The present disclosure relates to a method of navigating an unmanned aerial vehicle (UAV). The method includes the steps of controlling a flight path of the UAV by a remote operator, obtaining a recognized air picture of an observation space surrounding the UAV, assigning one of a plurality of threat levels to each of the aerial vehicles, the threat levels comprising a resolution advisory level and an automatic avoidance level and continuously automatically determining viable avoidance trajectories for the UAV). If an aerial vehicles is assigned the resolution advisory level, a message is provided to a remote operator including a first proposed viable avoidance trajectory. If an aerial vehicles is assigned the automatic avoidance level, control signals are provided to an on-board flight controller instructing the vehicle to follow a flight path corresponding to a second proposed viable avoidance trajectory.

Fiducial marker detection systems and methods are provided. In one example, a method includes capturing, by a camera of an unmanned aerial vehicle, an image. The method further includes identifying one or more image contours in the image. The method further includes determining a position of a fiducial marker in the image. The method further includes projecting, based at least on the position, models associated with one or more contours of the fiducial marker into an image plane of the camera to obtain one or more model contours. The method further includes determining a pose associated with the fiducial marker based at least on the one or more image contours and the one or more model contours. Related devices and systems are also provided.

Fiducial marker detection systems and methods are provided. In one example, a method includes capturing, by a camera of an unmanned aerial vehicle, an image. The method further includes identifying one or more image contours in the image. The method further includes determining a position of a fiducial marker in the image. The method further includes projecting, based at least on the position, models associated with one or more contours of the fiducial marker into an image plane of the camera to obtain one or more model contours. The method further includes determining a pose associated with the fiducial marker based at least on the one or more image contours and the one or more model contours. Related devices and systems are also provided.

The present disclosure is directed to unmanned aerial vehicle (UAV) comprising a convertible body operably coupled to at least one sensor, and further configured to rotate at least about a longitudinal axis, thereby providing a full field of regard for the at least one sensor, and a plurality of arms extending laterally from the convertible body, each arm of the plurality of arms having a rotor assembly coupled thereto.

The present technology is directed to a remotely controlled aircraft that can be transported without the risk of damaging certain components, such as the arms and/or propellers. In one non-limiting example, the remotely controlled aircraft technology described herein provides a housing that allows the arms of the remotely controlled aircraft to extend and/or retract through openings in the housing. When retracted, the arms and propellers are protected within an area of the structure of the housing, and when extended, the arms and propellers are operable to make the remotely controlled aircraft fly.

Damage mitigating apparatus comprises totally extending hollow tubes, and projectiles attached to undeployed fabric and formed with a tube-receivable rod. Pressurized gas which is generated upon triggering of a gas generator flows through the tubes to propel the projection and to cause performance of at damage mitigating operation. In one embodiment, a damage mitigating aerial vehicle comprises sensors for detecting flight related characteristics and a communication unit for commanding activation of parachute deploying apparatus and of a lift generator deactivation unit following determination of a flight failure. In one embodiment, an aerial vehicle transmits a critical failure alarm signal to an unmanned aircraft traffic management system (UTM) station following detection of to failure, and the UTM elation transmits a warning signal to neighboring aerial vehicles that are predicted to be in a vicinity of the descent path of the failed aerial vehicle to avoid collision with the failed aerial vehicle.

The present technology is directed to a remotely controlled aircraft that can be transported without the risk of damaging certain components, such as the arms and/or propellers. In one non-limiting example, the remotely controlled aircraft technology described herein provides a housing that allows the arms of the remotely controlled aircraft to extend and/or retract through openings in the housing. When retracted, the arms and propellers are protected within an area of the structure of the housing, and when extended, the arms and propellers are operable to make the remotely controlled aircraft fly.

A shock resistant fuselage system includes first and second fuselage side walls, each of the first and second fuselage side walls having a plurality of guide posts, and a printed circuit board (PCB) rigidly attached to at least one of the first and second fuselage side walls, the PCB having a plurality of guide slots, each of the plurality of guide posts slideably seated in a respective one of the plurality of guide slots so that elastic deformation of the PCB is guided by the guide slots between the first and second fuselage side walls.

A frame assembly for an unmanned aerial vehicle includes an upper cover, a lower cover, a housing, and a circuit board. The housing includes electric chamber between the upper cover and the lower cover. The circuit board assembly is disposed in the electric chamber and includes a first circuit board arranged close to the upper cover and a second circuit board close to the lower cover. The first circuit board is spaced apart from the second circuit board.

An aerial imaging aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons coupled therebetween. A two-dimensional distributed thrust array is coupled to the airframe. The thrust array includes a plurality of propulsion assemblies each operable for variable speed and omnidirectional thrust vectoring. A payload is coupled to the airframe and includes an aerial imaging module. A flight control system is operable to independently control the speed and thrust vector of each of the propulsion assemblies such that in an inclined flight attitude, the flight control system is operable to maintain the orientation of the aerial imaging module toward a target while translating the aircraft, changing aircraft altitude and/or circling the target.