Nonlinear Modeling of Composition Effects on Temperature Sensitivity of Double‐Base and NC‐Rich Propellants.
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| Title: | Nonlinear Modeling of Composition Effects on Temperature Sensitivity of Double‐Base and NC‐Rich Propellants. |
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| Authors: | Farshi Fasih, Hamidreza1 (AUTHOR) farshifasih@semnan.ac.ir, Gharaei, Nima1 (AUTHOR), Lekzian, Elyas1 (AUTHOR), Zhang, Rongchun1 (AUTHOR) zhangrongchun@buaa.edu.cn |
| Source: | International Journal of Aerospace Engineering. 9/9/2026, Vol. 2026, p1-9. 9p. |
| Subjects: | Propellants, Ballistics, Sensitivity analysis, Regression analysis, Burning velocity, Nonlinear statistical models |
| Abstract: | Temperature sensitivity plays a significant role in the development of ballistic properties in double‐base propellants across varying operating temperatures. The study aimed at investigating the effects of composition on ballistic properties and the temperature sensitivity coefficient (σp) using two conventional double‐base propellants and two NC‐rich formulations. All types of propellants undergo evaluation at three initial temperatures (+60°C, +25°C, and −30°C) in a laboratory‐scale rocket motor. The comparison shows that, despite similar propellant composition, differences in component percentages lead to variations in burning rate and σp. To assess these effects, nonlinear regression models incorporating quadratic and interaction terms are employed to capture coupled compositional influences. Results indicated that an increase in the initial temperature of the propellant led to higher burning rate and pressure inside the combustion chamber, with a concomitant decrease in burn time. Moreover, the two double‐base propellants exhibited nonlinear behavior, characterized by amplification of the effect due to interactions between the NG2 and NG × NC terms. In contrast, two NC‐rich demonstrated peak‐type nonlinear responses involving DFA quadratic and interaction terms. But the small number of casting batches made it impossible to derive reliable models, and cross‐validation showed quite limited predictive power. This modeling provides an exploratory perspective to analyze the relationship between composition and σp within the investigated formulation ranges and may assist in developing propellants with improved ballistic stability. [ABSTRACT FROM AUTHOR] |
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| Database: | Engineering Source |
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| Abstract: | Temperature sensitivity plays a significant role in the development of ballistic properties in double‐base propellants across varying operating temperatures. The study aimed at investigating the effects of composition on ballistic properties and the temperature sensitivity coefficient (σp) using two conventional double‐base propellants and two NC‐rich formulations. All types of propellants undergo evaluation at three initial temperatures (+60°C, +25°C, and −30°C) in a laboratory‐scale rocket motor. The comparison shows that, despite similar propellant composition, differences in component percentages lead to variations in burning rate and σp. To assess these effects, nonlinear regression models incorporating quadratic and interaction terms are employed to capture coupled compositional influences. Results indicated that an increase in the initial temperature of the propellant led to higher burning rate and pressure inside the combustion chamber, with a concomitant decrease in burn time. Moreover, the two double‐base propellants exhibited nonlinear behavior, characterized by amplification of the effect due to interactions between the NG2 and NG × NC terms. In contrast, two NC‐rich demonstrated peak‐type nonlinear responses involving DFA quadratic and interaction terms. But the small number of casting batches made it impossible to derive reliable models, and cross‐validation showed quite limited predictive power. This modeling provides an exploratory perspective to analyze the relationship between composition and σp within the investigated formulation ranges and may assist in developing propellants with improved ballistic stability. [ABSTRACT FROM AUTHOR] |
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| ISSN: | 16875966 |
| DOI: | 10.1155/ijae/2469088 |
