Screening of Nano-Aluminum Based Solid Fuels for Hybrid Rocket Applications

Hashim, Syed Alay; Kangle, Sanket Milind; Karmakar, Srinibas; Roy, Arnab

doi:10.2514/6.2018-0669

Cited by 6 publications

(4 citation statements)

References 21 publications

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“…It is observed that particle loaded samples consume less mass during combustion compared to SF1. In this context, similar observation has been reported by previous researchers with paraffin-wax or polymeric fuels loaded with metal particles which were examined by using OFB [28,36,[38][39][40]. Actually, the required temperature for HTPB pyrolysis is below 500°C whereas boron ignition occurs above 500°C (Figure 4).…”

Section: Evaluation Of Regression Ratesupporting

confidence: 85%

“…Therefore, a very old testing tool which was introduced in 1950s called opposed flow burner (OFB) has been used in the present study which can minimize the effort as well as cost for rapid screening of fuel. Recently OFB has been employed by many researchers for formulation and selection of different types of solid fuel combinations [28,[35][36][37][38][39][40]. In OFB the burning environment on the fuel surface can be digitally captured and analysed which is not possible in a rocket motor.…”

Section: Introductionmentioning

confidence: 99%

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Experimental Observation and Characterization of B−HTPB‐based Solid Fuel with Addition of Iron Particles for Hybrid Gas Generator in Ducted Rocket Applications

Hashim

Ojha

Karmakar

et al. 2019

Propellants Explo Pyrotec

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An extensive diversity in the formulation of HTPB‐based solid fuels with metal additives has now been accepted in rocket and missile applications. Boron, which is a metalloid and often occurs in compound form has maintained its dominance mainly due to its significant theoretical energy potential. Therefore, it is preferred as the primary choice for rockets and solid fuel ramjet (SFRJ) or ducted rocket (SFDR). In this paper, performance enhancement of B−HTPB‐based solid fuel is assessed through a rapid screening tool which is called an opposed flow burner (OFB). Screened fuel combinations may be further evaluated in the gas generator of a ducted rocket (DR) to fulfill the intention of the present investigation. The baseline fuel (B−HTPB) is included with a metal fuel/catalyst (iron) with the expectation that it would enhance the combustion performance of boron. Boron−iron loading has been taken 10 % of the total sample weight (wt.) giving a wt. ratio of 90 : 10. Pure oxygen has been used as an oxidizer which impinges on the fuel surface where oxygen mass flux (Gox) varies between 20–57 kg/m2‐s. In this study, the research focuses mainly on regression rate and amount of residual active boron in the condensed combustion product (CCP) of the samples. Addition of iron to B−HTPB increases the regression rate by around 12 % and active boron content in CCP reduces significantly to 2.5 % compared to 16 % of the baseline fuel. In addition to that, the heating value of the fuel samples and identification of gas phase intermediate species (OH, CH, C2, BO, BO2) are the other vital investigations undertaken in the present study.

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Section: Evaluation Of Regression Ratesupporting

confidence: 85%

Section: Introductionmentioning

confidence: 99%

Experimental Observation and Characterization of B−HTPB‐based Solid Fuel with Addition of Iron Particles for Hybrid Gas Generator in Ducted Rocket Applications

Hashim

Ojha

Karmakar

et al. 2019

Propellants Explo Pyrotec

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“…These findings resonate with enhanced reactivity in nanoscale materials, leading to a more rapid energy release during combustion processes. 14,15 The specific thrust and impulse implications are substantial because the combustion time directly affects these metrics.…”

Section: Discussionmentioning

confidence: 99%

Analysis of carbon nano particle variant as the propellant fuel to increase specific impulses of rockets

Navalino,

Muda,

Hafizah

et al. 2023

F1000Res

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Background: This study compares propellant fuels’ specific thrust and impulse parameters using nanocarbon variant fuels from coconut shells and coal. Specific impulses and impulses are essential parameters that determine rocket performance. The specific thrust and impulses are influenced by fuel type, material composition, heat flow, and burning time parameters. The characteristics of nanocarbon as a fuel are proven to have high-value features and a long combustion time. This parameter is essential to add value to specific thrusts and impulses. Methods: The method to prove the quality of solid fuel material was done experimentally. The composition of the propellant fuel variant mixed with NH4ClO4 as an oxidizer through the printing process and sample testing was carried out using scanning electron microscope (SEM), X-ray diffraction analysis (XRD), combustion time, and specific impulse tests. Results: Test results with the composition of CBK2 (Coconut Shell + NH4ClO4 + Binder + Al = 15: 70: 10: 5) produced a specific impulse of 267 seconds or an increase of 37 seconds without carbon. CBB2 (Coal + NH4ClO4 + Binder + Al = 15: 70: 10: 5) produced a specific impulse of 261 seconds or an increase of 31 seconds. Conclusions: The composition of nanocarbon as a solid fuel propellant has been proven to increase a rocket’s thrust and specific impulses. After all the material variants have been tested for thrust and specific impulse, the best rocket propellant is CBK2.

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“…This finding indicates that higher levels of residue absorption are not recommended. According to [20], which included 5 separate samples, raising the oxidizer flux increases the regression rate. Figure 2 shows that pure paraffin wax has the highest regression rate, while 20% aluminum loading has the lowest.…”

Section: Aluminiummentioning

confidence: 99%

Metals and Alloys Additives as Enhancer for Rocket Propulsion: A Review

Ismail

Nordin

Azami

et al. 2021

ARFMTS

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A rocket's engine usually uses fuel and oxygen as propellants to increase the rocket's projection during launch. Nowadays, metallic ingredients are commonly used in the rocket’s operation to increase its performance. Metallic ingredients have a high energy density, flame temperature, and regression rate that are important factors in the propulsion process. There is a wide range of additives have been reported so far as catalysts for rocket propulsion. The studies show that the presence of metal additives improves the regression rate, specific impulse and combustion efficiency. Herein, the common energetic additives for rocket propulsion such as metal and light metals are reviewed. Besides the effect of these energetic particles on the regression behaviors of base (hybrid) fuel has been exclusively discussed. This paper also proposed a new alloy namely high entropy alloys (HEAs) as a new energetic additive that can potentially increase the performance of the rocket propellant system.

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Screening of Nano-Aluminum Based Solid Fuels for Hybrid Rocket Applications

Cited by 6 publications

References 21 publications

Experimental Observation and Characterization of B−HTPB‐based Solid Fuel with Addition of Iron Particles for Hybrid Gas Generator in Ducted Rocket Applications

Experimental Observation and Characterization of B−HTPB‐based Solid Fuel with Addition of Iron Particles for Hybrid Gas Generator in Ducted Rocket Applications

Analysis of carbon nano particle variant as the propellant fuel to increase specific impulses of rockets

Metals and Alloys Additives as Enhancer for Rocket Propulsion: A Review

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