Abstract: A hover-capable aircraft includes a body including a tubular strut, a first rotor assembly rotatably coupled to the body and positioned about the strut, wherein the first rotor assembly includes a first plurality of circumferentially-spaced blades, a first actuation assembly including a first plurality of electronically controlled actuators coupled to a first swashplate and configured to control the movement of the first swashplate relative to the body, and a control system coupled to the body and configured to control the first plurality of actuators, wherein the control system includes a cable extending through a passage formed in the tubular strut and in signal communication with the first plurality of actuators.

Abstract: An electric machine includes a stator having a plurality of stator teeth. Each stator tooth of the plurality of stator teeth includes a winding disposed there around. Each stator tooth of the plurality of stator teeth is shaped to receive a plurality of microchannels. The microchannels contain a circulating heat-transfer fluid; Each stator tooth of the plurality of stator teeth is thermally exposed to the heat-transfer fluid via the plurality of microchannels so as to effectuate heat removal from each stator tooth of the plurality of stator teeth.

Abstract: An autonomous landing system includes a vertical landing aircraft, a visual cue coupled to an offshore landing platform and including a visual indicator located that extends vertically across a horizon and is maintained parallel with the horizon, and an autonomous control system configured to control a position of the aircraft with respect to the visual indicator to maneuver the aircraft into a hovering, predefined landing position above the offshore landing platform, and control the position of the aircraft with respect to the visual indicator to cause the aircraft to descend from the landing position and land on the offshore landing platform.

Abstract: An autonomous landing system for vertical landing aircraft includes a vertical landing aircraft including a powertrain and an onboard camera, a motion-stabilized visual cue including a visual indicator, wherein the visual cue is configured to maintain a fixed orientation of the visual indicator with respect to a horizon, and an autonomous control system configured to control a position of the aircraft with respect to the visual indicator of the visual cue based on image data captured by the onboard camera.

Abstract: A composite rotor for an electric motor includes an annular composite support plate extending radially relative a central axis of the composite rotor between an inner diameter defining a central opening of the composite support plate and an outer diameter, wherein the composite support plate includes a quasi-isotropic composite material, and an annular magnet assembly extending around the central axis of the composite rotor and coupled to a surface of the composite support plate.

Abstract: An amphibious vehicle for traversing land and bodies of water includes a chassis, and a cycloidal propeller coupled to the chassis and which includes a plurality of cycloidal propeller blades rotatably coupled to the chassis and each extending parallel a rotational axis of the cycloidal propeller, and an extension/retraction system configured to extend the plurality of cycloidal propeller blades away from the chassis and to retract the plurality of cycloidal propeller blades towards the chassis.

Abstract: A projectile-launched aircraft system includes a projectile launcher including a triggering mechanism, a rotary-wing, hover-capable aircraft including a rotor assembly that includes at least one rotor blade, wherein the rotor blade includes a stowed configuration and a deployed configuration that is circumferentially spaced from the stowed configuration about a pivot axis, wherein, upon actuation of the triggering mechanism, the projectile launcher is configured to launch the aircraft along a flightpath.

Abstract: A multi-modal vehicle includes a frame, a rotor pivotally mounted to the frame, the rotor including a first position and a second position circumferentially spaced from the first position, and a motor coupled to the rotor and configured to rotate the rotor, wherein, when the rotor is disposed in the first position, the rotor is configured to generate lift when actuated by the motor, wherein, when the rotor is disposed in the second position, the rotor is configured to engage a surface to transport the vehicle when actuated by the motor.

Abstract: An electric machine includes a stator having a plurality of stator teeth. Each stator tooth of the plurality of stator teeth includes a winding disposed there around. Each stator tooth of the plurality of stator teeth is shaped to receive a plurality of microchannels. The microchannels contain a circulating heat-transfer fluid; Each stator tooth of the plurality of stator teeth is thermally exposed to the heat-transfer fluid via the plurality of microchannels so as to effectuate heat removal from each stator tooth of the plurality of stator teeth.

Abstract: A cycloidal rotor air vehicle includes an airframe, a first cycloidal rotor assembly supported by the airframe and configured to rotate about a first axis of rotation relative to the airframe, the first cycloidal rotor assembly including a blade having a longitudinal axis oriented parallel to the first axis of rotation, a first motor configured to rotate the first cycloidal rotor assembly about the first axis of rotation, a first servo coupled to the blade of the first cycloidal rotor assembly and configured to adjust the pitch of the blade, and a control system supported on the airframe and configured to control the operation of the first motor and the first servo.

Abstract: A flapping-wing aircraft includes a support frame, a motor coupled to the support frame, a pair of wings coupled to the support frame, and a linkage assembly coupled to the support frame and configured to translate an output torque of the motor into flapping motion of the wings, wherein the linkage assembly includes a first link coupled to a rotational output of the motor, a second link pivotably coupled to the first link at a first pivot joint, a third link pivotably coupled to the second link at a second pivot joint, and a fourth link pivotably coupled to the support frame and slidably coupled to the third link, and wherein the fourth link is coupled to a first wing of the pair of wings.

Abstract: A projectile-launched aircraft system includes a projectile launcher including a triggering mechanism, a rotary-wing, hover-capable aircraft including a rotor assembly that includes at least one rotor blade, wherein the rotor blade includes a stowed configuration and a deployed configuration that is circumferentially spaced from the stowed configuration about a pivot axis, wherein, upon actuation of the triggering mechanism, the projectile launcher is configured to launch the aircraft along a flightpath.

Abstract: An autonomous landing system for vertical landing aircraft includes a vertical landing aircraft including a powertrain and an onboard camera, a motion-stabilized visual cue including a visual indicator, wherein the visual cue is configured to maintain a fixed orientation of the visual indicator with respect to a horizon, and an autonomous control system configured to control a position of the aircraft with respect to the visual indicator of the visual cue based on image data captured by the onboard camera.

Abstract: An amphibious vehicle for traversing land and bodies of water includes a chassis, and a cycloidal propeller coupled to the chassis and which includes a plurality of cycloidal propeller blades rotatably coupled to the chassis and each extending parallel a rotational axis of the cycloidal propeller, and an extension/retraction system configured to extend the plurality of cycloidal propeller blades away from the chassis and to retract the plurality of cycloidal propeller blades towards the chassis.

Abstract: A hover-capable aircraft includes a body including a tubular strut, a first rotor assembly rotatably coupled to the body and positioned about the strut, wherein the first rotor assembly includes a first plurality of circumferentially-spaced blades, a first actuation assembly including a first plurality of electronically controlled actuators coupled to a first swashplate and configured to control the movement of the first swashplate relative to the body, and a control system coupled to the body and configured to control the first plurality of actuators, wherein the control system includes a cable extending through a passage formed in the tubular strut and in signal communication with the first plurality of actuators.

Abstract: A flapping-wing aircraft includes a support frame, a motor coupled to the support frame, a pair of wings coupled to the support frame, and a linkage assembly coupled to the support frame and configured to translate an output torque of the motor into flapping motion of the wings, wherein the linkage assembly includes a first link coupled to a rotational output of the motor, a second link pivotably coupled to the first link at a first pivot joint, a third link pivotably coupled to the second link at a second pivot joint, and a fourth link pivotably coupled to the support frame and slidably coupled to the third link, and wherein the fourth link is coupled to a first wing of the pair of wings.

Abstract: A multi-modal vehicle includes a frame, a rotor pivotally mounted to the frame, the rotor including a first position and a second position circumferentially spaced from the first position, and a motor coupled to the rotor and configured to rotate the rotor, wherein, when the rotor is disposed in the first position, the rotor is configured to generate lift when actuated by the motor, wherein, when the rotor is disposed in the second position, the rotor is configured to engage a surface to transport the vehicle when actuated by the motor.

Abstract: A cycloidal rotor air vehicle includes an airframe, a first cycloidal rotor assembly supported by the airframe and configured to rotate about a first axis of rotation relative to the airframe, the first cycloidal rotor assembly including a blade having a longitudinal axis oriented parallel to the first axis of rotation, a first motor configured to rotate the first cycloidal rotor assembly about the first axis of rotation, a first servo coupled to the blade of the first cycloidal rotor assembly and configured to adjust the pitch of the blade, and a control system supported on the airframe and configured to control the operation of the first motor and the first servo.

Abstract: A fluid bearing includes a housing including an internal plenum disposed in the housing and an inlet in fluid communication with the plenum, wherein the inlet is configured to provide fluid to the plenum from an external source, a cushion surface facing away from the housing and the plenum, one or more nozzles positioned between the cushion surface and the housing, wherein the one or more nozzles extend from the plenum to the surrounding environment, wherein the one or more nozzles are configured to produce an annular curtain of fluid flowing at a velocity of at least Mach 1 and disposed about the cushion surface in response to a fluid flow entering the plenum from the inlet.

Abstract: A fluid bearing includes a housing including an internal plenum disposed in the housing and an inlet in fluid communication with the plenum, wherein the inlet is configured to provide fluid to the plenum from an external source, a cushion surface facing away from the housing and the plenum, one or more nozzles positioned between the cushion surface and the housing, wherein the one or more nozzles extend from the plenum to the surrounding environment, wherein the one or more nozzles are configured to produce an annular curtain of fluid flowing at a velocity of at least Mach 1 and disposed about the cushion surface in response to a fluid flow entering the plenum from the inlet.