Application of the Energetic Complex [Cu(TNBI)(NH3)2(H2O)] in Heterogeneous Solid Rocket Propellants

Bogusz, Rafał; Rećko, Judyta; Magnuszewska, Paulina; Lewczuk, Rafał

doi:10.22211/cejem/86538

Cited by 4 publications

(3 citation statements)

References 12 publications

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“…Prime cause seems to be the decrease in oxygen balance of compositions due to replacement of AP with RDX which leads to incomplete combustion of propellant ingredients. This phenomenon has also been observed by Rafal et al . There is almost a 12–16 % gain in calorimetric values in HTBCP25/NG compositions as compared to the corresponding HTPB/DOA compositions.…”

Section: Resultsmentioning

confidence: 99%

High Volumetric Specific Impulse Composite Propellant Based on Terminally Functionalized Block Copolymers of Polybutadiene and ϵ‐Caprolactone

Singh

Chimurkar

et al. 2019

Propellants Explo Pyrotec

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For enhanced range, higher payload capacities and for miniaturized propulsion systems, today's strategic and tactical weapon system designers demand for higher density and specific impulse of the propellant. In order to enhance the density impulse of HTPB/DOA/RDX/AP/Al based composite propellant, studies have been carried to replace conventional HTPB/DOA binder system with hydroxyl terminated block copolymer of polybutadiene and ϵ‐caprolactone with NG as plasticizer. Total eight numbers of compositions were formulated with varying content of RDX. Both binder systems were compared in propellant compositions by evaluating various physical, thermal and ballistic properties. Various rocket performance parameters of each formulation were theoretically predicted by NASA CEC‐71 program and burning rate was measured in pressure ranges of 3‐7 and 7‐11 MPa by the acoustic emission technique. In addition, density, viscosity build up, calorimetric values, thermal decomposition and sensitivity parameters of each composition were also assessed and compared. In an outcome, it was concluded that HTBCP25/NG based propellant compositions enhance the density by 4.4–5 % and calorimetric values by 12–15 % as compared to HTPB/DOA based compositions. Strand burning rate data show enhancement of burning rate by 40–70 % at 7 MPa pressure in HTBCP25/NG based compositions. Impact and friction sensitivity data also revealed their utility in propellant compositions for future applications.

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Section: Resultsmentioning

confidence: 99%

High Volumetric Specific Impulse Composite Propellant Based on Terminally Functionalized Block Copolymers of Polybutadiene and ϵ‐Caprolactone

Singh

Chimurkar

et al. 2019

Propellants Explo Pyrotec

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“…An application of [Cu(TNBI)(NH 3 ) 2 (H 2 O)] as an energetic complex [65] in solid rocket propellants has been studied. Rocket fuel was based on the AP/HTPB formulation and a complex was used to replace RDX, which is considered as a high explosive compound in the propellant formulation.…”

Section: Effects Of the Additives On The Performance Propertiesmentioning

confidence: 99%

Solid Propellant Formulations: A Review of Recent Progress and Utilized Components

2021

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“…Recently, polynitroimidazoles have attracted considerable interest as energetic materials [3,4], especially highly energetic materials [5]. Many articles have reported new synthetic methods, explosive properties and applications of nitroimidazole derived compounds [6][7][8][9]. 2,4,5-Trinitroimidazole (Scheme 1, compound 2) is one nitroimidazole derivative, but it is not stable enough to be isolated [10].…”

Section: Introductionmentioning

confidence: 99%

Crystal Structure and Thermal Behavior of Imidazolium 2,4,5-Trinitroimidazolate

Chen¹,

Lian²,

Chen³

et al. 2019

Cent. Eur. J. Energ. Mater.

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In this work, imidazolium 2,4,5-trinitroimidazolate was obtained from 2,4,5-tri-iodoimidazole in a yield of 48%. Single-crystal X-ray diffraction analysis showed that this compound belongs to the triclinic crystal system with space group P-1. Thermogravimetric-differential scanning calorimetry (TG-DSC) was performed under a nitrogen atmosphere at heating rates of 5, 10, 15 and 20 °C·min −1 . Compound 3 clearly exhibits an exothermic decomposition. The activation energy (E) and pre-exponential factor (lnA) calculated by the Kissinger method were 113.67 kJ·mol −1 and 25.30 s −1 , respectively. The E values obtained by the FWO and KAS methods changed slightly from 103.33 to 113.69 kJ·mol −1 and from 101.52 to 111.97 kJ·mol −1 , respectively, which makes us believe that its thermal decomposition can be described using only one reaction model. The Šatava-Šesták method and the compensation effect were used to study the thermal decomposition mechanism of imidazolium 2,4,5-trinitroimidazolate.is regarded as the most appropriate thermal decomposition kinetic equation. The impact sensitivity, friction sensitivity, detonation velocity and explosion pressure of imidazolium 2,4,5-trinitroimidazolate were 43 cm, 46%, 7056.9 m·s −1 and 1.9703 · 10 10 Pa (ρ = 1.538 g·cm −3 ), respectively. Imidazolium 2,4,5-trinitroimidazolate is incompatible with RDX, HMX, TKX-50 and CL-20.Supporting Information (SI), i.e. kinetic model functions, crystallographic data, spectra of FTIR and 1 H and 13 C NMR, and HPLC, for compound 3, as well as DSC curves of single and mixture systems, are available at:

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Application of the Energetic Complex [Cu(TNBI)(NH3)2(H2O)] in Heterogeneous Solid Rocket Propellants

Cited by 4 publications

References 12 publications

High Volumetric Specific Impulse Composite Propellant Based on Terminally Functionalized Block Copolymers of Polybutadiene and ϵ‐Caprolactone

High Volumetric Specific Impulse Composite Propellant Based on Terminally Functionalized Block Copolymers of Polybutadiene and ϵ‐Caprolactone

Solid Propellant Formulations: A Review of Recent Progress and Utilized Components

Crystal Structure and Thermal Behavior of Imidazolium 2,4,5-Trinitroimidazolate

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