One embodiment of a propulsion system for omnidirectional maneuverability and efficient forward flight of an airship comprising only fixed, unidirectional engines (17, 19, 20). The thrust vectors of the fixed engines (19, 20) are oriented in a way that their speeds can be chosen such that all forces acting on the airship (i.e., engine thrusts, gravity, buoyancy, wind and potentially others) are together resulting in the desired motion. In one embodiment these are four ducted fans (17) at the bow and four ducted fans (19) at the stern of the aircraft. Their thrust vectors can be decomposed into three vectors of equal length that are each parallel to one of the three axis of a cartesian coordinate system like defined in FIG. 8. In one embodiment efficient forward flight is achieved by an additional engine (20) at the stern of the airship.

One embodiment of a propulsion system for omnidirectional maneuverability and efficient forward flight of an airship comprising only fixed, unidirectional engines (17, 19, 20). The thrust vectors of the fixed engines (19, 20) are oriented in a way that their speeds can be chosen such that all forces acting on the airship (i.e., engine thrusts, gravity, buoyancy, wind and potentially others) are together resulting in the desired motion. In one embodiment these are four ducted fans (17) at the bow and four ducted fans (19) at the stern of the aircraft. Their thrust vectors can be decomposed into three vectors of equal length that are each parallel to one of the three axis of a cartesian coordinate system like defined in FIG. 8. In one embodiment efficient forward flight is achieved by an additional engine (20) at the stern of the airship.

A method and apparatus for controlling movement of an aircraft. An aerodynamic function desired for controlling the movement of the aircraft at a particular altitude is identified. The aerodynamic function identified is part of a group of aerodynamic functions used to control the movement of the aircraft at a number of different altitudes. A group of inflatable blades is filled with a fluid to a pressure that corresponds to the aerodynamic function. The group of inflatable blades at the pressure has a shape and a group of dimensions that provide the aerodynamic function.

A method and apparatus for controlling movement of an aircraft. An aerodynamic function desired for controlling the movement of the aircraft at a particular altitude is identified. The aerodynamic function identified is part of a group of aerodynamic functions used to control the movement of the aircraft at a number of different altitudes. A group of inflatable blades is filled with a fluid to a pressure that corresponds to the aerodynamic function. The group of inflatable blades at the pressure has a shape and a group of dimensions that provide the aerodynamic function.

A surveillance drone is disclosed. The surveillance drone includes a gas-filled container and propellers for aerial mobility. The surveillance drone also includes an electronic surveillance sensing device positioned below the gas-filled container. The gas-filled container may be filled with a lighter than air gas such as, for example, helium.

A surveillance drone is disclosed. The surveillance drone includes a gas-filled container and propellers for aerial mobility. The surveillance drone also includes an electronic surveillance sensing device positioned below the gas-filled container. The gas-filled container may be filled with a lighter than air gas such as, for example, helium.

An autonomous airborne carbon dioxide capturing assembly for carbon dioxide sequestration includes a plurality of airships each including a propulsion and navigation system, a sensor, and a carbon dioxide (CO.sub.2) capture and liquefaction module. The sensor measures CO.sub.2 concentrations. A computer is operationally engaged to the propulsion and navigation system, the sensor, the CO.sub.2 capture and liquefaction module, a positioning transceiver, and a communications transceiver. The computer automates decision-making and selectively actuates the propulsion and navigation system for controlled flight to a target area, to selectively actuate the CO.sub.2 capture and liquefaction module to capture and to liquefy CO.sub.2 from air at the target area, and to selectively actuate the propulsion and navigation system for controlled flight to a CO.sub.2 storage facility for offloading of the CO.sub.2.

An autonomous airborne carbon dioxide capturing assembly for carbon dioxide sequestration includes a plurality of airships each including a propulsion and navigation system, a sensor, and a carbon dioxide (CO.sub.2) capture and liquefaction module. The sensor measures CO.sub.2 concentrations. A computer is operationally engaged to the propulsion and navigation system, the sensor, the CO.sub.2 capture and liquefaction module, a positioning transceiver, and a communications transceiver. The computer automates decision-making and selectively actuates the propulsion and navigation system for controlled flight to a target area, to selectively actuate the CO.sub.2 capture and liquefaction module to capture and to liquefy CO.sub.2 from air at the target area, and to selectively actuate the propulsion and navigation system for controlled flight to a CO.sub.2 storage facility for offloading of the CO.sub.2.

A lighter than air airship (1) comprising a gas-filled flexible hull (2) which is elongate with a longitudinal axis (1) and with a front end (4) and a rear end (5), wherein a harness-structure (3) is abutting an outer side of the hull (2) and not perturbing the hull and not extending through the hull, the harness-structure (3) is made of a bendable material and carries a propeller engine (10) for forward thrust of the airship (1), rechargeable batteries (11) for providing electrical power to the propeller engine (10), and a solar panel for providing electrical power to recharge the batteries (11).

A lighter than air airship (1) comprising a gas-filled flexible hull (2) which is elongate with a longitudinal axis (1) and with a front end (4) and a rear end (5), wherein a harness-structure (3) is abutting an outer side of the hull (2) and not perturbing the hull and not extending through the hull, the harness-structure (3) is made of a bendable material and carries a propeller engine (10) for forward thrust of the airship (1), rechargeable batteries (11) for providing electrical power to the propeller engine (10), and a solar panel for providing electrical power to recharge the batteries (11).