Lockheed Martin

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.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …