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This paper presents a simulation of the movement of an aircraft that has an engine malfunction. The nonlinear equations of motion are formulated taking into account the yawing moment which is generated and occurs due to the asymmetry of the thrust line. For this simulation the equations are solved directly to find the trajectory of the aircraft and the variations of angles, angular rates, and velocities with time. An initial conditions is required for the simulation as (𝑉,𝛽,𝛿𝑟,𝛿𝑎,𝑇,𝑝,𝑞,𝑟,𝜙,𝜓,𝛾) and a trim condition is calculated to get the angle of attack. The derivatives of angular, linear velocities, angles, moments and position derivatives are calculated. The derivatives calculated are solved using ordinary differential equations solution 4th order Rung Kutta method to get the yawing, pitching, rolling moments, velocity, angle of attack, side slip angle and trajectory of the aircraft according to control surfaces deflections and thrust as inputs.

This paper presents a simulation of the movement of an aircraft that has an engine malfunction. The nonlinear equations of motion are formulated taking into account the yawing moment which is generated and occurs due to the asymmetry of the thrust line. For this simulation the equations are solved directly to find the trajectory of the aircraft and the variations of angles, angular rates, and velocities with time. An initial conditions is required for the simulation as (V, β, δr, δa, T, p, q, r, φ, ψ, γ) and a trim condition is calculated to get the angle of attack. The derivatives of angular, linear velocities, angles, moments and position derivatives are calculated. The derivatives calculated are solved using ordinary differential equations solution 4th order Rung Kutta method to get the yawing, pitching, rolling moments, velocity, angle of attack, side slip angle and trajectory of the aircraft according to control surfaces deflections and thrust as inputs. [ABSTRACT FROM AUTHOR]