A detailed study of a set combined acceleration methods is presented with the objective accelerating solid rocket motor grain burnback simulation based on level method. Relevant were improved by making use unique characteristics grains, and graphical processing unit (GPU) parallelization utilized to perform computationally intensive operations. The flow traced expansion burning surfaces, then Boolean operations applied resulting surfaces extract various geometric metrics. initial signed...

The thermo-structural response of solid rocket motor nozzles is widely investigated in the design modern rockets, and many factors related to material properties have been considered. However, little work has done evaluate effects structure gaps on generation flame leaks. In this paper, a numerical simulation was performed by finite element method study typical nozzle with consideration gap. Initial boundary conditions for were defined quasi-1D model, then coupled simulations different gap...

Abstract In this paper, a new measuring method of ablation rate was proposed based on X-ray three-dimensional (3D) reconstruction. The 4-direction carbon/carbon composite nozzles investigated in the combustion environment solid rocket motor, and macroscopic linear recession were studied through 3D reconstruction method. results showed that maximum relative error 0.0576%, which met minimum accuracy analysis; along nozzle axial direction, from convergence segment, throat to expansion gradually...

This paper describes a zero-dimensional model for evaluating the mass flow rate history of solid rocket motor igniter. Based on results an igniter-firing experiment, in which igniter is only source combustion gas and no propellant ignited, proposed can be used to compute Different species temperature-dependent properties, such as specific heat each species, are considered. The coupling between field variables chamber transfer at gas-solid interface computed segment way. Calculations...

In order to design solid rocket grain configuration intuitively and accurately, this paper introduces a 3D feature method based on the variational technology which is popular in field of Mechanical Product Computer Aided Design. First all, with help geometry constraint solver, fuzzy concept configurations can be converted geometric sketch. Then, through definition entities rules, as well identification algorithm Color-Marked Burning Surface process Boolean Operation, designers implement...

With a purpose to evolve the surfaces of complex geometries in their normal direction at arbitrarily defined velocities, we have developed robust level-set approach which runs on three-dimensional unstructured meshes. The is built basis an innovative spatial discretization and corresponding gradient-estimating approach. numerical consistency estimating method mathematically proven. A correction technology utilized improve accuracy near sharp geometric features. Validation tests show that...

The Coastal underwater evidence search system with surface-underwater collaboration is designed to revolutionize the for artificial objects in coastal environments, overcoming limitations associated traditional methods such as divers and tethered remotely operated vehicles. Our innovative multi-robot collaborative consists of three parts, an autonomous surface vehicle a mission control center, towed wide-area search, biomimetic robot inspired by marine organisms detailed inspections...

With the purpose of obtaining optimal designs heat insulating layers in solid rocket motors, we have proposed a numerical approach to compute ideal thickness layer. The method is compatible with motors that any shape and manner erosion. nonuniform dynamic burning rate taken into consideration achieve higher accuracy. A high-performance code developed uses triangular geometry as an input allow exchanging data from CAD platform. An improved geometric intersection algorithm generate required...

Currently, some necessary material performance parameters and accurate numerical simulation boundary can hardly be obtained via analysis of the ablation laws solid rocket motor throat. Based on throat diameter dynamic identification micron-CT 3D scanning reconstruction technique, nozzle diameters three types SRM during operating phase were dynamically identified, before after test was reconstructed static change analyzed. The results demonstrate that technique in this study exhibits higher...

Erosive burning refers to the augmentation of propellant rate appears when velocity combustion gas flowing parallel surface is relatively high. can influence total and performance solid rocket motors dramatically. There have been many different models evaluate erosive for now. Yet, due complication processes involving in motor combustion, unknown constants often exist these models. To use models, trial-and-error procedure must be implemented determine firstly. This makes difficult estimate...

In order to solve the problem of difficulty in judging abnormal test data solid ducted rocket, this paper introduces a mining method based on artificial neural network detect and recovery parameters. The has been verified with certain type motor. research shows that is an efficient, reliable novel approach for analyzing processing rocket test.

Multi-interface is a typical feature of solid rocket motor nozzles, and the interface evolution law an important aspect to analyze thermo-structural response nozzles. In this paper, based on friction coefficient test at different temperatures, coupled analysis model nozzle considering variation under operating conditions was established. Firstly, tested temperatures. Then, by adopting structure gap, variable coefficient, thermal contact resistance, heat production, strongly non-linear...

Abstract The new measured viscoelastic Poisson's ratio (VPR) is introduced to investigate the effect of its variation on structure integrity analysis solid rocket motor. A developed relaxation constitutive model considering VPR utilized implement in finite element code MSC.Marc. Cooling and ignition pressure loading case are designed analyze effects along inner surface propellant grains. Results show that little change including equilibrium (ePR) reference temperature will affect output...