FirePhysChem最新文献

{"title":"Editorial from the Guest Editors","authors":"","doi":"10.1016/j.fpc.2024.12.001","DOIUrl":"10.1016/j.fpc.2024.12.001","url":null,"abstract":"","PeriodicalId":100531,"journal":{"name":"FirePhysChem","volume":"5 2","pages":"Pages 101-102"},"PeriodicalIF":0.0,"publicationDate":"2024-12-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143511070","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Investigation on ignition overpressure wave characteristics and its ambience in launch pad","authors":"V Venkata Ramakrishna,&nbsp;G Venkatesh,&nbsp;S Sankaran","doi":"10.1016/j.fpc.2024.08.005","DOIUrl":"10.1016/j.fpc.2024.08.005","url":null,"abstract":"<div><div>Large solid rocket motors are widely used as booster stages as well as in core stages of heavy lift launch vehicles due to its simple operation and high thrust delivery capability compared to other propulsion types. The ignition transient of the solid rocket motors is marked by a very high chamber pressure rise rate compared to the liquid or other type of engines. This distinction causes generation of ignition overpressure wave during the start-up phase of solid rocket motor. Ignition overpressure (IOP) wave has a distinct characteristic of very high positive pressure, sharp rise and a relaxation (or negative pressure) waveform. Typically the overpressure relaxation wave has a very low frequency of &lt; 25 Hz for the large solid rocket motors and is very detrimental for the structures with large surface area. Unlike acoustic pressure fluctuations, overpressure waves are transient and poses high risk to the safety of launch vehicle and its sub-assemblies as it propagates upward towards the base of launch vehicle. This phenomenon happens when the launch vehicle is still sitting on the launch mount (or pedestal) with its nozzle inside the launch mount. Hence, the geometry of the launch mount (with blind and open zones) may affect the overpressure load distribution on the nozzle or its base protective structures. Post lift-off analysis of the developmental launch of a heavy lift launch vehicle revealed the damaging effects of overpressure wave especially on the base portion of the launch vehicle. In order to study this phenomenon, measurements are taken during the subsequent launches by measuring the unsteady pressure distribution inside the launch mount. It is observed that the intensity of IOP wave has a highly asymmetric distribution inside the launch mount, with the amplitude as high as two times at certain regions. Similar measurements were also taken with a thermo-physically scaled down model of actual launch vehicle along with geometrically scaled down launch pad elements. As the chamber pressure rise rate in the scaled models is much higher compared to that of full scale motors, the absolute amplitude of overpressure wave cannot be compared. Nevertheless similar asymmetric distribution of overpressure was also observed in the scaled model experiments. The experimental results of sub-scale and full scale overpressure measurements like amplitude and frequency of trailing wave are compared with the Broadwell-Tsu empirical model predictions and the results are found to be closely matching, which helps in the prediction of IOP intensity for the future developmental launch vehicles from scaled down models.</div></div>","PeriodicalId":100531,"journal":{"name":"FirePhysChem","volume":"5 2","pages":"Pages 138-143"},"PeriodicalIF":0.0,"publicationDate":"2024-10-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143510975","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Ballistic performance of alumina/carbon fiber/aramid composite against impact of different projectile shapes","authors":"S.S. Raut,&nbsp;M.D. Umbharatwala,&nbsp;Manmohan Dass Goel","doi":"10.1016/j.fpc.2024.09.005","DOIUrl":"10.1016/j.fpc.2024.09.005","url":null,"abstract":"<div><div>This study explores the ballistic performance of an alumina/carbon fibre/Kevlar^Ⓡ aramid composite panel against impacts from various projectile shapes, including ogive, conical, cylindrical, hemispherical, and 5.56 mm × 45 mm NATO rounds. The aim is to analyse the influence of projectile nose shape on penetration resistance and energy absorption, critical for defence and aerospace applications. Numerical simulations carried out in LS-DYNA^Ⓡ, validated by experimental data, reveal that the ceramic layer effectively initiates projectile deceleration, while the fabric layers absorb the majority of the kinetic energy. Hemispherical projectiles exhibit minimal plastic deformation, highlighting the composite's optimal performance against this shape. In contrast, ogive projectiles demonstrate greater penetrative potential, challenging the composite's multi-layered defence. The study finds that approximately 90% of the kinetic energy is absorbed by the fabric backing, with a small portion absorbed through projectile deformation and ceramic cracking. These results underscore the importance of considering projectile deformation in simulations and suggest that the composite design is well-suited for enhancing protection against high-velocity impacts in defence and aerospace sectors.</div></div>","PeriodicalId":100531,"journal":{"name":"FirePhysChem","volume":"5 2","pages":"Pages 144-154"},"PeriodicalIF":0.0,"publicationDate":"2024-10-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143510974","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Maltose-based pyrotechnic aerosol forming composites for fire extinguishing application","authors":"Braham Prakash ,&nbsp;Amit Saxena ,&nbsp;Yogesh Kumar Tyagi ,&nbsp;Kavita Devi ,&nbsp;Rajesh Kumar Tanwar ,&nbsp;Arvind Kumar","doi":"10.1016/j.fpc.2024.09.003","DOIUrl":"10.1016/j.fpc.2024.09.003","url":null,"abstract":"<div><div>This study explores the development of environmentally friendly aerosol forming composites (AFCs) for use in condensed aerosol-based fire extinguishing systems (CAFES). Traditional fire suppressants often pose environmental hazards; thus, a novel approach using maltose as a combustible binder combined with potassium nitrate as an oxidant was examined. To modify the burn rate and improve combustion efficiency, calcium carbonate (CaCO₃) and iron (III) oxide (Fe₂O₃) were incorporated as burn rate modifiers. AFCs demonstrated high combustion efficiencies (≥ 95%) and variable burn rates (3.3–13.8 mm/s). The fire extinguishing concentration of AFC was found ≤ 53 g/m³. Comprehensive analyses including thermogravimetric analysis (TGA), differential scanning calorimetry (DSC), X-ray diffraction, and Fourier transform infrared spectroscopy (FTIR) confirmed the formation of potassium carbonate, potassium bicarbonate, and potassium hydroxide in aerosols. Aerosol distribution within the fire test chamber was homogeneous, as evidenced by pH measurements at various locations. These findings suggest that maltose-based AFCs are promising candidates for the development of eco-friendly fire extinguishing systems.</div></div>","PeriodicalId":100531,"journal":{"name":"FirePhysChem","volume":"5 2","pages":"Pages 190-200"},"PeriodicalIF":0.0,"publicationDate":"2024-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143511069","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Analysis of the combined impulse of fragments and the shock wave composite load","authors":"Chuanyun Tao,&nbsp;Wenjin Yao,&nbsp;Yu Zheng,&nbsp;Weihang Li,&nbsp;Ning Jiang,&nbsp;Dou Hong","doi":"10.1016/j.fpc.2024.09.001","DOIUrl":"10.1016/j.fpc.2024.09.001","url":null,"abstract":"<div><div>This study conducted experiments and numerical simulations to investigate the Mechanical Properties of Fragments and Shock Waves generated blast. A combined impulse calculation model was established through the study of post-explosion motion patterns and impact load characteristics of fragments and shock waves acting on targets.The rationality of a combined impulse calculation model ed using a sled test.Numerical model of square plates subjected to blast loading was established by LS-DYNA to analyze the influence of composite loads with different cased charges on a square plate at different standoff distances.The variation laws of the combined impulse under different standoff distances and different charge structures were obtained.Results indicated that the combined impulse exhibited an exponential decrease with standoff distance in the near-field region of the explosion.The impact acting on the target was characterized by perforation and deflection.The impulse acting on deflection and penetration due to the inertial effect of the target, energy absorption effect, was approximately 15.6 % lower than the combined impulse at the beginning of the blast,the attenuation increases with the increase of distance.The length-to-diameter ratio of cased charges, the more the charge mass,the greater the combined impulse of the resulting multiple loads.With the same length-to-diameter ratio, increase the charge mass,the use of small-sized fragments or high-energy charges had an enhanced effect on the combined impulse.</div></div>","PeriodicalId":100531,"journal":{"name":"FirePhysChem","volume":"5 2","pages":"Pages 178-189"},"PeriodicalIF":0.0,"publicationDate":"2024-09-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143511068","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Effect on the performance of a hybrid rocket using AP in the PVC and HTPB-based hybrid fuel","authors":"Mehdi Abbas,&nbsp;Rajiv Kumar,&nbsp;Shelly Biswas","doi":"10.1016/j.fpc.2024.08.004","DOIUrl":"10.1016/j.fpc.2024.08.004","url":null,"abstract":"<div><div>Hybrid rocket is a type of chemical rocket propulsion system where the fuel and the oxidizer are stored separated and in different state of aggregation. Typically, the fuel is in the solid state and the oxidizer is either in the liquid or gaseous state. It offers various advantages over other type of chemical rockets such as throattability, controllability and reduced complexity. It also has some drawbacks such as low regression rate, poor combustion efficiency, higher sliver losses, etc. Various methods have been adopted to overcome these drawbacks and improve the performance of hybrid rocket. The present study focus on the improvement of regression rate with the addition of oxidizer particles in fuel content. Ammonium Perchlorate is used as an additive in Hydroxyl Terminated Polybutadiene (HTPB) and Poly Vinyl Chloride (PVC) based fuel grain. From the experimentations, it was observed that the thrust, pressure and regression rate of the HTPB fuel grain with additive have higher improvement than with the PVC based fuel grain. The sliver losses are also reduced due to uniform burning after addition of oxidizer in fuel grain. The overall study strongly suggests that addition of oxidizer in limited quantity can be used to overcome the drawbacks of hybrid propellant rocket.</div></div>","PeriodicalId":100531,"journal":{"name":"FirePhysChem","volume":"5 2","pages":"Pages 129-137"},"PeriodicalIF":0.0,"publicationDate":"2024-08-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143510973","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Low-sensitivity energetic material based on 1,2,4-oxadiazole","authors":"Gan Jin,&nbsp;Caijin Lei,&nbsp;Jie Tang,&nbsp;Guangbin Cheng,&nbsp;Hongwei Yang","doi":"10.1016/j.fpc.2024.08.002","DOIUrl":"10.1016/j.fpc.2024.08.002","url":null,"abstract":"<div><div>In this work, a new series of monocyclic compounds based on 1,2,4-oxadiazol-5(4H)-one was synthesized. The molecular structure, thermal stability and sensitivity to external stimuli for these compounds were characterized by X-ray diffraction analysis, NMR (¹H and ¹³C) spectroscopy, IR spectroscopy, differential scanning calorimetry (DSC) and the standard BAM method. Compound 3-((2,2,2-trinitroethyl) amino)-1,2,4-oxadiazol (<strong>3</strong>) with trinitromethyl exhibits a higher decomposition temperature (<em>T</em>_d = 143 °C) than that of 3-(dinitromethyl)-1,2,4-oxadiazol-5-one (<strong>4</strong>) (<em>T</em>_d = 76 °C) reported in the literature. In addition, compound <strong>3</strong> exhibits lower impact sensitivities (<em>IS</em>) (<em>IS</em> = 10 J) than <strong>4</strong>, N³-(2,2,2-Trinitroethyl)-1,2,4-oxadiazole-3,5-diamine (<strong>5</strong>) and <strong>RDX</strong> (<strong>4</strong>: 6 J; <strong>5</strong>: 6 J; <strong>RDX</strong>: 7.4 J). Charge distribution and Hirshfeld surface were calculated to make further research on the intermolecular interaction of <strong>3</strong> with trinitromethyl. The difference in stability of these compounds is mainly due to the existence of intermolecular hydrogen bonds. These results indicate that compound <strong>3</strong> has promising application prospects as the energetic material.</div></div>","PeriodicalId":100531,"journal":{"name":"FirePhysChem","volume":"5 2","pages":"Pages 171-177"},"PeriodicalIF":0.0,"publicationDate":"2024-08-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143511822","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Development of hydrogen peroxide based micro thruster utilizing biomass-based catalyst bed","authors":"Nitesh Kumar,&nbsp;Sankalp Jain,&nbsp;Shelly Biswas,&nbsp;Rajiv Kumar","doi":"10.1016/j.fpc.2024.08.003","DOIUrl":"10.1016/j.fpc.2024.08.003","url":null,"abstract":"<div><div>Micro thrusters, also referred to as micro-newton thrusters, are thrusters having a wide range of force capabilities in the micro-newton range. Micro thrusters are used in CubeSats, tiny robots and drones, micro- and nanosatellites, spacecraft attitude control, etc. The aim of the present study is to develop a monopropellant thruster (MPT) for 90 % concentrated hydrogen peroxide (H₂O₂). A rotatory evaporator was used to obtain a 90 % H₂O₂ form the available concentration of 50 % H₂O₂. The next stage involved the designing of the monopropellant thruster utilizing the NASA CEA rocket performance algorithm and the derived mathematical model. The test facility was constructed which includes a thruster, a feed line system, a static test firing platform, a data collecting system and the measuring sensors. To measure the thrust of the thruster, a pendulum thrust mechanism was constructed and fabricated into an experimental test stand. Lastly, the MPT chamber, which uses stainless steel mesh, was prepared and packed with the biomass-based catalyst. The 14 bar injection pressure conditions were used for the fire tests. With a mass flow rate of 5 g/s and a decomposition pressure of 10 bar, the theoretical specific impulse (<em>I</em>_sp) was calculated to be 1993.2 Ns/kg at an O/F ratio of 0.002. The test firing with 90 % concentrated hydrogen peroxide gave an experimental specific impulse of 794.5 Ns/kg, which gives efficiency of 39.9 %.</div></div>","PeriodicalId":100531,"journal":{"name":"FirePhysChem","volume":"5 2","pages":"Pages 121-128"},"PeriodicalIF":0.0,"publicationDate":"2024-08-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143511073","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Performance estimation of hybrid rocket by varying the flow rate at multi-location swirl injector","authors":"Arpit Dubey,&nbsp;Rajiv Kumar,&nbsp;Shelly Biswas","doi":"10.1016/j.fpc.2024.08.001","DOIUrl":"10.1016/j.fpc.2024.08.001","url":null,"abstract":"<div><div>This study attempts to evaluate the effect of varying the oxidizer mass flow rate through the secondary mid-location swirl injector on the performance of a hybrid rocket motor (HRM). The hybrid fuel used in this study was paraffin wax along with commercially available gaseous oxygen as oxidizer. Utilizing a swirl injector is crucial as it adds a tangential velocity component alongside the axial one. Introducing a secondary mid-location swirl injector heightens this effect, leading to noticeably improved performance in HRM. An increase in the oxidizer mass flow rate through the secondary mid-location swirl injector is associated with a reduction in the regression rate. This is attributed to the blowing away of wax melt layer and flame from the solid hybrid fuel grain. Furthermore, an overall increase in the oxidizer mass flow rate corresponds to a rise in combustion efficiency, closely linked to pressure development, which, in turn, correlates with the mass flowing out of the rocket nozzle. Peak thrust was observed and also maximum fuel was burnt in case where highest gaseous oxygen (GOX) rate of 50 g/s was utilized. The multi-location swirl injector assembly maintains swirling flow towards the nozzle end, presenting an optimal scenario for enhancing HRM performance.</div></div>","PeriodicalId":100531,"journal":{"name":"FirePhysChem","volume":"5 2","pages":"Pages 111-120"},"PeriodicalIF":0.0,"publicationDate":"2024-08-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143511072","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"New X-ray based characterization technique for aluminized explosives and effect of aluminum proportion on velocity of detonation","authors":"Satveer Kumar ,&nbsp;Manish Kumar ,&nbsp;Arjun Singh ,&nbsp;Pramod Kumar Soni ,&nbsp;Surinder Kumar ,&nbsp;Devinder Mehta ,&nbsp;Niladri Mukherjee","doi":"10.1016/j.fpc.2024.07.004","DOIUrl":"10.1016/j.fpc.2024.07.004","url":null,"abstract":"<div><div>Explosive samples of aluminized compositions based on RDX/HMX-TNT have been investigated using digital radiography comprising a flat panel detector and an ultra-fine focus X-ray tube. Melt-cast aluminized compositions have been designed and constructed into cylindrical charges with a diameter ∼50 mm and height ∼150 mm. These charges have been evaluated for velocity of detonation using ionization pin method. Projection radiography has been used to gain information about the microstructure of solidified explosive compositions using optimized system parameters. The resolution of the image has been investigated using a duplex wire type image quality indicator having thirteen wire pairs. Within the explosive samples, the patches of aluminum have been seen evenly dispersed. The size of these patches of aluminium grows with increase in aluminium proportion at the expense of HMX. The maximum VOD value has been observed for the composition with highest HMX content. Value of VOD is found to decrease by ∼4 % if HMX is replaced by RDX, keeping TNT proportion at 30 %. VOD values are found to decrease with increase in proportion of aluminium at the cost of HMX.</div></div>","PeriodicalId":100531,"journal":{"name":"FirePhysChem","volume":"5 2","pages":"Pages 103-110"},"PeriodicalIF":0.0,"publicationDate":"2024-07-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143511071","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}