An unmanned aerial vehicle includes a plurality of arm units, each having a rotary wing, a motor, and an arm main body and detachably coupled to a main body; the main body having a plurality of receptacles for coupling to the arm units; and a battery unit detachably coupled to the main body to be exposed to outside, in which at least a part of the battery unit is exposed to outside when the battery unit is coupled to the main body.

Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.

The embodiments is an unmanned aerial vehicle. The unmanned aerial vehicle includes: an airframe; and a fixed-wing assembly and a rotor assembly, both replaceably connected to the airframe. The fixed-wing assembly is connected to the airframe to form a vertical take-off and landing fixed-wing unmanned aerial vehicle and the rotor assembly is connected to the airframe to form a multi-rotor unmanned aerial vehicle, thereby implementing an unmanned aerial vehicle that can switch between the vertical take-off and landing fixed-wing unmanned aerial vehicle and the multi-rotor unmanned aerial vehicle.

The embodiments is an unmanned aerial vehicle. The unmanned aerial vehicle includes: an airframe; and a fixed-wing assembly and a rotor assembly, both replaceably connected to the airframe. The fixed-wing assembly is connected to the airframe to form a vertical take-off and landing fixed-wing unmanned aerial vehicle and the rotor assembly is connected to the airframe to form a multi-rotor unmanned aerial vehicle, thereby implementing an unmanned aerial vehicle that can switch between the vertical take-off and landing fixed-wing unmanned aerial vehicle and the multi-rotor unmanned aerial vehicle.

A MEUV that is able to navigate aerial, aquatic, and terrestrial environments through the use of different mission mobility attachments is disclosed. The attachments allow the MEUV to be deployed from the air or through the water prior to any terrestrial navigation. The mobility attachments can be removed or detached by and from the vehicle during a mission.

An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft.

A retention system includes a base supporting a wing spar and a post extending through the base from a first side of the base to a second side of the base. The post inserts through an aperture in the spar. A stop is selectively securable to the post over the second side of the base. A locking member engages the post on the first side of the base. The locking member is configured to selectively move the post from an unlocked position to a locked position in which the post is withdrawn toward the first side relative to the unlocked position. A biasing member encircles the post and is positioned between the stop and the second side. When the locking member is in a closed position the biasing member expands to engage the aperture and resist movement of the wing spar. A plurality of cradles may support the wing.

Disclosed are devices, systems and methods for mission-adaptable aerial vehicle. In some aspects, a mission-adaptable aerial vehicle includes a configuration having swappable, manipulatable, and interchangeable sections and components connectable by a connection and fastening system able to be modified by an end-user in the field. In some embodiments, a mission-adaptable aerial vehicle can be configured to include a main center body extending along a longitudinal direction, a wing with a lateral cross-sectional airfoil shape, and/or stabilizer and control surface structures with corresponding cross-sectional airfoil shapes.

A MEUV that is able to navigate aerial, aquatic, and terrestrial environments through the use of different mission mobility attachments is disclosed. The attachments allow the MEUV to be deployed from the air or through the water prior to any terrestrial navigation. The mobility attachments can be removed or detached by and from the vehicle during a mission.

Devices and methods described herein can use novel and efficient designs and layouts to improve the flight performance of unmanned aerial vehicles (UAVs). Some embodiments of the present disclosure can comprise a UAV including a novel and efficient wing design, while other embodiments can comprise a novel and efficient wing design for use with different UAVs. In this manner, wing systems and/or structures according to the present disclosure can have different sizes and/or be scaled to work with differently sized of UAVs. In other embodiments according to the present disclosure, the wing structures can have release mechanisms, wherein the wing structure can be detachable from the rest of the UAV. Some embodiments include a wing structure comprising a center wing panel connected to left and right wing panels. In some embodiments, the left/center/right wing panels are connected with a pin/slot system.