Published Paper Details:

The high launch cost of rockets has led to a great interest in the development of reusable rockets. These missions were achieved with the use of liquid engine thrust vectoring. This paper discusses design and flight simulation of solid propellant rocket equipped with thrust vector control. Solid rocket motor has been designed with a goal to reach 10 km altitude. It is aimed that the solid rocket motor is to be recovered so that it can be reused for subsequent launches. The design and simulation are carried out assuming that the motion takes place in vertical direction, considering flat earth approximations. This paper deals with selection of solid propellant, grain design, calculation of performance parameters, design and optimization of the rocket motor and nozzle for desired performance, computational analysis and flight simulation with structural constraint. The flight simulation has been carried out using MATLAB� and Simulink� to prove the effectiveness of the concept. For simplicity, rocket is assumed as a point mass in flight simulation. The simulation results testify that the ascent motor is meeting the design goal of 10 km altitude and descent motor works perfectly to bring the rocket back to ground with closer to zero velocity.