Provided is a device for controlling flight of a drone, the device including: a rotor on which a motor is mounted; and an inertial navigation control unit that controls a rotation speed of the motor mounted on the rotor, in which in order for a drone to perform a hovering operation, the inertial navigation unit computes the rotation speed of the motor using an x-axis inertia moment, a y-axis inertia moment, and a z-axis inertia moment, which are computed using equations, and a propeller rotation inertia moment (J.sub.r) that is an intrinsic constant for the drone, the equation being:

[00001]$I_{\mathrm{xx}}=I_{\mathrm{yy}}=\frac{2.Math.{\mathrm{mr}}^2}{5}+2.Math.l^2.Math.m_r$$I_{\mathrm{zz}}=\frac{2.Math.{\mathrm{mr}}^2}{5}+4.Math.l^2.Math.m_r,$ where I.sub.xx=x-axis inertia moment, I.sub.yy=y-axis moment, I.sub.zz=z-axis inertia moment, l denotes a distance from the center axis of the drone to the motor, m denotes a weight of the drone, r denotes a radius of the drone, and m.sub.r is a weight of one rotor.

Provided is a device for controlling flight of a drone, the device including: a rotor on which a motor is mounted; and an inertial navigation control unit that controls a rotation speed of the motor mounted on the rotor, in which in order for a drone to perform a hovering operation, the inertial navigation unit computes the rotation speed of the motor using an x-axis inertia moment, a y-axis inertia moment, and a z-axis inertia moment, which are computed using equations, and a propeller rotation inertia moment (J.sub.r) that is an intrinsic constant for the drone, the equation being:

[00001]$I_{\mathrm{xx}}=I_{\mathrm{yy}}=\frac{2.Math.{\mathrm{mr}}^2}{5}+2.Math.l^2.Math.m_r$$I_{\mathrm{zz}}=\frac{2.Math.{\mathrm{mr}}^2}{5}+4.Math.l^2.Math.m_r,$ where I.sub.xx=x-axis inertia moment, I.sub.yy=y-axis moment, I.sub.zz=z-axis inertia moment, l denotes a distance from the center axis of the drone to the motor, m denotes a weight of the drone, r denotes a radius of the drone, and m.sub.r is a weight of one rotor.

A system of hardware and software for determining the weight and center of gravity location of an airplane or other vehicles, like a forklift, truck, maritime vessel. The same system could be used to determine stresses or movement on stationary structures is disclosed. This system employs commercially available, off the shelf or existing, proven, and inexpensive technology and utilizes empirical data. Further, it is designed as a supplemental check on calculated results, which are subject to data errors and are circumvented by this invention's equipment. The system includes a set of pressure and load, strain, bending, and/or other sensors, a voltage source, a voltmeter, a computer, a display, an empirically derived database, a temperature sensor, a set of switches, wireless transmission, and a power source that allows the system to be used for determining the weight and center of gravity location of an airplane or other vehicle.

A system of hardware and software for determining the weight and center of gravity location of an airplane or other vehicles, like a forklift, truck, maritime vessel. The same system could be used to determine stresses or movement on stationary structures is disclosed. This system employs commercially available, off the shelf or existing, proven, and inexpensive technology and utilizes empirical data. Further, it is designed as a supplemental check on calculated results, which are subject to data errors and are circumvented by this invention's equipment. The system includes a set of pressure and load, strain, bending, and/or other sensors, a voltage source, a voltmeter, a computer, a display, an empirically derived database, a temperature sensor, a set of switches, wireless transmission, and a power source that allows the system to be used for determining the weight and center of gravity location of an airplane or other vehicle.

A system of hardware and software for determining the weight and center of gravity location of an airplane or other vehicles, like a forklift, truck, maritime vessel. The same system could be used to determine stresses or movement on stationary structures is disclosed. This system employs commercially available, off the shelf or existing, proven, and inexpensive technology and utilizes empirical data. Further, it is designed as a supplemental check on calculated results, which are subject to data errors and are circumvented by this invention's equipment. The system includes a set of pressure and load, strain, bending, and/or other sensors, a voltage source, a voltmeter, a computer, a display, an empirically derived database, a temperature sensor, a set of switches, wireless transmission, and a power source that allows the system to be used for determining the weight and center of gravity location of an airplane or other vehicle.

A system of hardware and software for determining the weight and center of gravity location of an airplane or other vehicles, like a forklift, truck, maritime vessel. The same system could be used to determine stresses or movement on stationary structures is disclosed. This system employs commercially available, off the shelf or existing, proven, and inexpensive technology and utilizes empirical data. Further, it is designed as a supplemental check on calculated results, which are subject to data errors and are circumvented by this invention's equipment. The system includes a set of pressure and load, strain, bending, and/or other sensors, a voltage source, a voltmeter, a computer, a display, an empirically derived database, a temperature sensor, a set of switches, wireless transmission, and a power source that allows the system to be used for determining the weight and center of gravity location of an airplane or other vehicle.

Systems and methods for a gyroscopic rotational wing for an aircraft are disclosed. In one embodiment, a safety and stability device for an aircraft comprises an inner ring, an outer ring that rotates relative to the inner ring, and a motor connected to the inner ring that drives rotation of the outer ring relative to the inner ring. In some embodiments, the safety and stability device rotates in a substantially horizontal plane and at a rotational speed sufficient to provide gyroscopic stability for the aircraft.

Systems and methods for a gyroscopic rotational wing for an aircraft are disclosed. In one embodiment, a safety and stability device for an aircraft comprises an inner ring, an outer ring that rotates relative to the inner ring, and a motor connected to the inner ring that drives rotation of the outer ring relative to the inner ring. In some embodiments, the safety and stability device rotates in a substantially horizontal plane and at a rotational speed sufficient to provide gyroscopic stability for the aircraft.

A vibration control assembly for an aircraft includes a housing operatively coupled to the aircraft. Also included is a cage disposed within an interior region of the housing, the cage rotatable within the housing about a first axis. Further included is a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis, wherein a controllable moment is imposed on the aircraft upon rotation of the gyroscope wheel to counter vibratory moments produced by the vehicle. Yet further included is a control assembly at least partially surrounding the gyroscope wheel for controlling the controllable moment. The control assembly includes a structure having an inner surface, a track disposed along the inner surface, and an arm operatively coupled to the gyroscope wheel, the arm having an end disposed within the track, the gyroscope wheel angularly displaceable upon translation of the arm along the track.

A vibration control assembly for an aircraft includes a housing operatively coupled to the aircraft. Also included is a cage disposed within an interior region of the housing, the cage rotatable within the housing about a first axis. Further included is a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis, wherein a controllable moment is imposed on the aircraft upon rotation of the gyroscope wheel to counter vibratory moments produced by the vehicle. Yet further included is a control assembly at least partially surrounding the gyroscope wheel for controlling the controllable moment. The control assembly includes a structure having an inner surface, a track disposed along the inner surface, and an arm operatively coupled to the gyroscope wheel, the arm having an end disposed within the track, the gyroscope wheel angularly displaceable upon translation of the arm along the track.