Aircraft Takeoff Simulation with MATLAB

Abstract

There are three primary ways for an aircraft to change its orientation relative to the passing air. Pitch (movement of the nose up or down, rotation around the transversal axis), Roll (rotation around the longitudinal axis, that is, the axis which runs along the length of the aircraft) and Yaw (movement of the nose to left or right, rotation about the vertical axis). In straight climbing flight, lift is less than weight. At first, this seems incorrect because if an aircraft is climbing it seems lift must exceed weight. When an aircraft is climbing at constant speed it is its thrust that enables it to climb and gain extra potential energy. Lift acts perpendicular to the vector representing the velocity of the aircraft relative to the atmosphere, so lift is unable to alter the aircraft's potential energy or kinetic energy. This can be seen by considering an aerobatic aircraft in straight vertical flight-one that is climbing straight upwards (or descending straight downwards). Vertical flight requires no lift! When flying straight upwards the aircraft can reach zero airspeed before falling earthwards-the wing is generating no lift and so does not stall. In straight, climbing flight at constant airspeed, thrust exceeds drag. In straight descending flight, lift is less than weight. In addition, if the aircraft is not accelerating, thrust is less than drag. In turning flight, lift exceeds weight and produces a load factor greater than one, determined by the aircraft's angle of bank Take off is the stage from the application of take off power until an altitude of 35 feet above the runway elevation. This includes the substages: takeoff and rejected takeoff. The initial climb is the stage from the end of the takeoff to the first prescribed power reduction or when the aircraft is 1,000 feet above the runway elevation, whichever is first.