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Home Aerospace & Aeronautics Technology of numerical modelling of processes in rocket based combined-cycle (RBCC)

Technology of numerical modelling of processes in rocket based combined-cycle (RBCC)


A technique of numerical simulations of the flow through internal space of an engine is used for mathematical models of rocket based combined cycle engines. The equations of the inviscial combustible gas presented as integral ones form the basis for building the finite-difference model. The difference model is built using the finite-volume method. Flows are approximated using the 2-nd order accuracy expressions and the principle of total variation decreasing (TVD principle). Based on used mathematical models with a various configuration of the partitioning mesh, the results of numerical simulations with experimental data.

Innovative Aspect and Main Advantages

Complexity of engineering realization of combined rocket - rocket based combined cycle engines (RBCC) and realization of full-scale tests represents, for today, a technological problem. The gained experience of mathematical simulation of processes in RBCC with use of an orthogonal low level cell has shown, that the major number of factors is necessary a carry the account enough at calculation of the engine. At apparent simplicity of a configuration of the setting of the engine there is a presence of fields where gradients of flow variations are significant that dictates introduction in mathematical model of a capability or to reduce parameters of cells, or them to augment. The designed mathematical model, provides use of the triangular form of a cell. The obtained computational outcomes and their comparative analysis with experimental data allows to state identity of character of change of parameters. It is expedient to apply to maintenance of maximum efficiency of a hybrid rocket engine except for an adjustable supersonic diffuser and nozzle adjustable mixing chamber and afterburnings. The received computing results and their comparative analysis with experimental data allow to formulate identity of a distinctive attribute of change of parameters. Novelty of development are applications of Navie-Stocks equations viscous, a compressible gas, in view of chemical reactions for designing combined rocket, and supersonic straight-flow airbreathing engines.

Areas of Application

The developed mathematical model and the software package intended for use at designing combined rocket and supersonic straight-flow air-breathing engines.

Stage of Development

The carried out testing on the basis of base data, and also results of experimental researches of supersonic ejectors of a TsAGI. It is received coincidences of results of calculations experimental data.

Contact Details

Contact persons: M.A. Katrenko, V.L. Bucharsky, A.A. Shinkarenko
Name of organization: Physical Technical Institute of Dniepropetrovsk National University
Address: Dniepropetrovsk, Ukraine
E-mail: This e-mail address is being protected from spambots. You need JavaScript enabled to view it

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