Provided is a current breaker for an aerial vehicle that can prevent occurrence of a minor collision of propellers or other components in operation with a person and can prevent occurrence of a deployment failure of a lift generating member at a crash of the aerial vehicle. A current breaker 100 for an aerial vehicle includes a rupture plate 23 that disconnects a current supply path 30 that electrically connects an electric device and an electric circuit, an igniter 10 that damages the rupture plate 23 by directly or indirectly applying a destructive force (heat and pressure) toward the current supply path 30 with respect to the rupture plate 23, and disconnects the current supply path 30 by the rupture plate 23 that has been damaged, and a controller 24 that drives the igniter 10 upon detection of an abnormality.

A hand-held emergency vision apparatus comprises an enclosed tubular structure having opposite first and second ends; first and second clear members disposed at respective the first and second ends; the structure including a plurality of tubular members retractable to a shorter length and extendable to one of several lengths, the tubular members are rigid and sealed from the outside air; and a filter operably associated with the tubular structure to filter the outside air such that when the tubular structure is extended from the compact form air the outside air is forced through the filter and clean air enters the tubular structure.

A passenger module that may be connected to an aircraft for transport, and may be detached and attach different module for carriage to a different destination. In alternative embodiments involving different aircrafts such as fixed wing and helicopter aircraft, a module may be adapted to have a transparent exterior so that passengers may have a broad range of unobstructed view of the outside surroundings. The module may have a range of free movements while still connected to the aircraft for such purposes as sightseeing.

An adaptive method and system for monitoring a shipping container for an environmental anomaly uses sensor-based ID nodes within the container and a command node. Sensors on each ID node generate sensor data about an environmental condition proximate the ID node as disposed within the container. Each ID node periodically broadcasts the sensor data. The command node monitors a first group of sensor data from the ID nodes over a first time period to detect an initial environmental threshold condition related to the container, then monitors a subsequent group of sensor data over a second time period under a modified monitoring parameter to detect a secondary environmental threshold condition related to the container as the anomaly. In response to detecting the secondary condition, the command node generates an alert notification and transmits the alert notification to an external transceiver to initiate a mediation response related to the anomaly.

An adaptive method and system for monitoring a shipping container for an environmental anomaly uses sensor-based ID nodes within the container and a command node. Sensors on each ID node generate sensor data about an environmental condition proximate the ID node as disposed within the container. Each ID node periodically broadcasts the sensor data. The command node monitors a first group of sensor data from the ID nodes over a first time period to detect an initial environmental threshold condition related to the container, then monitors a subsequent group of sensor data over a second time period under a modified monitoring parameter to detect a secondary environmental threshold condition related to the container as the anomaly. In response to detecting the secondary condition, the command node generates an alert notification and transmits the alert notification to an external transceiver to initiate a mediation response related to the anomaly.

A latch assembly for a decompression panel in an aircraft includes a base and a swing arm hinged to the base and pivotable relative to the base about a hinge axis between a latched position and an unlatched position. A load pin fixed to the swing arm has a pin axis a fixed distance from the hinge axis. A spring secured to the base is positioned to exert a spring force against the swing arm when the swing arm pivots from the latched position to the unlatched position. A bracket securable to the decompression panel defines a slot retaining the load pin when the swing arm is in the latched position. The load pin is movable in the slot under relative motion of the bracket and the base with the swing arm in the latched position, and exits the slot when the swing arm pivots to the unlatched position.

A load-bearing attachment assembly is provided for mounting a structure to an aircraft. The load-bearing attachment assembly comprises a male fastening component and a female fastening component. The male fastening component comprises a radially-extending head, a first aperture, and a cylindrical portion extending perpendicular to the radially-extending head. The cylindrical portion has a first threaded portion circumferentially disposed on an outer surface of the cylindrical portion. The radially-extending head comprises a first clamping surface. The female fastening component comprises an annulus enclosing a second aperture, a second clamping surface disposed on the annulus, and a second threaded portion circumferentially disposed on an inner surface perpendicular to the second clamping surface. The first aperture and the second aperture are configured for a fastener to extend therethrough. In response to rotation of the fastener, first clamping surface translates toward second clamping surface.

Disclosed herein is a helicopter flight support for use in case of emergencies. The helicopter flight support comprises a motor which causes a threaded shaft to turn which is coupled to an underside of the helicopter. This causes outer supports and inner supports to be deployed until they reach a wing-like configuration. The interior of the wing comprises a plurality of support cables for tensioning the wing. The helicopter flight support further comprises upper and lower support cables mounted to the tips of the wing to provide horizontal stability.

Disclosed herein is a helicopter flight support for use in case of emergencies. The helicopter flight support comprises a motor which causes a threaded shaft to turn which is coupled to an underside of the helicopter. This causes outer supports and inner supports to be deployed until they reach a wing-like configuration. The interior of the wing comprises a plurality of support cables for tensioning the wing. The helicopter flight support further comprises upper and lower support cables mounted to the tips of the wing to provide horizontal stability.

An emergency vision apparatus comprises an inflatable enclosure to enable a user to see through the enclosure when expanded and observe a source of information at a distal end of the enclosure while smoke or other particulate matter is in the environment. The enclosure includes an opening configured for insertion of a user's hand into the interior of the enclosure to allow the user to operate a touch sensitive screen or hardware visible through the second clear member disposed toward a user and a sealable closure for closing the opening and sealing the opening around the user's hand. The sealable closure includes flexible first and second sheets covering the opening, the first and second sheets including respective first and second slits disposed transversely to each other, the first and second slits being configured to allow insertion of the user's hand into the interior of the enclosure.