A hybrid aircraft system uses a combination of direct propeller driven gas engine and electric motor power to provide vertical thrust and control for hover of the aircraft. Furthermore, a portable launch/recovery system is configured for use with an aircraft such as a Vertical Takeoff and Landing (VTOL) Unmanned Air Vehicle (UAV). The system is configured to enable ships with limited available deck space to become UAV-compatible.

Disclosed is a sonobuoy that houses at least one unmanned vehicle that may be launched from the sonobuoy. The sonobuoy may include a canister, a parachute, an unmanned vehicle, and a launch mechanism. The parachute may be disposed within an interior cavity of the canister proximate to a first end of the canister. The unmanned vehicle may be disposed within the interior cavity of the canister proximate to a second end of the canister. The launch mechanism may be disposed within the interior cavity of the canister and operatively coupled to the unmanned vehicle. The launch mechanism may be configured to launch the unmanned vehicle from the canister. The sonobuoy may further include a launch deployment mechanism that may be configured to orient the canister with respect to a surface after the sonobuoy impacts the surface in order to facilitate the launch of the unmanned vehicle.

Disclosed is a sonobuoy that houses at least one unmanned vehicle that may be launched from the sonobuoy. The sonobuoy may include a canister, a parachute, an unmanned vehicle, and a launch mechanism. The parachute may be disposed within an interior cavity of the canister proximate to a first end of the canister. The unmanned vehicle may be disposed within the interior cavity of the canister proximate to a second end of the canister. The launch mechanism may be disposed within the interior cavity of the canister and operatively coupled to the unmanned vehicle. The launch mechanism may be configured to launch the unmanned vehicle from the canister. The sonobuoy may further include a launch deployment mechanism that may be configured to orient the canister with respect to a surface after the sonobuoy impacts the surface in order to facilitate the launch of the unmanned vehicle.

A barge for recovery of a rocket launch vehicle is proposed, which can recover a launch vehicle from the sea onto the land in safety during launch vehicle recovering work. The barge can recover the launch vehicle in safety by effectively preventing a slope of the structure which supports the launch vehicle.

A barge for recovery of a rocket launch vehicle is proposed, which can recover a launch vehicle from the sea onto the land in safety during launch vehicle recovering work. The barge can recover the launch vehicle in safety by effectively preventing a slope of the structure which supports the launch vehicle.

Disclosed is a device and method to load stores on an aircraft. The device may include a controller configured to: assign one or more stores to the aircraft; and control at least one actuator to: control a position of the aircraft; load the one or more stores onto one or more corresponding lift portions; position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from at least one sensor; and secure the one or more stores to the aircraft.

Disclosed is a device and method to load stores on an aircraft. The device may include a controller configured to: assign one or more stores to the aircraft; and control at least one actuator to: control a position of the aircraft; load the one or more stores onto one or more corresponding lift portions; position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from at least one sensor; and secure the one or more stores to the aircraft.

The invention relates to a landing zone arrangement (1) for aircraft (19), in particular aircraft capable of vertical take-off, said arrangement comprising: a plurality of segments (3) which together form a landing zone in an operating state; a storage space (2) in which the plurality of segments (3) are at least partially stowable in a stored state; and a base (5) with a rotatable rotor element (4) in order to rotate the plurality of segments (3) for transfer into the operating state and/or into the stored state. In order to create a landing zone arrangement which allows a lighter technical design, the invention provides that at least individual segments of the plurality of segments (3) are secured removably to the rotor element (4), and a securing unit (8) of the landing zone arrangement (1) is designed to fasten the removable segments (3) to the rotor element (4) for transfer into the operating state and to release this fastening for transfer into the stored state. A lifting unit (9) is provided, which has one or more lifting elements (10) arranged in or on the storage space (2) in order to move the removable segments (3) in the direction of the rotor element (4) when transferring into the operating state.

The invention relates to a landing zone arrangement (1) for aircraft (19), in particular aircraft capable of vertical take-off, said arrangement comprising: a plurality of segments (3) which together form a landing zone in an operating state; a storage space (2) in which the plurality of segments (3) are at least partially stowable in a stored state; and a base (5) with a rotatable rotor element (4) in order to rotate the plurality of segments (3) for transfer into the operating state and/or into the stored state. In order to create a landing zone arrangement which allows a lighter technical design, the invention provides that at least individual segments of the plurality of segments (3) are secured removably to the rotor element (4), and a securing unit (8) of the landing zone arrangement (1) is designed to fasten the removable segments (3) to the rotor element (4) for transfer into the operating state and to release this fastening for transfer into the stored state. A lifting unit (9) is provided, which has one or more lifting elements (10) arranged in or on the storage space (2) in order to move the removable segments (3) in the direction of the rotor element (4) when transferring into the operating state.

A chair for use in take-off or landing of a user wearing personal flying equipment may include a seat for the user to straddle such that the user faces in a forward direction. The chair may include a torso support for supporting a torso of the user sitting on the seat. The torso support may be concave and define an opening facing the seat. The seat and torso support may be mounted to a structure. A base member may be rigidly connected to the structure and may extend outwardly from either side of the structure, leaving a space below the structure for receiving a leg of the user when the user sits on the seat.