Numerical Simulation Of Flow Field In The Aluminum-ice Cryogenic Solid Propellant Motor

Aluminum-ice cryogenic solid propellant motor is a kind of high energy density of solid rocket motor, it uses the aluminum powder as fuel and water as oxidant, Aluminum react with water to release a large amount of heat, gas expansion in laval nozzle, converts heat energy to kinetic energy to produce thrust. Aluminum-ice propellant with high reactivity, highly active,superplasticity, low melting point and high energy density characteristics, it is widely used in the field of underwater propulsion and space.At first, this paper uses the computational fluid dynamics software to simulate the ignition process of aluminum-ice cryogenic solid propellant motor, In order to realize the gas injection, use the secondary development technology compile mass source term,momentum source term and energy source term of gas. Analyzes the flow field in ignition delay stage, flame propagation stage and gas filling stage of ignition process. Results indicate that compression wave shock in the combustion chamber before nozzle cover open, increase mass flow rate of ignition powder effectively promote combustion chamber pressure build,shorten the ignition time. Ignition dose increased from 8g to lOg and 10g to 12g, blocking cover open time shorten 10.1% and 8.5%.Secondly, this paper uses stochastic trajectory model to simulate the gas-solid two phase flow field of aluminum-ice cryogenic solid propellant motor, Results show that the vortex in flow field caused by sudden enlargement section in rocket motor. the velocity of flow is bigger in initial stage, small size particles have good fluidity, warming faster and easy to burn, nanoparticles react rapidly after inject into the combustion chamber, which is the main factor of maintain stabilize burning surface.Finally, This paper uses the secondary development technology to simulate the aluminum-ice cryogenic solid propellant motor which is assembled with two kind of grain.Realize the real working process of pressure driven boundary move. Results show that in the middle of combustion chamber internal combustion motor burn more violently,reactants almost no residues in outlet, the cigarette combustion motor shows more uniform temperature field and higher combustion performance.Results show that the method of numerical simulation that research aluminum-ice cryogenic solid propellant motor ignition flow field is reasonable. This paper provides a theoretical basis for research of aluminum-ice cryogenic solid propellant motor ignition process and the two phase flow field.