Casting Process Impact on Small-Scale Solid Rocket Motor Ballistic Performance

Advanced Computer Science on Internal Ballistics of Solid Rocket Motors

“…Here, the final peak after 3.5s is caused by unsteady effect due to the thinness of the web. The burning rate fluctuation through web thickness has dependence on burning direction 4,46,[48][49][50][51] . The burning rate along longitudinal axis as shown in Fig.5 is measured for each processed grain.…”

“…propellant slurry flow. Some studies have measured the burning rate fluctuation during combustion directly, and the evidence of burning rate fluctuation has been shown 4,49,51) . In the simulation system developing in ACSSIB, the local burning rate will be determined by tracing the casting process.…”

“…In the simulation system developing in ACSSIB, the local burning rate will be determined by tracing the casting process. Although it is known that the local burning rate is determined by the function of angles between layer of propellant sag (see section 5) and burning direction 4) , it is necessary to obtain the quantitative function and parameters by experiments for individual cases. In addition, physical mechanism of the phenomena has not been fully understood.…”

“…The casting process impact on local burning rate is known as a term "midweb anomaly" or "hump effect" 4,[48][49][50][51] . Midweb anomaly is a phenomenon that the local burning rate, which is normally depends on pressure, initial temperature and fluid dynamics of internal flow, depends on propellant casting process i.e.…”

“…Researches of numerical simulation of SRM have covered a variety of aspects, such as, SRM internal ballistics evaluation by burn-back simulation 1,2) , also with casting process effect 3,4) modeling and simulation of the random packing 5) and of the combustion of heterogeneous solid propellants [6][7][8][9][10] with aluminum agglomeration modeling [11][12][13][14] multi-dispersed multi-phase flow simulation including aluminum/alumina droplets 11,15,16) , model of aluminum agglomeration 17,18) , and simulation of slag mass accumulation of condensed phase 19) simulation of vortex-shedding 20) and thrust oscillation 21) with view points of adaptive control 22) of effect of burning aluminum droplets 23) , of nozzle cavity effect 24) , of wall and inhibitor effect 25,26) , and of large solid rocket boosters [27][28][29][30][31] simulation of internal flow with respect to nozzle ablation [32][33][34] and to roll-torque generation 35) simulation of combustion stability 36) assessment of acoustic, vibration, and shock environments of SRM firings 37) , assessments of attenuation of radio frequency signal due to the SRM plume 38,39) , and so on. In order to improve the reliability of SRMs, it is important to establish the accuracy of numerical simulation with progress of model refinement of each physical phenomenon checking with real firing results.…”