development of advanced computer science for solid-rocket-motor internal ballistics: acssib
- Paper number
IAC-10.C4.2.6
- Author
Prof. Toru Shimada, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Dr. Koki Kitagawa, Japan Aerospace Exploration Agency (JAXA)/ISAS, Japan
- Coauthor
Dr. Hiroshi Hasegawa, NOF CORPORATION, Japan
- Coauthor
Ms. Mihoko Fukunaga, IHI Aerospace Co, Ltd., Japan
- Coauthor
Mr. Hiroya Asakawa, IHI Aerospace Co, Ltd., Japan
- Year
2010
- Abstract
This paper describes the development of a numerical simulation system, "Advanced Computer Science on solid-rocket-motor Internal Ballistics (ACSSIB)" through 2008 to 2010. The objectives of this technology development consist of development of composite-propellant slurry filling-flow simulation, development of local burning-rate correlation with the slurry flow field characteristics, and development of the internal ballistics, i.e., combustion pressure time history, prediction. The first goal, the slurry-filling simulation, is done by combining the incompressible Navier-Stokes equations with the volume-of-fraction methodology. Both commercial code utilization and in-house programs development have been done. The simulation generates the local flow field characteristics, which are the input to the internal ballistics analysis through the correlation database of local burning rate. The local burning rate database, as the second goal of ACSSIB, is built by synthesizing the information of microscopic structure of composite propellant, the strand burner measurement of local burning rate, and small motor static firing tests. The microscopic structure is observed and quantified through a micro-focus X-ray computer tomography, which is then image-processed to extract information of oxidizer particles such as the location, the size, and the orientation. The firing tests and strand-burner measurements are used to get information of burning-rate fluctuation as a function of the location. The location is the bridge to the local flow field characteristics, such as the velocity and the shear-stress, etc., obtained from the propellant slurry filling simulation. The microscopic information and the macroscopic information, i.e., burning rate, are synthesized into the correlation database. Moreover, a random-packing code is developed to serve for a micro-scale modeling of a composite propellant, which will be used as models for microscopic combustion analyses. Finally, the third goal of ACSSIB is the internal ballistics analysis and it is a combustion surface burn-back simulation, in which local burning-rate distribution is evaluated according to the slurry-filling flow field. Moreover, erosive burning model and throat ablation models are implemented. The overall validation of ACSSIB will be done through comparisons with static-firing test results.
- Abstract document
- Manuscript document
IAC-10.C4.2.6.pdf (🔒 authorized access only).
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