A method for controlling a flying projectile which rotates during flight, comprising: determining an angle of rotation of an inertial mass spinning about an axis during flight; and controlling at least one actuator for altering at least a portion of an aerodynamic structure, selectively in dependence on the determined angle of rotation and a control input, to control aerodynamic forces during flight. An aerodynamic surface may rotate and interact with surrounding air during flight, to produce aerodynamic forces. A sensor determines an angular rotation of the spin during flight. A control system, responsive to the sensor, produces a control signal in dependence on the determined angular rotation. An actuator selectively alters an aerodynamic characteristic of the aerodynamic surface in response to the control signal.

Embodiments are directed to a rotorcraft comprising a body having a longitudinal axis, a wing coupled to the body, a single tiltrotor assembly pivotally coupled to the body, and the tiltrotor assembly configured to move between a position generally perpendicular to the longitudinal axis during a vertical flight mode and a position generally parallel to the longitudinal axis during a horizontal flight mode. The rotorcraft may further comprise an anti-torque system configured to counteract torque generated by the tiltrotor assembly during vertical flight. The rotorcraft may further comprise a center of gravity compensation system configured to manage a rotorcraft center of gravity during movement of the tiltrotor assembly between the vertical flight mode and the horizontal flight mode.

Embodiments are directed to a rotorcraft comprising a body having a longitudinal axis, a wing coupled to the body, a single tiltrotor assembly pivotally coupled to the body, and the tiltrotor assembly configured to move between a position generally perpendicular to the longitudinal axis during a vertical flight mode and a position generally parallel to the longitudinal axis during a horizontal flight mode. The rotorcraft may further comprise an anti-torque system configured to counteract torque generated by the tiltrotor assembly during vertical flight. The rotorcraft may further comprise a center of gravity compensation system configured to manage a rotorcraft center of gravity during movement of the tiltrotor assembly between the vertical flight mode and the horizontal flight mode.

A flight vehicle control and stabilization process detects and measures an orientation of a non-fixed portion relative to a fixed frame or portion of a flight vehicle, following a perturbation in the non-fixed portion from one or both of tilt and rotation thereof. A pilot or rider tilts or rotates the non-fixed portion, or both, to intentionally adjust the orientation and effect a change in the flight vehicle's direction. The flight vehicle control and stabilization process calculates a directional adjustment of the rest of the flight vehicle from this perturbation and induces the fixed portion to re-orient itself with the non-fixed portion to effect control and stability of the flight vehicle. The flight vehicle control and stabilization process also detects changes in speed and altitude, and includes stabilization components to adjust flight vehicle operation from unintentional payload movement on the non-fixed portion.

A flight vehicle control and stabilization process detects and measures an orientation of a non-fixed portion relative to a fixed frame or portion of a flight vehicle, following a perturbation in the non-fixed portion from one or both of tilt and rotation thereof. A pilot or rider tilts or rotates the non-fixed portion, or both, to intentionally adjust the orientation and effect a change in the flight vehicle's direction. The flight vehicle control and stabilization process calculates a directional adjustment of the rest of the flight vehicle from this perturbation and induces the fixed portion to re-orient itself with the non-fixed portion to effect control and stability of the flight vehicle. The flight vehicle control and stabilization process also detects changes in speed and altitude, and includes stabilization components to adjust flight vehicle operation from unintentional payload movement on the non-fixed portion.

To provide a rotary wing aircraft capable of self-leveling and ensuring a stable landing state. The rotary wing aircraft according to the present disclosure comprises a plurality of rotary blades, an arm part for supporting the plurality of rotary blades, a mounting part for mounting an object, and a connecting part for connecting the mounting part to the arm part in a state where the mounting part is movable within a predetermined range. The position of the connecting part of the rotary wing aircraft of the present disclosure is above the center of gravity of the arm part. Thereby, self-leveling is made possible and a stable landing state can be ensured.

To provide a rotary wing aircraft capable of self-leveling and ensuring a stable landing state. The rotary wing aircraft according to the present disclosure comprises a plurality of rotary blades, an arm part for supporting the plurality of rotary blades, a mounting part for mounting an object, and a connecting part for connecting the mounting part to the arm part in a state where the mounting part is movable within a predetermined range. The position of the connecting part of the rotary wing aircraft of the present disclosure is above the center of gravity of the arm part. Thereby, self-leveling is made possible and a stable landing state can be ensured.

Certain examples of the present disclosure relate to systems and methods for controlling a vehicle. In particular, the present disclosure provides systems and methods for moving an aerial vehicle by decoupling the pitch- and roll-movement from thrust production. This decoupling can occur by shifting the center of gravity of the vehicle to create a moment about a desired axis. Some examples describe single-shaft rotary vehicles, while other examples describe coaxial rotary vehicles. The vehicles described herein may include a first mass moveable from a first position to a second position to create at least one of a rolling moment or a pitching moment to alter the direction of movement of the vehicle. A second mass may also be provided to alter the rolling moment or pitching moment. Methods for controlling the vehicles are also provided herein.

Certain examples of the present disclosure relate to systems and methods for controlling a vehicle. In particular, the present disclosure provides systems and methods for moving an aerial vehicle by decoupling the pitch- and roll-movement from thrust production. This decoupling can occur by shifting the center of gravity of the vehicle to create a moment about a desired axis. Some examples describe single-shaft rotary vehicles, while other examples describe coaxial rotary vehicles. The vehicles described herein may include a first mass moveable from a first position to a second position to create at least one of a rolling moment or a pitching moment to alter the direction of movement of the vehicle. A second mass may also be provided to alter the rolling moment or pitching moment. Methods for controlling the vehicles are also provided herein.

A monocopter includes a housing and a propeller connected to a shaft. The shaft is connected to a main motor that is fixed to the housing (e.g., mounted within the housing) such that upon operation of the main motor, the shaft rotates and the propeller rotates. A first counterweight is interfaced to a shaft of a first motor that is interfaced to the housing and a second counterweight is interfaced to a shaft of a second motor that is also interfaced to the housing such that the shaft of the first motor is in a plane that is perpendicular to the shaft of the second motor (e.g., the shafts are at right angles to each other). The main motor, the first motor and the second motor are controlled (e.g., using artificial intelligence) to enable stable flight of the monocopter.