Comprehensive view of the combustion models of composite solid propellants

Kishore, K.

doi:10.2514/3.7618

Cited by 34 publications

(4 citation statements)

References 38 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…A number of studies were carried out to realize the decomposition mechanism of AP [45][46][47][48][49][50] and they provide good accounts of the probable decomposition mechanism of AP; moreover, numerous mechanisms have been proposed, but the decomposition mechanism of AP is still a debated matter. Two probable mechanisms have been highlighted here.…”

Section: Mechanism Of Thermal Decomposition Of Apmentioning

confidence: 99%

Graphene-iron oxide nanocomposite (GINC): an efficient catalyst for ammonium perchlorate (AP) decomposition and burn rate enhancer for AP based composite propellant

et al. 2015

View full text Add to dashboard Cite

A facile and ecofriendly method for synthesis of nano size iron oxide (Fe 2 O 3 ) decorated graphene (GINC) hybrid by the use of ultrasonication via microwave irradiation has been developed. During this process, nano size Fe 2 O 3 particles with a size of approximately 20-30 nm were decorated uniformly over graphene sheet. The nano hybrid was characterized by XRD, HRTEM and Raman spectroscopy 10 and mapping. To study the enhancement of catalytic activity of iron oxide by making GINC, several AP based compositions containing 1-5 weight % GINC were made and characterized through simultaneous thermal analysis (STA). Along with this, formulations with other catalyst with 1-5 weight % concentrations were also prepared and evaluated. Experimental results showed that GINC with 5 weight % concentration was much more effective as compared to other compositions. To extend this application further as a burn rate enhancer in composite propellant, several formulations of composite propellant containing 1 part of different burn rate enhancers like Fe 2 O 3, nano 15 size Fe 2 O 3 and GINC were made and evaluated by means of theoretical prediction, viscosity, ballistic properties, sensitivity parameter and thermophysical properties. To quantify the burn rate enhancement in the presence of GINC, burn rate measurement, STA, DSC and activation energy calculation were performed. The results show that burn rate of propellant increases from micron size Fe 2 O 3 (30% increases) to nano Fe 2 O 3 (37% increase). In the presence of GINC, a significant increase (52%) in burn rate is achieved. In GINC, effective iron content is about 50% as compared to nano and micron size Fe 2 O 3 . Hence GINC was found to be excellent burn rate 20 modifier for advance AP based propellant system. 65 and environmentally benign techniques.The metal/metal oxide particles have got much attention due to their distinctive optical, electronic and catalytic

show abstract

Section: Mechanism Of Thermal Decomposition Of Apmentioning

confidence: 99%

Graphene-iron oxide nanocomposite (GINC): an efficient catalyst for ammonium perchlorate (AP) decomposition and burn rate enhancer for AP based composite propellant

et al. 2015

View full text Add to dashboard Cite

show abstract

“…Numerous mechanisms have been proposed for the thermal decomposition of AP; [23][24][25][26][27][28] whereas two of them attracted the attention of researchers and they are still debatable, the majority are electron transfer and proton transfer mechanisms which we have well described in our previous work. 14 The present experimental ndings suggest that the GTNC accelerates both the LTD and the HTD (Fig.…”

Section: Resultsmentioning

confidence: 99%

A graphene titanium dioxide nanocomposite (GTNC): one pot green synthesis and its application in a solid rocket propellant

Dey

Nangare

et al. 2015

RSC Adv.

View full text Add to dashboard Cite

A green process was developed for a graphene-titanium dioxide nanocomposite (GTNC) synthesis by dispersing titanium dioxide (TiO 2 ) nanoparticles and graphene nano-sheets (GNSs) in ethanol via ultrasonication followed by microwave irradiation. The synthesized GTNC was well characterized by various tools: viz. XRD, HRTEM, FTIR and Raman spectroscopy. Also, Simultaneous Thermal Analysis (STA) and Differential Scanning Calorimetry (DSC) techniques have been employed to study the enhancement of the catalytic activity of the GTNC for the decomposition of Ammonium perchlroate (AP). The GTNC with 5 wt% in AP was found to be a highly effective catalyst for the AP decomposition.The decomposition temperature decreases from 412.87 C to 372.50 C and DH increases from 2053 to 3903 J g À1 . Furthermore, the GTNC was identified as an effective burn rate enhancer (i.e. combustion catalyst) for an AP based composite propellant for solid rocket propellants as confirmed by STA, DSC, activation energy calculations and burn rate measurements. The results show that the burn rate of the propellant increases by 24% for the TiO 2 nanoparticle based composition compared to the base composition, whereas a significant increase of 50% is achieved in the presence of the GTNC. Hence, the performance is improved significantly for the solid rocket propellant. † Electronic supplementary information (ESI) available: Details of raw materials, instrumentation, nano TiO 2 synthesis, Raman spectra, additional FESEM images, additional HRTEM images, detailed procedure of the thermoelectric properties measurement and summary of the thermoelectric properties of the best composite of inorganic and organic materials. See

show abstract

“…As the main power source, propellants directly affect the performance of rocket and missile engines. − Most propellant molecules contain nitro and/or nitrate groups, which decompose to produce small hydrocarbons (CH 4 , C 2 H 6 , C 2 H 4 , C 2 H 2 , and C 3 H 6 ) and NO x (N 2 O, NO 2 , and NO). ,, Clearly, the interaction chemistry between NO x and small hydrocarbons is very important for understanding gas-phase combustion of solid propellants. For internal combustion engines with exhaust gas recirculation (EGR), NO x (NO, NO 2 , and N 2 O) formed during fuel combustion will be recirculated in the next cycle and then influence the combustion of the fresh mixtures.…”

Section: Introductionmentioning

confidence: 99%

Comparative Study of the Effects of Nitrous Oxide and Oxygen on Ethylene Ignition

et al. 2017

View full text Add to dashboard Cite

To explore the effects of N2O and O2 on C2H4 ignition, ignition delay times of stoichiometric C2H4/O2/N2O/Ar mixtures with mole blending ratios of N2O/(N2O + O2) = 0, 50, 80, and 100% were measured in a high-pressure shock tube. Reflected shock conditions cover a range of pressures from 1.2 to10 atm and temperatures from 1090 to 1760 K. In addition, ignition delay times of C2H4/N2O/Ar mixtures are measured at pressures of 1.2–10 atm, equivalence ratios of 0.5–2.0, and temperatures of 1214–1817 K. The results indicate that, in the studied conditions, the ignition delay times of C2H4 greatly increase as the N2O concentration increases at a given pressure and temperature. Five recent literature models are tested against the new measured ignition delay times and show very small discrepancies among each other for the C2H4/N2O/Ar mixtures but exhibit significant discrepancies for the C2H4/N2O/O2/Ar mixtures. Moreover, the kinetic analysis is performed to reveal the reason for the discrepancies among the five models and to investigate the different effects of N2O and O2 on the C2H4 ignition.

show abstract

Comprehensive view of the combustion models of composite solid propellants

Cited by 34 publications

References 38 publications

Graphene-iron oxide nanocomposite (GINC): an efficient catalyst for ammonium perchlorate (AP) decomposition and burn rate enhancer for AP based composite propellant

Graphene-iron oxide nanocomposite (GINC): an efficient catalyst for ammonium perchlorate (AP) decomposition and burn rate enhancer for AP based composite propellant

A graphene titanium dioxide nanocomposite (GTNC): one pot green synthesis and its application in a solid rocket propellant

Comparative Study of the Effects of Nitrous Oxide and Oxygen on Ethylene Ignition

Contact Info

Product

Resources

About