Abstract: An electric-powered aircraft battery pack and associated battery pack cooling system. The battery pack comprises a plurality of thermally conductive cooling plates and at least one battery cell coupled with each cooling plate. Heat generated by the battery cells is transferred by conduction to the associated cooling plate. The heat carried by the cooling plates is then transferred by convection to a fluid medium. In some embodiments, heat is transferred from the cooling plate to ambient air or ram air of the aircraft. In some embodiments, heat is transferred from the cooling plate to coolant liquid of a battery pack cooling system.

Abstract: In an embodiment, a method of managing force equalization (FEQ) on a vehicle utilizing redundant actuation systems for one or more control surfaces includes determining, via a force sensor, a measured force applied by a first actuation system in relation to a control surface, where the control surface is redundantly serviced by a plurality of actuation systems. The method also includes updating a measured-force time series for the first actuation system with the measured force. The method also includes analyzing movement over at least a portion of the measured-force time series. The method also includes identifying a force-fight cycle in the measured-force time series. The method also includes indicating the force-fight cycle in cumulative force-fight cycle data for the first actuation system.

Abstract: In an embodiment, a method of monitoring force equalization (FEQ) sensors on a vehicle utilizing redundant actuation systems for one or more control surfaces includes determining, via a force sensor, a first measured force applied by a first actuation system in relation to a control surface, where the control surface is redundantly serviced by a plurality of actuation systems that include the first actuation system. The method also includes updating a measured-force time series for the first actuation system with the first measured force. The method also includes determining variation in at least a portion of the measured-force time series responsive to the updating. The method also includes identifying a first static condition in the measured-force time series in response to a determination that the variation in the measured-force time series is no greater than a minimum amount of variation.

Abstract: A spherical bearing centrifugal force retention link includes an inboard spherical bearing to attach to a rotor hub and an outboard spherical bearing to attach to a rotor blade. In use, the inboard spherical bearing and the outboard spherical bearing react centrifugal force radially and a torsional moment of the centrifugal force link is substantially constant throughout the rotor blade pitch range.

Abstract: A fast-rope system for use with a rotary aircraft includes a tubular housing attached to an interior portion of a cabin and adjacent to an upper portion of an exit door opening of the rotary aircraft and a fast-rope frame structure rotatably coupled to the tubular housing. The fast-rope frame structure includes a cylindrical pipe contained partially within the tubular housing and operable to rotate within the tubular housing and a cantilever beam structure fixedly connected to the cylindrical pipe and configured to have a fast rope attached thereto and move in response to rotation of the cylindrical pipe within the tubular housing.

Abstract: A method for reducing form drag on a tailsitter aircraft during at least one of takeoff or landing includes vertically taking off from the ground in a tailsitter orientation. The method also includes determining an actual pitch of the tail sitter aircraft in the tailsitter orientation. The method also includes determining a difference between the actual pitch and a predetermined pitch. The method also includes adjusting a heading of the tailsitter aircraft based on the difference to minimize a pitch angle to reduce the form drag on the tailsitter aircraft.

Abstract: A propulsion system for providing propulsion of an aircraft includes a plurality of electric motors coupled with a rotor of the aircraft to drive the rotor and a propulsion motor control. The propulsion motor control includes at least one processor electrically connected with at least one electric motor to actuate the at least one electric motor and at least one battery electrically connected with the at least one processor and at least one electric motor to provide power to the at least one processor and the at least one electric motor. The propulsion motor control actuates the plurality of electric motors based on a desired torque level to drive the rotor to provide propulsion of the aircraft.

Abstract: A nonintegral cold plate is described for providing cooling of battery charging. The nonintegrated cold plate can receive and circulate coolant against a surface of a battery or of a vehicle. After charging the nonintegrated cold plate can be removed to save weight on the vehicle's payload.

Abstract: An aircraft includes a fuselage and an airframe supporting the fuselage. The airframe includes a pair of longitudinally-extending beams. The aircraft further includes a battery assembly including a cold plate secured to the pair of longitudinally-extending beams, and a battery mounted to the cold plate.

Abstract: A battery assembly for an aircraft includes a cold plate having an upper planar member, a lower planar member, and at least one fluid channel positioned between the upper and lower planar members and configured to receive a cooling fluid. The battery assembly also includes an upper battery mounted to the upper planar member for transferring heat from the upper battery to the cooling fluid through the upper planar member. The battery assembly further includes a lower battery mounted to the lower planar member for transferring heat from the lower battery to the cooling fluid through the lower planar member.

Abstract: A cold plate is couplable with a component for dissipating heat from a component. The cold plate includes a top plate coupled with a bottom plate to receive a cooling medium therebetween. The top plate includes a body and a plurality of walls extending from the body, wherein each wall of the plurality of walls includes a recess extending within the wall. The bottom plate includes a body and a plurality of walls extending from the body such that an end portion of each wall of the bottom plate is inserted within the recess of each wall of the top plate to form an interlocking joint.

Abstract: An aircraft includes fuselage, a seat, and battery compartment. Fuselage extends along a longitudinal axis. Seat is configured to support a passenger. The battery compartment that includes a battery configured to provide power to propel the aircraft. The battery compartment, including the battery, is located laterally adjacent to the seat along the longitudinal axis.

Abstract: A pump assembly, comprising a pump and housing having an inlet passage and an outlet passage. The pump includes inlet and outlet ports and opposing first and second drive inputs configured to be rotated together in a pumping direction to operate the pump. The pump can be installed in the housing in a first orientation, in which the first drive input is configured for being rotated by a drive source in a first external direction to operate the pump, and a second orientation, in which the second drive input is configured for being rotated by the drive source in a second external direction opposite of the first external direction to operate the pump. In both the first orientation and the second orientation, the inlet port is in fluid communication with the inlet passage and the outlet port is in fluid communication with the outlet passage.

Abstract: A fuel sample extractor (FSE) for an aircraft includes a sample chamber, a lid configured to seal the sample chamber, a pump in selective fluid communication with an upper portion of the sample chamber, and a straw in selective fluid communication with a lower portion of the sample chamber and a fuel tank.

Abstract: Embodiments are directed to a rotorcraft comprising an airframe having an engine compartment, an engine disposed within the engine compartment, at least one fire bottle configured to hold a fire extinguishing agent, at least one agent tube coupled to the fire bottle and configured to carry the fire extinguishing agent to the engine compartment, and a nozzle on the at least one agent tube, the nozzle positioned above the engine and oriented in a downward-facing direction. The nozzle has at least one opening and is configured to allow liquid to drain out of the at least one opening instead of allowing the liquid to flow into the at least one agent tube. The nozzle may have a chamfer opening that faces downward.

Abstract: A vertical takeoff and landing aircraft is described in which rotors can be disposed underneath the booms. This will allow for zero downward force resulting from thrust on the aircraft and therefore greater energy efficiency. Retractable doors can shield the rotors when not in use, decreasing drag during forward flight.

Abstract: A method of preparing a composite article including providing a first bias assembly with a first bias roll; providing a first non-bias assembly with a first non-bias roll; positioning the first bias assembly to a dispensing position; dispensing a bias ply from the first bias roll along a bias path on a mold; cutting the bias ply; positioning the first non-bias assembly to a dispensing position; dispensing a non-bias ply from the first non-bias roll; and cutting the non-bias ply; wherein the bias path and the non-bias path are substantially parallel.

Abstract: The current disclosure describes a cloaking system for an aircraft. Cameras on the aircraft can detect background colors during flight. Electroluminescent paint on the aircraft can be powered on that resembles the background color. The color and luminescence of the aircraft will allow for dynamic cloaking unachievable by prior art camouflage paint colors.

Abstract: Methods and systems are described for increasing the safety of unmanned vehicles. Failure rates of components can be combined and adjusted if necessary given sensor data or statistical or historical data that impacts failure rates. The failure rates of components can be combined to give an overall failure or success rate for a vehicle and can be compared to an accepted failure or success rate in connection with a hazard. Hazards with heightened safety requirements can be avoided by a contingency maneuver if the unmanned vehicle's failure or success rate is not acceptable.

Abstract: In an embodiment, an aircraft includes a pilot input device, a position sensor coupled to the pilot input device, a flight condition sensor and a flight control computer (FCC). The FCC includes a first microprocessor and a second microprocessor. The first microprocessor is configured to receive input data from the position sensor and the condition sensor and determine therefrom a first output. The second microprocessor is configured to receive input data from the position sensor and the condition sensor and determine therefrom a second output. The FCC is configured to compare the first output and the second output to yield resultant data. Responsive to a determination that the first output and the second output do not match, the FCC is configured to execute first remediation logic if the resultant data satisfies first error criteria and to execute second remediation logic if the resultant data satisfies second error criteria.