An airbag system includes a VTOL aircraft fuselage having an airbag compartment defined within the fuselage. A protective cover defines a portion of the exterior surface of the fuselage. The protective cover encloses at least a portion of the airbag compartment. An airbag is folded within the airbag compartment secured to a point on the fuselage. A method for deploying an airbag in an aircraft includes sending a signal to a gas generator to inflate at least one airbag secured within an airbag compartment within a fuselage of an aircraft. The method includes jettisoning off a protective cover from the airbag compartment. The method includes inflating the airbag with the gas generator to extend outside of the airbag compartment to attenuate forces and cushion the aircraft upon ground impact.

A sensor for monitoring rotors includes a rotating shaft coupled to a set of rotor blades and a non-rotating tube at least partially disposed within the rotating shaft and coupled to the rotating shaft. The non-rotating tube includes a first end and a second end, a sensor mount disposed within the non-rotating tube proximate to the second end of the non-rotating tube. One or more sensors are attached to the sensor mount.

A system and method for providing a supplemental power includes: an engine, a transmission coupled to the engine, a motor-generator coupled to the transmission, and a battery system coupled to the motor-generator. The motor-generator is configured to draw an energy from the transmission and store the energy in the battery system when the engine is driving the transmission. The battery system is configured to discharge the energy to the motor-generator, and the motor-generator is configured to provide the supplemental power to the transmission.

The present invention includes a safety apparatus and method for protecting users during maintenance operations for a rotorcraft comprising: at least one permanent, semi-permanent, or detachable safety bar, strap, fastener, hook, or loop that is attached or attachable to a rotorcraft, wherein the safety bar, strap, fastener, hook, or loop is positioned in an area or surface between a windshield of the rotorcraft and a tail boom of the rotorcraft and is connectable to a user safety device to provide fall protection from the area or surface.

An aircraft includes; a plurality of rotor units each of which includes a propeller and a motor which drives the propeller, and generates thrust for flight of the aircraft; a controller which controls rotation of the propellers included in the plurality of rotor units; a balloon which laterally covers the plurality of rotor units; and a detector which detects a state of the aircraft, wherein the controller decreases a rotational speed of the propeller included in at least one rotor unit among the plurality of rotor units, according to a result of detection by the detector.

The present invention includes an emergency egress system of a vehicle, including: a rope compartment, wherein the rope compartment is located on or near a vertical plane along a longitudinal axis of the vehicle, within reach of one or more occupant seats; a rope, wherein at least a portion of the rope is stored within the rope compartment and is securely tethered to a portion of a structure of the vehicle; and a rope compartment cover to secure the rope in the rope compartment.

An aircraft having an electric motor coupled to a rotor and an instrument electronically connected to the electric motor and configured to communicate a time available value before a motor condition reaches a motor condition limit.

The present invention relates to a control method in case of engine failure of a hybrid helicopter having a power plant connected to at least one lift rotor and to at least one propeller, said lift rotor having a plurality of first blades and said at least one propeller having a plurality of second blades. The method comprises the following steps: (i) measuring a forward speed of the hybrid helicopter, (ii) on condition that said forward speed is greater than a first speed threshold and that each engine has failed, automatically implementing a first emergency piloting mode comprising a step for automatic reduction by an automatic piloting system of a pitch of said second blades toward an objective pitch making said at least one propeller produce a motive power which is transmitted to the lift rotor.

The present invention relates to an aircraft provided with a rotary airfoil, a power plant and an assistance system having an electric motor. The power plant comprises a power transmission box and at least one heat engine. The aircraft includes at least one accessory which is set in motion by a secondary output shaft of the power transmission box. The assistance system is provided with a mechanical connection module having a connection shaft which is connected to the secondary output shaft. A first connection member is connected to said at least one accessory and is connected by a first mechanical link internal to the connection shaft, a second connection member being connected to the electric motor and connected by a second mechanical link internal to the connection shaft.

Disclosed herein is a VTOL tilt-wing aircraft that serves as a 4-6 passenger airliner for scheduled service between city centers and that is optimized for travel distances from 100-500 miles fully loaded with passengers and fuel. The VTOL aircraft solves technical, cost, and time problems inherent in other forms of transportation, including, but not limited to, rail, passenger airlines, and helicopters. The VTOL aircraft (1) takes off and lands like a helicopter, (2) flies fast like a jet, and (3) costs less than or comparable to a helicopter.