Systems and methods are provided for autonomous robotic surgery which is preferably integrated with autonomous-assisted intraoperative real-time single modality and/or multi-modality fusion imaging/electrophysiological diagnostics. The robotic surgery systems and methods can be integrated with autonomous-assisted intraoperative body/limb positioning, and integrated with autonomous-assisted land and unmanned aerial vehicular patient transportation.

Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.

An aerial vehicle may include a first wing structure. The aerial vehicle may further include a first propeller and a second propeller disposed along the first wing structure. The aerial vehicle may further include a second wing structure disposed to intersect the first wing structure to form a cross configuration. The aerial vehicle may further include a third propeller and a fourth propeller disposed along the second wing structure. In a hovering orientation of the aerial vehicle, respective propeller rotational axes of the first and second propellers may be angled off-vertical in respective planes which may be perpendicular to a transverse axis of the first wing structure, and respective propeller rotational axes of the third and fourth propellers may be angled off-vertical in respective planes which may be perpendicular to a transverse axis of the second wing structure.

An aerial vehicle including a first wing structure and a second wing structure which intersects the first wing structure perpendicularly at a position offset from a midpoint of a transverse axis of the first wing structure in a direction towards a first wingtip of the first wing structure. The aerial vehicle may further include a first set of at least two propellers with respective propeller rotational axes disposed side-by-side along a portion of the first wing structure extending between the midpoint of the transverse axis of the first wing structure and a second wingtip of the first wing structure. The aerial vehicle may further include a second set of at least two propellers with respective propeller rotational axes disposed side-by-side along a first portion of the second wing structure extending from a first surface of the first wing structure. The aerial vehicle may further include a third set of at least two propellers with respective propeller rotational axes disposed side-by-side along a second portion of the second wing structure extending from a second surface of the first wing structure.

This disclosure is directed to an unmanned aerial vehicle (UAV) that transitions in-flight between vertical flight configuration and horizontal flight configuration by changing an orientation of the UAV by approximately ninety degrees. The UAV may include propulsion units that are coupled to a wing. The wing may include wing segments rotatably coupled together by pivots that rotate to position the propulsion units around a center of mass of the UAV when the fuselage is oriented perpendicular with the horizon. In this vertical flight configuration, the UAV may perform vertical flight or hover. During the vertical flight, the UAV may cause the wing to extend outward via the pivots such that the wing segments become positioned substantially parallel to one another and the wing resembles a conventional fixed wing. With the wing extended, the UAV assumes a horizontal flight configuration that provides upward lift generated from the wing.

An aircraft includes a short-range radar that is configured to detect a trajectory, which is specified based on a position detection of the aircraft by a ground station.

Disclosed herein are aspects of a hybrid unmanned aerial vehicle (UAV). In one embodiment, the hybrid UAV includes a fuselage configured to hold cargo, and at least one wing. The wing has a body that includes upper and lower surfaces and is configured to generate lift to enable the UAV to glide through the air. At least one rotor assembly is held within the body of the wing between the upper and lower surfaces of the wing. The upper and lower surfaces of the wing include upper and lower doors, respectively, extending above and below, respectively, the rotor assembly. The upper and lower doors are configured to be opened during gliding of the UAV to an open position that exposes the rotor assembly such that the rotor assembly is configured to draw air through the body of the wing and thereby generate lift.

An aircraft power system according to an exemplary embodiment of this disclosure includes, among other possible things, a battery, a motor/generator coupled to the battery, an inertial drum rotatable about an axis of rotation and coupled to the motor/generator, wherein the motor/generator drives rotation of the inertial drum in a first operating mode and is driven by the inertial drum in a second operating mode; and a housing defining a chamber for the inertial drum, the chamber filled with low-viscosity medium to reduce friction on the inertial drum.

A power supply for an aircraft includes a drone capable of flight and including rotors, a DC-to-DC converter, a battery for driving the rotors and a locking device for securing a plug connection between the drone and the aircraft. The drone is set up to secure the plug connection by the locking device until the aircraft reaches a prescribed altitude, and the power supply is configured in such a way that the battery supplies power to the aircraft by the DC-to-DC converter as long as the plug connection exists.

An aircraft includes a battery, an airfoil and heat conducting elements, and the heat conducting elements connect the battery thermally to the airfoil in such a way that heat which is produced in the battery is distributed to the airfoil.