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Thermal Decomposition Kinetics Studies of HTPB/Al/AP Solid Propellants Formulated With Iron Oxide Burning Rate Catalyst in Nano and Micro Scale

Thermal Decomposition Kinetics Studies of HTPB/Al/AP Solid Propellants Formulated With Iron Oxide Burning Rate Catalyst in Nano and Micro Scale

Luis Eduardo Nunes Almeida, Aureomar F. Martins, Susane R. Gomes, Flavio A. L. Cunha
Copyright: © 2018 |Pages: 23
ISBN13: 9781522529033|ISBN10: 1522529039|EISBN13: 9781522529040
DOI: 10.4018/978-1-5225-2903-3.ch010
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MLA

Almeida, Luis Eduardo Nunes, et al. "Thermal Decomposition Kinetics Studies of HTPB/Al/AP Solid Propellants Formulated With Iron Oxide Burning Rate Catalyst in Nano and Micro Scale." Energetic Materials Research, Applications, and New Technologies, edited by Rene Francisco Boschi Goncalves, et al., IGI Global, 2018, pp. 211-233. https://doi.org/10.4018/978-1-5225-2903-3.ch010

APA

Almeida, L. E., Martins, A. F., Gomes, S. R., & Cunha, F. A. (2018). Thermal Decomposition Kinetics Studies of HTPB/Al/AP Solid Propellants Formulated With Iron Oxide Burning Rate Catalyst in Nano and Micro Scale. In R. Goncalves, J. Atilio Fritz Fidel Rocco, & K. Iha (Eds.), Energetic Materials Research, Applications, and New Technologies (pp. 211-233). IGI Global. https://doi.org/10.4018/978-1-5225-2903-3.ch010

Chicago

Almeida, Luis Eduardo Nunes, et al. "Thermal Decomposition Kinetics Studies of HTPB/Al/AP Solid Propellants Formulated With Iron Oxide Burning Rate Catalyst in Nano and Micro Scale." In Energetic Materials Research, Applications, and New Technologies, edited by Rene Francisco Boschi Goncalves, José Atilio Fritz Fidel Rocco, and Koshun Iha, 211-233. Hershey, PA: IGI Global, 2018. https://doi.org/10.4018/978-1-5225-2903-3.ch010

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Abstract

The thermal decomposition kinetics of ammonium perchlorate (AP)/hydroxyl-terminated-polybutadiene (HTPB) samples, with Iron Oxide catalyst at nano and micro scale were studied by thermal analysis techniques at different heating rates in dynamic nitrogen atmosphere. The exothermic reaction kinetics was studied by differential scanning calorimetry (DSC) in isothermal conditions. The Arrhenius kinetic parameters were obtained by Flynn-Wall and Ozawa Kissinger and Starink methods. The propellant samples thermal decomposition was studied simultaneously by TG-DTA. For this purpose, solid propellant grains containing nano and micro scale iron oxide were formulated. The effect of catalysts on the propellant burning rate and the propellant initiation sensitivity were also evaluated by friction and impact. The effect of the catalyst in the propellant binder reaction was evaluated by viscosity and mechanical properties. SEM/EDS technique was used to evaluate the iron oxide morphology. Three bench firing tests were performed with rockets motor in order to know the ballistics parameters.

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