Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons extending therebetween. The first and second wings each having first and second outboard nacelle stations. A two-dimensional distributed thrust array is attached to the airframe. The thrust array including a plurality of outboard propulsion assemblies coupled to the first and second outboard nacelle stations of the first and second wings. A flight control system is coupled to the airframe and is operable to independently control each of the propulsion assemblies. A cargo hook module is coupled to the airframe. The cargo hook module is operable for external load operations.

Abstract: An aircraft has multiple independent yaw authority mechanisms. The aircraft includes an airframe having first and second wings with at least first and second pylons extending therebetween and with a plurality of tail members extending therefrom each having an active control surface. A two-dimensional distributed thrust array is coupled to the airframe that includes a plurality of propulsion assemblies each having a rotor assembly and each operable for thrust vectoring. A flight control system is operable to independently control each of the propulsion assemblies. A first yaw authority mechanism includes differential speed control of rotor assemblies rotating clockwise compared to rotor assemblies rotating counterclockwise. A second yaw authority mechanism includes differential longitudinal control surface maneuvers of control surfaces of two symmetrically disposed tail members. A third yaw authority mechanism includes differential thrust vectoring of propulsion assemblies.

Abstract: An aerial imaging aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons coupled therebetween. A two-dimensional distributed thrust array is coupled to the airframe. The thrust array includes a plurality of propulsion assemblies each operable for variable speed and omnidirectional thrust vectoring. A payload is coupled to the airframe and includes an aerial imaging module. A flight control system is operable to independently control the speed and thrust vector of each of the propulsion assemblies such that in an inclined flight attitude, the flight control system is operable to maintain the orientation of the aerial imaging module toward a target while translating the aircraft, changing aircraft altitude and/or circling the target.

Abstract: Systems and methods of prioritizing the use of flight attitude controls of aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. A method includes determining an optimal flight attitude state for the aircraft during flight, the aircraft including first and second wings with first and second pylons coupled therebetween forming an airframe with a two-dimensional distributed thrust array and a plurality of aerosurfaces coupled to the airframe; monitoring the current flight attitude state of the aircraft; identifying deviations between the current flight attitude state and the optimal flight attitude state; ordering the flight attitude controls of the aircraft based upon the flight attitude control authority of each in the current flight attitude state; and implementing the highest order flight attitude control to bias the aircraft from the current flight attitude state toward the optimal flight attitude state.

Abstract: A propulsion assembly for an aircraft includes a nacelle having a rapid connection interface, at least one battery disposed within the nacelle, a speed controller coupled to the battery and a propulsion system coupled to the speed controller and the battery. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that are rotatable with the output drive of the electric motor in a rotational plane to generate thrust. The electric motor is operable to rotate responsive to power from the battery at a speed responsive to the speed controller. The rapid connection interface of the nacelle is couplable to a rapid connection interface of an airframe nacelle station to provide structural and electrical connections therebetween that are operable for rapid in-situ assembly.

Abstract: An autonomous package delivery aircraft is operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft includes an airframe with a distributed thrust array coupled thereto. A flight control system is operably associated with the distributed thrust array and is configured to independently control each of the propulsion assemblies of the distributed thrust array. A package delivery module is coupled to the airframe. In the VTOL orientation, a first pair of propulsion assemblies is forward of the package delivery module while a second pair of propulsion assemblies is aft of the package delivery module. In a forward flight orientation, the first pair of propulsion assemblies is below the package delivery module and the second pair of propulsion assemblies is above the package delivery module.

Abstract: An aircraft for capturing drones includes an airframe having a drone channel with first and second wings extending outboard thereof. A two-dimensional distributed thrust array includes a plurality of propulsion assemblies coupled to each of the first and second wings such that the rotor disc of each propulsion assembly is outboard of the drone channel. A flight control system is coupled to the airframe and is operable to independently control each of the propulsion assemblies. A mesh bag is coupled to the drone channel forming a drone capture net. The aircraft is configured to convert between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft is also configured to overtake a drone during flight in the biplane orientation such that the drone passes through the drone channel into the mesh bag, thereby capturing the drone in the drone capture net.

Abstract: An aircraft includes an airframe having first and second wings with first and second pylons extending therebetween and having a two-dimensional distributed thrust array of outboard propulsion assemblies attached thereto. A flight control system is coupled to the airframe and is operable to independently control a rotor speed and a thrust vector of each propulsion assembly. In a low thrust to weight configuration, transitions from the VTOL orientation to the biplane orientation include establishing a pitch down flight attitude while engaging in collective thrust vectoring of the outboard propulsion assemblies to maintain hover stability followed collectively reducing the thrust vector angles to initiate forward flight. In a high thrust to weight configuration, transitions from the VTOL orientation to the biplane orientation include maintaining a level flight attitude while collectively increasing the thrust vector angles of the outboard propulsion assemblies to initiate forward flight.

Abstract: An inertia weight assembly positionable within a receiving portion of a rotor blade for use on a rotorcraft. The inertia weight assembly includes a weighted core and a casing having a closed outboard end and forming a cavity. The weighted core is disposed in the cavity such that the casing at least partially encloses the weighted core. The weighted core is formed from a first material and the casing is formed from a second material that is dissimilar to the first material. The casing provides an interface between the weighted core and the receiving portion of the rotor blade. The second material is more bondable to the receiving portion of the rotor blade than the first material.

Abstract: An aircraft has multiple independent yaw authority mechanisms. The aircraft includes an airframe having first and second wings with at least first and second pylons extending therebetween and with a plurality of tail members extending therefrom each having an active control surface. A two-dimensional distributed thrust array is coupled to the airframe that includes a plurality of propulsion assemblies each having a rotor assembly and each operable for thrust vectoring. A flight control system is operable to independently control each of the propulsion assemblies. A first yaw authority mechanism includes differential speed control of rotor assemblies rotating clockwise compared to rotor assemblies rotating counterclockwise. A second yaw authority mechanism includes differential longitudinal control surface maneuvers of control surfaces of two symmetrically disposed tail members. A third yaw authority mechanism includes differential thrust vectoring of propulsion assemblies.

Abstract: An aircraft has an airframe with a two-dimensional distributed thrust array attached thereto having a plurality of propulsion assemblies that are independently controlled by a flight control system. Each propulsion assembly includes a housing with a gimbal coupled thereto that is operable to tilt about first and second axes responsive to first and second actuators. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that rotate in a rotational plane to generate thrust having a thrust vector. Responsive to a thrust vector error of a first propulsion assembly, the flight control system commands at least a second propulsion assembly, that is symmetrically disposed relative to the first propulsion assembly, to counteract the thrust vector error, thereby providing redundant directional control for the aircraft.

Abstract: An aircraft is operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons extending therebetween forming a central region. A two-dimensional distributed thrust array and a flight control system are coupled to the airframe. A nose cone and an afterbody are each selectively coupled to the airframe. In a cargo delivery flight configuration, the nose cone and the afterbody are coupled to the airframe such that the nose cone and the afterbody each extend between the first and second wings and between first and second pylons to form a cargo enclosure with an aerodynamic outer shape. In a minimal drag flight configuration, the nose cone and the afterbody are not coupled to the airframe such that air passes through the central region during flight.

Abstract: A wing airframe for a wing of a tiltrotor aircraft includes a wing airframe core assembly and a wing skin assembly disposed on the wing airframe core assembly. The wing skin assembly includes an outer skin and a damping sublayer, the damping sublayer interposed between the outer skin and the wing airframe core assembly. The tiltrotor aircraft includes a pylon assembly subject to aeroelastic movement during forward flight. The wing is subject to deflection in response to the aeroelastic movement of the pylon assembly. The damping sublayer reduces the deflection of the wing, thereby stabilizing the wing during forward flight.

Abstract: An autonomous package delivery aircraft is operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft includes an airframe with a distributed thrust array coupled thereto. A flight control system is operably associated with the distributed thrust array and is configured to independently control each of the propulsion assemblies of the distributed thrust array. A package delivery module is coupled to the airframe. In the VTOL orientation, a first pair of propulsion assemblies is forward of the package delivery module while a second pair of propulsion assemblies is aft of the package delivery module. In a forward flight orientation, the first pair of propulsion assemblies is below the package delivery module and the second pair of propulsion assemblies is above the package delivery module.

Abstract: A rotorcraft rotor blade assembly includes a stub spar extending less than a full span of the rotor blade assembly. An upper skin portion extends substantially the full span of the rotor blade assembly. A lower skin portion extends substantially the full span of the rotor blade assembly. The stub spar is positioned between the upper skin portion and the lower skin portion.

Abstract: An aircraft has an airframe with a distributed thrust array attached thereto that includes a plurality of propulsion assemblies each of which is independently controlled by a flight control system. Each propulsion assembly includes a housing with a single axis gimbal coupled thereto and operable to tilt about a single axis. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that rotate in a rotational plane to generate thrust having a thrust vector with a direction. Actuation of each gimbal is operable to tilt the respective propulsion system including the electric motor and the rotor assembly relative to the airframe to change the rotational plane of the respective rotor assembly relative to the airframe, thereby controlling the direction of the respective thrust vector.

Abstract: An aircraft for capturing drones includes an airframe having a drone channel with first and second wings extending outboard thereof. A two-dimensional distributed thrust array includes a plurality of propulsion assemblies coupled to each of the first and second wings such that the rotor disc of each propulsion assembly is outboard of the drone channel. A flight control system is coupled to the airframe and is operable to independently control each of the propulsion assemblies. A mesh bag is coupled to the drone channel forming a drone capture net. The aircraft is configured to convert between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft is also configured to overtake a drone during flight in the biplane orientation such that the drone passes through the drone channel into the mesh bag, thereby capturing the drone in the drone capture net.

Abstract: An aerial imaging aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons coupled therebetween. A two-dimensional distributed thrust array is coupled to the airframe. The thrust array includes a plurality of propulsion assemblies each operable for variable speed and omnidirectional thrust vectoring. A payload is coupled to the airframe and includes an aerial imaging module. A flight control system is operable to independently control the speed and thrust vector of each of the propulsion assemblies such that in an inclined flight attitude, the flight control system is operable to maintain the orientation of the aerial imaging module toward a target while translating the aircraft, changing aircraft altitude and/or circling the target.

Abstract: An aircraft has an airframe with first and second wings having first and second pylons extending therebetween. A distributed propulsion system attached to the airframe includes at least first, second, third and fourth propulsion assemblies that are independently controlled by a flight control system. A pod assembly is coupled to the airframe. In a VTOL flight mode, the first and second propulsion assemblies are forward of the pod assembly and the third and fourth propulsion assemblies are aft of the pod assembly. In a forward flight mode, the first and second propulsion assemblies are below the pod assembly and the third and fourth propulsion assemblies are above the pod assembly. In both the VTOL and forward flight modes, the first and fourth propulsion assemblies generate thrust having a first direction while the second and third propulsion assemblies generate thrust having a second direction that is different from the first direction.

Abstract: An aircraft includes an airframe and a distributed thrust array coupled to the airframe including at least six propulsion assemblies. A flight control system is operably associated with the distributed thrust array and is operable to independently control each of the propulsion assemblies. A package delivery module is coupled to the airframe. In a VTOL orientation utilizing thrust-borne lift, a first pair of propulsion assemblies is forward of the package delivery module, a second pair of propulsion assemblies is aft of the package delivery module and a third pair of propulsion assemblies is lateral of the package delivery module. In a forward flight orientation utilizing wing-borne lift, the first pair of propulsion assemblies is below the package delivery module, the second pair of propulsion assemblies is above the package delivery module and the third pair of propulsion assemblies is lateral of the package delivery module.