A portable wireless aircraft security monitoring system including first, second and third apparatuses configured to removably attach to an exterior of an aircraft via vacuum suction mounting devices that may include one or more suction cups. The first and second apparatus may include a camera, a motion sensor, a microphone/speaker, and a data processor; and wherein the camera, motion sensor, and the microphone provide information to the data processor, which wirelessly communicates with the device of the third apparatus to communicate via the Internet to a user smartphone software application. The third apparatus may include a Wi-Fi wireless router hotspot configured to connect to the Internet and may broadcast a Wi-Fi signal which allows the Wi-Fi enabled first and second apparatus to connect to the internet to send/receive data alerts to the user's smartphone.

A flying machine having a light weight housing is described. Th light weight housing includes a cabin for housing one or more passengers, a flight control system, and at least two nonpneumatic wheels. Each non-pneumatic wheel includes a ground contacting annular tread portion; a plurality of vanes extending between a hub of the non-pneumatic wheel and the annular tread, wherein each vane is formed of a reinforced layer of fabric, wherein each nonpneumatic wheel is mounted on a rotatable support arm, and wherein the wheel is rotated at a high rate of speed to generate lift of the flying machine.

An aeronautical car includes a ground-travel system including a drivetrain; an air-travel system including a detachable portion configured to house a propulsion device configured to provide thrust and to be driven by the drivetrain when the detachable portion is connected to the aeronautical car, and at least one flight mechanism configured to provide lift once the aeronautical car is in motion; and a weather manipulation device. The weather manipulation device may be configured to manipulate at least one aspect of a weather condition while the aeronautical car is in the air.

A method is described to stabilize a reflector in the upper atmosphere to reflect solar irradiance back into Space before it can be absorbed or scattered by Earth's atmosphere. Thin reflective sheets are flown under control in the upper atmosphere above Earth, in contrast to reflecting from Space orbits or the ground. The high altitude enables nearly total reflection. This embodiment uses buoyant aerostatic lift and pneumatic pressure to support and hold sheets stretched while providing aerostatic lift. During the daytime solar power is used to provide energy for propulsion and gain altitude by volume expansion. During the night the aerostatic lift holds the system above controlled airspace. Edgewise gliding permits seasonal movement of the system and station-keeping. In one example application, a swarm of aerostatically stabilized reflectors placed around the edge of the Antarctic continent will reduce summer melting of ice, in order to reverse the rise in sea level.

A system for redirecting light to a mobile platform includes a satellite and a mobile platform including a first RF antenna that transmits a trajectory data for the mobile platform, and a photovoltaic cell that converts light into electrical energy. The satellite includes a second RF antenna that receives the trajectory data, and a processor coupled to the second RF antenna. The processor computes a target position of the mobile platform based on the trajectory data, and instructs a diffuser system to generate the beam of light and direct the beam to the target position.

The present invention relates to a hydrogen recycling flight system and flight method, the hydrogen recycling flight system including: a flight fuselage which has at least one pair of wings at each of both sides of a body; a hydrogen gas balloon which is air-tightly connected to the flight fuselage; a hydrogen fuel cell which is connected with the hydrogen gas balloon and is installed outside or inside the flight fuselage; and a secondary battery which is charged with electricity generated from the hydrogen fuel cell, electricity generated from a solar cell provided at an outer peripheral portion of the flight fuselage, or electricity of an external power network, in which by using a switch, the hydrogen fuel cell is switched to a water electrolysis device or the water electrolysis device is switched to the hydrogen fuel cell, the hydrogen recycling flight system includes: a water tank which stores water generated from the hydrogen fuel cell; the water electrolysis device which electrolyzes the stored water; a switch control device which switches functions of the hydrogen fuel cell and the water electrolysis device; and a high-pressure gas barrel which high-pressure stores hydrogen gas and oxygen gas generated in the water electrolysis device, and the flight fuselage flies by controlling the volume of the hydrogen gas balloon that is flotation power of a flight vehicle by an operation of the hydrogen fuel cell or the high-pressure gas barrel.

A vacuum lighter than air vehicle (VLTAV) includes a rigid frame of rods connected together to form a hexakis icosahedron. A membrane skin covers the rigid frame and defines therewith a vessel configured to hold an internal vacuum that allows the vessel to float in the air. The plurality of rods and membrane skin have weights and dimensions that result in a neutral and/or positive buoyancy for the vessel while preventing geometric instability.

An assembly and a method for powering an electric aircraft by way of a supplementary energy-supplying device. The electric energy delivered by such device reduces the energy drawn from the battery and recharges the battery when the supplementary electrical power exceeds that consumed. A greater extension of the flight time may be achieved by defining a number of energy profiles that can be automatically activated by energy management components. In the preferred embodiment of the invention, the supplementary energy-supplying device is a photovoltaic film covering at least a portion of a frame of the aircraft. The invention relates also to an electric aircraft equipped with the assembly.

An aircraft includes a body defining an interior compartment configured to hold at least one of a passenger and a payload, a battery system, a plurality of arms coupled to and extending from the body, and a plurality of propulsion devices configured to provide thrust to fly the aircraft. Each of the plurality of propulsion devices is coupled to a respective one of the plurality of arms. The plurality of propulsion devices are powered by the battery system. Each of the plurality of propulsion devices is selectively pivotable about at least one axis. The plurality of propulsion devices include at least one of (i) counter rotating ducted fans and (ii) ionizing electrode engines.

A microelectronic module for cleaning a surface is described. The microelectronic module comprises at least one voltage converter for converting a provided first voltage into a higher, lower, or identical second voltage. The module also comprises at least one actuator. The actuator comprises at least one generator for generating an ionic current, an electrical plasma, harmonic components and/or an electrostatic field from the second voltage which is provided by the voltage converter. At least the voltage converter and the actuator are disposed on a thin-film, planar substrate. At least most of at least one object adhering to the surface is removed by the actuator.