A flexible electric cable for the electric power supply of planes on the ground is subjected to an unspooling and spooling process, the cable having a conductor layout including a plurality of insulated energy supply conductors which are arranged concentrically with respect to a longitudinal central axis of the generally circular in cross-section cable, several insulated neutral conductors which are arranged concentrically with respect to the central axis, and several insulated control conductors which are arranged concentrically with respect to the central axis. A non-metallic, tension- and compression-resistant support member is disposed at the center of the cable, which support member extends over the length of the cable. At least the energy supply conductors include CCA wires having a copper content of at least 15%.

A flexible electric cable for the electric power supply of planes on the ground is subjected to an unspooling and spooling process, the cable having a conductor layout including a plurality of insulated energy supply conductors which are arranged concentrically with respect to a longitudinal central axis of the generally circular in cross-section cable, several insulated neutral conductors which are arranged concentrically with respect to the central axis, and several insulated control conductors which are arranged concentrically with respect to the central axis. A non-metallic, tension- and compression-resistant support member is disposed at the center of the cable, which support member extends over the length of the cable. At least the energy supply conductors include CCA wires having a copper content of at least 15%.

An autogyro includes a frame and a rotor hub coupled to the frame. The autogyro also includes a connector coupled to the rotor hub and configured to couple the rotor hub to a ground-based pre-rotator device to rotate the rotor hub during a vertical take-off operation. The autogyro further includes a plurality of rotor blades coupled to the rotor hub, each rotor blade configured such that rotation of the rotor hub, during the vertical take-off operation, results in twisting the rotor blade from a first blade pitch distribution to a second blade pitch distribution.

An autogyro includes a frame and a rotor hub coupled to the frame. The autogyro also includes a connector coupled to the rotor hub and configured to couple the rotor hub to a ground-based pre-rotator device to rotate the rotor hub during a vertical take-off operation. The autogyro further includes a plurality of rotor blades coupled to the rotor hub, each rotor blade configured such that rotation of the rotor hub, during the vertical take-off operation, results in twisting the rotor blade from a first blade pitch distribution to a second blade pitch distribution.

A mobile vehicle for supplying pressurized air to an aircraft, the vehicle being configured to tow the aircraft during its movements on the ground and including a pneumatic supply system configured to supply pressurized air to the aircraft, the pneumatic supply system being manually connectable to a high-pressure connector of the aircraft and remotely disconnectable from the connector.

A mobile vehicle for supplying pressurized air to an aircraft, the vehicle being configured to tow the aircraft during its movements on the ground and including a pneumatic supply system configured to supply pressurized air to the aircraft, the pneumatic supply system being manually connectable to a high-pressure connector of the aircraft and remotely disconnectable from the connector.

Various embodiments of the present disclosure provide a parasail-assisted system for launching a fixed-wing aircraft into free flight and for retrieving a fixed-wing aircraft from free flight.

Various embodiments of the present disclosure provide a parasail-assisted system for launching a fixed-wing aircraft into free flight and for retrieving a fixed-wing aircraft from free flight.

Systems and methods for starting a powerplant are provided. In one exemplary aspect, a starting system of a powerplant includes one or more features that allow for the powerplant to be started electrically with a burst of electrical power and without deriving electrical power from an offboard power source or a relatively heavy onboard energy storage device.

A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed, where the controller modulates a duty cycle of the discrete starter valve via pulse width modulation.