The Experts below are selected from a list of 306 Experts worldwide ranked by ideXlab platform
A G Korotkikh - One of the best experts on this subject based on the ideXlab platform.
-
effect of iron and boron ultrafine powders on combustion of aluminized Solid Propellants
Combustion and Flame, 2017Co-Authors: V A Arkhipov, V E Zarko, A G Korotkikh, O G Glotov, A B KiskinAbstract:Abstract The paper presents the results of measurement of the burning rate of aluminized composite Solid Propellants (CSPs) and parameters of sampled condensed combustion products including their particle size distribution, chemical and phase composition. Effect of ultra-fine iron and amorphous boron additives in CSP formulations based on AP, butadiene rubber and Alex (2 wt. %) on the combustion characteristics was studied. The sampled particles of condensed combustion products (CCPs) were classified as oxide particles (less than 55 µm) and agglomerate particles (up to 500 µm). The CCPs particles were subjected to morphological, particle size, chemical and phase analyses. It was found that partial replacement of Alex by 2 wt. % of iron in CSP leads to 1.3-1.4 fold increase in the burning rate in the pressure range of 2.2-7.5 MPa. At the same time the agglomeration of metal fuel is slightly increased: the mean diameter of agglomerate particles in CCPs is increased up to 1.2 fold and their content is increased up to 1.4 fold. The content and mean diameter of oxide particles in CCPs are reduced by 16 % and 13 %, respectively. Upon partial replacement of Alex by 2 wt. % of boron the burning rate is practically unchanged as compared with that for basic propellant with Alex. However the agglomeration is significantly enhanced, which is manifested at the increase in the agglomerate particles content in CCPs by 1.8-2.2 times, increase by 1.6-1.7 times in the agglomerates mean diameter and increase in the unburned metal fraction in agglomerates by 1.6-1.9 times. The content and the mean diameter of the oxide particles are reduced more significantly than in the case of iron introduction, namely, by 20-30 % and 30-40 %, respectively.
-
laboratory method for measurement of the specific impulse of Solid Propellants
Combustion Explosion and Shock Waves, 2014Co-Authors: V A Arkhipov, A B Kiskin, V E Zarko, A G KorotkikhAbstract:A new laboratory express-method of determining the specific impulse of Solid Propellants based on the measurement of the reactive force of gasification products escaping from the burning propellant surface is presented in this work. The values of the specific impulse for a model composite Solid propellant by varying the pressure in the combustion chamber are determined.
-
the influence of aluminum powder dispersity on composite Solid Propellants ignitability by laser radiation
Combustion and Flame, 2012Co-Authors: V A Arkhipov, A G KorotkikhAbstract:Abstract The results of experimental study of ignition process of composite Solid Propellants based on ammonium nitrate and energetic binder containing aluminum powders of various particle sizes by CO2-laser radiation in air (with ambient pressure) are presented. Partial or complete replacement of micron-sized aluminum powder on Alex ultrafine powder as part of composite Solid Propellants leads to the reduction of ignition time by decrease the temperature of burning surface, thickness of reaction layer and by increase of the heating rate in condensed phase. It was found that the efficiency of ultrafine aluminum powder additives in formulations increasing with decreasing of laser radiation intensity. The temperature of the formulation’s burning surface at the ignition moment was measured by usage of the thermal imager. The temperature of burning surface under ignition by radiant heat flux was 545–660 °C (formulations containing ultrafine aluminum powder) and 713–820 °C (formulations with micron-sized aluminum powder) for the radiation intensity 60 W/cm2.
V A Arkhipov - One of the best experts on this subject based on the ideXlab platform.
-
effect of iron and boron ultrafine powders on combustion of aluminized Solid Propellants
Combustion and Flame, 2017Co-Authors: V A Arkhipov, V E Zarko, A G Korotkikh, O G Glotov, A B KiskinAbstract:Abstract The paper presents the results of measurement of the burning rate of aluminized composite Solid Propellants (CSPs) and parameters of sampled condensed combustion products including their particle size distribution, chemical and phase composition. Effect of ultra-fine iron and amorphous boron additives in CSP formulations based on AP, butadiene rubber and Alex (2 wt. %) on the combustion characteristics was studied. The sampled particles of condensed combustion products (CCPs) were classified as oxide particles (less than 55 µm) and agglomerate particles (up to 500 µm). The CCPs particles were subjected to morphological, particle size, chemical and phase analyses. It was found that partial replacement of Alex by 2 wt. % of iron in CSP leads to 1.3-1.4 fold increase in the burning rate in the pressure range of 2.2-7.5 MPa. At the same time the agglomeration of metal fuel is slightly increased: the mean diameter of agglomerate particles in CCPs is increased up to 1.2 fold and their content is increased up to 1.4 fold. The content and mean diameter of oxide particles in CCPs are reduced by 16 % and 13 %, respectively. Upon partial replacement of Alex by 2 wt. % of boron the burning rate is practically unchanged as compared with that for basic propellant with Alex. However the agglomeration is significantly enhanced, which is manifested at the increase in the agglomerate particles content in CCPs by 1.8-2.2 times, increase by 1.6-1.7 times in the agglomerates mean diameter and increase in the unburned metal fraction in agglomerates by 1.6-1.9 times. The content and the mean diameter of the oxide particles are reduced more significantly than in the case of iron introduction, namely, by 20-30 % and 30-40 %, respectively.
-
Solid propellant combustion in a high-velocity cross-flow of gases (review)
Combustion Explosion and Shock Waves, 2016Co-Authors: V A Arkhipov, V E Zarko, I. K. Zharova, A. S. Zhukov, E. A. Kozlov, D. D. Aksenenko, A. V. KurbatovAbstract:Combustion of Solid Propellants in rocket propulsion systems usually occurs in an intense cross-flow of combustion products (Solid rocket motor), gaseous oxidizer (hybrid rocket motor) or air (ramjet and air-breathing engines). This leads to the so-called erosive burning effects, resulting in a change in the burning law under the influence of the gas flow. The main approaches to modeling the erosive burning of Solid Propellants in a high-velocity cross-flow of gases are considered. Methods for the criterial description of the results of experimental studies of the erosive burning of Solid Propellants under transonic and supersonic flow conditions are analyzed.
-
laboratory method for measurement of the specific impulse of Solid Propellants
Combustion Explosion and Shock Waves, 2014Co-Authors: V A Arkhipov, A B Kiskin, V E Zarko, A G KorotkikhAbstract:A new laboratory express-method of determining the specific impulse of Solid Propellants based on the measurement of the reactive force of gasification products escaping from the burning propellant surface is presented in this work. The values of the specific impulse for a model composite Solid propellant by varying the pressure in the combustion chamber are determined.
-
the influence of aluminum powder dispersity on composite Solid Propellants ignitability by laser radiation
Combustion and Flame, 2012Co-Authors: V A Arkhipov, A G KorotkikhAbstract:Abstract The results of experimental study of ignition process of composite Solid Propellants based on ammonium nitrate and energetic binder containing aluminum powders of various particle sizes by CO2-laser radiation in air (with ambient pressure) are presented. Partial or complete replacement of micron-sized aluminum powder on Alex ultrafine powder as part of composite Solid Propellants leads to the reduction of ignition time by decrease the temperature of burning surface, thickness of reaction layer and by increase of the heating rate in condensed phase. It was found that the efficiency of ultrafine aluminum powder additives in formulations increasing with decreasing of laser radiation intensity. The temperature of the formulation’s burning surface at the ignition moment was measured by usage of the thermal imager. The temperature of burning surface under ignition by radiant heat flux was 545–660 °C (formulations containing ultrafine aluminum powder) and 713–820 °C (formulations with micron-sized aluminum powder) for the radiation intensity 60 W/cm2.
-
experimental study of the acoustic admittance of the burning surface of composite Solid Propellants
Combustion Explosion and Shock Waves, 2011Co-Authors: V A Arkhipov, S A Volkov, L N RevyaginAbstract:A method for measuring the acoustic admittance of the burning surface of Solid Propellants using a two-dimensional combustion chamber (T-burner) is considered. The paper presents the results of an experimental study of the effect of the pressure and frequency of acoustic oscillations in the combustion chamber and the effects of the composition, mass content, and aluminum powder particle size on the acoustic admittance of the burning surface of composite Solid Propellants.
Charles Grix - One of the best experts on this subject based on the ideXlab platform.
-
Solid State Digital Propulsion Cluster Thrusters for Small Satellites Using High Performance Electrically Controlled Extinguishable Solid Propellants
19th Annual AIAA USU Conference on Small Satellites, 2005Co-Authors: Wayne N Sawka, Arthur Katzakian, Charles GrixAbstract:Electrically controlled extinguishable Solid Propellants (ESCSP) are capable of multiple ignitions, extinguishments and throttle control by the application of electrical power. Both core and end burning no moving parts ECESP grains/motors to three inches in diameter have now been tested. Ongoing research has led to a newer family of even higher performance ECESP providing up to 10% higher Isp, manufacturing ease, and significantly higher electrical conduction. The high conductivity was not found to be desirable for larger motors; however it is ideal for downward scaling to micro and pico-propulsion applications with a web thickness of less than 0.125 inch. As a Solid solution propellant, this ECESP is molecularly uniform, having no granular structure. Because of this homogeneity and workable viscosity it can be directly cast into thin layers or vacuum cast into complex geometries. Both coaxial and grain stacks have been demonstrated. Combining individual propellant coaxial grains and/or grain stacks together form three-dimensional arrays of modular cluster thrusters. Adoption of fabless manufacturing methods and standards from the electronics industry will provide custom, highly reproducible micro-propulsion arrays and clusters at low costs. These stack and cluster thruster designs provide a small footprint saving spacecraft surface area for solar panels and/or experiments. The simplicity of these thrusters will enable their broad use on micro-pico satellites for primary propulsion, ACS and formation flying applications. Larger spacecraft may find uses for ECESP thrusters on extended booms, on-orbit refueling, pneumatic actuators, and gas generators.
-
Solid State Digital Propulsion "Cluster Thrusters" For Small Satellites, Using High Performance Electrically Controlled Extinguishable Solid Propellants*
19th Annual AIAA USU Conference on Small Satellites, 2005Co-Authors: Wayne N Sawka, Arthur Katzakian, Charles GrixAbstract:Electrically controlled extinguishable Solid Propellants (ESCSP) are capable of multiple ignitions, extinguishments and throttle control by the application of electrical power. Both core and end burning no moving parts ECESP grains/motors to three inches in diameter have now been tested. Ongoing research has led to a newer family of even higher performance ECESP providing up to 10% higher Isp, manufacturing ease, and significantly higher electrical conduction. The high conductivity was not found to be desirable for larger motors; however it is ideal for downward scaling to micro and pico-propulsion applications with a web thickness of less than 0.125 inch. As a Solid solution propellant, this ECESP is molecularly uniform, having no granular structure. Because of this homogeneity and workable viscosity it can be directly cast into thin layers or vacuum cast into complex geometries. Both coaxial and grain stacks have been demonstrated. Combining individual propellant coaxial grains and/or grain stacks together form three-dimensional arrays of modular cluster thrusters. Adoption of fabless manufacturing methods and standards from the electronics industry will provide custom, highly reproducible micro-propulsion arrays and clusters at low costs. These stack and cluster thruster designs provide a small footprint saving spacecraft surface area for solar panels and/or experiments. The simplicity of these thrusters will enable their broad use on micro-pico satellites for primary propulsion, ACS and formation flying applications. Larger spacecraft may find uses for ECESP thrusters on extended booms, on-orbit refueling, pneumatic actuators, and gas generators.
-
Solid state digital propulsion cluster thrusters for small satellites using high performance electrically controlled extinguishable Solid Propellants
2005Co-Authors: Wayne N Sawka, Arthur Katzakian, Charles GrixAbstract:Electrically controlled extinguishable Solid Propellants (ESCSP) are capable of multiple ignitions, extinguishments and throttle control by the application of electrical power. Both core and end burning no moving parts ECESP grains/motors to three inches in diameter have now been tested. Ongoing research has led to a newer family of even higher performance ECESP providing up to 10% higher performance, manufacturing ease, and significantly higher electrical conduction. The high conductivity was not found to be desirable for larger motors; however it is ideal for downward scaling to micro and pico- propulsion applications with a web thickness of less than 0.125 inch/ diameter. As a Solid solution propellant, this ECESP is molecularly uniform, having no granular structure. Because of this homogeneity and workable viscosity it can be directly cast into thin layers or vacuum cast into complex geometries. Both coaxial and grain stacks have been demonstrated. Combining individual propellant coaxial grains and/or grain stacks together form three-dimensional arrays yield modular cluster thrusters. Adoption of fabless manufacturing methods and standards from the electronics industry will provide custom, highly reproducible micro-propulsion arrays and clusters at low costs. These stack and cluster thruster designs provide a small footprint saving spacecraft surface area for solar panels and/or experiments. The simplicity of these thrusters will enable their broad use on micro-pico satellites for primary propulsion, ACS and formation flying applications. Larger spacecraft may find uses for ECESP thrusters on extended booms, on-orbit refueling, pneumatic actuators, and gas generators.
Wayne N Sawka - One of the best experts on this subject based on the ideXlab platform.
-
electrical Solid Propellants a safe micro to macro propulsion technology
49th AIAA ASME SAE ASEE Joint Propulsion Conference, 2013Co-Authors: Wayne N Sawka, Michael McphersonAbstract:In this work we developed three high performance families of plastisol Solid Propellants that are IM-capable and highly manufacturable, using benign processes and “green” ingredients. Highly aluminized Electric Solid Propellant (ESP) “igniterless” rocket motors have been demonstrated at 4inch diameter scale. These igniterless rocket motors use inert metal electrodes for direct ignition of the electric Solid propellant, thereby eliminating the need for pyrotechnic ignition systems. A fast cook-off Insensitive Munitions test of a 4-inch diameter aluminum-cased ESP motor yielded a TypeV reaction, with no materials ejected from the burn pit. We successfully demonstrated pyrogen-free, igniterless electrically-initiated ignition of 200 lbf thrust class static tests in three separate firings conducted during the development program. In related activities, both nonmetalized minimum signature formulations and reduced-signature boron-fueled plastisol ESP compositions continue to undergo qualification testing for technology transfer applications in defense and commercial endeavors.
-
Solid State Digital Propulsion Cluster Thrusters for Small Satellites Using High Performance Electrically Controlled Extinguishable Solid Propellants
19th Annual AIAA USU Conference on Small Satellites, 2005Co-Authors: Wayne N Sawka, Arthur Katzakian, Charles GrixAbstract:Electrically controlled extinguishable Solid Propellants (ESCSP) are capable of multiple ignitions, extinguishments and throttle control by the application of electrical power. Both core and end burning no moving parts ECESP grains/motors to three inches in diameter have now been tested. Ongoing research has led to a newer family of even higher performance ECESP providing up to 10% higher Isp, manufacturing ease, and significantly higher electrical conduction. The high conductivity was not found to be desirable for larger motors; however it is ideal for downward scaling to micro and pico-propulsion applications with a web thickness of less than 0.125 inch. As a Solid solution propellant, this ECESP is molecularly uniform, having no granular structure. Because of this homogeneity and workable viscosity it can be directly cast into thin layers or vacuum cast into complex geometries. Both coaxial and grain stacks have been demonstrated. Combining individual propellant coaxial grains and/or grain stacks together form three-dimensional arrays of modular cluster thrusters. Adoption of fabless manufacturing methods and standards from the electronics industry will provide custom, highly reproducible micro-propulsion arrays and clusters at low costs. These stack and cluster thruster designs provide a small footprint saving spacecraft surface area for solar panels and/or experiments. The simplicity of these thrusters will enable their broad use on micro-pico satellites for primary propulsion, ACS and formation flying applications. Larger spacecraft may find uses for ECESP thrusters on extended booms, on-orbit refueling, pneumatic actuators, and gas generators.
-
Solid State Digital Propulsion "Cluster Thrusters" For Small Satellites, Using High Performance Electrically Controlled Extinguishable Solid Propellants*
19th Annual AIAA USU Conference on Small Satellites, 2005Co-Authors: Wayne N Sawka, Arthur Katzakian, Charles GrixAbstract:Electrically controlled extinguishable Solid Propellants (ESCSP) are capable of multiple ignitions, extinguishments and throttle control by the application of electrical power. Both core and end burning no moving parts ECESP grains/motors to three inches in diameter have now been tested. Ongoing research has led to a newer family of even higher performance ECESP providing up to 10% higher Isp, manufacturing ease, and significantly higher electrical conduction. The high conductivity was not found to be desirable for larger motors; however it is ideal for downward scaling to micro and pico-propulsion applications with a web thickness of less than 0.125 inch. As a Solid solution propellant, this ECESP is molecularly uniform, having no granular structure. Because of this homogeneity and workable viscosity it can be directly cast into thin layers or vacuum cast into complex geometries. Both coaxial and grain stacks have been demonstrated. Combining individual propellant coaxial grains and/or grain stacks together form three-dimensional arrays of modular cluster thrusters. Adoption of fabless manufacturing methods and standards from the electronics industry will provide custom, highly reproducible micro-propulsion arrays and clusters at low costs. These stack and cluster thruster designs provide a small footprint saving spacecraft surface area for solar panels and/or experiments. The simplicity of these thrusters will enable their broad use on micro-pico satellites for primary propulsion, ACS and formation flying applications. Larger spacecraft may find uses for ECESP thrusters on extended booms, on-orbit refueling, pneumatic actuators, and gas generators.
-
Solid state digital propulsion cluster thrusters for small satellites using high performance electrically controlled extinguishable Solid Propellants
2005Co-Authors: Wayne N Sawka, Arthur Katzakian, Charles GrixAbstract:Electrically controlled extinguishable Solid Propellants (ESCSP) are capable of multiple ignitions, extinguishments and throttle control by the application of electrical power. Both core and end burning no moving parts ECESP grains/motors to three inches in diameter have now been tested. Ongoing research has led to a newer family of even higher performance ECESP providing up to 10% higher performance, manufacturing ease, and significantly higher electrical conduction. The high conductivity was not found to be desirable for larger motors; however it is ideal for downward scaling to micro and pico- propulsion applications with a web thickness of less than 0.125 inch/ diameter. As a Solid solution propellant, this ECESP is molecularly uniform, having no granular structure. Because of this homogeneity and workable viscosity it can be directly cast into thin layers or vacuum cast into complex geometries. Both coaxial and grain stacks have been demonstrated. Combining individual propellant coaxial grains and/or grain stacks together form three-dimensional arrays yield modular cluster thrusters. Adoption of fabless manufacturing methods and standards from the electronics industry will provide custom, highly reproducible micro-propulsion arrays and clusters at low costs. These stack and cluster thruster designs provide a small footprint saving spacecraft surface area for solar panels and/or experiments. The simplicity of these thrusters will enable their broad use on micro-pico satellites for primary propulsion, ACS and formation flying applications. Larger spacecraft may find uses for ECESP thrusters on extended booms, on-orbit refueling, pneumatic actuators, and gas generators.
Gurdip Singh - One of the best experts on this subject based on the ideXlab platform.
-
catalytic thermal decomposition of ammonium perchlorate and combustion of composite Solid Propellants over green synthesized cuo nanoparticles
Thermochimica Acta, 2015Co-Authors: J K Sharma, Pratibha Srivastava, Gurdip Singh, Shaheer M Akhtar, Sadia AmeenAbstract:Abstract This paper reports on the synthesis of CuO nanoparticles (NPs) by the leaves extract of Calotropis gigantea plant in aqueous medium through green synthesis and their characterizations in terms of morphology, structure, crystallinity and catalytic properties. The synthesized CuO NPs are crystalline in nature having the average sizes in range of 30–40 nm. Green synthesized CuO NPs are utilized as effective catalyst in the thermal decomposition of ammonium perchlorate (AP) and combustion of composite Solid Propellants (CSPs) by measuring the thermo gravimetric analysis–differential scanning calorimetry (TGA–DSC), ignition delay and burning rate. High catalytic activity to AP decomposition and high burning rate for CSPs containing hydroxyl terminates polybutadiene (HTPB) as binder and AP as oxidizer have observed over the surface of green synthesized CuO NPs. Kinetics of thermal decomposition of AP with and without green synthesized CuO NPs was also studied by isoconversional method using isothermal TG data.
-
biosynthesized nio nanoparticles potential catalyst for ammonium perchlorate and composite Solid Propellants
Ceramics International, 2015Co-Authors: J K Sharma, Pratibha Srivastava, Gurdip Singh, Shaheer M Akhtar, Sadia AmeenAbstract:Abstract A facile and eco-friendly biosynthetic method was employed to synthesize NiO nanoparticles (NPs) using leaf extract of plant Calotropis gigantea. The crystalline and structural characterizations confirmed the formation of NiO NPs. A possible mechanism was proposed to explain the formation of NiO NPs through the plant assisted synthesis. The catalytic effect of biosynthesized NiO NPs on thermal decomposition of ammonium perchlorate (AP) and burning rate of composite Solid Propellants (CSPs) has been analyzed. The Kinetic studies of slow and rapid thermal decomposition have also been done.
-
bi metallic nanocomposites of mn with very high catalytic activity for burning rate enhancement of composite Solid Propellants
Thermochimica Acta, 2013Co-Authors: Reena Dubey, Mohit Chawla, Prem Felix Siril, Gurdip SinghAbstract:Abstract Bimetallic nanocomposites of Mn with Co, Ni and Zn were successfully synthesized by polyol method. Particles of the nanocomposites varied in shape from spherical to cubic having an average size of the order of 9–18 nm. The nanocomposites showed very high activity as burning rate catalysts for composite Solid Propellants (CSPs) containing hydroxyl terminates polybutadiene (HTPB) as binder and ammonium perchlorate (AP) as oxidizer. MnCo was the best catalyst among the three nanocomposites as it enhanced the burning rate of the CSP to more than three fold. Catalytic activity of the nanocomposites for thermal decomposition of AP and CSPs was investigated by simultaneous thermogravimetric analysis–differential scanning calorimetry (TGA–DSC) and ignition delay measurements. MnCo was found to be the best catalyst in terms of lowering decomposition temperature of both AP and CSPs. Kinetics of catalyzed thermal decomposition of AP was also studied using isoconversional method from isothermal TGA data.
-
studies of energetic compounds part 29 effect of nto and its salts on the combustion and condensed phase thermolysis of composite Solid Propellants htpb ap
Combustion and Flame, 2003Co-Authors: Gurdip Singh, Prem S FelixAbstract:Abstract The effect of 5-nitro-2,4-dihydro-3H-1,2,4-triazole-3-one (NTO) and two of its transition metal salts, namely Cu(NTO) 2 and Fe(NTO) 3 , during the combustion of composite Solid Propellants (CSPs) of hydroxyl-terminated polybutadiene (HTPB) and ammonium perchlorate (AP) has been studied. The activities of Cu(NTO) 2 and Fe(NTO) 3 have been compared with those of CuO and Fe 2 O 3 at their equivalent metal concentrations. The processing parameters and mechanical properties of the Propellants were also evaluated using Cu(NTO) 2 and Fe(NTO) 3 as additives, and a comparison has been made with that of copper chromite (CC) and active iron oxide (AIO) at pilot plant scale. The safety aspects of using these energetic salts as burning-rate modifiers have been studied in terms of the impact-sensitivity of the modified Propellants. An attempt has been made to evaluate experimentally the condensed phase activity of these additives during the slow thermolysis of Propellants, as well as AP. Rapid thermolysis of the Propellants and AP has been studied using measurements of ignition delay.
