In an aspect, a system for vibration monitoring of an electric aircraft. A system include a propulsor. A system includes a sensor coupled to a propulsor. A sensor is configured to measure a vibration datum of a propulsor and transmit the vibration datum to a flight controller. A flight controller is configured to receive a vibration datum from a sensor. A flight controller is configured to generate a throttle datum as a function of a vibration datum. A flight controller is configured to transmit a throttle datum to a propulsor.

A device attachable to an aerial vehicle that incorporates electronics to control sensor position data and verify safety of aerial vehicle landing area. The device may be easily attached to an existing aerial vehicle. The device monitors sensor data from one or more distance measuring sensors and pressure sensors to set an angle of incidence for the distance measuring sensors. This pressure sensor derived angle setting allows for a continual data mapping of the aerial vehicles landing area to enhance and improve the landing zone.

A robot including a hybrid fan-based and fluid-based propulsion system to provide thrust, such as deceleration during fall to create a smooth landing or to provide a quick reduction in velocity, and to provide actuation/controlled motion, such as to hover after quick deceleration and to control orientation or pose. The hybrid propulsion system uses discharging of pressurized fluid and exhausted gas (or fluid in some cases) from ducted fans (or propellers, impellers, and the like) to provide controlled thrust and/or lift forces. The hybrid propulsion system uses of pressurized fluid for generating larger or primary thrust and quick changes in velocity. The hybrid propulsion system includes a fan-based propulsion assembly with ducted fans that use environmental air (or fluids) to provide lower or secondary thrust. Both types of propulsion can be integrated into a robot or robotic figure to move the robot during flight (e.g., during falling or hovering).

A system and method for the transfer of cryogenic fluid fuel includes a nozzle positionable with respect to fuel tank inlet, e.g., of an unmanned aerial vehicle (UAV), a seal to seal the area where the nozzle and inlet are connected, a collapsible and expandable bellows providing an isolation volume where the fluid is transferred from the nozzle into the inlet; a vacuum is provided in the volume to avoid accumulation of fuel or other species in the volume.

The present invention comprises a device designed to fly in planetary atmospheres via the photophoretic force. The photophoretic force may result from the phenomena of ΔT photophoresis, Δα photophoresis, and/or thermal creep flow. Certain embodiments of the structure may control flight by changing the direction of the net photophoretic force through structural elements that impart magnetic, electric, or gravitational torques on the entire structure. Payloads with many conceivable uses may be integrated into this invention. Examples of use include but are not limited to wireless data communications, optical devices, microelectronics, and remote sensing technologies.

A liquid propelled unmanned aerial vehicle includes a carrier and a nozzle assembly mounted to the carrier. The nozzle assembly includes a nozzle adapted to eject a liquid propulsion jet, and a liquid inlet connection in fluid communication with the nozzle to connect the nozzle assembly to a pressurized liquid source. The nozzle has a variable orientation relative to the carrier. A control unit is operationally connected to the moveable nozzle so as to control the orientation of the nozzle and thereby the direction of the propulsion jet. A stabilising weight is suspended from the carrier and arranged such that a centre of gravity of the aerial vehicle is located in use below the nozzle.

Provided is an aerial vehicle having a structure in which a rotating body has been excluded from a portion that can be touched by a user during flight. An aerial vehicle includes: a balloon unit; a control unit provided at the bottom of the balloon unit; and a plurality of micro-mechanisms (micro blowers), each of which blows out air. The micro blowers have a structure in which a vibrating member is vibrated in a space in communication with a plurality of openings, thereby blowing out, through a second opening, the air that has flowed into the space through a first opening. The control unit controls the micro blowers to change the position or the attitude of the aerial vehicle.

The present invention relates to a target positioning method and device, and an unmanned aerial vehicle. The method includes: acquiring a target image through an image acquisition device; acquiring the position information of a target in the target image according to the target image; acquiring original point clouds of an environment in front of the unmanned aerial vehicle through a depth sensor; acquiring the point clouds corresponding to the target in the original point clouds according to the original point clouds and the position information of the target in the target image; and acquiring the position information of the target in a three-dimensional space according to the point clouds corresponding to the target.

A system and method for the transfer of cryogenic fluid fuel includes a nozzle positionable with respect to fuel tank inlet, e.g., of an unmanned aerial vehicle (UAV), a seal to seal the area where the nozzle and inlet are connected, a collapsible and expandable bellows providing an isolation volume where the fluid is transferred from the nozzle into the inlet; a vacuum is provided in the volume to avoid accumulation of fuel or other species in the volume.

The present invention discloses a wirelessly controlled vehicle that is configured to travel in air, on liquid and under liquid with an ability to communicate with a remote operator through wireless communication.