Abstract: A floating nut plate quarter turn fastener receptacle configured for fastening two structures together is disclosed. The quarter turn fastener includes a basket portion with flanges configured to loosely retain a nut element. The nut element is able to glide or shift between the flanges of the basket portion. The nut element includes an aperture and a wire recessed into a channel which intersects the aperture. The nut element is able to be moved within the flanges for aligning the aperture with a corresponding aperture through the basket portion, thereby enabling a fastening device to be inserted through both apertures and twisted a quarter turn for securing to the wire and fastening two structures together.

Abstract: A doorway side guide system includes a base mechanically coupled with a bottom portion of a doorway. A mounting member is rotatably coupled to the base via a hinge for rotating between a deployed position and a stowed position. A contact member is mechanically coupled with the mounting member via a pivot such that the contact member is configured to rotate about the pivot. The contact member extends outside of the doorway in the deployed position for guiding cargo through the doorway and for protecting a doorframe of the doorway.

Abstract: An aircraft rudder control system having one or more rudder pedal adjustment systems, each including a rudder pedal actuatable to control movement of a rudder, and further including a support frame component, a rudder pedal arm, a pin, a pin receiving component, a first lever, a second lever, and/or a solenoid. The rudder pedal arm is rotatably attached to the support frame component and the rudder pedal is attached to the rudder arm. While the pin is received in the pin receiving component, the rudder pedal arm is prevented from rotating. When the pin is withdrawn from the pin receiving component, the rudder pedal arm is freed to be rotatably repositioned by user foot actuation. The first lever can manually actuate the pin into and out of the pin receiving component, and the second lever is operated by the solenoid, actuating the pin when the solenoid is activated and deactivated.

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 control servo for an aircraft engine control system, the control servo broadly comprising a housing, a stepper motor, a drivetrain, an output shaft, and an output lever. The housing includes a drivetrain chamber, a drive opening, and an output opening. The stepper motor includes a drive shaft extending through the drive opening into the drivetrain chamber. The drivetrain is at least partially positioned in the drivetrain chamber. The output shaft extends through the output opening from the drivetrain chamber. The drivetrain drivably connects the drive shaft and output shaft. The output lever includes an output lever arm and a friction interface. The output lever arm has opposing proximal and distal ends and is connected to the output shaft near the proximal end. The friction interface is near the proximal end and configured to be adjusted to set a slip friction threshold between the output lever and the output shaft.

Abstract: An aircraft skin alignment system includes at least one support structure to support one or more aircraft skins and one or more assembly tools; the one or more assembly tools having a holding mechanism to releasably engage with a first aircraft skin; a pulling mechanism to apply a pulling force to the first aircraft skin; and an edge locator; the pulling mechanism is to pull the first aircraft skin such that a first edge of the first aircraft skin abuts the edge locator, the edge locator preventing the first edge from being pulled past the edge locator; and one or more tool holes can be drilled into the first aircraft skin such that the one or more tool holes are aligned based on an edge index due to a position of the edge locator.

Abstract: An aircraft structure includes a fuselage, a tail structure, a hinge support structure, and at least one internal actuator. The tail structure is pivotally attached to the fuselage and includes a tailcone and horizontal stabilizers fixed to the tailcone. Each of the horizontal stabilizers have a stabilizer leading edge and a stabilizer trailing edge and extend in opposite directions from the tailcone, forming an H-tail or a U-tail configuration. The hinge support structure is fixed at least partially within the fuselage, pivotally coupling the fuselage and the tail structure. The at least one internal actuator actuates the tail structure, rotating the stabilizer leading edge up and down relative to the fuselage, thereby trimming the horizontal stabilizers for aircraft stabilization.

Abstract: An aircraft or aircraft body having an airframe structure, a pylon, a protrusion, and a nacelle. The airframe structure is a wing or a fuselage. The pylon has a first end, a second end opposite the first end, a first surface extending between the first end and the second end, and a second surface opposite the first surface. The first end is fixed to the airframe structure. The protrusion extends outward from the first surface and/or the second surface. The nacelle is located at the second end of the pylon and has a leading end, a trailing end, and a tapered boattail at the trailing end. The protrusion is located between the airframe structure and the tapered boattail. The protrusion is sized, shaped, and positioned between the boattail and the fuselage or wing to mitigate boundary layer separation.

Abstract: A wire twisting device may include a driven rotating mechanism having a groove configured to receive two wires, an electric motor associated with an encoder, wherein the encoder is configured to generate an electrical signal corresponding to changes in rotation of the electric motor, a drive gear mechanically coupled with the electric motor for rotating the driven rotating mechanism, a current sensor on a printed circuit board configured to detect an electrical current to the electric motor and generate a voltage that corresponds to the amount of electrical current, and a control unit configured to perform steps comprising: receiving the electrical signal generated by the encoder, receiving the voltage generated by the current sensor, determining an amount of torque applied to the two wires; and when the amount of torque exceeds a predetermined limit, communicating a control signal to reduce the electrical current provided to the electric motor.

Abstract: A handle assembly for an escape hatch. A handle assembly for an escape hatch comprises an interior handle and an exterior handle. The interior handle has an interior cam associated therewith and the exterior handle has an exterior cam associated therewith. The interior cam and the exterior cam each have a concave profile surface and a curved profile surface. A middle cam is sandwiched between the interior cam and the exterior cam and has a notched profile. The interior and exterior cams are associated with a tumbler having a flag. The middle cam is associated with an output rod operatively coupled to a second flag. Each of the interior handle and the exterior handle can be successively rotated in a first arc of rotation and a second arc of rotation with one hand. The first and second arcs of rotation are respectively associated with the flag and the second flag.

Abstract: A system and a method for contactless power generation for a lighting arrangement configured on an aircraft propeller. Power is produced when a magnetic field produced by an arrangement of magnets on an airframe magnetically interacts with coils configured on an aircraft propeller. When the propeller spins, rotation of the mounted coils through the magnetic fields of the magnets generate power. Electrical wiring carrying charge from the coils to the lights is laid into grooves formed in propeller blades which connect to lights inserted in formed sockets.