Abstract: An unmanned aircraft system operable for wing-borne lift in a flying wing orientation. The unmanned aircraft system includes an airframe having a leading edge, a trailing edge, first and second wingtips and a root chord. The airframe has an airfoil cross-section along chord stations thereof. A thrust array is coupled to the airframe including first and second motor mounts coupled to the leading edge respectively between the root chord and the first and second wingtips. The motor mounts each have first and second propulsion assemblies coupled to respective first and second distal ends thereof. The motor mounts each have a flight configuration substantially perpendicular with the leading edge forming a two-dimensional distributed thrust array such that the airframe extends outboard of the first and second motor mounts. The unmanned aircraft system includes an electric power system and a flight control system that are operably associated with the thrust array.

Abstract: An example of a collapsible pylon for a drone aircraft includes a bore extending through a length of a barrel, a first and a second flex-pin bore formed through a wall of the barrel, a first arm slidably positioned within a first end of the bore, a first flex pin disposed on the first arm to engage the first flex-pin bore, a second arm slidably positioned within a second end of the bore, and a second flex pin disposed on the second arm to engage the second flex-pin bore.

Abstract: A tailsitter aircraft includes an airframe having first and second wings with first and second pylons extending therebetween, a thrust array attached to the airframe, payloads and payload saddle assemblies coupled to the pylons each configured to secure a respective payload. The thrust array includes propulsion assemblies configured to transition the airframe between a forward flight orientation for wing-borne lift and a VTOL orientation for thrust-borne lift. Each payload saddle assembly includes a latch assembly and a retainer configured to secure the respective payload against a respective pylon. A latch assembly is movable between various positions including an open position and a closed position and is configured to secure the respective payload in the closed position and release the respective payload in the open position. Each latch assembly is configured to move from the closed position to the open position to release the respective payload in the VTOL orientation.

Abstract: An aircraft includes an airframe with a thrust array attached thereto. The thrust array includes a plurality of propulsion assemblies that are independently controlled by a flight control system. A landing gear assembly is coupled to the airframe and includes a plurality of landing feet. An altitude sensor array includes a plurality of altitude sensors each of which is disposed within one of the landing feet such that when the aircraft is in the VTOL orientation, the altitude sensor array is configured to obtain multifocal altitude data relative to a landing surface. The flight control system is configured to generate a three-dimensional terrain map of the surface based upon the multifocal altitude data.

Abstract: An unmanned aircraft system operable for wing-borne lift in a flying wing orientation. The unmanned aircraft system includes an airframe having a leading edge, a trailing edge, first and second wingtips and a root chord. The airframe has an airfoil cross-section along chord stations thereof. A thrust array is coupled to the airframe including first and second motor mounts coupled to the leading edge respectively between the root chord and the first and second wingtips. The motor mounts each have first and second propulsion assemblies coupled to respective first and second distal ends thereof. The motor mounts each have a flight configuration substantially perpendicular with the leading edge forming a two-dimensional distributed thrust array such that the airframe extends outboard of the first and second motor mounts. The unmanned aircraft system includes an electric power system and a flight control system that are operably associated with the thrust array.

Abstract: An example of an aerial vehicle includes a rudder removably connected to the aerial vehicle by a twist lock mechanism. The twist lock mechanism is biased in a locked position by an elastic member.

Abstract: An aircraft includes an airframe with a thrust array attached thereto. The thrust array includes a plurality of propulsion assemblies that are independently controlled by a flight control system. A landing gear assembly is coupled to the airframe and includes a plurality of landing feet. An altitude sensor array includes a plurality of altitude sensors each of which is disposed within one of the landing feet such that when the aircraft is in the VTOL orientation, the altitude sensor array is configured to obtain multifocal altitude data relative to a landing surface. The flight control system is configured to generate a three-dimensional terrain map of the surface based upon the multifocal altitude data.

Abstract: An unmanned aircraft system includes a flying wing airframe having leading and trailing edges with respective sweep angles. A thrust array is coupled to the airframe and includes first and second motor mounts each selectively rotatably coupled to the leading edge by a locking joint. Each motor mount has first and second propulsion assemblies coupled to respective first and second distal ends thereof. A power system is operably associated with the thrust array and is operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and is operable to independently control the speed of each propulsion assembly. In a flight configuration, each motor mount is locked substantially perpendicular with the leading edge by the respective locking joint. In a compact storage configuration, each motor mount is locked substantially parallel with the leading edge the respective locking joint.

Abstract: An example of a collapsible pylon for a drone aircraft includes a bore extending through a length of a barrel, a first and a second flex-pin bore formed through a wall of the barrel, a first arm slidably positioned within a first end of the bore, a first flex pin disposed on the first arm to engage the first flex-pin bore, a second arm slidably positioned within a second end of the bore, and a second flex pin disposed on the second arm to engage the second flex-pin bore.

Abstract: An unmanned aircraft system having a flying wing orientation includes an airframe having leading and trailing edges, a two-dimensional thrust array coupled to the leading edge, a power system and a flight control system operable to independently control the speed of each propulsion assembly of the two-dimensional thrust array.

Abstract: An unmanned aircraft system includes a flying wing airframe having leading and trailing edges with respective sweep angles. A thrust array is coupled to the airframe and includes first and second motor mounts each rotatably coupled to the leading edge. Each motor mount has first and second propulsion assemblies coupled to respective first and second distal ends thereof. A power system is operably associated with the thrust array and is operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and is operable to independently control the speed of each propulsion assembly. In a flight configuration of the system, each motor mount is substantially perpendicular with the leading edge such that the thrust array forms a two-dimensional thrust array. In a compact storage configuration of the system, each motor mount is substantially parallel with the leading edge.

Abstract: Systems and methods include providing vertical takeoff and landing (VTOL) aircraft with a cargo pod having a selectively inflatable bladder system that firmly secures a payload disposed within the cargo pod when the bladder system is pressurized. The bladder system also controls the location, position, and/or orientation of the payload in order to adjust, control, and/or maintain the center of gravity of the aircraft during flight. The aircraft includes an impact protection system that further pressurizes the bladder system to protect the payload and/or that disperses a flame-retardant fluid into the cargo pod to protect electrical components of the aircraft. The aircraft is fully autonomous and self-directed via a preprogrammed location-based guidance system to allow for accurate delivery of the payload to its intended destination. The bladder system is depressurized in response to a landing event to allow for e f the payload from the cargo pod.

Abstract: An unmanned aerial vehicle has an airframe having first and second wing modules with first and second pylons extending therebetween. A thrust array is coupled to the airframe including two propulsion assemblies coupled to each of the first and second wings. An electric power system is operably associated with the thrust array and operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and operable to independently control the speed of each propulsion assembly. Each wing module is selected from a plurality of wing modules each having a respective function and each interchangeably couplable with the first and second pylons to enable the airframe to support the functions of the plurality of wing modules.

Abstract: An unmanned aerial vehicle has a flight mode and a compact storage mode. The unmanned aerial vehicle includes an airframe having first and second wings with first and second pylons extending therebetween. A thrust array is coupled to the airframe including two propulsion assemblies coupled to each of the first and second wings. An electric power system is operably associated with the thrust array and operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and operable to independently control the speed of each propulsion assembly. In the flight mode, the first and second wings are substantially parallel with the vertical dimension therebetween at a maximum. In the compact storage mode, the first and second pylons are rotated relative to the first and second wings such that the vertical dimension between the first and second wings is at a minimum.

Abstract: A foldable wing system for an unmanned aerial system having a fuselage includes a left wing frame having an inboard gear rotatably coupled to the fuselage, a right wing frame having an inboard gear rotatably coupled to the fuselage and a wing actuator coupled to a linkage point on at least one of the wing frames. The wing frames are movable between a plurality of positions including a deployed position and a stowed position. The inboard gear of the left wing frame is engaged with the inboard gear of the right wing frame such that the wing frames move symmetrically between the plurality of positions in response to movement of the linkage point by the wing actuator.

Abstract: A wing module for an aerial vehicle in which the wing module has a flight configuration and an access configuration. The wing module includes an external wing skin having an upper skin with an upper surface having a curved profile and a lower skin forming the leading and trailing edges and having a generally planar lower surface. A hinge joint couples the upper and lower skins enabling relative rotation of the upper and lower skins between the flight configuration and the access configuration. The hinge joint is proximate the leading edge. An interior cavity is formed at least partially within the lower skin. In the flight configuration, the upper and lower skins have an airfoil cross section. In the access configuration, the upper and lower skins are split in the chordwise direction such that distal ends of the first and second skins are separated providing access to the interior cavity.

Abstract: An Unmanned Aerial Vehicle (UAV) has a fuselage, a rotor system, and a wing configured for selective positioning during flight of the UAV to a deployed position, a stowed position, and to positions between the deployed position and the stowed position. The UAV has a flexible wing skin at least partially carried by a leading arm and the leading arm is rotatable relative to the fuselage.

Abstract: An example of an aerial vehicle includes a rudder removably connected to the aerial vehicle by a twist lock mechanism. The twist lock mechanism is biased in a locked position by an elastic member.

Abstract: An example of an aerial vehicle includes a rudder removably connected to the aerial vehicle by a twist lock mechanism. The twist lock mechanism is biased in a locked position by an elastic member.

Abstract: An unmanned aerial vehicle has a flight mode and a compact storage mode. The unmanned aerial vehicle includes an airframe having first and second wings with first and second pylons extending therebetween. A thrust array is coupled to the airframe including two propulsion assemblies coupled to each of the first and second wings. An electric power system is operably associated with the thrust array and operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and operable to independently control the speed of each propulsion assembly. In the flight mode, the first and second wings are substantially parallel with the vertical dimension therebetween at a maximum. In the compact storage mode, the first and second pylons are rotated relative to the first and second wings such that the vertical dimension between the first and second wings is at a minimum.