A method of stabilizing a payload fitted in a carrier includes providing a first carrier component of the carrier, supporting a second carrier component of the carrier using the first carrier component, and supporting a third carrier component of the carrier using the second carrier component. The first carrier component is configured to permit rotation of the payload about a pitch axis. The second carrier component is configured to permit rotation of the payload about a yaw axis. The third carrier component is configured to permit rotation of the payload about a roll axis and connects to the payload.

A method of stabilizing a payload fitted in a carrier includes providing a first carrier component of the carrier, supporting a second carrier component of the carrier using the first carrier component, and supporting a third carrier component of the carrier using the second carrier component. The first carrier component is configured to permit rotation of the payload about a pitch axis. The second carrier component is configured to permit rotation of the payload about a yaw axis. The third carrier component is configured to permit rotation of the payload about a roll axis and connects to the payload.

Disclosed is an air-ground integrated landslide monitoring method and device. The monitoring method comprises the following steps: step one, performing high-precision (centimeter-level) vertical aerial photogrammetry and oblique photogrammetry on a monitored area by using an unmanned aerial vehicle, and quickly generating a digital topographic map, a digital orthographic map and a digital surface model; step two, performing accurate and intensive monitoring on the monitored area through a monitoring device; and step three, finally sending obtained data to a processor, and after the monitoring data are processed by the processor, sending the data to a remote-control center, so that real-time transformation and spatialization of dynamic landslide monitoring information are achieved. The present disclosure also provides a landslide monitoring device. The landslide monitoring device comprises a control box, a bottom plate and an unmanned aerial vehicle.

Disclosed is an air-ground integrated landslide monitoring method and device. The monitoring method comprises the following steps: step one, performing high-precision (centimeter-level) vertical aerial photogrammetry and oblique photogrammetry on a monitored area by using an unmanned aerial vehicle, and quickly generating a digital topographic map, a digital orthographic map and a digital surface model; step two, performing accurate and intensive monitoring on the monitored area through a monitoring device; and step three, finally sending obtained data to a processor, and after the monitoring data are processed by the processor, sending the data to a remote-control center, so that real-time transformation and spatialization of dynamic landslide monitoring information are achieved. The present disclosure also provides a landslide monitoring device. The landslide monitoring device comprises a control box, a bottom plate and an unmanned aerial vehicle.

Provided is a flight vehicle and in particular a flight vehicle in which a main module equipped with a device capable of carrying cargo, photographing, etc. may freely switch directions during flight while applying a posture independent of a thrust module because the thrust module is configured to freely perform roll and pitch motions with respect to the main module.

Described herein are systems, methods, and apparatuses for performing a user-less payment for an item upon its delivery by an unmanned delivery vehicle. The unmanned delivery vehicle may navigate to a delivery location, receive payment information, initiate a payment transaction with a remote server, and release the item at a specified location upon successful completion of the payment transaction. Upon arrival of the unmanned delivery vehicle, a wireless data transmission device may send payment information to a remote server, and the remote server may provide the unmanned delivery vehicle with an indication of whether the item can be released and a specific location at which the item can be released.

An aircraft (100) includes a body (10) and an outer frame (1) rotatably coupled to the body (10). The body (10) includes a plurality of rotary blades (15a-15d) and a driver (14a-14d) configured to rotate the plurality of rotary blades (15a-15d). The outer frame (1) includes a rotary frame (1a-1c) rotatable about a rotation axis intersecting the direction of gravity, and a center of gravity of the plurality of rotary blades (15a-15d) and the driver (14a-14d) is located lower than the rotation axis in the direction of gravity.

An aircraft (100) includes a body (10) and an outer frame (1) rotatably coupled to the body (10). The body (10) includes a plurality of rotary blades (15a-15d) and a driver (14a-14d) configured to rotate the plurality of rotary blades (15a-15d). The outer frame (1) includes a rotary frame (1a-1c) rotatable about a rotation axis intersecting the direction of gravity, and a center of gravity of the plurality of rotary blades (15a-15d) and the driver (14a-14d) is located lower than the rotation axis in the direction of gravity.

An aircraft landing assist apparatus includes an image obtaining unit, a shape obtaining unit, a measuring unit, and a calculating unit. The image obtaining unit is configured to obtain an image of a surrounding region of a landing point on which an aircraft is to land. The shape obtaining unit is configured to obtain a shape of the surrounding region of the landing point on the basis of the obtained image. The measuring unit is configured to measure an above-air wind direction and an above-air wind velocity. The calculating unit is configured to calculate a landing-point wind direction and a landing-point wind velocity on the basis of the obtained shape of the surrounding region of the landing point, the measured above-air wind direction, and the measured above-air wind velocity.

An aircraft landing assist apparatus includes an image obtaining unit, a shape obtaining unit, a measuring unit, and a calculating unit. The image obtaining unit is configured to obtain an image of a surrounding region of a landing point on which an aircraft is to land. The shape obtaining unit is configured to obtain a shape of the surrounding region of the landing point on the basis of the obtained image. The measuring unit is configured to measure an above-air wind direction and an above-air wind velocity. The calculating unit is configured to calculate a landing-point wind direction and a landing-point wind velocity on the basis of the obtained shape of the surrounding region of the landing point, the measured above-air wind direction, and the measured above-air wind velocity.