Effect of the thermal and gas-dynamic properties of solid rocket propellant particles on the propellant combustion rate

The aim of this work is to eliminate the explosion possibility of a rocket engine that operates on a fast-burning solid propellant. The problem is considered by analogy with experiments conducted earlier. Various ways to increase the propellant combustion rate are presented. Examples of how the solid propellant combustion rate depends on the metal fuel and the oxidizer particle size are given. It is shown that unstable combustion of a solid propellant at high combustion chamber pressures is due to unstable combustion of the gas phase in the vicinity of the bifurcation point. Zeldovich’s theory of nonstationary powder combustion is applied to analyzing the explosion dynamics of the Hrim-2 missile’s solid-propellant sustainer engine. This method of analysis has not been used before. The suggested version that this phenomenon is related to the aluminum particle size allows one to increase the combustion rate in the combustion chamber of a liquid-propellant engine, thus avoiding the vicinity of the bifurcation point. The combustion of solid propellants differing in aluminum particle size is considered. The metal fuel and the oxidizer particle sizes most optimal in terms of explosion elimination are determined and substantiated. The use of submicron aluminum enhances the evaporation of ammonium perchlorate due to the infrared radiation of aluminum particles heated to an appropriate radiation temperature. This increases the gas inflow into the charge channel, thus impeding the suppression of ammonium perchlorate sublimation by a high pressure, which is important in the case where the engine body materials cannot withstand a high pressure in the charge channel. This increases the stability and rate of solid propellant combustion. It is shown that the Hrim-2 missile’s solid propellant cannot be used in the Hran missile. The combustion rate is suggested to be increased by using fine-dispersed aluminum in the solid propellant.

CHARACTERIZATION OF SIZE AND SHAPE OF AMMONIUM PERCHLORATE PARTICLE FROM CHINA, SOUTH KOREA, AND INDONESIA AND THEIR INFLUENCES ON PROPERTIES OF PROPELLANT

The aim of this study is to obtain characteristics of ammonium perchlorate particle that used in Rocket Technology Center (LAPAN). Characterization begin from the determination of particle size distribution with Particle Size Analyzer. The SEM is used to obtain information about the morphology of AP, furthermore, the results are reprocessed using ImageJ software to analyze the shape of AP particle, and the Surface area was obtained by using BET. Characteristic of AP such as particle size, shape, and surface area are important parameters because those are directly related to propellant combustion energy. Ammonium perchlorate was procured from China, South Korea, and Indonesia with a particle size of 200µm From this study, the particle size of APC200, APH200 and API200 was obtained, which are 265 µm, 236 µm, and 242 µm, with particle shape aggregate value of 0,68, 0,38 and 0,33, roundness of 0,57, 0,79,0,63, and surface area of 1,104 m2/g, 5,561 m2/g, and 2,972 m2/g.

Copper (II) Phthalocyanine Effects On Solid Propellant Combustion

<p>In the present work, the effects of copper (II) phthalocyanine, CuP (C₃₂H₁₆CuN₈) on the combustion of rocket solid propellant is investigated. For this purpose, parameters such as ignition temperature, mass and volume of generated gases are measured. For such purpose, the sucrose-potassium nitrate (KNSu) was employed as a “model system”. It was found that CuP interferes with the combustion of the KNSu propellant, inhibiting the thermal degradation of potassium carbonate and also decreasing the ignition temperature of KNSu. It was identified that, in a percentage of 50%, CuP reduces the ignition temperature of KNSu by ~ 60 ºC.</p>

Copper (II) Phthalocyanine Effects On Solid Propellant Combustion

<p>In the present work, the effects of copper (II) phthalocyanine, CuP (C₃₂H₁₆CuN₈) on the combustion of rocket solid propellant is investigated. For this purpose, parameters such as ignition temperature, mass and volume of generated gases are measured. For such purpose, the sucrose-potassium nitrate (KNSu) was employed as a “model system”. It was found that CuP interferes with the combustion of the KNSu propellant, inhibiting the thermal degradation of potassium carbonate and also decreasing the ignition temperature of KNSu. It was identified that, in a percentage of 50%, CuP reduces the ignition temperature of KNSu by ~ 60 ºC.</p>