Comparison of burn rate and thermal decomposition of AP as oxidizer and PVC and HTPB as fuel binder based composite solid propellants

Manash, Aniket; Kumar, Pratim

doi:10.1016/j.dt.2018.08.010

Cited by 31 publications

(10 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Hence, it is necessary to study the ignition and combustion mechanism of NEPE propellants. For recent years, researchers have been concerned about the ignition characteristics of solid propellants, including the influence of propellant components [12], ignition pressure [13], and oxygen content [14] on the ignition combustion process of propellants. In view of agglomeration of aluminum particles during ignition combustion of solid propellant, previous research has investigated the effects of aluminum particle size, oxidant size, and different additives on polymerization characteristics in the propellant.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on Combustion Characteristics and Agglomeration of Al/NEPE Propellants

Zhang

Feng³

et al. 2021

Propellants Explo Pyrotec

View full text Add to dashboard Cite

In order to understand the ignition and combustion characteristics of NEPE propellants under different pressure conditions and the agglomeration behavior of aluminum particles on the burning surface, the Al/NEPE propellant was tested on a sealed high-pressure laser ignition platform. Laser ignition experiments show that both ignition delay time and combustion time are inversely proportional to ambient pressure. With the increase of pressure, the reduction of ignition delay time and self-sustaining combustion time is reduced. The impact of pressure on ignition and combustion is very complex. We then analyze the effect of pressure on ignition delay time using a theoretical mechanism. High-speed microscopic images display the agglomeration of aluminum particles in propellants mainly through the following three processes: accumulation, aggregation, and agglomeration. It is also found that many aluminum particles are agglomerated on the surface, the aluminum droplet agglomerates formed on the combustion surface are separated from the combustion surface, and the agglomerates rupture and flow out of the liquid alumina during the combustion process. The phenomenon of secondary agglomeration is also observed. The microstructure and elemental composition of combustion products of aluminum particles in NEPE propellant were obtained by scanning electron microscopy (SEM) and energy dispersive spectrometer (EDS). The detection results confirmed some agglomeration phenomena. At 3.0 MPa, the combustion of the propellant sample is sufficient, and the aluminum particles are smooth spherical alumina particles. At 1.0 MPa, the combustion of the propellant sample is insufficient, and the aluminum particles are rough. The particle size under different pressure was analyzed by a laser particle size analyzer. The results show that increasing the pressure can reduce the average agglomeration size of aluminum particles and improve combustion efficiency. The number of large particle aggregates is more at 3 MPa. From the perspective of overall particle size results, within the same diameter interval, the percentage of particle number does not increase or decrease significantly with the increase of pressure.

show abstract

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on Combustion Characteristics and Agglomeration of Al/NEPE Propellants

Zhang

Feng³

et al. 2021

Propellants Explo Pyrotec

View full text Add to dashboard Cite

show abstract

“…HTPB and Polyvinyl Chloride (PVC) plastisol blends were studied. Thermogravimetric analysis (TGA) shows that 100 % mass loss in AP-HTPB based propellants decomposes at 420.3 °C, whereas in the case of AP-PVC 80 % mass loss occurs at 397.6 °C [148]. Backburning of propellants with HTPB was improved with the addition of polyethylene glycol (PEG) polymer [149].…”

Section: Possibilities For Improving Liner and Composite Propellant P...mentioning

confidence: 99%

Properties of Hydroxyl‐Terminal Polybutadiene (HTPB) and Its Use as a Liner and Binder for Composite Propellants: A Review of Recent Advances

Amado

Ross

Murakami

et al. 2022

Propellants Explo Pyrotec

View full text Add to dashboard Cite

This paper reviews hydroxyl-terminal polybutadiene (HTPB) used as liner and binder for composite propellants, applied in rocket motors studied throughout the last decades, emphasizing the recent advances. The contribution aims to show the importance of HTPB in the propellant composition and on the liner coating of the rocket motor, which is in contact with the propellant grain. This paper also shows that many researchers have thoroughly studied several properties of HTPB, which are rele-vant to its role in liners and propellants. We have also reviewed analytical techniques such as Fourier Transform Infrared Spectroscopy (FTIR) as a characterization technique for HTPB and HTPB-based polyurethanes. Reflection and transfectants FTIR may be a future trend in studies about polymeric matrices for liners and propellants, and in the area of propellant formulations that use energetic binders, graphene and nanomaterials.

show abstract

“…AP could decompose with the release of free oxygen. AP exposes complex decomposition process with phase transition from an orthorhombic to a cubic structure at 240 0 C; this strong endothermic crystallographic phase change could withstand high activation energy [4][5][6][7][8][9][10]. AP crystal lattice becomes unstable and melts at 557 0 C; therefore AP undergoes degradation along with dissociative sublimation [11].…”

Section: Introductionmentioning

confidence: 99%

Nickel Nanoparticles with Superior Catalytic Activity for Autonomous Decomposition of Ammonium Percholorate

Elbasuney

Yehia

Saadoune

2021

Preprint

View full text Add to dashboard Cite

Nickel nanoparticles with partially filled d-shell could offer advanced catalytic performance; to common solid propellant catalysts (ferric oxide). This study reports on the facile fabrication of nickel and ferric oxide catalysts of 10 nm, and 5 nm particle sizes respectively. Fabricated particles were re-dispersed in organic solvent and effectively integrated into ammonium percholorate (AP). Elemental mapping confirmed uniform particle dispersion into APC. The catalytic efficiency of nickel was evaluated to Fe2O3 particles using DSC and TGA. AP demonstrated endothermic crystallographic phase change at 242 0C, with subsequent two exothermic decomposition reactions. Nickel demonstrated decrease in endothermic phase change by 49 % compared with 39 % for ferric oxide; this action means high catalytic activity with low activation energy. Whereas AP demonstrated total heat release of 742 J/g; nickel offered enhanced heat output by 89 % compared with 57 % for ferric oxide. The two main decomposition peaks were merged into single peak. Nickel demonstrated decrease in main decomposition temperature by 105 oC compared with 62 oC for ferric oxide. This manuscript shaded the light on nickel as novel emergent nanocatalyst with superior performance for advanced energetic systems.

show abstract

Comparison of burn rate and thermal decomposition of AP as oxidizer and PVC and HTPB as fuel binder based composite solid propellants

Cited by 31 publications

References 5 publications

Experimental Investigation on Combustion Characteristics and Agglomeration of Al/NEPE Propellants

Experimental Investigation on Combustion Characteristics and Agglomeration of Al/NEPE Propellants

Properties of Hydroxyl‐Terminal Polybutadiene (HTPB) and Its Use as a Liner and Binder for Composite Propellants: A Review of Recent Advances

Nickel Nanoparticles with Superior Catalytic Activity for Autonomous Decomposition of Ammonium Percholorate

Contact Info

Product

Resources

About