Modern chemical synthesis techniques have allowed for improved incorporation of nano‐scale additives into solid propellants. Various. Kumar Ishitha, P. A. Ramakrishna. () Activated charcoal: as burn rate modifier and its mechanism of action in non-metalized composite solid propellants. The combustion of hydroxyl-terminated polybutadiene (HTPB) propellants containing ne ammonium perchlo- rate (AP) was investigated using laser-excited, .

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The kinetic Shimadzu software, based on the Ozawa method, feed with the exothermic peak temperatures and the heating rate data, gives the Arrhenius kinetic parameters Ea, A relative to the thermal decomposition of composite and, consequently, with sp eq.

The activation energy and kinetic parameters of thermal decomposition of propellant samples were calculated by Ozawa method propellanfs DSC curves at different heating rates: Activation energy is calculated from the slope of the curve using the following equation:. It means that the propellants in Table 6 could be show higher explosion heat and more steady explosive procedures than samples in Htbp 5. Retrieved from ” https: From Table 1as the kneading time increase, the mean values of decomposition temperature of samples decease smoothly from to.

The hydrochloric acid component of APCP exhaust leads to the condensation of atmospheric moisture in the plume and this enhances the visible signature of the contrail. This phenomenon generates a great variation on the mole fractions of propelpants as the high temperature enhance the speed of the slower reactions, generating more radicalswhich modify the concentration of the main species specially in the flame zoneso the different slope is observed.

In Table 5utpb explosion heat of propellant with simple mixed nano-CuO is increased with the increase of kneading time, while the STD and RSD of explosion heat decreased.

These methods are widely used for the investigation of thermal decomposition of organic materials [ 10 ], polymers [ 1112 ], composites [ 13 ] and explosives [ 14 ]. Propellanys, it seems that there is no or little influence on the thermal decomposition temperatures of HTPB propellants in Table 2. It is obtained by reaction between ammonia and perchloric acid, or by double decomposition between an ammonium salt and sodium perchlorate, and crystallizes with romboedric structure in room temperature and pressure, with relative density of 1.


Ammonium perchlorate composite propellant – Wikipedia

Though increasing the ratio of metal fuel to oxidizer up to the stoichiometric point increases the combustion temperature, the presence of an increasing molar fraction of metal prropellants, particularly aluminum oxide Al 2 O 3 hypb from the gaseous solution creates globules of solids or liquids that slow down the flow velocity as the mean molecular mass of the flow increases.

Because of little diameter and proportion, nanocatalyst becomes the most difficult dispersing composition of HTPB propellants.

However, when compared with Table 1 at the same kneading time, taking 3 hours for example, all the RSD values and mean values of decomposition temperature in Table 2 are much lower. This provides manufacturing regularity and repeatability, which are necessary requirements for use in the aerospace industry.

The nanometer catalysts show excellent catalysis on the thermal decomposition of AP.

The combustion mechanism of AP has been studied and modified. In the gas phase region of a monopropellant, the flame is essentially premixed. The exhaust from APCP solid rocket motors contains mostly watercarbon dioxidehydrogen chlorideand a metal oxide typically aluminium oxide.

Ammonium perchlorate composite propellant

Xiao-Bin [ 25 ] showed that the burning rates of propellants were very closely related to the exothermic peak temperature of ammonium nitrate AN that is used as an oxidizer in smokeless propellant formulation. This mechanism was proposed by Gross [ 6 ], according to literature data.

The breaking changes the dispersity of nano-CuO in the propellant. Because of little diameter and proportion, nanocatalyst becomes the most difficult dispersing composition of many combustion systems.

Because of the size discrepancy between the AP and Al, Al will often take an interstitial position in a pseudo-lattice of AP particles. Minimum signature propellants contain primarily nitrogen-rich organic molecules e.

Although some of them emphasized the dispersibility improvement technologies of nanomaterials, little attention has been paid to the relationship between dispersibility and catalysis lropellants nanomaterials.


The thermal decomposition of solid composite propellant is a multistep process and the reaction mechanism changes with the temperature and, consequently, the activation energy varies with the extent of the reaction.

The vendor is charged with the responsibility by the NAR and TRA to check hobbyists for high power rocket certification before propllants sale can be made. January 23rd DOI: The DSC curves show that the first stage propellatns endothermic and the second stage is exothermic. In the present work, the DSC curves at different heating rates were obtained for original and synthetically aged samples that have the same raw materials and with the same manufacture process.

This process may be a rate-limiting step in the overall combustion rate of APCP.

The thermal decomposition of AP may htpn observed by differential thermal analysis DTA and thermal gravimetry TGin the figure below [ 5 ]. Implicit in any discussion about the decomposition is the fact that the overall process is complex, and any derived rate parameters do not correspond to an elementary single step.

Table of Contents Alerts. Other methods should be employed to improve the dispersibility of nanocatalyst in the propellant. Due this, the flame structure of AP composite propellants is prkpellants and locally three-dimensional in shape. In a previous work propellabts 7 ], these simulations were done, considering a perfectly stirred reactor, different internal pressures and a specific temperature profile. September Learn how and when to remove this template message.

The synthetic aging process was conducted by exposing the cured propellant formulation to a temperature of K for days in a muffle FNT-F3-T W that was monitored day by day during this period. More statistics for editors and authors Login to your personal dashboard for more detailed statistics on your publications.