An improved system detects an environmental anomaly in a shipping container and initiates a mediation response through a generated layered alert notification. The system includes sensor-based ID nodes associated with packages within the container, and a command node mounted to the container communicating with the ID nodes and an external transceiver on a vehicle transporting the container. The command node is programmed to detect sensor data from the ID nodes; compare the sensor data to package environmental thresholds in context data related to each ID node; detect the environmental anomaly when the comparison indicates an environmental condition for at least one package exceeds its environmental threshold; responsively generate a layered alert notification identifying a mediation recipient and mediation action, and establishing a mediation response priority based upon the comparison; and transmit the layered alert notification to the transceiver unit to initiate a mediation response related to the mediation action.

An electronic module assembly (EMA) for use in controlling one or more personal restraint systems. A programmed processor within the EMA is configured to determine when a personal restraint system associated with each seat in a vehicle should be deployed. In addition, the programmed processor is configured to perform a diagnostic self-test to determine if the EMA and the personal restraint systems are operational. In one embodiment, results of the diagnostic self-test routine are displayed on a display included on the electronic module assembly. In an alternative embodiment, the results of the diagnostic self-test routine are transmitted via a wireless transceiver to a remote device. The remote device can include a wireless interrogator or can be a remote computer system such as a cabin management computer system.

An electronic module assembly (EMA) for use in controlling one or more personal restraint systems. A programmed processor within the EMA is configured to determine when a personal restraint system associated with each seat in a vehicle should be deployed. In addition, the programmed processor is configured to perform a diagnostic self-test to determine if the EMA and the personal restraint systems are operational. In one embodiment, results of the diagnostic self-test routine are displayed on a display included on the electronic module assembly. In an alternative embodiment, the results of the diagnostic self-test routine are transmitted via a wireless transceiver to a remote device. The remote device can include a wireless interrogator or can be a remote computer system such as a cabin management computer system.

To provide a safety device that can control a landing point of a flight vehicle in the event of a crash. The safety device provided with a flight vehicle includes a first parachute configured to reduce a falling velocity and control an attitude of the flight vehicle during falling, a second parachute configured to be opened later than the first parachute and to reduce an impact when the flight vehicle lands, a sensor portion configured to detect a fall of the flight vehicle, and a control unit configured to control opening of the first parachute and the second parachute. In addition, the control unit opens the first parachute at a first timing after the sensor portion detects the fall and opens the second parachute at a second timing after the first timing and when a predetermined condition is satisfied.

To provide a safety device that can control a landing point of a flight vehicle in the event of a crash. The safety device provided with a flight vehicle includes a first parachute configured to reduce a falling velocity and control an attitude of the flight vehicle during falling, a second parachute configured to be opened later than the first parachute and to reduce an impact when the flight vehicle lands, a sensor portion configured to detect a fall of the flight vehicle, and a control unit configured to control opening of the first parachute and the second parachute. In addition, the control unit opens the first parachute at a first timing after the sensor portion detects the fall and opens the second parachute at a second timing after the first timing and when a predetermined condition is satisfied.

A method of fire suppression may include injecting a reactive agent into a reaction zone to produce a catalytically active species for fire suppression and conveying the catalytically active species to a fire to catalytically interfere with flame chemistry of the fire. Fire in a fuel tank may be suppressed by injecting the reactive agent into a convective flow of a mixture of fuel and oxidizer in a fuel tank, the reactive agent reacting in the fuel tank to release a species which catalytically interferes with flame chemistry to suppress fire in the fuel tank. Fire at an airplane crash may be suppressed by releasing the reactive agent from the container at the crash site to produce an active species to catalytically interfere with a fire at the crash site.

A method of fire suppression may include injecting a reactive agent into a reaction zone to produce a catalytically active species for fire suppression and conveying the catalytically active species to a fire to catalytically interfere with flame chemistry of the fire. Fire in a fuel tank may be suppressed by injecting the reactive agent into a convective flow of a mixture of fuel and oxidizer in a fuel tank, the reactive agent reacting in the fuel tank to release a species which catalytically interferes with flame chemistry to suppress fire in the fuel tank. Fire at an airplane crash may be suppressed by releasing the reactive agent from the container at the crash site to produce an active species to catalytically interfere with a fire at the crash site.

An aircraft, the aircraft including a whole-aircraft ballistic parachute that is coupled to the aircraft. The aircraft determines if a pre-activation action needs to be performed before activation of the whole-aircraft ballistic parachute. The aircraft also receives a whole-aircraft ballistic parachute activation request. The aircraft then issues a command to perform the pre-activation action and then activates the deployment of the whole-aircraft ballistic parachute. The aircraft then issues a command to perform a post-activation action.

An unmanned aircraft 1 according to an embodiment of the present invention provides an unmanned aircraft that properly makes a forced landing in case of an abnormality. The unmanned aircraft 1 is configured as a multicopter that flies with lift and thrust generated by rotation of six rotors 13. The unmanned aircraft 1 identifies a forced landing site in a case of having detected an abnormality during flight and controls motors 12 configured to drive the respective rotors 13, to make a landing at the identified forced landing site. The unmanned aircraft 1 is consequently enabled to make an autonomous forced landing at a specific site in case of an abnormality.

An unmanned aircraft 1 according to an embodiment of the present invention provides an unmanned aircraft that properly makes a forced landing in case of an abnormality. The unmanned aircraft 1 is configured as a multicopter that flies with lift and thrust generated by rotation of six rotors 13. The unmanned aircraft 1 identifies a forced landing site in a case of having detected an abnormality during flight and controls motors 12 configured to drive the respective rotors 13, to make a landing at the identified forced landing site. The unmanned aircraft 1 is consequently enabled to make an autonomous forced landing at a specific site in case of an abnormality.