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] |
| Copyright of International Journal of Aerospace Engineering is the property of Wiley-Blackwell and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.) | |
| Database: | Engineering Source |
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| Header | DbId: egs DbLabel: Engineering Source An: 196888693 AccessLevel: 6 PubType: Academic Journal PubTypeId: academicJournal PreciseRelevancyScore: 0 |
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| Items | – Name: Title Label: Title Group: Ti Data: Nonlinear Modeling of Composition Effects on Temperature Sensitivity of Double‐Base and NC‐Rich Propellants. – Name: Author Label: Authors Group: Au Data: <searchLink fieldCode="AR" term="%22Farshi+Fasih%2C+Hamidreza%22">Farshi Fasih, Hamidreza</searchLink><relatesTo>1</relatesTo> (AUTHOR)<i> farshifasih@semnan.ac.ir</i><br /><searchLink fieldCode="AR" term="%22Gharaei%2C+Nima%22">Gharaei, Nima</searchLink><relatesTo>1</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Lekzian%2C+Elyas%22">Lekzian, Elyas</searchLink><relatesTo>1</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Zhang%2C+Rongchun%22">Zhang, Rongchun</searchLink><relatesTo>1</relatesTo> (AUTHOR)<i> zhangrongchun@buaa.edu.cn</i> – Name: TitleSource Label: Source Group: Src Data: <searchLink fieldCode="JN" term="%22International+Journal+of+Aerospace+Engineering%22">International Journal of Aerospace Engineering</searchLink>. 9/9/2026, Vol. 2026, p1-9. 9p. – Name: Subject Label: Subjects Group: Su Data: <searchLink fieldCode="DE" term="%22Propellants%22">Propellants</searchLink><br /><searchLink fieldCode="DE" term="%22Ballistics%22">Ballistics</searchLink><br /><searchLink fieldCode="DE" term="%22Sensitivity+analysis%22">Sensitivity analysis</searchLink><br /><searchLink fieldCode="DE" term="%22Regression+analysis%22">Regression analysis</searchLink><br /><searchLink fieldCode="DE" term="%22Burning+velocity%22">Burning velocity</searchLink><br /><searchLink fieldCode="DE" term="%22Nonlinear+statistical+models%22">Nonlinear statistical models</searchLink> – Name: Abstract Label: Abstract Group: Ab Data: 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] – Name: AbstractSuppliedCopyright Label: Group: Ab Data: <i>Copyright of International Journal of Aerospace Engineering is the property of Wiley-Blackwell and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.) |
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| RecordInfo | BibRecord: BibEntity: Identifiers: – Type: doi Value: 10.1155/ijae/2469088 Languages: – Code: eng Text: English PhysicalDescription: Pagination: PageCount: 9 StartPage: 1 Subjects: – SubjectFull: Propellants Type: general – SubjectFull: Ballistics Type: general – SubjectFull: Sensitivity analysis Type: general – SubjectFull: Regression analysis Type: general – SubjectFull: Burning velocity Type: general – SubjectFull: Nonlinear statistical models Type: general Titles: – TitleFull: Nonlinear Modeling of Composition Effects on Temperature Sensitivity of Double‐Base and NC‐Rich Propellants. Type: main BibRelationships: HasContributorRelationships: – PersonEntity: Name: NameFull: Farshi Fasih, Hamidreza – PersonEntity: Name: NameFull: Gharaei, Nima – PersonEntity: Name: NameFull: Lekzian, Elyas – PersonEntity: Name: NameFull: Zhang, Rongchun IsPartOfRelationships: – BibEntity: Dates: – D: 09 M: 09 Text: 9/9/2026 Type: published Y: 2026 Identifiers: – Type: issn-print Value: 16875966 Numbering: – Type: volume Value: 2026 Titles: – TitleFull: International Journal of Aerospace Engineering Type: main |
| ResultId | 1 |
