A rocket or ballistic launch rotary wing air vehicle may include a rocket or ballistic launch propulsion system for launching the vehicle, a rotary wing flight system for providing powered flight comprising dual counter rotating coaxial rotors, and a control system programmed to adjust the pitch of a rotor to anyh determined degree of pitch independently of a flap angle of the flap hinge during a transition of the dual counter rotating coaxial rotors from a stowed position to a deployed position.

The application relates to a fueling station for a fuel generator having a fuel generator reservoir, the fueling station comprising: a station reservoir (11) for storing at least one reactant for fuel generation; a fueling interface (14) configured to engage with the fuel generator reservoir and dispense the at least one reactant to the fuel generator reservoir; and a controller (18) configured to: receive a parameter indicative of an intended use of the fuel generator; and control the fueling interface to dispense the at least one reactant in accordance with the parameter.

An aerial system includes a body, a propeller coupled to the body, and a motor coupled to the propeller. The motor is configured to rotate the propeller in a first direction, wherein an other portion of the aerial system rotates in an opposing second direction. The other portion of the aerial system that rotation in the opposing second direction may be the body or a second propeller. The aerial system also includes a processing system configured to control the motor to cause the aerial system to hover in a substantially fixed pose, and a camera configured to obtain images of an environment proximate the aerial system while the aerial system is hovering.

Autonomous craft capable of extended duration operations as lighter-than-air craft, having the ability to alight on the surface of a body of water and generate hydrogen gas for lift via electrolysis using power derived from a photovoltaic system, as well as methods of launching an unmanned aerial vehicle (UAV) having a deployable envelope from a surface of a body of water.

A system and a method for providing service on a golf course using a fuel cell drone using a hydrogen fuel cell as a power source to provide various services while preventing a rounding delay of golfers are provided. A fuel cell drone of a system for providing service on a golf course may include a hydrogen fuel tank in which hydrogen is charged, a power pack configured to generate power to drive the fuel cell drone using the hydrogen in the hydrogen fuel tank, and a controller configured to move the fuel cell drone to a docking station or a gas supply place in response to determining that an amount of hydrogen remaining in the hydrogen fuel tank is below a set value.

A system and a method for providing service on a golf course using a fuel cell drone using a hydrogen fuel cell as a power source to provide various services while preventing a rounding delay of golfers are provided. A fuel cell drone of a system for providing service on a golf course may include a hydrogen fuel tank in which hydrogen is charged, a power pack configured to generate power to drive the fuel cell drone using the hydrogen in the hydrogen fuel tank, and a controller configured to move the fuel cell drone to a docking station or a gas supply place in response to determining that an amount of hydrogen remaining in the hydrogen fuel tank is below a set value.

An aircraft that includes a fuselage, an electric motor driven propulsion system, and a fuel cell system configured to provide electricity to the electric motor. The fuel cell system includes a fuel cell, a hydrogen tank, an oxygen tank, an air channel, and a cathode switch. The cathode switch being configured to convert between an air mode, wherein the fuel cell operates utilizing air from the air channel, and an oxygen mode, wherein the fuel cell operates utilizing oxygen from the oxygen tank.

A fluid tank for integration into a structure of an unmanned aircraft includes a shell having a first axial wall, an oppositely arranged second axial wall, an upper side, a lower side, and an enclosed interior, at least one receiving chamber in the interior for storing fluid, and a collection chamber, which is arranged on the lower side and which is fluidically connected to the at least one receiving chamber. The collection chamber includes a bottom surface, through which there extends a drain, wherein a covering surface is arranged above the bottom surface and covers at least a portion of the collection chamber. At least one flow opening could be arranged on an upper side of the collection chamber, which flow opening allows gas bubbles to escape in the direction of the upper side of the fluid tank.

A fluid tank for integration into a structure of an unmanned aircraft includes a shell having a first axial wall, an oppositely arranged second axial wall, an upper side, a lower side, and an enclosed interior, at least one receiving chamber in the interior for storing fluid, and a collection chamber, which is arranged on the lower side and which is fluidically connected to the at least one receiving chamber. The collection chamber includes a bottom surface, through which there extends a drain, wherein a covering surface is arranged above the bottom surface and covers at least a portion of the collection chamber. At least one flow opening could be arranged on an upper side of the collection chamber, which flow opening allows gas bubbles to escape in the direction of the upper side of the fluid tank.

The disclosed embodiments include a trailer for an autonomous vehicle controlled by a command and control interface. The trailer includes a trailer body configured to retain the autonomous vehicle in an undeployed configuration. The trailer also anchors the autonomous vehicle in a deployed configuration. A tether is provided having a first end coupled to the trailer body and a second end that is configured to couple to the autonomous vehicle. A winch is utilized to adjust a length of the tether to move the autonomous vehicle between the undeployed configuration and deployed configuration. Further, a communication system communicates with the command and control interface and the autonomous vehicle to control movement of the autonomous vehicle between the undeployed configuration and deployed configuration.