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 paper, the catalytic performance of MgCo2O4 nanowires on the thermal decomposition of ammonium perchlorate (AP) was investigated by differential scanning calorimetry (DSC) and simultaneous thermogravimetry-mass spectrometry (TG/MS) techniques.
23 citations
Patent•
07 Jun 1973
TL;DR: In this paper, a polybutadiene binder was used to provide a smokeless exhaust and burn stably in a motor at a burning rate above 0.40 in/sec at 1,000 psia with no combustion instability.
Abstract: Ammonium perchlorate propellants utilizing a polybutadiene binder provide a smokeless exhaust and burn stably in a motor at a burning rate above 0.40 in/sec at 1,000 psia with no combustion instability if they include 0.25-5% of refractory metal carbides or oxides and carbon in the form of hollow, broken or unbroken carbon spheres, carbon particles or carbon flakes.
23 citations
TL;DR: In this article, a model is developed which correlates the experimentally observed burning rates of composite nonmetallized propellants subjected to acceleration fields normal to the burning surface to additional energy transfer to the surface from the combustion of ammonium perchlorate particles retained on the propellant surface by the acceleration forces.
Abstract: A model is developed which correlates the experimentally observed burning rates of composite nonmetallized propellants subjected to acceleration fields normal to the burning surface. The model attributes the increased burning rates to additional energy transfer to the propellant surface from the combustion of ammonium perchlorate particles retained on the propellant surface by the acceleration forces. A method for predicting, with limited experimental data, the burning rate of a propellant as a function of pressure and acceleration is described.
23 citations
TL;DR: The synthesis and characterization of a novel green high-density energetic oxidizer octanitropyrazolopyrazole (ONPP) is reported, which can potentially replace AP in composite propellants.
23 citations
20 Jul 2003
TL;DR: Dokhan et al. as discussed by the authors investigated the ignition of ultrafine aluminum (UFAl) compared to conventional sized aluminum (CSAl) particles in ammonium perchlorate (AP)-polybutadiene acrylonitrile acrylic acid (PBAN) solid propellants.
Abstract: A preliminary experimental investigation was carried out to investigate the ignition of ultrafine aluminum (UFAl) compared to conventional sized aluminum (CSAl) particles in ammonium perchlorate (AP)-polybutadiene acrylonitrile acrylic acid (PBAN) solid propellants. To evaluate the temperature criteria for igniting UFAl, matrix samples (binder, fine AP and Al only) were prepared with various loadings of 10μm fine AP (fAP) as a means of varying the AP-binder flame temperature, and with Al coarse-to-fine ratio of 0(30μm)/20(UFAl) and 80(30μm)/20(UFAl). Preliminary results showed that UFAl sized particles ignite at lower gasphase flame temperatures than CSAl particles and that the UFAl particles tend to affect the combustion processes close to the propellant surface depending upon the availability of oxidizer. * Senior Combustion/Propulsion Engineer. AIAA Member. E mail: allandokhan@hotmail.com † ‡ Regent Professor Emeritus. Fellow Member. Associate Professor. Senior Member. E mail: jerry.seitzman@ae.gatech.edu Senior Research Engineer. INTRODUCTION In recent studies of ultra-fine aluminum (UFAl~0.1μm) in ammonium perchlorate (AP) solid propellants with bimodal AP (10μm:400μm and 82.5μm:400μm) and bimodal aluminum (Al) distribution (30μm:UFAl), the burning of UFAl was found to create a very dense aluminum burning region (ABR) directly above and some distance beyond the propellant surface (~3000-4000μm) compared to the burning of conventional sized aluminum (CSAl~12-100μm). The density of the ABR was found to be the product of the number of burning Al particles/droplets/agglomerates leaving the propellant surface per unit area (one 30μm Al particle is the mass equivalent of 10 UFAl particles), which is very dependent upon the propellant microstructure (see later). The combustion of fine Al (~3μm) and UFAl particles occur much closer behind the AP-binder flame because of their near equilibrium state with the gas flow (temperature & velocity) compared to CSAl. As a result, they ignite quickly as they pass through the flame surface and burn close behind the convoluted flame canopy. This dense luminous bright ABR was found to be responsible for a significant amount of heat feedback to the propellant surface and to the AP-binder flame array in the form of either radiation and/or conduction, which resulted in high burning rate propellants. Copyright© 2003 A. Dokhan, E. W. Price, J. M. Seitzman and R. K. Sigman. Published by the American Institute of Aeronautics and Astronautics, Inc. with permission 1
23 citations