Abstract: A cloaking system for an aircraft is provided. 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: A landing guidance system for an aircraft is described and includes at least one receiver for installation on the aircraft, the at least one receiver configured to receive signals emitted by a plurality of emitters associated with a landing area; and a processing system for processing the received signals to determine at least one of a location, a distance, an orientation, a configuration, and a geometry of the landing area relative to the aircraft.

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 below the engine and oriented in a upward-facing direction. The nozzle has at least one opening that is closed by a spring-loaded valve.

Abstract: A wing for an aircraft includes a first end, a second end, and a skin extending longitudinally from the first end to the second end. The wing also includes at least one channel positioned within the skin and extending longitudinally between the first and second ends. The at least one channel defines a longitudinal translation path for translating at least one electrical power source longitudinally between the first and second ends.

Abstract: A rotorcraft includes a drive shaft coupled to an engine; a sprag clutch coupled the drive shaft; and an output shaft coupled to the sprag clutch, wherein the sprag clutch physically contacts a first contact surface of the output shaft during operation, wherein a first cross-sectional thickness of the output shaft near the middle of the first contact surface is greater than a second cross-sectional thickness of the output shaft near a first edge of the first contact surface.

Abstract: A battery cell assembly, including a rolled cell formed from a first electrode and a second electrode rolled together about a longitudinal axis. The rolled cell includes a primary section in which the first electrode and the second electrode overlap in a radial direction from the longitudinal axis, and a first extension end extending from a first longitudinal end of the primary section and formed from a first edge section of the first electrode. The first edge section includes a first folded portion folded to contact an adjacent portion of the first edge section. The battery cell assembly further includes a first end cap coupled to the rolled cell and contacting the first folded portion.

Abstract: An aircraft has a seat that has at least one of (1) a nonplanar back surface profile and a touch sensitive film display system carried by the seat and configured to conform to the nonplanar back surface profile and (2) a privacy screen selectively stowed within an interior of the seat. An aircraft has a pilot seat, a passenger seat disposed aft relative to the pilot seat, and a holographic display system configured to project a holographic image in a space between the pilot seat and the passenger seat.

Abstract: A method includes measuring a first rotational speed of a first element of a sprag clutch of a rotorcraft, measuring a second rotational speed of a second element of the sprag clutch, determining if the sprag clutch is in an overrunning condition, wherein the determining is based on the first rotational speed and the second rotational speed, generating an estimation of an instantaneous wear rate of the sprag clutch, wherein the estimation of the instantaneous wear rate is generated based on the first rotational speed and the second rotational speed, and displaying an indication of the estimation of the instantaneous wear rate of the sprag clutch. The method includes generating an estimation of an accumulated wear of the sprag clutch, wherein the estimation of the accumulated wear is based on the estimation of the instantaneous wear rate, and displaying an indication of the estimation of the accumulated wear.

Abstract: A stairway for aircraft is disclosed which includes first and second stair halves, one which nests in the other. The first half is hinged to the doorway and the second half is hinged to the first half. A mechanical resistance system uses different devices to allow for the airstair to be damped when switching between modes. A retracting arrangement is also disclosed.

Abstract: A telescoping tail assembly for use on an aircraft that has a fore-aft length. The telescoping tail assembly includes a housing extending in an aftward direction and a tailboom slidable along the housing into various positions including an extended position and a retracted position. A jackscrew is coupled to the tailboom. An actuator is coupled to the jackscrew and is configured to selectively rotate the jackscrew to translate the tailboom between the plurality of positions. The tailboom has one or more control surfaces coupled thereto. The tailboom increases the fore-aft length of the aircraft in the extended position and decreases the fore-aft length of the aircraft in the retracted position.

Abstract: A vehicle transaxle comprising a plurality of mounting flanges fixedly mountable to an axle tube of the vehicle absent any additional structure for mounting the transaxle to the vehicle. The axle tube houses a wheel axle to which the transaxle is operably couplable. The transaxle additionally comprises a transaxle mounting collar that is fixedly mounted to or integrally formed with a housing of the transaxle. The mounting collar is structured and operable to have a prime mover of the vehicle mounted thereto and to support the weight/mass of the prime mover such that the prime mover is mountable to the vehicle via only the mounting collar absent any additional structure for mounting the prime mover to the vehicle such that the prime mover can be cantilevered from (e.g., suspended from) the transaxle, e.g., the prime mover is ‘free floating’.

Abstract: In an embodiment, an aircraft includes an actuator and a flight control computer interfaced with the actuator.

Abstract: A door management system on an aircraft includes a fuselage extending along a longitudinal axis in a fore-aft direction parallel to forward flight, an opening in a sidewall of the fuselage, a door mounted on the sidewall to slide in the fore-aft direction between a closed position covering the opening and an open position revealing the opening, a cable attached to the fuselage and the door and a speed governor operatively coupled to the cable to limit a velocity of the door as it moves between the open position and the closed position.

Abstract: A rotorcraft has a drive system including a main rotor coupled to a main rotor gearbox to rotate the main rotor at a rotor speed, a main engine coupled to the drive system to provide a first power, a supplemental engine coupled, when a first clutch is engaged, to the drive system to provide a second power additive to the first power, and a control system operable to control the main engine and the supplemental engine to provide a total power demand, where the main engine is controlled based on variations in rotor speed and a power compensation command to produce the first power, and the supplemental engine is controlled to produce the second power in response to a supplemental power demand.

Abstract: One embodiment is a system including a component for installation on a vehicle comprising a central maintenance computer (“CMC”); a configuration/maintenance module (“CMM”) associated with the component and including memory for storing component information, a sensor for detecting a condition and generating data indicative thereof; a microprocessor for processing the sensor data and updating the component information with the processing results; and a communications interface between the CMM and the CMC. The system further includes a remaining useful life (“RUL”) module associated with the component that periodically updates an RUL, the RUL module periodically updating an RUL value for the component and communicating the updated RUL value to the CMM for storage in the memory. The CMC communicates with the CMM to update the component information included in the memory based on information input to the CMC by a user or changes in a condition of the vehicle.

Abstract: A pneumo-mechanical landing gear deployment system includes a dual-stage handle operatively connected to a pressurized tank, a nose landing gear pneumatically connected to the pressurized tank, and a main landing gear pneumatically connected to the pressurized tank. Actuation of the dual-stage handle to a first position opens the pressurized tank thereby deploying the nose landing gear. Actuation of the dual-stage handle to a second position causes further opening of the pressurized tank thereby deploying the main landing gear. The system may be employed as a backup landing gear deployment system in the case of a primary landing gear system failure.

Abstract: A window roller shade and dimming pane assembly includes a rigid frame having a first side member on a first side and a second side member on a second side opposite the first side. An outer pane and an inner pane are disposed within the rigid frame with a gap between the outer pane and the inner pane. A roller shade includes a motor for rolling and unrolling the roller shade. A first constant force spring and a second constant force spring are each configured to pull the roller shade downwardly through the gap while the motor is unrolling the roller shade. A dimming film is disposed on the inner pane for dimming light through the inner pane. A window interface is operatively coupled to the inner pane for receiving touch input for controlling the dimming film and the roller shade.

Abstract: An aircraft is described and includes a fuselage; wings attached to the fuselage; and a torque box within the fuselage, the torque box including a side panel, the side panel comprising a composite laminate material including a plurality of stiffening beads integrated therewith. The plurality of stiffening beads may be integrated with the side panel and extend parallel to one another.