An autonomous drone is programed with the geo-location of one or more remote sensors, and the autonomous drone then flies to each of the remote sensors to acquire a most recent sensing data record, and then return to a base where the most recent data record for each remote sensor can be transferred to a computing system. Upon arriving at the location of each remote sensor, the drone causes the remote sensor to activate a local area radio transceiver so that a communication link can be established between the drone and the remote sensor.

Certain aspects of the present disclosure provide a vehicle, comprising: a housing; a battery comprising a plurality of layers and disposed within the housing; and a first removable battery compression device disposed within the housing and configured to apply compressive force to the plurality of layers of the battery via a first side of the battery.

An apparatus (1) for changing a power source of a drone, the apparatus (1) comprises an adaptor (2) for securing a power source (3) to a drone and comprising a first energy connection for supplying energy from the power source (3) and a second energy connection for supplying energy to a drone, wherein one of the first and second energy connections comprises a pair of energy links (20, 21) which are movable between a first position (FIG. 5) to facilitate energy supply and secure the power source (3) to the drone and a second position (FIG. 4) to interrupt energy supply and enable the power source (3) to be removed from the drone.

A vertical landing of an aircraft is performed using the first battery where the aircraft is unoccupied when the vertical landing is performed, the unoccupied aircraft includes the first battery, and the unoccupied aircraft excludes a second, removable battery. In response to detecting that the second, removable battery is detachably coupled to the aircraft, a power source for the aircraft is switched from the first battery to the second, removable battery. After switching the switch power source, a vertical takeoff of the aircraft is performed using the second, removable battery, wherein the aircraft is occupied when the vertical takeoff is performed.

A collapsible unmanned aerial vehicle has: a cylindrical structural body; a plurality of deployable mechanisms laterally distributed about the cylindrical structural body; a control unit; a portable power source; each of the plurality of deployable mechanisms comprising a lift-generating device, a pliable pylon and an actuation mechanism, the cylindrical structural body being terminally mounted to the pliable pylon, the lift-generating device being terminally mounted to the pliable pylon, the actuation mechanism being operatively integrated along the pliable pylon, the pliable pylon being selectively configured to be radially straightened from the cylindrical structural body and to arcuately collapsed into the cylindrical structural body via the actuation mechanism, the control unit and the portable power source each being electrically connected to the actuation mechanism; the control unit and the portable power source being mounted within the cylindrical structural body; and the portable power source being electrically connected to the control unit.

An aerial vehicle and system for automatically detecting an object (e.g., human, pet, or other animal) approaching the aerial vehicle is described. When an approaching object is detected by an object detection component, a safety profile may be executed to reduce or avoid any potential harm to the object and/or the aerial vehicle. For example, if the object is detected entering a safety perimeter of the aerial vehicle, the rotation of a propeller closest to the object may be stopped to avoid harming the object and rotations of remaining propellers may be modified to maintain control and flight of the aerial vehicle.

The current invention concerns an improved system for cargo delivery through (unmanned) aerial vehicles (preferably UAVs or drones) to specifically designed home stations. Additionally, a method is described according to which the system of the invention functions.

The present invention provides a pod (100) for an aircraft (1000), comprising: a housing (1); a unit (2) comprising a propulsion system, the unit comprising at least one attachment point (5) for coupling the unit to the housing (1), wherein the position of the unit relative to the housing is selected from a plurality of positions based on the centre of gravity of the aircraft, such that deflection of control surfaces required for the aircraft to maintain a constant angle of attack is minimised. The invention also provides an aircraft (1000) having the pod (100) and a method of balancing the aircraft (1000).

A vertical landing of an aircraft is performed using the first battery where the aircraft is unoccupied when the vertical landing is performed, the unoccupied aircraft includes the first battery, and the unoccupied aircraft excludes a second, removable battery. In response to detecting that the second, removable battery is detachably coupled to the aircraft, a power source for the aircraft is switched from the first battery to the second, removable battery. After switching the switch power source, a vertical takeoff of the aircraft is performed using the second, removable battery, wherein the aircraft is occupied when the vertical takeoff is performed.

An example UAV landing structure includes a landing platform for a UAV, a cavity within the landing platform, and a track that runs along the landing platform and at least a part of the cavity. The UAV may include a winch system that includes a tether that may be coupled to a payload. Furthermore, the cavity may be aligned over a predetermined target location. The cavity may be sized to allow the winch system to pass a tethered payload through the cavity. The track may guide the UAV to a docked position over the cavity as the UAV moves along the landing platform. When the UAV is in the docked position, a payload may be loaded to or unloaded from the UAV through the cavity.