Cold Gas Simulations of the Influence of Inhibitor Shape in Combustor Combustion

Analysis of Injecting Wall Inclination on Segmented Solid Rocket Motor Instability

“…In other words, the presence of an unsteady mechanism in the main flow actually initiates the latter. Comparisons between results from small-scale solid propellant rocket motor and cold gas setups were recently published and provide solid confirmation of these findings [21]. Experiments carried out on the combustor included nonablative inhibitors on the final segment forward face; four inhibitor shapes were tested, each corresponding to specific pressure oscillation behavior.…”

Solid propulsion for space applications: An updated roadmap

“…• Multi-disperse, multi-phase flow simulations that include aluminum/alumina droplets [31][32][33], aluminum agglomeration [31,[34][35][36], and the slag mass accumulation [37]. • Simulation of vortex-shedding [38] and thrust oscillation [39] with the view point of the adaptive control [40], of the effect of burning aluminum droplets [41], of the nozzle cavity effect [42], of the wall and the inhibitor effect [43,44], and of the large solid rocket boosters [45][46][47][48][49]. • Simulation of the internal flow with respect to the nozzle ablation [50][51][52] and to the roll-torque generation [53].…”

Advanced Computer Science on Internal Ballistics of Solid Rocket Motors

“…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.…”