Abstract
A Solid propellant Retro Rocket Motor with a C-D Nozzle is analyzed using Ansys Fluent 17.1 .Steady State analysis of a retro rocket motor has been done for Viscous models like Inviscid and k-ɛ (Realizable) with air and gas as working fluids. The dimensions and the boundary conditions of the nozzle are kept consistent for both the viscous models to compare the exit parameters to theoretical values obtained by using one dimensional equations. The results obtained shows that the exit temperature of the nozzle in Inviscid viscous model is higher than theoretical value by 2.2% and for k-ɛ viscous model it is higher by 5.4% with gas as working fluid.
Highlights
A Retro Rocket Motor essentially consists of a solid or liquid propellant and a C-D nozzle
A retro rocket motor is used in project Gemini, Apollo program, Space shuttle program and landers etc
For Air, pressure obtained in Inviscid model is similar to theoretical value with an error of 0.07% whereas for k-ε model it is 10.9% higher than theoretical value
Summary
A Retro Rocket Motor essentially consists of a solid or liquid propellant and a C-D nozzle. For a spacecraft in orbit around the earth, retro rockets are fired to lower their orbit and re-enter earth’s atmosphere. Without retrograde firing the spacecraft remains in its orbit until it loses altitude naturally in its own time. For efficient functioning of a retro rocket motor the C-D nozzle plays a vital role. It requires an optimum expansion nozzle for effective application. To simulate flow through nozzle various viscous models are available in Ansys software. Inviscid model is close to an ideal flow neglecting viscous effects. In reality no flow is ideal in nature. To simulate a real Turbulent flow we choose k-ε viscous model
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