Abstract: A data delivery system has a tether deployable from an aircraft having a first data repository, a transmission pod at a deployed end of the tether, the transmission pod having first wireless communication circuitry, a communication conductor in parallel with the tether connecting the data repository in the aircraft with the first wireless communication circuitry in the transmission pod, and a receiving station on ground surface having a receiving antenna, second wireless communication circuitry compatible with the first wireless communication circuitry in the transmission pod, and a second data repository. The tether is deployed from the aircraft in a manner to position the transmission pod stationary proximate the receiving station antenna, and data is downloaded from the data repository in the aircraft to the data repository in the receiving station via the communication conductor and the wireless communication circuitry in the transmission pod.

Abstract: A satellite is provided, configured for stacking with another similarly designed satellite and to facilitate separation thereof. The satellite comprises a housing for carrying functional components, having a plurality of pairing arrangements and a separation arrangement. Each of the pairing arrangements comprises a post extending perpendicularly to a horizontal plane of the housing, and first and second guide members. First guide members of the satellite are configured to couple with second guide members of the other satellite when stacked therewith. The separation arrangement comprises a thrust element configured to impart an ejection force to facilitate the separation, and a release assembly configured to selectively facilitate allowing the ejection force to propel one of the satellites, thereby initiating the separation. The first guide member of the satellite cooperates with the second guide member of the other satellite to deflect it from the horizontal plane during separation.

Abstract: A satellite refueling system has a refueling satellite carrying fuel, a fuel hose connected to the fuel carried by the refueling satellite, with a maneuverable end effector at a deployed end of the fuel hose, the end effector comprising a fuel supply nozzle connected to the fuel hose, a plurality of thrusters on the end effector providing thrust in a plurality of directions, an imaging device on the end effector capturing images in an immediate environment of the end effector, and computerized circuitry operating individual ones of the plurality of thrusters in response to the images captured by the imaging device. The refueling satellite deploys the fuel hose, and the computerized circuitry operates the thrusters to maneuver the end effector, bringing the fuel supply nozzle to a location to deliver fuel.

Abstract: A rotor assembly for a fixed-wing VTOL aircraft. The rotor assembly is configured to provide vertical flight for the fixed-wing VTOL aircraft. In one embodiment, the rotor assembly includes a hub assembly, a first rotor blade affixed to the hub assembly, and a second rotor blade affixed to the hub assembly. The hub assembly orients the second rotor blade in relation to the first rotor blade about an axis of rotation of the hub assembly with the first rotor blade and the second rotor blade vertically stacked when the hub assembly is stopped for wing-borne flight.

Abstract: A process of joining a wing to an aircraft fuselage comprising the steps of: mapping the wing root of the wing, mapping the center-wing-box (CWB) of the aircraft fuselage, determining the position to provide the hole pattern on the CWB, providing the holes on the CWB, and attaching the wing root to the CWB. Primary and secondary templates with corresponding hole patterns may be used in combination with targets and laser trackers to implement the process. The hole pattern of the wing root can therefore be duplicated on the CWB at a position such that when the wings are joined to the fuselage, the aircraft will have optimum flight performance and dynamic symmetry. A predictive fit is thus provided, based on virtual representation and analysis, and advantageously permits the hole pattern to be provided without requiring the CWB and wing root to be brought together.

Abstract: A stabilizing system for a winch cable has a winch cable deployed and suspended from a helicopter, a cargo support attached at a deployed end of the winch cable, an end effector attached to the winch cable, the end effector comprising thrusters directed in a plurality of directions orthogonal to a vertical axis of the winch cable, first control circuitry in the helicopter, and second control circuitry in the end effector. Thrust of individual thrusters is controlled through the first and second control circuitry maintaining the axis of the winch cable vertical, damping swinging of the cable.

Abstract: A wing, a method of controlling lift on a wing, and a system to produce lift on a wing are provided. The wing may include a fore-element, an aft-element, a pivotable linkage that operatively connects the aft-element leading edge to the fore-element trailing edge in a span-wise direction, and an actuator. The actuator may deflect the aft-element through a predetermined deflection angle about the pivotable linkage relative to the fore-element within less than or equal to two convective periods. The method may include deflecting a span-wise flap through the deflection angle in less than or equal to two convective periods to produce high lift. The system may include a sensor to detect an input and a controller to deflect the span-wise flap of the wing by the deflection angle in not more than two convective periods based on the received input signal.

Abstract: An aircraft capable of carrying at least 400 pounds of payload, has four rotors systems, each of the rotor systems being independently driven by an electric motor or other torque-producing source. Each of the rotor systems provide sufficient thrust such that the aircraft is capable of controlled vertical takeoff and landing, even if one of the variable pitch rotor is inoperable. An electronic control system is configured to control the rotational speed and pitch of at least one of the rotor systems in each of the first and second rotor pairs. The rotors may be arranged in coaxial stacks or maybe otherwise configured.

Abstract: Disclosed is a device and method to load stores on an aircraft. The device may include a controller configured to: assign one or more stores to the aircraft; and control at least one actuator to: control a position of the aircraft; load the one or more stores onto one or more corresponding lift portions; position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from at least one sensor; and secure the one or more stores to the aircraft.

Abstract: A variable camber wing for mounting to a vehicle chassis has an actuator shaft and a static pin extending from the chassis. The wing's nose segment defines a proximal edge and a distal edge and has a channel therethrough between the proximal and distal edges, an arcuate aperture therethrough aft of the channel, and a second aperture therethrough aft of the arcuate aperture. The wing has a first linkage defining a clevis on a proximal end and hingeably connected to the nose segment. The clevis can rotatably engage with the static pin extending through the arcuate aperture. A second linkage defines a second clevis on a proximal end and a distal edge. The second linkage is configured to hingeably connect to the first linkage.

Abstract: A variable camber wing for mounting to a vehicle chassis has an actuator shaft and a static pin extending from the chassis. The wing's nose segment defines a proximal edge and a distal edge and has a channel therethrough between the proximal and distal edges, an arcuate aperture therethrough aft of the channel, and a second aperture therethrough aft of the arcuate aperture. The wing has a first linkage defining a clevis on a proximal end and hingeably connected to the nose segment. The clevis can rotatably engage with the static pin extending through the arcuate aperture. A second linkage defines a second clevis on a proximal end and a distal edge. The second linkage is configured to hingeably connect to the first linkage.

Abstract: A system delivering fire retardant materials in fighting a surface fire is provided, having an aircraft carrying the fire-retardant material, a hose deployable from the aircraft, the delivery hose connected to the reservoir and having a controllable nozzle at a deployed end with a remotely operable valve, an end effector connected by a multi-axis gimbal at the deployed end of the delivery hose the end effector having fixed wings with ailerons and elevators, and a rudder, the ailerons, elevators and rudder moved by electrical actuators, and control apparatus and circuitry in the aircraft and the end effector enabling an operator in manipulating the ailerons, elevators and the rudder. An operative in the aircraft controls the end effector via the control apparatus to fly at a lower altitude and in a different path than the aircraft, and opens the remotely operable valve to deliver the fire-retardant material from the delivery hose.

Abstract: A refueling system has a first vehicle having a fuel tank connected to a deployable fuel hose with a nozzle on the deployable end, a second vehicle carrying a supply of fuel, having a refueling panel with a refueling port adapted to connect to the nozzle on the deployed end of the fuel hose, an end effector joined to the fuel hose proximate the nozzle, the end effector having a plurality of thrusters providing thrust in a plurality of directions; and control circuitry in the first vehicle and in the end effector enabling an operative to vary direction and thrust of the thrusters. The operative controls the thrusters through the control circuitry to direct the nozzle toward and to connect the nozzle to the refueling port on the refueling panel of the second vehicle.

Abstract: Methods and systems for attaching and detaching an item satchel from an autonomous delivery unit. An attachment system includes an attachment system frame, and a satchel comprising a plurality of external pins. The attachment system also includes a plurality of hooks, mechanically attached to the frame, each hook including a first engagement surface and a second engagement surface, one or more electric actuators, mechanically attached to the frame, and mechanically connected to the plurality of hooks. Each of the first engagement surfaces engage a corresponding pin of the plurality of external pins at a first position between the horizontal and vertical positions, and each of the second engagement surfaces engage the corresponding pin of the plurality of external pins at the vertical position to secure an item satchel to an autonomous delivery unit.

Abstract: A UAV catch and release system has a UAV adapted to fly a mission, an aircraft adapted to carry, launch, and retrieve the UAV, a fuel hose deployed and retrieved by mechanisms from the aircraft, an end effector joined by a gimbal joint to a lowermost end of the fuel hose, a downward projecting aerodynamic acquisition blade connected at a lowermost end of the hose, and an acquisition port opening upward from the body of the UAV, with a roller mechanism operable to engage the acquisition blade, and to draw the blade into the body until a refueling nozzle on an end of the acquisition blade is engaged to a refueling port of the UAV.

Abstract: A plate folding and unfolding device and a solar panel structure are provided. The plate folding and unfolding device includes a cam fixed with first plate piece, and a rotating shaft is disposed inside the cam in an axial direction of the cam; a connecting rod, where the connecting rod includes a first end and a second end that are opposite to each other, the first end is connected vertically to the rotating shaft, and the second end is fixed to a second plate piece; a positioning shaft, where the positioning shaft is disposed, on the connecting rod; and an elastic piece, where the elastic piece is disposed on the connecting rod, one end of the elastic piece is connected to the positioning shaft, where a groove that accommodates the positioning shaft is disposed at at least one location of the outer peripheral surface of the cam.

Abstract: An unmanned aerial vehicle (UAV) includes a sprayer configured to generate a pressurized fluid flow and a nozzle configured to receive the pressurized fluid from the sprayer and to generate a spray fan to apply the fluid to a surface. The UAV includes sensors and a control unit to control both flight of the UAV and spraying by the sprayer. The fluid can be stored onboard the UAV in a reservoir or can be remotely stored and pumped to the UAV. The UAV control unit can be preloaded with a spray plan and a flight plan, or the UAV can be controlled by a user.

Abstract: A method for de-icing or anti-icing an aircraft portion having at least one piezoelectric element fastened on the inner face of the aircraft portion includes, during a design phase of the aircraft portion, placing the piezoelectric element on an area of the aircraft portion to determine frequencies of resonance and increased dynamic coupling, and during the de-icing or anti-icing of the aircraft portion, the same piezoelectric element is excited according to the natural frequencies of the area.

Abstract: The invention relates to a propulsion device for an aircraft, comprising a blade (2) which can be rotated about an axis of rotation (51) of the propulsion device along a circular path (52) and is mounted for pivoting about a blade bearing axis parallel to the axis of rotation; a pitch mechanism having a coupling device (31) and a bearing device (33); and an offset device (4) to which the blade is coupled, the offset device defining an eccentric bearing axis (41) which is mounted at an adjustable offset distance. The coupling device is coupled to the blade at a coupling point (32) which is positioned in such a way that the plane that comprises the blade bearing axis and the coupling point and the tangential plane to the circular path through the blade bearing axis include a certain, non-vanishing angle (w?) when the offset distance is set to zero.

Abstract: An aircraft capable of carrying at least 400 pounds of payload, has four rotors systems, each of the rotor systems being independently driven by an electric motor or other torque-producing source. Each of the rotor systems provide sufficient thrust such that the aircraft is capable of controlled vertical takeoff and landing, even if one of the variable pitch rotor is inoperable. An electronic control system is configured to control the rotational speed and pitch of at least one of the rotor systems in each of the first and second rotor pairs. The rotors may be arranged in coaxial stacks or maybe otherwise configured.