Lockheed Martin Corporation

James C Copp

Steven J Ellzey

David L Hunn

Sang J Lee

Toby D Thomas

Kenneth W Havens

David Louis Hoelscher

Gregory M Richards

Lloyd K Farris

An internal wing control surface linkage system comprising: an actuator arm configured to rotate around a first rotation axis within an airfoil body. A linking arm is mounted within the airfoil body. The linking arm comprises a linking tube and a linkage rod slideably received within the linking tube. The linking tube comprises a hinged end pivotally coupled to the actuator arm about a first pivot axis parallel to the first rotation axis to cause deflection of a control surface coupled to the airfoil body during rotation of the actuator arm. The linkage rod comprising a hinged end coupled to a clevis about a second pivot axis of the control surface. A spherical bearing swivelly coupling the linking arm and providing a fixed swivel pivot which swivels the linking arm, as the linking tube simultaneously slides within the spherical bearing and, in combination, the rod simultaneously slides within the linking tube.

Internal wing control surface linkage system

An apparatus, having: a fuselage body section () configured to be secured to an aircraft fuselage (); a pivot column () protruding from the fuselage body section; and a center wing section () configured to be secured to a center wing panel of a trifold wing (). The fuselage body section and the center wing section are configured to cooperate with each other to rotate the center wing section relative to the fuselage body section from a stowed position () to a deployed position (). The pivot column comprises a column feature () configured to engage with tip features () of the trifold wing to hold the trifold wing in a folded configuration when the trifold wing is in the stowed position and to disengage from the tip features as the trifold wing rotates to the deployed position, thereby freeing the trifold wing to unfold.

Apparatus for retaining and deploying a wing of an aerial vehicle

An aircraft is provided comprising: a fuselage, a first tail fin rotatably mounted to a first lateral side and a second tail fin rotatably mounted to the second lateral side. A wing body is rotatably mounted to the underside of the fuselage. A pair of independent tail fin latch and release devices are provided to independently latch the first tail fin and the second tail fin when the wing body having a first angle is in a stowed position with respect to the fuselage, to independently unlatch the first tail fin in response to a second angle of the wing body with respect to the fuselage, and to independently unlatch the second tail fin in response to a third angle of the wing body with respect to the fuselage. The first angle, second angle and third angle are different angles with respect to the longitudinal axis of the fuselage.

System and method for independent retention and release of individually stowed flight control surfaces

A control surface assembly for an unmanned aerial vehicle (UAV) is disclosed. The control surface assembly has a fin configured to be rotatably coupled to a fuselage of the UAV, with a control surface member rotatably coupled to the fin. A control surface linkage is configured to be coupled between the control surface member and an actuator disposed in the fuselage. The fin is rotatable with respect to the fuselage between a stowed configuration and a deployed configuration. In the deployed configuration, the control surface linkage is configured to rotate the control surface member with respect to the fin, when the actuator actuates the control surface linkage. In the stowed configuration, however, the control surface linkage is configured to move with respect to the fin without rotating the control surface member, when the actuator actuates the control surface linkage.

Rotatable control surface assembly for an unmanned aerial vehicle

A projectile has a liner forming an interior void, and a core disposed in a first region of the void proximal to a trailing end portion of the liner, with a portion of the void disposed forward with respect to the core. An outer jacket covers a leading end portion of the liner to enclose the interior void. When the projectile impacts a target object, the core travels in a direction of flight through the leading end portion of the liner to impact the object. When the projectile impacts a target surface at a non-zero angle of approach with respect to the normal of the target surface, the projectile creates a deformation in the target surface immediately before the core travels through the leading end portion of the liner to impact the target. This deformation reduces the probability that the core will ricochet off the deformed portion of the surface.

Penetrating and fragmenting projectile

A blast resistant vehicle hull includes an enclosure and a blast channel extending between and through a lower, outer surface of the enclosure and a surface of the enclosure other than the lower, outer surface of the enclosure. A vehicle includes a blast resistant vehicle hull. The blast resistant vehicle hull includes an enclosure and a blast channel extending between and through a lower, outer surface of the enclosure and a surface of the enclosure other than the lower, outer surface of the enclosure.

Blast resistant vehicle hull

A transportable electrical energy storage system includes an electrical energy storage unit, an electrical energy storage unit management system operably associated with the electrical energy storage unit, an AC/DC rectifier operably associated with the electrical energy storage unit management system, and a DC/DC converter operably associated with the electrical energy storage unit management system. The system further includes at least one bi-directional adapter operatively associated with the electrical energy storage unit and a case for protecting the electrical energy storage unit, the electrical energy storage unit management system, the AC/DC rectifier, the DC/DC converter, and the at least one bi-directional adapter.

Transportable electrical energy storage system including enclosure with charging and output circuitry containing interconnectable cells

A vehicle hull includes a personnel compartment and an apparatus for inhibiting effects of an explosive blast operably associated with the personnel compartment. The apparatus is configured to redirect at least a portion of a blast wave resulting from an explosive blast. The apparatus defines a cavity in which a blast attenuator is disposed. The blast attenuator comprises a core defining a plurality of interconnecting pores defining a pore volume of the core, a shear thickening fluid disposed in the pore volume of the core, and an enclosure in which the core and the shear thickening fluid are disposed.

Vehicle hull including apparatus for inhibiting effects of an explosive blast

An apparatus for inhibiting effects of an explosive blast includes a central portion including a stiffening element and defining a radiused exterior surface and a plurality of sides extending from the central portion for attachment to a structure. The central portion and the plurality of sides are configured to redirect at least a portion of a blast wave resulting from an explosive blast. A vehicle hull includes a personnel compartment and an apparatus for inhibiting effects of an explosive blast operably associated with the personnel compartment. The apparatus includes a central portion including a stiffening element and defining a radiused exterior surface and a plurality of sides extending between the central portion and the personnel compartment. The central portion and the plurality of sides are configured to redirect at least a portion of a blast wave resulting from an explosive blast.

Growing community of inventors

Arlington, TX, United States of America

James C Copp