An aircraft safety system includes impact energy reduction systems including: an aircraft parachute, at least one rotor configured for autorotation, and an energy absorbing system. An automatic control system uses data from speed and altitude sensors to selectively and sequentially deploy the impact energy reduction systems depending on the portion of the aircraft speed and altitude flight envelope in which the aircraft is operating when an emergency is detected.

To provide a flying object including a lift generating member deployment device that makes it easier than before to automatically avoid collision with an obstacle. A flying object 30 includes an obstacle detecting unit 5, a control unit 6, a battery 7, a storage unit 8 that stores information transmitted from the control unit 6, a transmitting/receiving unit 9 that receives an operation signal from a controller 40 and transmits information regarding the flying object 30 to the controller 40, and others. The obstacle detecting unit 5 is to detect the altitude of the flying object 30 and outputs an altitude detection signal, which represents the detected altitude information, to the control unit 6. In addition, upon detecting an obstacle present within a predetermined distance, the obstacle detecting unit 5 outputs an obstacle detection signal to the control unit 6, detects the distance between the flying object body 31 and the obstacle, and outputs a distance detection signal, which represents the detected distance information, to the control unit 6. The control unit 6 determines whether or not to actuate left and right brake cord pulling devices 10 in accordance with the signal received from the obstacle detecting unit 5.

An aircraft emergency power unit (EPU) includes a battery powered subsystem that replaces toxic hydrazine fuel use. The battery of the battery powered subsystem is utilized to supply power to an aircraft electrical system in the event of a failure of the EPU turbine-powered generator. The battery of the battery powered subsystem is also utilized to supply power to an electric hydraulic motor pump in the event of a failure of the EPU turbine-powered hydraulic pump (or to augment the output of the EPU-turbine-powered hydraulic pump). The battery of the battery powered subsystem is capable of simultaneously powering the electrical system and the electric hydraulic motor pump or of powering either one of the electrical system and electric hydraulic motor pump independently based upon aircraft fault conditions. Intermittent operation of the electrical system and/or the electric hydraulic motor pump in an intermittent fashion on an as-needed basis is also possible.

An air mobility may include a seat in which an airbag or a parachute is stored; and an escape portion configured to support the seat mounted to the escape portion, coupled to the air mobility to form part of the air mobility, and configured to enable a passenger to perform an emergency bailout with the seat to an outside of the air mobility when the escape portion is separated from the air mobility.

A cargo packaging system for a mobility vehicle may include a housing mounted on the mobility vehicle; a plurality of air cushions provided at a plurality of positions on an internal surface of the housing, and applying a pressure to and cushioning the cargo accommodated in the housing in a plurality of directions during expansion thereof; an air charging part connected to the plurality of air cushions and configured for injecting gas into each air cushion of the housing and controlling a flow rate or a pressure of the injected gas; and an outlet controlled by the air charging part and discharging the gas injected into each air cushion to the outside of the outlet.

A lap expanding reactionary airbag apparatus includes separate expanding lap and chest portions of the airbag. When loaded in a frontal or oblique crash event, the two portions act as a reactionary surface against each other, reducing the chest velocity of a vehicle occupant, thereby reducing the forward movement of the occupant. This restriction in forward movement results in reduced lumbar injuries.

An unmanned cargo loading and transport system adapted for operation with an unmanned aerial vehicle (UAV) comprising a payload pad comprising a plurality of support members movable from an extended mode to a retracted mode when exposed to a lateral force applied to the support members and a payload container adapted to attach to a UAV and pick up cargo from the payload pad by transferring the weight of the cargo from the payload pad to the payload container. The lower portion of the payload container comprises two generally opposed cargo doors movably mounted at opposed sides and movable inwardly to a closed position and outwardly to an open position to receive cargo when the payload container is positioned at the payload pad. The system further comprises a motive power mechanism coupled to the cargo doors for selectively moving the doors between their open and their closed positions.

A life protection device system is proposed. More particularly, the life protection device system includes: a shock absorbing device provided with a shock absorbing part, a shock absorber, and an airbag that are mounted on a moving object so as to absorb impact to protect the life of passengers in a crash or collision of the moving object; a measuring device detecting the shock applied to the moving object; a controller generating a preset driving control signal according to the detected shock of the measuring device; and an artificial intelligence part notifying of an occurrence of a disaster and asking for help from a designated disaster center in response to the driving control signal of the controller, wherein the impact on the passengers is minimized even when the moving object such as a drone, autonomous aircraft, and autonomous vehicle crashes or collides, or falls into a river or sea.

An air mobility control system is provided. The system includes one or more shock absorbing units that are mounted in an aircraft and are configured to absorb a vertical force impacting on the air mobility vehicle. A distance sensor is mounted in the air mobility vehicle and is configured to sense the distance to a ground or an approaching object. A safety controller is configured to detect an abnormal descent of the air mobility vehicle and to operate the one or more shock absorbing units to be deployed according to the distance sensed by the distance sensor.

An aircraft includes: a plurality of rotor units each including a propeller and a motor that drives the propeller; a balloon that laterally covers the plurality of rotor units, across a height of the plurality of rotor units in an up-and-down direction; and a drive unit configured to change the external shape of the balloon at a predetermined timing.