, 2%), nickel (Ni, 1%), ammonium perchlorate (AP, 30%), and cyclotetramethylene tetranitramine (HMX, 30%). The addition of PbSa increases the burning rate, but does not improve the flame temperature characteristics. The addition of Ni increases the flame temperature significantly at pressures below 30 atm. The Ni acts as a catalyst to promote the flame reaction while it does not act as a burning rate modifier. The additions of AP and HMX increase the thermal performance of the propellant system, however, the HMX does not improve the stable combustion limit of the rocket motor at low pressures. The addition of Ni or AP is found to increase the flame temperature at pressures below 30 atm, and the stable combustion limit is lowered to below 3 atm.
30 citations
Patent•
29 Sep 1978TL;DR: In this article, an enhanced recovery of ammonium perchlorate from waste solid rocket propellant is effected by leaching shredded particles of the propellant with an aqueous leach solution containing a low concentration of surface active agent while stirring the suspension.
Abstract: Enhanced recovery of ammonium perchlorate from waste solid rocket propellant is effected by leaching shredded particles of the propellant with an aqueous leach solution containing a low concentration of surface active agent while stirring the suspension.
24 citations
TL;DR: Ammonium perchlorate decomposition in the presence of several oxides was studied by differential scanning calorimetry as mentioned in this paper, and a general kinetic law was used in interpreting the experimental runs.
13 citations
TL;DR: In this paper, the aging behavior of polystyrene/ammonium perchlorate solid-propellants was studied as a function of oxidizer loading in the propellants, and the authors concluded that the thermal decomposition of the propellant may be responsible for bringing about ballistic changes during the ageing process.
11 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 paper, a novel method of detecting the charge-carrying species in inorganic decomposable salts is described, and it is observed that the charge carrying species at temperatures 150 and 230°C are oppositely charged; i.e., they are negatively charged (ClO−4 ions) at 230°c and positively charged (H+ or NH+4) at 150°C.
6 citations
5 citations
TL;DR: In this article, the influence of phase transition on the process of thermal development of a latent image arising after X-ray and uv irradiation of ammonium perchlorate (AP) crystals has been studied.
4 citations
TL;DR: In this paper, a diffusion flame is formed in the stagnation region between a gaseous stream of fuel and an opposing stream of oxidizer originating at the solid surface of ammonium perchlorate (AP) based propellants.
Abstract: To examine the gas-kinetics parameters pertinent to the flame reactions of ammonium perchlorate (AP) based propellants we have employed the heterogeneous opposed flow diffusion flame (HOFD). In this combustion system a diffusion flame is formed in the stagnation region between a gaseous stream of fuel and an opposing stream of oxidizer originating at the solid surface of A P. With increasing fuel flux the steady-state mass flux of AP reaches a value at which the kinetics of reaction limit the consumption of reactants. This limiting condition provides information on the gas phase kinetic parameters of the combustion system. Both the composition of the solid oxidizer and the gaseous fuels were varied in ( The experimental studies. The effect of different catalysts and solid fuels on the burning rate characteristics of the solid phase were examined. A number of gaseous hydrocarbon fuels were used . Based on the results kinetic expressions are derived for the overall combustion progress in the diffus...
TL;DR: Isotherme TG- und DTA-Untersuchungen zeigen, das Ubergangsmetallfluoride (im Verhaltnis 1 : l 0 Gew.-% zugesetzt) die thermische Zersetzung von NH4CIO4 katalysieren as discussed by the authors.
Abstract: Isotherme TG- und DTA-Untersuchungen zeigen, das Ubergangsmetallfluoride (im Verhaltnis 1 : l0 Gew.-% zugesetzt) die thermische Zersetzung von NH4CIO4 katalysieren.
01 Mar 1978
TL;DR: In this article, Debye Scherrer and diffractometer powder techniques were used to characterize isomorphous oxidizer solid solutions, and the x-ray powder patterns helped to illustrate the unique nature of the solid solutions involved.
Abstract: : Debye Scherrer and diffractometer powder techniques were used to characterize isomorphous oxidizer solid solutions. Those involved were: AP-KP, AN-AP, AN-3KN.AN, KN-3KN.AN, and AN-KP. In most cases we showed that the x-ray powder patterns were different from physical mixtures with the same relative amounts of constituents. Observations were made on the shift of major diffraction lines with introduction of an isomorphous oxidizer component into another oxidizer host crystal. The x-ray powder patterns helped to illustrate the unique nature of the solid solutions involved. Some theoretical speculation was made on the possibility of the existence of superstructure in such materials, particularly the AP-KP solid solutions.
TL;DR: In this paper, it has been argued that the above behavior of the propellant is due to the strain caused by the binder film on ammonium perchlorate contained in the mixture.
Abstract: Thermal decomposition of ammonium perchlorate-polystyrene propellant as a function of oxidizer loading has been found to behave in a fashion analogous to the thermal decomposition of ammonium perchlorate as a function of precompression pressure. It has been argued that the above behaviour of the propellant is due to the strain caused by the binder film on ammonium perchlorate contained in the propellant matrix. The presence of strain has been demonstrated independently by x-ray diffraction peak and infrared peak broadening and strain energy measurements.
TL;DR: In this article, the results of these two experiments suggest strong interaction between ammonium perchlorate (AP) and polyvinyl pyrrolidone (PVP) in the solid state.
Abstract: Thermal decomposition of ammonium perchlorate (AP) containing different concentrations of a polymeric additive such as polyvinyl pyrrolidone (PVP) has been studied by the technique of differential thermal analysis (DTA). The decomposition products have been identified by means of a mass spectrometer. The results of these two experiments suggest strong interaction between AP and PVP in the solid state.
Patent•
31 Jul 1978TL;DR: In this article, a polysulfide binder with the formula-SCH 2 CH 2 OCH 2OCH 2CH 2 --S n was proposed for generating gas to pressurize the fuel systems in air-breathing missiles.
Abstract: A propellant formulation comprising a polysulfide binder having the formula-SCH 2 CH 2 OCH 2 OCH 2 CH 2 --S n wherein n is a positive integer of sufficient magnitude to render the binder an elastomeric solid, ammonium perchlorate, ammonium oxalate and iron oxide. The formulation has properties which render it useful for generating gas to pressurize the fuel systems in air-breathing missiles.