In some embodiments, an apparatus, comprises an unmanned vehicle configured to be disposed with a vehicle and a processor operatively coupled to the unmanned vehicle. The processor is configured to receive a first signal indicating a stop of the vehicle without a user request and a second signal indicating a location of the vehicle. The processor is configured to determine, based on the location of the vehicle, a target location in a pre-defined area surrounding the vehicle. The processor is configured to send a third signal to the unmanned vehicle to instruct the unmanned vehicle to move to the target location to alert other vehicles via a warning regarding occurrence of the stop.

Aircraft information systems, aircraft that include the aircraft information systems, methods of utilizing the aircraft information systems, and methods of configuring the aircraft information systems are disclosed herein. The aircraft information systems include a fixed computing device configured to be fixedly installed within an aircraft. The fixed computing device is programmed to provide a cabin function interface that provides cabin functionality for a cabin attendant of the aircraft and also to provide a mechanic function interface that provides mechanic functionality for a mechanic for the aircraft. The aircraft include a fuselage, at least one wing, at least one engine, and the aircraft information systems.

An exterior aircraft image projector includes at least one light source, providing a light output in operation; an optical system configured for transforming the light output of the at least one light source into a light beam and projecting said light beam onto the ground below the aircraft and the of the aircraft; a photo detector arranged to detect a brightness level (Iambient) of the ground or the exterior and configured to provide a corresponding brightness signal; and a controller, coupled to the photo detector and the at least one light source configured to control an intensity of the light output of the at least one light source as a function of the brightness level (Iambient), as provided by the photo detector via the brightness signal.

An aircraft includes a fuel cell-powered electric engine system configured to power the aircraft and produce water vapor exhaust, and an exhaust system configured to receive the water vapor exhaust, condense the water vapor into ice or water, and expel the ice or water from the aircraft such that water vapor cloud formation is inhibited. A method of powering an aircraft includes operating a fuel cell-powered electric engine system to power the aircraft, condensing water vapor exhaust of the fuel cell-powered electric engine system into ice or water, and expelling the ice or water from the aircraft such that water vapor cloud formation is inhibited.

An aircraft includes a fuel cell-powered electric engine system configured to power the aircraft and produce water vapor exhaust, and an exhaust system configured to receive the water vapor exhaust, condense the water vapor into ice or water, and expel the ice or water from the aircraft such that water vapor cloud formation is inhibited. A method of powering an aircraft includes operating a fuel cell-powered electric engine system to power the aircraft, condensing water vapor exhaust of the fuel cell-powered electric engine system into ice or water, and expelling the ice or water from the aircraft such that water vapor cloud formation is inhibited.

A gravity simulation system, including a computing system running a program thereon to receive input for a gravity environment and calculate the gravity environment based on a predetermined gravity algorithm, and a gravity simulation aircraft connected to the computing system to simulate the gravity environment received from the computing system based on at least one of a flight setting and a gravity setting.

A gravity simulation system, including a computing system running a program thereon to receive input for a gravity environment and calculate the gravity environment based on a predetermined gravity algorithm, and a gravity simulation aircraft connected to the computing system to simulate the gravity environment received from the computing system based on at least one of a flight setting and a gravity setting.

Aspects relate to methods and systems for optimizing battery recharge management for use with an electric vertical take-off and landing aircraft. An exemplary system includes an electric vertical take-off and landing (eVTOL) aircraft comprising at least battery mechanically coupled to the eVTOL aircraft and configured to power at least an aircraft component of the eVTOL aircraft, wherein the at least a battery comprises a plurality of battery cells, and at least a sensor, configured to measure battery data associated with the at least a battery, and a server remote from the eVTOL and in communication with the at least a sensor, wherein the server is configured to receive the battery data from the at least a sensor, receive mission data associated with a planned flight mission of the eVTOL aircraft, and generate a recharge time as a function of the battery data and the mission data.

A support frame is provided that includes an upper plate, a lower plate, side support members, an upper support structure, and a lower support structure. The upper plate defines a first inner surface and an opposed first outer surface. The lower plate defines a second inner surface and an opposed second outer surface. A TEM test space is defined between the first inner surface and the second inner surface. The side support members are disposed between the upper plate and the lower plate proximate a periphery of the test space. The upper support structure is coupled to and supports the upper plate. The upper support structure extends from the first outer surface of the upper plate. The lower support structure is coupled to and supports the lower plate. The lower support structure extends from the second outer surface of the lower plate.

A support frame is provided that includes an upper plate, a lower plate, side support members, an upper support structure, and a lower support structure. The upper plate defines a first inner surface and an opposed first outer surface. The lower plate defines a second inner surface and an opposed second outer surface. A TEM test space is defined between the first inner surface and the second inner surface. The side support members are disposed between the upper plate and the lower plate proximate a periphery of the test space. The upper support structure is coupled to and supports the upper plate. The upper support structure extends from the first outer surface of the upper plate. The lower support structure is coupled to and supports the lower plate. The lower support structure extends from the second outer surface of the lower plate.