A stage positioning system, includes a first body, a second body and a coupling arranged to couple the first body and the second body to each other. The coupling includes a visco-elastic element arranged to couple the first body and the second body to each other. The stage positioning system may further include a sensor to provide a signal representative of a position of the first body. The stage positioning system may further include an actuator to move the first body. The second body may be arranged to couple the actuator and the coupling to each other.

Proposed method and device could be applied as controlling system facilitating the maneuverability and stabilization parameters of UAV, as well as various flight objects and small satellites. The aim of the invention is to reduce the occurrences of imbalances of UAV in strong wind or atmospheric turbulence situations and simultaneously rehabilitation of maneuverability and stabilization parameters without increasing flight speed.

Thus, in order to upgrade the above mentioned parameters of UAV along with the gyroscopic momentum compensation it's necessary to increasing of the kinetic moment by means of gyroscope.

This is achieved by installing the gyroscopes oppose to the propeller taking into account the gravity center of UAV (with rear-mounted propeller gyroscope should be installed in front sector), the direction of rotation of the gyro rotor is directed against the rotation of the propeller (the axis of the gyro rotor and propeller are in straight line); availing high kinetic momentum the devise becomes less subjected to the effects of the wind and turbulence; changing of the flight trajectory performed by moving axis of the gyroscope (stabilization and moments motors) and reductor, that fixed on moving shaft of the rotary frame, and the gyroscope is installed in a device to perform coincidence of the gyroscopic moments with the direction of the rotation of UAV. Coincidence of the directions of gyroscopic moments with the moments of the elevator and rudder increases the UAVs maneuverability. Stabilization and modification of the angular position of the UAV relative to the longitudinal roll axis is performed by increasing or decreasing of rotations of the gyro rotor with adjustable inertial moment.

Proposed method and device could be applied as controlling system facilitating the maneuverability and stabilization parameters of UAV, as well as various flight objects and small satellites. The aim of the invention is to reduce the occurrences of imbalances of UAV in strong wind or atmospheric turbulence situations and simultaneously rehabilitation of maneuverability and stabilization parameters without increasing flight speed.

Thus, in order to upgrade the above mentioned parameters of UAV along with the gyroscopic momentum compensation it's necessary to increasing of the kinetic moment by means of gyroscope.

This is achieved by installing the gyroscopes oppose to the propeller taking into account the gravity center of UAV (with rear-mounted propeller gyroscope should be installed in front sector), the direction of rotation of the gyro rotor is directed against the rotation of the propeller (the axis of the gyro rotor and propeller are in straight line); availing high kinetic momentum the devise becomes less subjected to the effects of the wind and turbulence; changing of the flight trajectory performed by moving axis of the gyroscope (stabilization and moments motors) and reductor, that fixed on moving shaft of the rotary frame, and the gyroscope is installed in a device to perform coincidence of the gyroscopic moments with the direction of the rotation of UAV. Coincidence of the directions of gyroscopic moments with the moments of the elevator and rudder increases the UAVs maneuverability. Stabilization and modification of the angular position of the UAV relative to the longitudinal roll axis is performed by increasing or decreasing of rotations of the gyro rotor with adjustable inertial moment.

Various forms of a gyroscopically stabilised aerial vehicle are provided. The aerial vehicle comprises a jet turbine and or an electric motor coupled to a gyroscopic stabilisation assembly via a shaft assembly. In preferred embodiments the gyroscopic stabilisation assembly comprises a gyroscopic fan with alternating pivoting fan blades to provide controlled stable flight. The aerial vehicle is preferably configured for vertical take off and landing (VTOL) to enable it to be used in a wide variety of situations, including in relation to fighting fires with its exhaust gasses.

Various forms of a gyroscopically stabilised aerial vehicle are provided. The aerial vehicle comprises a jet turbine and or an electric motor coupled to a gyroscopic stabilisation assembly via a shaft assembly. In preferred embodiments the gyroscopic stabilisation assembly comprises a gyroscopic fan with alternating pivoting fan blades to provide controlled stable flight. The aerial vehicle is preferably configured for vertical take off and landing (VTOL) to enable it to be used in a wide variety of situations, including in relation to fighting fires with its exhaust gasses.

The present disclosure describes autonomous flight safety systems (AFSSs) that incorporate an autonomous flight termination unit (AFTU) enabling AFSS monitoring for various termination conditions that are used to activate a flight termination system (e.g., in the event a termination condition is detected). Such termination conditions include boundary limit detection (e.g., whether a vehicle position is outside or projected outside a planned flight envelope), as well as body instability detection (e.g., whether a pitch rate and yaw rate exceed some threshold indicative of vehicle instability). For instance, an AFTU may incorporate a three-axis gyroscope sensor and may implement instability detection processing based on information obtained via the sensor. Instability detection processing may include, for example, a BID algorithm that may be implemented by an AFTU to monitor angular rates of the vehicle, to determine if the vehicle is no longer under stable control, and to issue termination commands when termination conditions are detected.

The present disclosure describes autonomous flight safety systems (AFSSs) that incorporate an autonomous flight termination unit (AFTU) enabling AFSS monitoring for various termination conditions that are used to activate a flight termination system (e.g., in the event a termination condition is detected). Such termination conditions include boundary limit detection (e.g., whether a vehicle position is outside or projected outside a planned flight envelope), as well as body instability detection (e.g., whether a pitch rate and yaw rate exceed some threshold indicative of vehicle instability). For instance, an AFTU may incorporate a three-axis gyroscope sensor and may implement instability detection processing based on information obtained via the sensor. Instability detection processing may include, for example, a BID algorithm that may be implemented by an AFTU to monitor angular rates of the vehicle, to determine if the vehicle is no longer under stable control, and to issue termination commands when termination conditions are detected.

A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.

A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.

A gimbal mount for a sensor having an outer and inner gimbal mount to stabilize vibrations in a wide frequency band without having to statically balance the sensor. A direct drive is provided for at least one drive of an outer axis of rotation of the outer gimbal mount and an amplified piezo actuator is provided for at least one drive of an inner axis of rotation of the inner gimbal mount. The at least one outer axis of rotation is provided for vibration stabilization in a first range of the frequency band to be stabilized and the at least one inner axis of rotation stabilization is provided for vibration stabilization in a second range in the frequency band to be stabilized. The outer gimbal mount and the inner gimbal mount are embodied as mechanically rigid constructions which transmit vibrations in the frequency band to be stabilized essentially without damping.