Provided is an airbag device for a flying object sufficiently having a performance of protecting a battery.

An airbag device 1 is an airbag device for a flying object including an upper cover member 19 and a lower cover member 20 as a housing, and a battery 24 provided inside the housing and includes an expandable member 2 which is provided inside the housing of the flying object 10 and is expandable inside the housing, a gas generator 3 which is connected to the expandable member 2 and receives a predetermined amount of current to make gas flow into the expandable member 2, and a current supply section which supplies current to the gas generator 3 according to collision of the flying object 10.

An apparatus for preconditioning a power source of an electric aircraft is presented. The apparatus includes a power source of an electric aircraft, a computing device, and a user device. The computing device is configured to receive a flight plan, determine a predicted power usage model as a function of the flight plan, and initiate a power source modification on the electric aircraft as a function of the predicted power usage model. The user device is configured to display a flight performance infographic as a function of the predicted power usage model.

An apparatus for preconditioning a power source of an electric aircraft is presented. The apparatus includes a power source of an electric aircraft, a computing device, and a user device. The computing device is configured to receive a flight plan, determine a predicted power usage model as a function of the flight plan, and initiate a power source modification on the electric aircraft as a function of the predicted power usage model. The user device is configured to display a flight performance infographic as a function of the predicted power usage model.

A system for the prioritization of flight controls in an electric aircraft is illustrated. The system includes a plurality of flight components, a sensor, and a computing device. The plurality of flight components are coupled to the electric aircraft. The sensor is coupled to each flight component of the plurality of flight components. Each sensor of the plurality of sensors is configured to detect a failure event of a flight component of the plurality of flight components and generate a failure datum associated to the flight component of the plurality of flight components. The computing device is communicatively connected to the sensor and is configured to receive the failure datum associated to the flight component of the plurality of flight component from the sensor, determine a prioritization element as a function of the failure datum, and restrict at least a flight element as a function of the prioritization element.

A system for monitoring moisture content in a battery pack of an electric aircraft. The system includes a at least an energy storage element, a user interface configured to display moisture content datum to a user, and at least a sensor. At least a sensor is configured detect a moisture content datum of the energy storage element and communicate with the energy storage element. The system also includes a computing device communicatively connected to the at least a sensor. That computing device is configured to generate a notification as a function of the moisture content datum and transmit the notification to a user interface.

A system for monitoring moisture content in a battery pack of an electric aircraft. The system includes a at least an energy storage element, a user interface configured to display moisture content datum to a user, and at least a sensor. At least a sensor is configured detect a moisture content datum of the energy storage element and communicate with the energy storage element. The system also includes a computing device communicatively connected to the at least a sensor. That computing device is configured to generate a notification as a function of the moisture content datum and transmit the notification to a user interface.

An apparatus for loading and unloading cargo, capable of loading cargo while distributing the weight of the cargo and unloading the cargo regardless of the loading order of the cargo, is provided. The apparatus for loading and unloading cargo may include: a base portion; a rail installed on the base portion; a plurality of movable plates disposed on the rail, supporting the cargo, and moving along the rail; and a raising-lowering portion connected between the base portion and a body so that the base portion can be raised and lowered.

The invention relates to an electronic display device on board an aircraft capable of landing or maintaining a hover above a landing zone and comprising: a module for calculating a distance between the aircraft and the landing zone according to a horizontal direction and for determining a height of the aircraft; and a module for displaying an exocentric aircraft symbol, positioned at a distance said exocentric from the aircraft according to an exocentric direction and at a height difference said exocentric relative to the aircraft, the display module being further configured to display an exocentric landing zone symbol, positioned at a distance from the landing zone equal to the exocentric distance according to the exocentric direction and at the same height as the exocentric aircraft symbol.

Embodiments are directed to systems and methods for estimating wear in aircraft rotor systems. Data associated with loads and motions of a swashplate actuator is collected. The swashplate actuator drives a swashplate and at least one control link is coupled to the swashplate. The loads and motions of the at least one control link is estimated based upon the loads and motions of the swashplate actuator. Using a wear model, the current wear of control link components is estimated due to the loads and motions of the at least one control link. Wear estimates for the components are aggregated across multiple flights and used to determine when maintenance actions should occur.