A power supply system includes a rotor for generating at least one of lift or thrust of an aircraft, a component group formed of a plurality of electrical components for rotating the rotor, and a battery for supplying power to the component group. The rotor includes a VTOL rotor and a cruise rotor, and the component group includes a VTOL component group and a cruise component group. The VTOL component group and the cruise component group are supplied with power from the same battery.

An aircraft has a first antenna arrangement, a payload and a processing unit. The first antenna arrangement is designed to wirelessly receive electromagnetic signals. The processing unit is coupled to the first antenna arrangement, on the one hand, and to the payload, on the other hand. The processing unit is designed to modulate an electromagnetic signal received by the first antenna arrangement and thereby to generate a first modulated signal and to forward it to the payload. The payload is designed to use the first modulated signal as working signal. A radiofrequency power signal on an uplink is thus remodulated into a payload working signal, such that the payload working signal is able to be used directly by the payload without rectification into a DC voltage.

An aircraft has a first antenna arrangement, a payload and a processing unit. The first antenna arrangement is designed to wirelessly receive electromagnetic signals. The processing unit is coupled to the first antenna arrangement, on the one hand, and to the payload, on the other hand. The processing unit is designed to modulate an electromagnetic signal received by the first antenna arrangement and thereby to generate a first modulated signal and to forward it to the payload. The payload is designed to use the first modulated signal as working signal. A radiofrequency power signal on an uplink is thus remodulated into a payload working signal, such that the payload working signal is able to be used directly by the payload without rectification into a DC voltage.

Flight control unit and flight unit start flight in accordance with a flight plan. Flight history acquisition unit acquires a flight history of drone. Flight plan acquisition unit acquires a flight plan for drone. Inspection timing determination unit calculates a difference between the acquired flight plan and the acquired flight history, and based on the difference, determines an inspection timing for drone. Inspection timing notification unit provides notification of the determined inspection timing.

This method comprises: obtaining first data representative of amounts of a first gas and second data representative of amounts of a second tracer gas emitted by the source together with the first gas, calculating at least one coefficient of correlation between the amounts of the first gas and the amounts of the second gas from the first representative data and the second representative data; obtaining a measured or computed flow of the second gas emitted by the source; computing a flow of the first gas emitted by the source on the basis of the measured or computed flow of the second gas emitted by the source and the correlation coefficient.

A system including a payload bay having at least one sensor configured to determine the identity of an object being transported in the payload bay and verify that the object is properly seated within the payload bay. As an object is inserted into the payload bay of the vehicle, the sensor(s) detects a pattern located on the side of the object. As the sensor(s) detects the pattern, it transmits information that enables the system to determine both the identity of the object and position of the object within the payload bay. In this way, the sensor(s) enables the system to identify when a wrong object is loaded into the payload bay, and/or when the object is improperly seated within the payload bay.

A system including a payload bay having at least one sensor configured to determine the identity of an object being transported in the payload bay and verify that the object is properly seated within the payload bay. As an object is inserted into the payload bay of the vehicle, the sensor(s) detects a pattern located on the side of the object. As the sensor(s) detects the pattern, it transmits information that enables the system to determine both the identity of the object and position of the object within the payload bay. In this way, the sensor(s) enables the system to identify when a wrong object is loaded into the payload bay, and/or when the object is improperly seated within the payload bay.

A system and method for distributing control over a drone and an active-payload carried by the drone to loosely coupled drone controller and payload controller, are disclosed. The active-payload includes a self-embedded payload controller and at least one controllable thrust source or moving weight. The drone controller identifies a current active-payload type that is coupled to the drone for performing one or more tasks and selects a control-type, which defines degrees of freedom (DOFs) to be controlled by the drone controller and released DOFs to be controlled by the payload controller, accordingly. The drone and active-payload perform the one or more task, wherein the drone controller controls maneuver instructions in drone controller controlled DOFs and simultaneously and asynchronously the payload controller controls maneuver instructions in the released DOFs by exerting controllable force or torque in the released DOFs by the at least one thrust source and/or moving weight.

A system and method for distributing control over a drone and an active-payload carried by the drone to loosely coupled drone controller and payload controller, are disclosed. The active-payload includes a self-embedded payload controller and at least one controllable thrust source or moving weight. The drone controller identifies a current active-payload type that is coupled to the drone for performing one or more tasks and selects a control-type, which defines degrees of freedom (DOFs) to be controlled by the drone controller and released DOFs to be controlled by the payload controller, accordingly. The drone and active-payload perform the one or more task, wherein the drone controller controls maneuver instructions in drone controller controlled DOFs and simultaneously and asynchronously the payload controller controls maneuver instructions in the released DOFs by exerting controllable force or torque in the released DOFs by the at least one thrust source and/or moving weight.

A coated wire suitable for aerospace applications includes a metallic conductor elongated along an axis and having an outer surface extending along the axis, and three coating layers surrounding the conductor. A first coating layer is connected to the outer surface of the conductor and extends along the axis to surround the conductor, and the first coating layer is formed of ethene-tetrafluoroethene. A second coating layer is connected to the first coating layer and extends along the axis to surround the first coating layer, and the second coating layer is formed of polyaryletherketone. A third coating layer is connected to the second coating layer and extends along the axis to surround the third coating layer, wherein the third coating layer is formed of ethene-tetrafluoroethene. The three coating layers may each be continuous and seamless extruded layers in one configuration.