## 5 Maneuverability of the Rotor and Levitation in a Gravitational Field  
Here, a distinction is made between two states: horizontal flight and vertical flight. The orientation of the rotor's axis of rotation at takeoff determines the flight state. Due to the principle of propulsion, the axis of rotation must always be perpendicular to the future plane of movement in which the translational displacement of the rotor will occur. Within this plane of movement, the flight direction is determined by the position of the rotor sector in which the unbalance is activated, specifically by the bisector of this rotor sector. This position can be adjusted through the electrical control of the unbalance and can, therefore, be easily changed. The new position of the bisector can be set within a single rotation of the rotor, if necessary, potentially in milliseconds. This allows for rapid changes in the direction of the UAV within the x, y plane of movement (e.g., horizontal curved flight with a constant vertical axis direction). By reversing thrust, the aircraft can also decelerate (potentially with a subsequent change in flight direction) by electrically rotating the active rotor sector by 180 degrees relative to the previous direction of propulsion. In principle, no aerodynamic actuators are required to initiate these yaw and braking maneuvers. During changes in attitude of a rotor-driven aircraft, gyroscopic forces can occur, which couple the movements around the aircraft's axes, and their influence on the flight motion must be taken into account. Here is an example: After takeoff and before landing, it is necessary to tilt the rotor's axis of rotation by 90\({}^{\circ}\) to transit from horizontal flight to vertical flight (or vice versa). This requires a rotation around the pitch axis, which is oriented perpendicular to the direction of propulsion and the vertical axis of rotation. In this transition phase, gyroscopic forces occur because the law of conservation of angular momentum opposes the change in direction. This also applies to rolling. Only in yawing (as described above) does the angular momentum remain directionally stable, and disruptive gyroscopic forces cannot occur. There are generally two methods for maneuvering under the influence of gyroscopic forces:  
1. Utilization of gyroscopic forces;
2. Compensation of gyroscopic forces. The utilization of gyroscopic forces refers to the exploitation of the UAV's inertia moments to perform maneuvers. By deliberately changing the rotational speeds of the rotors, the UAV can be rotated around its longitudinal, lateral, and vertical axes. This allows for rolling, pitching, and yawing of the UAV. The compensation of gyroscopic forces refers to the mitigation of the undesirable effects of gyroscopic forces to ensure a stable flight attitude. This can be achieved through the use of sensors and control systems that adjust the rotational speeds of the rotors accordingly to compensate for unwanted rotations or vibrations. In our pending patent /19/, it is shown in detail how the maneuverability around all three axes of the UAV can be optimized. The patent specification demonstrates how these two methods can be combined to optimize the maneuverability of the UAV. By strategically utilizing gyroscopic forces and compensating for the undesirable effects, precise and stable maneuvers can be performed.