Systems, methods, and devices include an aerial vehicle (AV) with a plurality of coaxially aligned vertical ducts. The lower vertical duct has a larger diameter than the upper vertical duct. Furthermore, the upper vertical duct at least partially contains a first propulsion component and the lower vertical duct at least partially contains a second propulsion component. The lower vertical duct can be coupled to the upper vertical duct by duct couplers which forms an air intake gap between the upper vertical duct and the lower vertical duct. The AV also includes one or more steering flaps disposed on the lower vertical duct, configured to manipulate an air flow out the bottom of the lower duct, thus controlling navigation and stability of the AV.

Embodiments disclosed provide a pump assembly including a first pump for delivering at least one fluid. The first pump may include a first inlet coupled to the first pump for delivering at least one first fluid to the first pump, a second inlet coupled to the first pump for delivering at least one second fluid to the first pump, a first discharge coupled to the first pump for delivering the at least one first fluid at a first pressure, and a second discharge coupled to the first pump for delivering the at least one second fluid at a second pressure. In some embodiments, the first discharge and the second discharge are isolated from each other.

Embodiments disclosed provide a pump assembly including a first pump for delivering at least one fluid. The first pump may include a first inlet coupled to the first pump for delivering at least one first fluid to the first pump, a second inlet coupled to the first pump for delivering at least one second fluid to the first pump, a first discharge coupled to the first pump for delivering the at least one first fluid at a first pressure, and a second discharge coupled to the first pump for delivering the at least one second fluid at a second pressure. In some embodiments, the first discharge and the second discharge are isolated from each other.

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 hybrid aerial hydro drone includes a body with a plurality of hydraulic thrusters supported on an outer surface of the body and configured to propel the body in a marine environment. The drone also includes a plurality of rotor arms arranged on the body, each rotor arm comprising a rotor system configured to propel the body in an aerial environment. Each rotor arm is deployably configured between a deployed position in which the rotor systems are extended from the body for aerial traversal, and a folded position in which the arms are hydrodynamically folded behind the body for marine traversal. The body also includes a controller, an energy source, a main ballast chamber and a pump with snorkel for operation of the drone.

A hybrid aerial hydro drone includes a body with a plurality of hydraulic thrusters supported on an outer surface of the body and configured to propel the body in a marine environment. The drone also includes a plurality of rotor arms arranged on the body, each rotor arm comprising a rotor system configured to propel the body in an aerial environment. Each rotor arm is deployably configured between a deployed position in which the rotor systems are extended from the body for aerial traversal, and a folded position in which the arms are hydrodynamically folded behind the body for marine traversal. The body also includes a controller, an energy source, a main ballast chamber and a pump with snorkel for operation of the drone.

The present invention relates to a hybrid flying and driving robot comprising a plurality of wheels; a plurality of propellers; a plurality of motors, each of which is configured to drive the rotation of a respective wheel of said plurality of wheels; wherein each respective motor of said plurality of motors is connected to a respective propeller of said plurality of propellers by means of a respective gear arrangement; wherein each respective gear arrangement is rearrangeable between two configurations: a) a first configuration wherein the respective motor is configured to drive the rotation of the respective propeller; b) a second configuration wherein the respective motor does not drive the rotation of the respective propeller.

The present invention relates to a hybrid flying and driving robot comprising a plurality of wheels; a plurality of propellers; a plurality of motors, each of which is configured to drive the rotation of a respective wheel of said plurality of wheels; wherein each respective motor of said plurality of motors is connected to a respective propeller of said plurality of propellers by means of a respective gear arrangement; wherein each respective gear arrangement is rearrangeable between two configurations: a) a first configuration wherein the respective motor is configured to drive the rotation of the respective propeller; b) a second configuration wherein the respective motor does not drive the rotation of the respective propeller.