Abstract: A compact battery module incorporating a dual-sided printed circuit board (PCB) bus is presented. The present disclosure provides for an increase in battery cells per given volume by utilizing both sides of a PCB bus. In one embodiment, a PCB bus can be configured to receive battery cell terminals on both sides of the PCB via one or more connectors, thereby providing for a more compact battery module that is simpler and eliminates interconnections. By having a single PCB disposed between battery cells having both the positive negative terminals on one side, a more compact design can be realized with fewer printed circuit boards and lower weight.

Abstract: A modular airfoil-shaped battery disposed in a wing of an aircraft is presented. In one embodiment, the present disclosure provides for a system configured to have batteries or battery modules stored and accessible through access openings in the forward wing spar. The access openings in the forward spar can provide access for battery insertion and removal, as well as electrical and thermal management connections. Such forward spar access openings can be a relatively small, as the access opening need to only be as large as the battery cross section. A battery can comprise one or more battery modules based on the application requirements. The aircraft battery can be distributed among more, smaller battery modules. The battery modules can be placed in different locations in the wing. For example, the battery modules can be placed proximate an aircraft fuselage to achieve a better center of gravity.

Abstract: A battery assembly for an aircraft includes a cold plate having an upper planar member, a lower planar member, and at least one fluid channel positioned between the upper and lower planar members and configured to receive a cooling fluid. The battery assembly also includes an upper battery mounted to the upper planar member for transferring heat from the upper battery to the cooling fluid through the upper planar member. The battery assembly further includes a lower battery mounted to the lower planar member for transferring heat from the lower battery to the cooling fluid through the lower planar member.

Abstract: A ducted fan assembly has a central axis, a duct having an outer wall and an inner wall, a fan hub at least partially disposed on the central axis, a plurality of fan blades coupled to the fan hub, and a first stator. The first stator has a first end coupled to the inner wall, a second end coupled to the inner wall, and a hub interface disposed between the first end and the second end, wherein the hub interface is coupled to the fan hub.

Abstract: A nonintegral cold plate is described for providing cooling of battery charging. The nonintegrated cold plate can receive and circulate coolant against a surface of a battery or of a vehicle. After charging the nonintegrated cold plate can be removed to save weight on the vehicle's payload.

Abstract: A battery assembly for an aircraft includes a cold plate having an upper planar member, a lower planar member, and at least one fluid channel positioned between the upper and lower planar members and configured to receive a cooling fluid. The battery assembly also includes an upper battery mounted to the upper planar member for transferring heat from the upper battery to the cooling fluid through the upper planar member. The battery assembly further includes a lower battery mounted to the lower planar member for transferring heat from the lower battery to the cooling fluid through the lower planar member.

Abstract: A cold plate is couplable with a component for dissipating heat from a component. The cold plate includes a top plate coupled with a bottom plate to receive a cooling medium therebetween. The top plate includes a body and a plurality of walls extending from the body, wherein each wall of the plurality of walls includes a recess extending within the wall. The bottom plate includes a body and a plurality of walls extending from the body such that an end portion of each wall of the bottom plate is inserted within the recess of each wall of the top plate to form an interlocking joint.

Abstract: An aircraft includes a fuselage and an airframe supporting the fuselage. The airframe includes a pair of longitudinally-extending beams. The aircraft further includes a battery assembly including a cold plate secured to the pair of longitudinally-extending beams, and a battery mounted to the cold plate.

Abstract: A ducted fan assembly has a central axis, a duct having an outer wall and an inner wall, a fan hub at least partially disposed on the central axis, a plurality of fan blades coupled to the fan hub, and a first stator. The first stator has a first end coupled to the inner wall, a second end coupled to the inner wall, and a hub interface disposed between the first end and the second end, wherein the hub interface is coupled to the fan hub.

Abstract: A latch system has a pin movable along a pin axis, a control rod connected to the pin, a control wall comprising a control aperture comprising a lock hole joined to an unlock hole by a rod channel, and a control knob biased toward the pin, wherein the control knob comprises a lock tip sized to fit within each of the lock hole and the unlock hole.

Abstract: A modular latch system has an activation module comprising an activation rod, a latch module comprising a biased latch, and a control cable connecting the activation module to the latch module so that rotation of the activation rod can retract the latch.

Abstract: A latch system has a pin movable along a pin axis, a control rod connected to the pin, a control wall comprising a control aperture comprising a lock hole joined to an unlock hole by a rod channel, and a control knob biased toward the pin, wherein the control knob comprises a lock tip sized to fit within each of the lock hole and the unlock hole.

Abstract: A modular latch system has an activation module comprising an activation rod, a latch module comprising a biased latch, and a control cable connecting the activation module to the latch module so that rotation of the activation rod can retract the latch.

Abstract: A lightweight skid shoe assembly comprises a body of wear resistant, non-metallic or partially metallic material; and a structure coupling mechanism; wherein the body prevents friction-related damage to the structure. Another lightweight skid shoe assembly comprises a body of wear resistant, non-metallic or partially metallic material selected from the group consisting of: a polyamide or polyimide impregnated carbon fiber layup, a peek or PEI injection mold with carbon fiber, compression molded carbon fiber or fiberglass, a resin infusion with carbon fiber preform fabric, a fiber reinforced thermoset, acetal resin, machined acetal or thermoplastic, thermosetting plastic, or a metal-matrix composite; wherein the body prevents friction-related damage to a structure.

Abstract: A landing gear for an aircraft can include a skid tube having an inboard flat side wall and an outboard flat side wall, the skid tube having a skid tube centerline plane that is parallel to at least one of the outboard flat side wall and the inboard flat side wall, the skid tube being canted inboard at an angle The landing gear can include a forward cross tube having a straight horizontal portion, a first bend transitioning the straight horizontal portion into a straight angled portion, and a second bend transitioning the straight angled portion into a straight end portion.

Abstract: A lightweight skid shoe assembly comprises a body of wear resistant, non-metallic or partially metallic material; and a structure coupling mechanism; wherein the body prevents friction-related damage to the structure. Another lightweight skid shoe assembly comprises a body of wear resistant, non-metallic or partially metallic material selected from the group consisting of: a polyamide or polyimide impregnated carbon fiber layup, a peek or PEI injection mold with carbon fiber, compression molded carbon fiber or fiberglass, a resin infusion with carbon fiber preform fabric, a fiber reinforced thermoset, acetal resin, machined acetal or thermoplastic, thermosetting plastic, or a metal-matrix composite; wherein the body prevents friction-related damage to a structure.

Abstract: According to one embodiment, a windshield attachment device for coupling a windshield to a body includes a fastener portion, a bolt, and an elastomeric load isolator. The fastener portion has an opening therethrough. The bolt is configured to extend through the opening of the fastener portion and couple the fastener portion to the body. The elastomeric load isolator surrounds at least a portion of the fastener portion and separating the fastener portion from the windshield.

Abstract: An energy attenuating seat system for an aircraft includes energy attenuating features and is also configured to provide mobility for the occupant. The system is configured to suspend the operator, or gunner, with a support from the roof of the aircraft. The system includes an armored seat or body harness for the occupant. The system provides energy attenuation in multiple directions. The system also optionally includes a floor tether in order to control the movements of the occupant. The system may also include an impact detection system to selectively change the tension of the support and/or floor harness. The system may also include one or more airbags either within in the fuselage of the aircraft, or included in the seat system in order to provide energy attenuation.

Abstract: A skid landing gear assembly is provided. One embodiment of the landing gear assembly may include a first and a second skid member, and a forward and an aft cross member. The forward and aft cross-members may have integrated attachment members coupled to a forward portion and an aft portion of the first and second skid members. In more particular embodiments, the cross-members may be beam members with open cross-sections, and the skid members may be beam members with a closed cross-section.