Lockheed Martin Patente

A convertible aircraft includes a fuselage defining a flight axis, and a wing assembly including a pair of wings. Each wing includes a first panel coupled to the fuselage and extending along a wing axis, transverse to the flight axis, a second panel including a thruster having a blade assembly configured to rotate about a thruster axis, a first hinge configured to couple the second panel to the first panel for pivoting about a first hinge axis, a third panel, and a second hinge configured to couple the third panel to the second panel for pivoting about a second hinge axis, parallel to the first hinge axis.

An aircraft vehicle (100) includes an elongated spine element (140) with a first and second end (142, 143), and an elongated lift boom (130) at the first end (142), extending perpendicular to the spine (140). The vehicle (100) features a left coaxial counterrotating rotor assembly (120) with a front rotor blade (121) and motor (123), an aft rotor blade (122) and motor (124) rotating in the opposite direction to the front rotor blade (121), and a servo motor for tilting the assembly. Similarly, it has a right coaxial counterrotating rotor assembly with a front rotor blade and motor, an aft rotor blade and motor, and a servo motor (125) for tilting the assembly (120). Additionally, a tail coaxial counterrotating rotor assembly (150) is situated along the spine (140), with top and bottom rotor blades (151, 152) and motors (153, 154) rotating in opposite directions to each other. The aircraft (100) includes a power supply (180) for the rotor assemblies (120, 150) and a controller (190) to manage the power supplied to the motors (123, 124, 153, 154).

A vertical takeoff and landing aircraft, includes a main rotor system, a gearbox mechanically connected to the main rotor system, a first gas turbine engine mechanically connected to the gearbox, a first electrical motor-generator mechanically connected to the first gas turbine engine and mechanically connected to the gearbox, a second electrical motor-generator mechanically connected to the gearbox, a third electrical motor electrically connected to the second electrical motor-generator and mechanically connected to an anti-torque device, the third electrical motor configured to provide mechanical power to the anti-torque device, and a plurality of power-controller interface units. The plurality of power-controller interface units are configured to, during a first phase of flight, control the first gas turbine engine and the first electrical motor-generator to provide mechanical power to the gearbox, and control the second electrical motor-generator to provide electrical power to the third electrical motor.

A gear for transmitting motion and torque between components includes a first gear portion having a first material and which is formed by a first additive manufacturing process. The gear also includes a second gear portion having a second material and which is formed on the first gear portion. The second gear portion is formed by a second additive manufacturing process that is different from the first additive manufacturing process. At least one of the first gear portion or the second gear portion defines a plurality of teeth.

A temporary fastener actuation tool (120) includes a protrusion (122), multiple spring clips (124), and a bearing shaft (127). The protrusion (122) includes a groove (230) that matches a shape of an indentation (301) of a temporary fastener (130). Each spring clip (124) includes an end (240) that is aligned with an end (250) of the protrusion (122). The spring clips (124) are configured to hold the indentation (301) of the temporary fastener (130) secure against the protrusion (122). The temporary fastener actuation tool (120) further includes a first bearing (125) that is coupled to the bearing shaft (127) and is configured to contact a cylindrical body (300) of the temporary fastener (130) and rotate the cylindrical body (300) of the temporary fastener (130) in a first direction. The temporary fastener actuation tool (120) further includes a second bearing (126) coupled to the bearing shaft (127) that is configured to contact a stem (302) of the temporary fastener (130) and to rotate the stem (302) in a second direction. A motor shaft (121) is coupled to the bearing shaft (127).

A non-dichroic coating thin film structure (100), consisting of a Bragg-reflector structure (130) and a graded index layer (120), is deposited on a substrate. The Bragg-reflector structure includes several pairs of layers: each pair has a first layer (131) of a first material with a first refractive index and a quarter-wavelength thickness determined by a target wavelength, positioned adjacent to a second layer (132) of a second material with a second refractive index, having a quarter-wavelength thickness. The first refractive index is at least 0.5 higher than that of the second. Over the Bragg-reflector structure (130), a graded index layer (120) with a continuously changing refractive index is deposited, transitioning from a third refractive index to the first refractive index. The thickness of the graded index layer (120) is selected such that the reflection coefficient for light in the visible spectrum of 400-700 nanometers varies by no more than 25 percent for this wavelength range.

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According to some embodiments, a computer-implemented method is applied to calibrate a wireless test module (WTM) of a wireless harness automated measurement system (WHAMS) using a computer server and a calibration fixture (1500). The WTM includes a plurality of field effect transistors (FETs). The calibration fixture (1500) includes a plurality of resistors. The method measures, using the calibration fixture (1500), a first/second resistance value of the plurality of FETs from a first/second internal measurement test for the WTM. The method determines a resistance calibration value by subtracting the first resistance value from the second resistance value. The method measures a plurality of calibration factors to determine a measured resistor value for a target resistor value for a respective resistor of the calibration fixture (1500).

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In one embodiment, systems and methods include using an inspection system to remove or seal foreign object debris. An inspection system comprises a borescope; wherein a plurality of optical fibers is disposed within the borescope; a mounting system; an articulation system; and a controller, wherein the controller comprises a display; wherein a proximal end of the borescope is coupled to the mounting system, wherein the mounting system is configured to secure the inspection system to an external surface, wherein the mounting system is coupled to the articulation system, wherein the articulation system is configured to actuate the borescope, wherein the articulation system is communicatively coupled to the controller.

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Systems and methods for providing tactile feedback via an inceptor. A control system for an aircraft includes an inceptor and a controller. The inceptor includes a grip portion moveable between a plurality of positions and one or more motors to apply a variable force to the grip portion. The controller is coupled to the one or more motors. The controller includes an electronic processor and a memory. The controller is configured to operate in a first operating mode, select a first tactile feedback profile associated with the first operating mode, and control the one or more motors based on the first tactile feedback profile. The controller is further configured to detect a transition from the first operating mode to a second operating mode, select a second tactile feedback profile associated with the second operating mode, and control the one or more motors based on the second tactile feedback profile.

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In an embodiment, a system includes a three-dimensional (3D) printer, a neutral feedstock, a p-doped feedstock, an n-doped feedstock, and a laser. The 3D printer includes a platen and an enclosure. The platen includes an inert metal. The enclosure includes an inert atmosphere. The neutral feedstock is configured to be deposited onto the platen. The neutral feedstock includes a halogenated solution and a nanoparticle having a negative electron affinity. The p-doped feedstock is configured to be deposited onto the platen. The p-doped feedstock includes a boronated compound introduced to the neutral feedstock. The n-doped feedstock is configured to be deposited onto the platen. The n-doped feedstock includes a phosphorous compound introduced to the neutral feedstock. The laser is configured to induce the nanoparticle to emit solvated electrons into the halogenated solution to form, by reduction, layers of a ceramic comprising a neutral layer, a p-doped layer, and an n-doped layer.

A rotary shaft assembly includes a rotary shaft having a first end portion, a second end portion opposite the first end portion, a longitudinal axis extending centrally through the first and second end portions, and a shaft body that defines a bore between the first and second end portions . An anti-flailing mechanism is positioned within the bore of the shaft body. The anti-flailing mechanism is coupled to rotary shaft and extends at least partially between the first and second end portions to contain the rotary shaft about the longitudinal axis when the rotary shaft fails.

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Aerial navigation is disclosed. A system can detect a difference between forces applied to a plurality of ground contact points of an aerial vehicle taxiing on a ground surface. The system can determine an adjustment to a vertical component of a thrust. The thrust can be produced by at least one of a rotor or a propeller of the aerial vehicle to reduce the difference between the forces applied to the plurality of ground contact points of the aerial vehicle. The system can generate a control output to cause the at least one of the rotor or the propeller to adjust the vertical component of the thrust to reduce the difference between the forces.

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This disclosure relates to apparatuses, systems, and methods for controlling an aircraft. A computing system may identify a first command signal received via a flight control at a time point to control navigation of the aircraft through an environment. The computing system may attenuate the first command signal using a fade function over a time window relative to the time point to generate a second command signal. The computing system may input the second command signal to a model to generate predicted paths for the aircraft through the environment over the time window. The computing system may determine that at least one predicted path intersects with an obstacle in the environment during the time window. The computing system may generate a location to which to navigate the aircraft to avoid the obstacle. The computing system may perform an action to direct the aircraft to the location.

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