This disclosure describes systems and processes using multirotor lifter to deploy and/or engage fixed wing aircraft. For example, one or more unmanned multirotor lifters may engage an unmanned fixed wing aircraft, aerially navigate the fixed wing aircraft vertically to a desired altitude, and then release the fixed wing aircraft so that the fixed wing aircraft can initiate a flight plan. In some implementations, multirotor lifter may also be configured to engage fixed wing aircraft while both the multirotor lifters and the fixed wing aircraft are in flight.

An unmanned aerial vehicle (UAV) that can operate both as a conventional multicopter with no wing attached, or, it can operate as a winged multicopter. The detachable wing design used in the invention provides versatility without compromising performance; the wing attachment receptacles add no weight to the wingless multicopter configuration because they also function as the leg receptacles. In one embodiment, the base multicopter configuration is a quad-copter with four propeller drives. Four tubular receptacles, two forward and two aft, provide attachment points for the vertical struts of a detachable rectangular shaped wing, these vertical struts also function as the legs of the multicopter. The wing is fabricated using lightweight struts and rip stop nylon fabric which can be easily folded into a compact shape using quick release pins. In another embodiment, the wing is fabricated using a foam core. In both embodiments, the angle of the detachable wing can be adjusted to optimize lift and drag in the forward thrust, tilted position of the multicopter.

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.

A method of delivering heavy payload using an autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV is equipped with two movable wing systems that rotate from a stowed position to a deployed position upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expendable UAV.

A method of delivering heavy payload using an autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV is equipped with two movable wing systems that rotate from a stowed position to a deployed position upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expendable UAV.

A modular unmanned aerial vehicle (UAV) system comprises a body module, a rotor module, and a wing module. The body module includes a flight controller and a power distribution device. The body module is releasably attachable to the rotor module or the wing module, and the body module is releasably attachable to the rotor module. The rotor module includes one or more motors and electronic speed controllers (ESCs), while the wing module includes a wing having a flap, elevator, aileron, or rudder. Various UAV configurations can be formed from the body module, the rotor module, and the wing module. Each configuration includes different advantages for flight time, distance, battery life, and payload capacity. A UAV can be configured to a particular configuration to optimize parcel delivery.

A modular unmanned aerial vehicle (UAV) system comprises a body module, a rotor module, and a wing module. The body module includes a flight controller and a power distribution device. The body module is releasably attachable to the rotor module or the wing module, and the body module is releasably attachable to the rotor module. The rotor module includes one or more motors and electronic speed controllers (ESCs), while the wing module includes a wing having a flap, elevator, aileron, or rudder. Various UAV configurations can be formed from the body module, the rotor module, and the wing module. Each configuration includes different advantages for flight time, distance, battery life, and payload capacity. A UAV can be configured to a particular configuration to optimize parcel delivery.

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.

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 drone having a fuselage in which a battery is mounted and a forward direction is set in an x-axis. A plurality of rotors disposed about the fuselage in four or more, each rotational axis of which is aligned in a z-axis direction. An x-axis tilting mechanism formed to tilt the plurality of rotors about an axis parallel to the x-axis. A y-axis tilting mechanism formed to tilt the plurality of rotors about an axis parallel to the y-axis. A first drive motor drives the y-axis tilting mechanism unit. A second drive motor drives the x-axis tilting mechanism unit. A control unit configured to implement a plurality of flight modes by controlling the first, second, third rotor and fourth rotors, the first and second drive motors, and a wing part installed on an upper portion of the fuselage and formed as an air foil to provide lift.