A landing apparatus for an airship or hybrid air vehicle. The landing apparatus comprises a hollow, non-toroidal, flexible enclosure (103), having a substantially vertical axis (104), and a substantially circular cross-section centred on the axis. A base (122) of the enclosure is arranged to contact the ground. The enclosure (103) is inflatable with air or gas for landing, and deflatable for retraction of the enclosure during flight.

An anchoring platform is disclosed for captive aircraft that addresses problems when handling captive aerostats, including excessive workload required to switch between flying and anchored states. The anchoring platform includes an anchoring device. Cords, together with a confluence point, are wound into the anchoring device, by the winch. The structure for anchoring the captive aircraft is the cradle which bears the aerostat, while the winch exerts tension to hold same static in the structure.

An anchoring platform is disclosed for captive aircraft that addresses problems when handling captive aerostats, including excessive workload required to switch between flying and anchored states. The anchoring platform includes an anchoring device. Cords, together with a confluence point, are wound into the anchoring device, by the winch. The structure for anchoring the captive aircraft is the cradle which bears the aerostat, while the winch exerts tension to hold same static in the structure.

A high altitude atmospheric energy storing apparatus having a new structure, which is conceived to store the energy of low-temperature air located at high altitude in the sky and utilize it as needed, is provided. The high altitude atmospheric energy storing apparatus includes an air tank adapted to store air, an air supply pipe provided such that it extends in a vertical direction and its lower end is connected to the air tank, and a compression device provided in the sky, connected to the upper end of the air supply pipe, and configured to compress air using the wind and supply the compressed air to the air tank through the air supply pipe, thereby enabling air to be compressed by the wind blowing at high altitude and to be then stored in the air tank.

Provided is a transportation system comprising a hybrid vehicle that is propelled on a highway by a linear induction electric motor comprising a stationary motor element (“stator”) and a moving motor element (“rotor”), where the stator is incorporated into a groove in the highway and the rotor is incorporated into the hybrid vehicle and protrudes into the groove in the highway; and where the hybrid vehicle further comprises at least one wing that elevates the hybrid vehicle when propelled to a take-off speed on the highway. Methods of transportation utilizing this hybrid vehicle transportation system are further provided.

Provided is a transportation system comprising a hybrid vehicle that is propelled on a highway by a linear induction electric motor comprising a stationary motor element (“stator”) and a moving motor element (“rotor”), where the stator is incorporated into a groove in the highway and the rotor is incorporated into the hybrid vehicle and protrudes into the groove in the highway; and where the hybrid vehicle further comprises at least one wing that elevates the hybrid vehicle when propelled to a take-off speed on the highway. Methods of transportation utilizing this hybrid vehicle transportation system are further provided.

A hybrid airship-aerostat includes a hull, a motor, a fin, a controller, and a bridle system. The motor is coupled to the hull and is configured to rotate between a thrust configuration and a lift configuration. The motor is configured to generate a lift force, a thrust force, or a combination thereof. The fin is coupled to a tail of the hull and is configured to provide directional control of the hull. The controller is configured to operate the motor and the fin to pilot the hull. The bridle system is configured to removably couple to a first end of a tether.

A hybrid airship-aerostat includes a hull, a motor, a fin, a controller, and a bridle system. The motor is coupled to the hull and is configured to rotate between a thrust configuration and a lift configuration. The motor is configured to generate a lift force, a thrust force, or a combination thereof. The fin is coupled to a tail of the hull and is configured to provide directional control of the hull. The controller is configured to operate the motor and the fin to pilot the hull. The bridle system is configured to removably couple to a first end of a tether.

An anchoring vehicle for anchoring an airship at the tail whilst coupled to a mooring mast at the bow. Airships are generally coupled at the bow to a mooring-mast after landing on the ground. However, vertical gusts can result to a considerable amount of damage to the airship with this mechanism. To avoid such damage, the proposed anchoring mechanism designed as an anchoring vehicle, is coupled via an anchor-mast to the tail of the airship near the height of its middle axis. Thus, the vehicle stabilizes the airship vertically and can independently maneuver horizontally without considerable rolling resistance to a predefined airship position, thus preventing a tilting moment. The all-terrain, autonomous anchoring vehicle captures direction and strength data of horizontal deflection caused by wind power via sensors on the anchoring-mast. A control unit regulates the drive systems for navigation and wheel drive.

An aerostat system with an extended flight envelope in which the aerostat system can safely operate is provided. The aerostat system includes an aerostat, multiple tether groups and a base station. Spatially distinct tether groups allow for improved stability and controllability over a wide range of wind conditions. Independent actuation of the tether groups allows for control of the aerostat pitch and roll angle. A rotating platform including rails to rest the aerostat allows docking without auxiliary tethers, minimizing or eliminating the ground crew required to dock traditional aerostat systems. An optional controller allows remote or autonomous operation of the aerostat system.