Disclosed is a motor bracket of a multicopter flying robot. The motor bracket for the multicopter flying robot disclosed in the present invention includes: a body 110 receiving a rotary motor 500 therein which is used in the multicopter flying robot, a connection portion 120 which is formed on the outer surface of the body and receives two power supply lines 510 and 520 connected to a power terminal of the rotary motor 500, and a power supply member 300 which is pushed into the connection portion 120 and electrically contacts the at least two power supply lines 510 and 520. The connection portion 120 includes a spatial separation portion 122 which performs a function of forming separated spaces of which the number is the same as the number of the at least two power supply lines 510 and 520.

This invention presents a unique propulsion and maneuver-control system for crafts and devices. This invention develops its desired thrust force vectors from the vectors sum of centrifugal force vectors of rotating masses and their controlled gyroscopic force vectors. Also shown are applications of this propulsion and maneuver-control system for future VTOL-Hovering-Flying crafts, Scooters, Surfboards, marine/submarine-crafts, earth, moon, mars satellites disks and space-crafts. This invention has great potentials of creating new businesses in aerospace markets, all planets' weather modification business, bring people of the world closer together and perform critical tasks of modify trajectories to prevent run-away asteroids from hitting the earth.

The main purpose of the invention is a propeller (32) for a turbomachine (1) comprising a plurality of blades (48) and a blade support ring (47) fitted with housings (50) each of which holding a pivot (52) supporting the root (58) of one of said blades (48), characterized in that at least one of the pivots (52) is associated with at least one dynamic scoop (100), capable of moving between distinct positions, an open position in which a cooling airflow (F) can be captured, and a closed position as a function of the orientation of the corresponding blade.

A method of managing a loss of power from a power plant having three engines. During a monitoring step, each engine is monitored in order to detect whether the engine is suffering a loss of power. During a verification step, it is determined whether the power plant is overpowered. During a signalling step, a first alert is generated when an engine has lost power but the power plant is in fact overpowered, and a second alert different from the first alert is generated when an engine has lost power and the power plant is not overpowered.

A method of managing a loss of power from a power plant having three engines. During a monitoring step, each engine is monitored in order to detect whether the engine is suffering a loss of power. During a verification step, it is determined whether the power plant is overpowered. During a signalling step, a first alert is generated when an engine has lost power but the power plant is in fact overpowered, and a second alert different from the first alert is generated when an engine has lost power and the power plant is not overpowered.

An engine system with a multi-gas-generator, tip-turbine driven lift fan with pressurized air circulation control for use on vertical and short-take-off and landing (V/STOL) aircraft is disclosed. Gas generators located around the periphery of the fan drive the fan through action on a fan blade-tip turbine or provide compressed gas (hot or cold) to circulation control devices. Variable pitch fan blades improve part-power cruise performance. Enclosed in a nacelle, the engine employs circulation control to enhance V/STOL performance. In some embodiments, a core cruise turbine gas generator mounted in the center of the fan duct powers the fan during cruise mode. In some hybrid gas and electric power embodiments, the core cruise gas generator is replaced by an electric motor that draws power from a battery in the fuselage. The battery may be charged by an electric generator driven by a gas generator around the periphery of the fan.

Embodiments disclosed include a rotary-wing drone that includes a drone body and linking arms, such that a propulsion unit is located at the distal ends of the linking arms. The rotary-wing drone may also include a stiff battery pack with at least one fixation means and a guiding profile. The drone body may also include a platform with at least one guiding rail configured to cooperate and receive the complementary guiding profile of the battery pack and at least one fixation means complementary to the fixation means of the battery pack so that the battery pack attaches onto and stiffens the drone body.

Embodiments disclosed include a rotary-wing drone that includes a drone body and linking arms, such that a propulsion unit is located at the distal ends of the linking arms. The rotary-wing drone may also include a stiff battery pack with at least one fixation means and a guiding profile. The drone body may also include a platform with at least one guiding rail configured to cooperate and receive the complementary guiding profile of the battery pack and at least one fixation means complementary to the fixation means of the battery pack so that the battery pack attaches onto and stiffens the drone body.

A compressed gas ejection assembly 10 for a rotating wing aircraft blade 2 comprises a compressed gas passage 114 adapted to allow a substantially constant mass flow through the compressed gas ejection assembly 10 across at least a portion of the width of the compressed gas ejection assembly 10.

A compressed gas ejection assembly 10 for a rotating wing aircraft blade 2 comprises a compressed gas passage 114 adapted to allow a substantially constant mass flow through the compressed gas ejection assembly 10 across at least a portion of the width of the compressed gas ejection assembly 10.