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.

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.

An unmanned aerial vehicle includes an airframe and a plurality of rotor assemblies operatively connected to the airframe and configured to propel the unmanned aerial vehicle. The air frame includes a plurality of tubes and a plurality of hardpoints. Each of the plurality of hardpoints may include a tubular protrusion for receiving one of the plurality of tubes. The unmanned aerial vehicle may further include structural adhesive bonding the tubular protrusion of each of the plurality of hardpoints to a corresponding one of the plurality of tubes.

An unmanned aerial vehicle includes an airframe and a plurality of rotor assemblies operatively connected to the airframe and configured to propel the unmanned aerial vehicle. The air frame includes a plurality of tubes and a plurality of hardpoints. Each of the plurality of hardpoints may include a tubular protrusion for receiving one of the plurality of tubes. The unmanned aerial vehicle may further include structural adhesive bonding the tubular protrusion of each of the plurality of hardpoints to a corresponding one of the plurality of tubes.

Systems and apparatus are provided for a high-power microwave sensor using an unmanned aerial vehicle. The unmanned aerial vehicle may include a central body, at least one electric motor, and a barometric pressure feedthrough. The central body may include a first enclosure housing a plurality of low voltage components, a voltage feedthrough connector, and a second enclosure housing a plurality of high voltage components. The low voltage components may include a first signal processing system, a first radio transceiver, a flight controller, a second signal processing system, a second radio transceiver, and a navigation system. The high voltage components may include a plurality of electronic speed controllers, a power distribution module, an input power interface, and a plurality of high power filters. The components of each enclosure may be segregated such that the high voltage components do not create electromagnetic interference with the low voltage components.

Systems and apparatus are provided for a high-power microwave sensor using an unmanned aerial vehicle. The unmanned aerial vehicle may include a central body, at least one electric motor, and a barometric pressure feedthrough. The central body may include a first enclosure housing a plurality of low voltage components, a voltage feedthrough connector, and a second enclosure housing a plurality of high voltage components. The low voltage components may include a first signal processing system, a first radio transceiver, a flight controller, a second signal processing system, a second radio transceiver, and a navigation system. The high voltage components may include a plurality of electronic speed controllers, a power distribution module, an input power interface, and a plurality of high power filters. The components of each enclosure may be segregated such that the high voltage components do not create electromagnetic interference with the low voltage components.

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.

Systems, devices, and methods including: a spine spanning from a tail portion to a nose portion of an aircraft, wherein the spine is configured to provide rigidity to the aircraft; and one or more modules configured to be detachably attached to the spine, wherein the one or more modules are configured to be movable on the spine to obtain a desired center of gravity for the aircraft.