The universal vehicle system is designed with a lifting body which is composed of a plurality of interconnected modules which are configured to form an aerodynamically viable contour of the lifting body which including a front central module, a rear module, and thrust vectoring modules displaceably connected to the front central module and operatively coupled to respective propulsive mechanisms. The thrust vectoring modules are controlled for dynamical displacement relative to the lifting body (in tilting and/or translating fashion) to direct and actuate the propulsive mechanism(s) as needed for safe and stable operation in various modes of operation and transitioning therebetween in air, water and terrain environments.

The present disclosure relates to a reconfigurable battery system and method of operating the same. The reconfigurable battery system comprising a plurality of switchable battery modules, a battery supervisory circuit, and a battery pack controller, where the plurality of switchable battery modules electrically arranged in series to define a battery string defining an output voltage. The battery pack controller operable to connect the battery string to the external bus via a pre-charge switch to perform a pre-charge cycle.

Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.

An autonomous cargo delivery aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes a fuselage having an aerodynamic shape with a leading edge, a trailing edge and first and second sides. First and second wings are coupled to the fuselage proximate the first and second sides, respectively. A distributed thrust array includes a first pair of propulsion assemblies coupled to the first wing and a second pair of propulsion assemblies coupled to the second wing. A flight control system is operably associated with the distributed thrust array and configured to independently control each of the propulsion assemblies. The first side of the fuselage includes a door configured to provide access to a cargo bay disposed within the fuselage from an exterior of the aircraft with a predetermined clearance relative to the first pair of propulsion assemblies.

An aircraft is provided which includes a fuselage having a first wing with curved wingtips positioned above a second wing having curved wingtips. Rotor assemblies located in between the curved wingtips of the first and second wing, are employable to both provide vertical thrust for vertical take off of the aircraft and auto rotation to generate electric energy to recharge an onboard electric power supply. The first wing may be formed in a V-shape, and additional rotor assemblies to provide forward and vertical thrust to the airplane can be included on rotatable canards.

A flow path duct system for a propulsion system of an aircraft includes a base defining a flow surface. The base has an internal surface and an external surface. A plurality of perforations are formed through the base between the internal surface and the external surface. A plurality of supports define a plurality of cavities. The plurality of supports extend outwardly from the external surface of the of the base. One or more of the plurality of cavities are in fluid communication with the one or more of the plurality of perforations. A backing surface is secured to the plurality of supports. The plurality of supports are disposed between the base and the backing surface. The one or more of the plurality of cavities are in fluid communication with an internal volume defined by the internal surface of the base through the one or more of the plurality of perforations. The base, the plurality of supports, and the backing surface can be integrally formed together as a monolithic, load-bearing structure.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) including: a fuselage; a first pair of airfoils rotatable between a retracted position and a deployed position, the deployed position extending out from the fuselage and the retracted position extending substantially along a first portion on an exterior of the fuselage; a second pair of airfoils rotatable between a second retracted position and a second deployed position, the second deployed position extending out from the fuselage and the second retracted position extending substantially along the first portion on the exterior of the fuselage; and a rudder foldable against the fuselage in a pre-deployment position.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.

An aircraft operable between a deployed position and a stowed position is disclosed. The aircraft includes a fuselage, a pair of wing segments, and a translation and rotation mechanism for attaching the wing segments to the fuselage. The mechanism includes an upper assembly having an outer shaft and an inner shaft. A first wing segment is attached to the outer shaft and a second wing segment is attached to the inner shaft. The outer shaft translates downward with respect to the inner shaft. Thereafter, the outer and inner shafts rotate in opposite directions in order to rotate the wing segments on top of one another, parallel to a long axis of the fuselage, and into the stowed position. The operation of the outer and inner shafts is reversed in order to return the wing segments to the deployed position.