Proceedings ArticleDOI
Development of AP/HTPB based Fuel-rich Propellant for Solid Propellant Ramjet
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TLDR
In this article, pyral was added as a metal fuel which resulted in propellants having higher burn rates and their density variations along the length were absent contrary to those without pyral.Abstract:
It is well known that reduction of Ammonium Perchlorate (AP) content in composite propellant reduces the burn rate of solid composite propellants. Below a certain level of AP content the propellant does not burn. This paper explores ways to enhance the burn rate of fuel-rich composite solid propellant. The methods employed to enhance the burn rate of the propellant in the study are 1) Use of pyral 2) Recrystallization of AP, 3) Method to add catalyst into the propellant and 4) Addition of AC with moisture. Pyral was added as a metal fuel which resulted in propellants having higher burn rates and their density variations along the length were absent contrary to those without pyral. Addition of AC with moisture in these propellants increases the burn rate pressure index. The highest burn rate achieved is 3.8 mm/s at 70 bar with the propellant comprised of AP (particle size < 15 μm) and nanosized catalyst.read more
Citations
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Journal ArticleDOI
The Effects of Metal Complexes of Nano-Graphene Oxide to Thermal Decomposition of FOX-7.
TL;DR: The results show that the Fe3+ based complex affect the decomposition of FOX-7 more than the Cu2+ based one with the initial decomposition temperature of 230 °C and the apparent heat release of 3535.6 J·g−1.
Journal ArticleDOI
Combustion Characteristics of Ramjet Fuel Grains with Boron and Aluminum Additives
TL;DR: An experimental investigation of the effect of boron (B) and aluminum (Al) additives to fuel-rich propellant for a solid fuel ramjet application was performed in this paper.
Journal ArticleDOI
Attaining Hypersonic Flight with Aluminum-Based Fuel-Rich Propellant
Nikunj Rathi,P. A. Ramakrishna +1 more
TL;DR: In this article, experimental results of an aluminized fuel-rich propellant having energy similar to boron-based fuel rich propellant and having no residue after combustion are discussed.
Proceedings ArticleDOI
Performance Evaluation of Ramjet Fuel Grains with Boron and Magnesium Additives
Journal ArticleDOI
Flow Field Computational Analysis in a Solid Fuel Scramjet Combustor
TL;DR: In this article, the authors adopted the numerical simulation method to construct the numerical model of the combustion chamber, using RNG k- turbulence model and eddy dissipation combustion model, simulation combustor working condition, analysis of combustion chamber flow field data, concluded that the combustion phenomenon occurs mainly in the center of the flow field area.
References
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Journal ArticleDOI
Effect of nano-aluminium in plateau-burning and catalyzed composite solid propellant combustion
TL;DR: In this article, nano-aluminium particles of ∼50nm size, produced at this laboratory, are added to composite solid propellants based on ammonium perchlorate and hydroxyl-terminated poly-butadiene binder that exhibit plateau burning rate trends and those including burning rate catalysts.
Journal ArticleDOI
The effects of bimodal aluminum with ultrafine aluminum on the burning rates of solid propellants
TL;DR: In this article, the authors measured the burning rates of composite aluminized composite propellants with different aluminum (Al) sizes and with bimodal Al distributions containing various amounts of ultrafine Al (UFAl).
Journal ArticleDOI
Burning Characteristics and Thermochemical Behavior of AP/HTPB Composite Propellant Using Coarse and Fine AP Particles
TL;DR: In this paper, the authors investigated the burning characteristics and thermal decomposition behavior of AP/HTPB composite propellant using coarse and fine AP particles with and without Fe2O3 at various AP contents.
Journal ArticleDOI
Activated charcoal – A novel burn rate enhancer of aluminized composite propellants
Sumit Verma,P. A. Ramakrishna +1 more
TL;DR: In this article, the authors reported the discovery of activated charcoal as an effective burn rate enhancer of aluminized composite solid propellant and further explored the possibility of further enhancing the burn rates of ALM by using iron oxide along with activated charcoal.
Proceedings ArticleDOI
Enhancement of regression rate in hybrid rockets
TL;DR: In this article, a potential HTPB based propellant that gives a very good density specific impulse but yet does not burn like a solid propellant was identified, and the enhancement of regression rate of this propellant w ith known burn rate modifiers like iron oxide and copper chromite.
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