A Development of Numerical Solution for Non-Linear Inventor Rocket Equation of Motion
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Abstract
When an inventor rocket moves away from the launch point, the inventor rocket passes through the medium, which is air, to the target area along the designed line of motion. But because there are factors. As a result, the movement of the inventor rocket trajectory deviates from the normal direction it was designed for and the nature of the equation is nonlinear. Therefore, it is essential to study, design and solve this nonlinear motion problem in order to reduce possible faults and further increase the efficiency of emission accuracy. Solving the nonlinear motion equations can be done in a variety of ways, with this paper presenting the method of finding the deuteronomy of the equations with the methods of Runge-Kutta 4th, using the inventor rocket trajectory equation based on the Modified Point Mass Trajectory Model, which experimented with transforming the initial state into 21 patterns. The simulation results showed inventor rocket trajectories with different lift angles and initial conditions. Whereas with a greater lift angle and starting conditions, the distance perpendicular to the flight plane is significantly higher. In addition to that, it will result in the position of the inventor rocket at any given time. There are markedly different values as flight time increases.
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