scholarly journals Synthesis of asymmetric [bis(imidazolyl)-BH2]+-cation-based ionic liquids as potential rocket fuels

RSC Advances ◽  
2021 ◽  
Vol 11 (60) ◽  
pp. 38040-38046
Author(s):  
Xue Li ◽  
Yin Zhang ◽  
Hongping Li ◽  
Jing Ding ◽  
Hui Wan ◽  
...  
Keyword(s):  
Ionic Liquids ◽  
Specific Impulse ◽  
High Density ◽  
Rocket Propellants

Asymmetric [bis(imidazolyl)-BH2]+-cation-based hypergolic ionic liquids are successfully synthesized, which possess a high density-specific impulse ranging from 305.4 to 357.8 s g cm−3, that make them promising candidates for rocket propellants.

Bishydrobis(tetrazol-1-yl)borate (BTB) based energetic ionic liquids with high density and energy capacity as hypergolic fuels

2017 ◽  
Vol 5 (30) ◽  
pp. 15525-15528 ◽  
Author(s):  
Xingye Li ◽  
Chenbin Wang ◽  
Haibo Li ◽  
Fude Nie ◽  
Hongquan Yin ◽  
...  
Keyword(s):  
Ionic Liquids ◽  
High Density ◽  
Energy Capacity ◽  
New Family ◽  
Energetic Ionic Liquids

A new family of bishydrobis(tetrazol-1-yl)borate (BTB) based energetic ionic liquids were synthesized, which are hypergolic with oxidizers and show superior energy capacity and high density.

High-Density Carrier Accumulation in ZnO Field-Effect Transistors Gated by Electric Double Layers of Ionic Liquids

2009 ◽  
Vol 19 (7) ◽  
pp. 1046-1053 ◽  
Author(s):  
Hongtao Yuan ◽  
Hidekazu Shimotani ◽  
Atsushi Tsukazaki ◽  
Akira Ohtomo ◽  
Masashi Kawasaki ◽  
...  
Keyword(s):  
Ionic Liquids ◽  
Field Effect ◽  
Field Effect Transistors ◽  
High Density ◽  
Double Layers ◽  
Electric Double Layers

scholarly journals Synthesis and performance of cyclopropanated pinanes with high density and high specific impulse

Fuel ◽  
2022 ◽  
Vol 307 ◽  
pp. 121906
Author(s):  
Yakun Liu ◽  
Chengxiang Shi ◽  
Lun Pan ◽  
Xiangwen Zhang ◽  
Ji-Jun Zou
Keyword(s):  
Specific Impulse ◽  
High Density ◽  
And Performance

STUDIES OF THE INFLUENCE OF ENERGETIC ADDITIVES ON SELECTED PROPERTIES OF HETEROGENEOUS SOLID ROCKET PROPELLANT WITH LOW CONTENT OF HCL IN COMBUSTION PRODUCTS

2018 ◽  
Vol 144 (4) ◽  
pp. 15-30
Author(s):  
Paulina MAGNUSZEWSKA ◽  
Rafał Bogusz ◽  
Bogdan Florczak
Keyword(s):  
Sodium Nitrate ◽  
Specific Impulse ◽  
Combustion Products ◽  
Heat Of Combustion ◽  
Mechanical Stimuli ◽  
Rocket Propellants ◽  
Ballistic Properties ◽  
Solid Rocket ◽  
Solid Rocket Propellants ◽  
Heterogeneous Solid

The paper presents influence of additives like aluminium, magnesium, AMD (aluminium-magnesium dust) and boron on selected properties of heterogeneous solid rocket propellants (HSRP) based on HTPB in which ammonium chlorate was partly replaced by sodium nitrate. The presence of sodium nitrate reduces the content of hydrogen chloride (HCl) in combustion products. Theoretical values of thermochemical and thermodynamical properties like isochoric heat of combustion (Q), specific impulse (Isp) and combustion products in motor chamber and nozzle were identified by ICT-Code program. A laboratory rocket motor (LRM) was used to examine ballistic properties for prepared samples of propellants. Their temperature of decomposition, heat of combustion and hardness were tested both with sensitivity to mechanical stimuli (impact, friction) and rheological properties at curing.

STUDIES OF HIGH EXPLOSIVES IMPACT ON REDUCTION OF HCL IN HETEROGENEOUS SOLID ROCKET PROPELLANTS

2017 ◽  
pp. 29-45
Author(s):  
Rafał Bogusz ◽  
Paulina Magnuszewska ◽  
Bogdan Florczak
Keyword(s):  
Specific Impulse ◽  
Calorific Value ◽  
Combustion Products ◽  
Decomposition Temperature ◽  
Mechanical Stimuli ◽  
High Explosives ◽  
Combustion Heat ◽  
Rocket Propellants ◽  
Solid Rocket ◽  
Heterogeneous Solid

The paper describes an influence of high explosives: hexogene (RDX), octogene (HMX), and dinitro-diaminoethene (FOX-7) on the properties of heterogeneous solid rocket propellant (HSRP) prepared on the base of Hydroxy Terminated Polybutadiene (HTPB) in which ammonium perchlorate (AP) was partially replaced by sodium nitrate (SN). It reduced the content of HCl in combustion products. Theoretical values of thermochemical and thermodynamic properties such as isochoric combustion heat (Q), specific impulse (Isp) and contents of combustion products in motor combustion chamber and nozzle have been identified by using the ICT-Code program. The rheological properties (virtual viscosity) of the propellant slurry during curing process, the sensitivity to mechanical stimuli (impact, friction), decomposition temperature, calorific value and hardness of propellants containing explosive materials were tested by instruments and ballistic properties were investigated by laboratory rocket motor (LRM).

ESTIMATION OF THERMODYNAMIC AND THERMOCHEMICAL PROPERTIES OF SOLID HETEROGENEOUS ROCKET PROPELLANTS CONTAINING SCAVENGERS

2019 ◽  
Vol 150 (2) ◽  
pp. 59-70
Author(s):  
Katarzyna Gańczyk-Specjalska ◽  
Rafał Bogusz ◽  
Rafał Lewczuk ◽  
Paulina Magnuszewska
Keyword(s):  
Hydrogen Chloride ◽  
Alkaline Earth ◽  
Specific Impulse ◽  
Earth Metal ◽  
Combustion Products ◽  
Metal Salts ◽  
Alkaline Earth Metal ◽  
Oxygen Balance ◽  
Thermochemical Properties ◽  
Rocket Propellants

A new trend in development of solid heterogeneous rocket propellants (SHRP) is a reduction of emission of gases, generated during combustion of propellants, leaving a trace of white smoke behind the nozzle as a result of condensation of combustion products including above all the hydrogen chloride. This smoke is called as secondary smoke in accordance with the AGARD classification. The SHRP based on ammonium perchlorate (commonly used oxidizer) generates significant amounts of hydrogen chloride in combustion products. There are various methods to reduce the emission of secondary smokes – one of them is the ad-dition of scavengers to SHRP. Alkaline earth metal salts are used as scavengers. The estimation of thermodynamic and thermochemical properties of SHRP containing selected scavengers was carried out by using the ICT-Code software (The ICT-Thermodynamic Code). The influence of different scavengers and their amount on selected properties, e.g. oxygen balance, density, caloricity, specific impulse, and amount of hydrogen chloride in combustion products, was determined.

scholarly journals Preparation and characterisation of high-density ionic liquids incorporating halobismuthate anions

2014 ◽  
Vol 43 (28) ◽  
pp. 10910-10919 ◽  
Author(s):  
Nico E. A. Cousens ◽  
Leah J. Taylor Kearney ◽  
Matthew T. Clough ◽  
Kevin R. J. Lovelock ◽  
Robert G. Palgrave ◽  
...  
Keyword(s):  
Ionic Liquids ◽  
High Density

1-Butyl-3-methylimidazolium tetrahalobismuthates. Chlorobismuthates are colourless. Upon substitution of chloride for bromide or iodide the liquids become progressively more yellow or red.

scholarly journals Impulse and Performance Measurements of Electric Solid Propellant in a Laboratory Electrothermal Ablation-Fed Pulsed Plasma Thruster

Aerospace ◽  
2020 ◽  
Vol 7 (6) ◽  
pp. 70
Author(s):  
Matthew S. Glascock ◽  
Joshua L. Rovey ◽  
Kurt A. Polzin
Keyword(s):  
Solid Propellant ◽  
Specific Impulse ◽  
Energy Levels ◽  
Early Discharge ◽  
Initial Energy ◽  
Pulsed Plasma ◽  
Performance Measurements ◽  
Rocket Propellants ◽  
Pulsed Plasma Thruster ◽  
Plasma Thruster

Electric solid propellants are advanced solid chemical rocket propellants that can be controlled (ignited, throttled and extinguished) through the application and removal of an electric current. This behavior may enable the propellant to be used in multimode propulsion systems utilizing the ablative pulsed plasma thruster. The performance of an electric solid propellant operating in an electrothermal ablation-fed pulsed plasma thruster was investigated using an inverted pendulum micro-newton thrust stand. The impulse bit and specific impulse of the device using the electric solid propellant were measured for short-duration test runs of 100 pulses and longer-duration runs to end-of-life, at energy levels of 5, 10, 15 and 20 J. Also, the device was operated using the current state-of-the-art ablation-fed pulsed plasma thruster propellant, polytetrafluoroethylene (PTFE). Impulse bit measurements for PTFE indicate 100 ± 20 µN-s at an initial energy level of 5 J, which increases linearly with energy by approximately 30 µN-s/J. Within the error of the experiment, measurements of the impulse bit for the electric solid propellant are identical to PTFE. Specific impulse when operating on PTFE is calculated to be about 450 s. It is demonstrated that a surface layer in the hygroscopic electric solid propellant is rapidly ablated over the first few discharges of the device, which decreases the average specific impulse relative to the traditional polytetrafluoroethylene propellant. Correcting these data by subtracting the early discharge ablation mass loss measurements yields a corrected electric solid propellant specific impulse of approximately 300 s.

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