Thermal Decomposition Behaviors and Burning Characteristics of AN/Nitramine-Based Composite Propellant

Naya, Tomoki; Kohga, Makoto

doi:10.1080/07370652.2014.902406

Cited by 22 publications

(9 citation statements)

References 31 publications

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“…However, this cannot be regarded as a definitive difference in the thermal decomposition behaviors of these composite propellants due to the heterogeneity of composite propellants. Furthermore, the thermal decomposition behaviors of the AN=RDX propellants with these catalysts were similar to the behaviors of the propellants without catalysts, as shown in Naya and Kohga [13]. Thus, the thermal decomposition behaviors of the AN=RDX propellants were hardly dependent on the presence of the catalyst in this experiment.…”

Section: Thermal Decomposition Behaviorssupporting

confidence: 73%

“…The thermal decomposition behaviors of AN=RDX propellants without catalysts at n ¼ 0, 0.2, 0.4, 0.6, 0.8, and 1 were investigated by TG-DTA [13]. The AN propellant (n ¼ 0) exhibited an endothermic peak at 443 K attributed to AN melting.…”

Section: Thermal Decomposition Behaviorsmentioning

confidence: 99%

“…The effect of the replacement of RDX was investigated in a previous study [13]. For the evaluation of the effect of n on the increase in burning rate upon the addition of a catalyst to the AN=RDX propellant, the ratios of the burning rate of the propellants with catalysts to that of the corresponding propellant without catalyst (R) were calculated.…”

Section: Catalytic Effect On Burning Rate Of An=rdx-based Propellantmentioning

confidence: 99%

“…The burning rate of the AN propellant was also increased by the addition of nitramines such as RDX (1,3,5-trinitroperhydro-1,3,5-triazine, hexogen) and HMX (octahydro-1,3,5,7-tetranitro-1,3,5,7-tetrazocine, octogen) because of the high energy of nitramine [13]. The increase in the rate caused by the addition of RDX was larger than that produced by the addition of HMX.…”

Section: Introductionmentioning

confidence: 98%

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Thermal Decomposition Behaviors and Burning Characteristics of AN/RDX-Based Composite Propellants Supplemented with MnO₂and Fe₂O₃

Kohga

Naya

2015

Journal of Energetic Materials

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Ammonium nitrate (AN)-based composite propellants have gained popularity because of the clean burning nature of AN as an oxidizer. However, such propellants have several disadvantages such as poor ignition and low burning rate. The burning characteristics of the AN propellant were improved when a portion of this propellant was replaced by an energetic material and the addition of a catalyst. In this study, RDX (1,3,5-trinitroperhydro-1,3,5-triazine) was used as the energetic material, and Fe 2 O 3 and MnO 2 were used as catalysts. The burning characteristics of the AN=RDX RDX propellants supplemented with catalysts were investigated, and the effects of the replacement of AN by RDX and the catalyst addition were evaluated.

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Section: Thermal Decomposition Behaviorssupporting

confidence: 73%

Section: Thermal Decomposition Behaviorsmentioning

confidence: 99%

Section: Catalytic Effect On Burning Rate Of An=rdx-based Propellantmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 98%

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Thermal Decomposition Behaviors and Burning Characteristics of AN/RDX-Based Composite Propellants Supplemented with MnO₂and Fe₂O₃

Kohga

Naya

2015

Journal of Energetic Materials

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“…The energy level of solid propellants can be improved significantly by using energetic materials such as energetic binders, energetic plasticizers and energetic additives. Due to the advantages of high energy, stable performance and convenient manufacturing, the nitramine explosives including RDX, HMX and CL-20 are widely used in high energy, reduced smoke and smokeless solid propellants [4][5][6]. However, considering its smooth furface and inert group, the nitramine explosives are regarded as the non-reinforcing.…”

Section: Introductionmentioning

confidence: 99%

Research Progress of Bonding Agents for Nitramine Composite Solid Propellants

Liu¹,

Sun²,

Hong³

et al. 2018

IJASS

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This review article summaries the method to improve mechanical properties of nitramine composite solid propellants. It concludes that the use of bonding agents is an economical, effective and convenient way to enhance the mechanical properties of propellants. The bonding mechanism and characteristics of bonding agents are analyzed. The review article presents the overview on the types and development of bonding agents for nitramine composite solid propellants. It is considered that the multi-functionalization of polymer bonding agents is a development direction of bonding agents. According to the surface characteristics of nitramine fillers and the structure characteristics of different binders, a universal bonding agent suitable for different binder-nitramine systems should be prepared through molecular design. Some suggestions are put forward for the design of universal bonding agents.

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Influence of MnO₂ and Fe₂O₃ on the Burning Characteristics of AN/AP‐Based Composite Propellants

Kohga

Togo

2019

Propellants Explo Pyrotec

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The partial substitution of ammonium perchlorate (AP) for ammonium nitrate (AN) improves the burning characteristics of AN‐based propellants, because the advantages of AP propellants compensate for the drawbacks of AN propellants and vice versa. The burning characteristics of AN/AP‐based propellants supplemented with MnO2 and Fe2O3 were measured, and the effects of these catalysts on the burning characteristics of the propellants were investigated using the collected data. The ignitability and the burning rate of the AN/AP propellant was improved by the addition of MnO2. The addition of the MnO2/Fe2O3 bicatalyst improved the ignitability of the propellants compared to adding only MnO2, but the improvement was identical to that obtained using Fe2O3. The burning rate increased in the order MnO2<Fe2O3<bicatalyst. Furthermore, the effect of these catalysts on the burning characteristics was found to depend on the size of the AP particles and the type of binder.

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Thermal Decomposition Behaviors and Burning Characteristics of AN/Nitramine-Based Composite Propellant

Cited by 22 publications

References 31 publications

Thermal Decomposition Behaviors and Burning Characteristics of AN/RDX-Based Composite Propellants Supplemented with MnO₂and Fe₂O₃

Thermal Decomposition Behaviors and Burning Characteristics of AN/RDX-Based Composite Propellants Supplemented with MnO₂and Fe₂O₃

Research Progress of Bonding Agents for Nitramine Composite Solid Propellants

Influence of MnO₂ and Fe₂O₃ on the Burning Characteristics of AN/AP‐Based Composite Propellants

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Thermal Decomposition Behaviors and Burning Characteristics of AN/Nitramine-Based Composite Propellant

Cited by 22 publications

References 31 publications

Thermal Decomposition Behaviors and Burning Characteristics of AN/RDX-Based Composite Propellants Supplemented with MnO2and Fe2O3

Thermal Decomposition Behaviors and Burning Characteristics of AN/RDX-Based Composite Propellants Supplemented with MnO2and Fe2O3

Research Progress of Bonding Agents for Nitramine Composite Solid Propellants

Influence of MnO2 and Fe2O3 on the Burning Characteristics of AN/AP‐Based Composite Propellants

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Thermal Decomposition Behaviors and Burning Characteristics of AN/RDX-Based Composite Propellants Supplemented with MnO₂and Fe₂O₃

Thermal Decomposition Behaviors and Burning Characteristics of AN/RDX-Based Composite Propellants Supplemented with MnO₂and Fe₂O₃

Influence of MnO₂ and Fe₂O₃ on the Burning Characteristics of AN/AP‐Based Composite Propellants