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 apparatus is provided for absorbing shocks and a control method capable of protecting cargo from shocks without a separate additional system in a cargo hold of a moving object. The apparatus for absorbing shocks includes at least one inflatable member disposed in a moving object, an air conditioner module installed on the moving object, and a supply pipe connected between the air conditioner module and the inflatable member and providing a refrigerant of the air conditioner module to the inflatable member.

A monument mounted airbag system includes an airbag assembly including at least an airbag mounted directly forward of a passenger, and configured to deploy away from the passenger along an intercepting course with a predetermined path of travel of the passenger. Additionally, the airbag may be configured to substantially conform to a monument disposed in proximity thereto, and may include side support, lower support, and active vents.

A multicopter (100) having a plurality of propellers (1) is configured to be electrically operated. The multicopter (100) is provided with electric motors (2), at least one main battery (3), a generator (4), an engine (5), and a battery condition detecting section (71). The electric motors (2) drive the propellers (1). The main battery (3) is a first electric power source that supplies the electric power to the electric motors (2). The generator (4) is a second electric power source that supplies the electric power to the electric motors (2). The engine (5) drives the generator (4). The battery condition detecting section (71) detects abnormality of the main battery (3). When the battery condition detecting section (71) detects the abnormality of the main battery (3), the generator (4) supplies the electric power that has been converted from motive power from the engine (5) directly to the electric motors (2).

An impact mitigation system for an aircraft and method of deploying the impact mitigation system is disclosed. A state parameter of the aircraft is obtained. The state parameter is used with an aircraft performance model to determine an acceleration capability of the aircraft. A trajectory of the aircraft is predicted using the state parameter of the aircraft and the acceleration capability of the aircraft. A location of an object with respect to the aircraft is determined and the impact mitigation system is deployed when the predicted trajectory indicates a contact with the object at a predicted contact velocity higher than a threshold velocity at a future time.

A method comprising receiving aerial images captured by one or more unmanned aerial vehicle; receiving metadata associated with the aerial images captured by the one or more unmanned aerial vehicle; geo-referencing the aerial images based on a geographic location of a surface to determine geographic coordinates of pixels of the aerial images; receiving a geographic location from a user; retrieving one or more of the aerial images associated with the geographic location based on the determined geographic coordinates; and displaying to the user one or more overview image depicting the geographic location and overlaid with one or more icons indicative of and associated with the retrieved aerial images associated with the geographic location.

Multi-chamber airbag systems for use in aircraft and other vehicles are described herein. In some embodiments, an occupant restraint system includes a multi-chamber airbag that deploys from an occupant restraint (e.g., a lap seat belt) in an aircraft. The multi-chamber airbag can include a first portion that inflates generally upward in front of the occupant's torso, and a second portion that inflates in front of the first portion. The first portion and/or the second portion can include multiple chambers (e.g., generally cylindrical-shaped chambers) that, when inflated, provide the airbag with a shape and/or contact surfaces which can help to maintain the position of the airbag between the occupant and a strike object or hazard. In other embodiments, multi-chamber airbags configured in accordance with the present disclosure can me mounted to a structure (e.g., a monument, console, seat back, etc.) positioned generally in front of the occupant. The structure-mounted airbag can deploy generally toward the occupant in the event of a vehicle impact or other potentially harmful event to protect the occupant from impact injury.

The emergency landing gear actuator for aircraft utilizes a pair of airbags for rapid emergency deployment of landing gear when the conventional hydraulic actuator fails. In the retracted position, the at least one wheel of the landing gear is stored in a first cavity formed in the lower portion of the wing. The shock strut and the side strut are stored in an adjacent second cavity formed in the lower portion of the wing. First and second airbags are respectively mounted in the first and second cavities. The first airbag and the second airbag are each selectively inflatable for emergency deployment of the at least one wheel, the shock strut and the side strut. When the hydraulic actuator fails to deploy the landing gear, the first and second airbags are inflated, forcing the shock strut to rotate and position the at least one wheel in its deployed position.

A method of making a flame resistant airbag suitable for use in aviation applications is discussed. A flame resistant fabric for the use in the construction of aviation airbags is woven from a high tenacity continuous polyester fiber substrate. A polyurethane coating is applied to the woven fabric, which has been treated with a flame retardant, to impart high pressure permeability resistance to the flame resistant fabric. The resulting fabric complies with Federal Aviation Requirement 25.853 as well as exhibits sufficient high pressure permeability resistance which is measured as a pressure of not less than about 198 kPa after five seconds from an initial inflation and pressurization to about 200 kPa, such as may be encountered in and during an inflation of aviation airbag assemblies.

The present invention provides an unmanned aerial vehicle (UAV) such as a rotorcraft and a method of improving the performance thereof. The UAV is equipped with an inflated bag to prevent or alleviate property damage and personal injury caused by a collision between the UAV and a foreign object (e.g. a human being and a pet). The inflated bag in the proximity of a propeller's tip can also disrupt the tip vortex of the propeller generated in UAV operation state. The invention exhibits numerous technical merits such as enhanced operational safety, UAV drag reduction, higher propulsive efficiency, and reduction of UAV vibration level, among others.