Journal of Energetic Materials
Iranian Scientific Association of Energetic Materials
Mon, Dec 1, 2025
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Volume 20, Issue 1 (3-2025)
مواد پرانرژی 2025, 20(1): 43-55 |
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tavangar S, asgari A, hoseini G, bahri M, zarei M. رویکرد محاسباتی-تجربی جهت ارتقاء عملکرد پیشرانههای جامد از طریق بهینهسازی درصد اجزاء با استفاده از روش سطح پاسخ. مواد پرانرژی 2025; 20 (1) : 05
URL: http://isaem.ir/article-1-1498-en.html
URL: http://isaem.ir/article-1-1498-en.html
, asasgary@yahoo.com
Abstract: (20 Views)
In this research, the effect of formulation and the components percentages of composite solid propellant on their performance were investigated. The Propep software was used to evaluate the performance. Response surface method was used to analyze and optimize the effect of oxidizer (AP), aluminum metal as fuel (Al), nitrate ester energetic plasticizer, and polyester binder as inputs. Combustion chamber temperature, molecular weight of combustion products, and the characteristic velocity of the exhaust gases were used as response in central composite design (CCD) method. The modeling results indicated that the highest percentage of polyester binder (+1 level) increases the specific impulse, while increasing the percentage of AP, Al, and plasticizer to more than (-1) level results in decreasing the specific impulse. At this level, the mentioned components compositions are 49.9, 19.8, and 17.8 respectively. The values of R2 for responses including specific impulse, combustion chamber temperature, molecular weight of combustion products, and characteristic velocity are 0.9948, 0.9986, 0.9996, and 0.9935 respectively. A high value for R2 indicates that the fitted models can estimate a high percentage of variances of the experimental data. The value of the specific impulse predicted at optimum formulation is 271.17 s which is not significantly different from the theoretical value of 271.4 s obtained from Propep software at 95% confidence level. Also, the predicted value of the responses for combustion chamber temperature, molecular weight of combustion products and characteristic velocity at this point with a degree of desirability of 0.937 are 3707.276 K, 26.629 g/g mol and 5303.644 ft/s respectively.
Article number: 05
Keywords: Composite Solid Propellant, Formulation Design, Specific Impulse, Characteristic Velocity, Polyester Binder, Energetic Plasticizer, Response Surface Method
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