An additively manufactured lattice structure includes (a) a first three-dimensional lattice including a repeating interconnected array of a first lattice unit cell, (b) a second three-dimensional lattice including a repeating interconnected array of a second lattice unit cell, wherein said second lattice unit cell is different from said first lattice unit cell, and (c) a first transition segment interconnecting said first three-dimensional lattice and said second three-dimensional lattice. The first transition segment includes (i) a first three-dimensional transitional lattice including a repeating array of said first lattice unit cell and (ii) interleaved with and interconnected to said first three-dimensional transitional lattice, a second three-dimensional transitional lattice including a repeating array of said second lattice unit cell.

A trailing edge flap actuation mechanism has a flap drive link with a first end pivotally coupled to a fore flap structure of a flap and a second end pivotally coupled to an underwing support structure. An aft tension link has a leading end pivotally coupled proximate an aft end of the underwing support structure and a trailing end coupled to a mid-section structure of the flap. An actuator, when actuated, rotates the flap drive link about a first pivot axle to move the flap between a retracted position and a deployed lowered position. The actuator, including a ball-screw drive shaft having a universal joint, is positioned in a cove above the underwing support structure whereby the extent that the underwing support structure protrudes below the wing is reduced.

A trailing edge flap actuation mechanism has a flap drive link with a first end pivotally coupled to a fore flap structure of a flap and a second end pivotally coupled to an underwing support structure. An aft tension link has a leading end pivotally coupled proximate an aft end of the underwing support structure and a trailing end coupled to a mid-section structure of the flap. An actuator, when actuated, rotates the flap drive link about a first pivot axle to move the flap between a retracted position and a deployed lowered position. The actuator, including a ball-screw drive shaft having a universal joint, is positioned in a cove above the underwing support structure whereby the extent that the underwing support structure protrudes below the wing is reduced.

A pressure back-up valve (300) includes a release piston (320) movable between first and second stop positions and a closing body (340) movable to a closing position in which this separates first and second connection pressure chambers (327, 326) when the release piston (320) is in a first stop position. The release piston (320) moves the closing body (340), in the second stop position, into an opening position. The release piston (320) is pressurizable on a first pressure surface (A1) from a first side via a third connection pressure chamber (324) and on a second pressure surface (A2) from a second side via a second connection pressure chamber (326). The closing body (340) is pressurized, in the closing position, from a first side via the second connection pressure chamber (326) on a first pressure surface (A4) and from a second side via the first connection pressure chamber (327) on a second pressure surface (A3) of the closing body (34).

The present invention is an Electric servo system which controls and automates gate openings based on GPS speed and position data that results in precise and reliable modern variable and constant rate application. The Electric servo system also allows for Mechanical gate linkages to remain intact, resulting in few changes to the aircraft and redundancy of emergency components. A Mechanical input connect/disconnect is used to effortlessly transfer between the automated Electric servo system and the Mechanical gate system.

The present invention is an Electric servo system which controls and automates gate openings based on GPS speed and position data that results in precise and reliable modern variable and constant rate application. The Electric servo system also allows for Mechanical gate linkages to remain intact, resulting in few changes to the aircraft and redundancy of emergency components. A Mechanical input connect/disconnect is used to effortlessly transfer between the automated Electric servo system and the Mechanical gate system.

A lid controlling apparatus includes a casing having a target region, a lid, and a rod driving mechanism connected between the casing and the lid. The rod driving mechanism includes a first rod pivoted to the casing, a non-rotatable gear fixed to the casing, a driven gear pivoted to a side of the first rod and connected to the lid, and a planetary gear device pivoted to the side of the first rod and engaged with the non-rotatable gear and the driven gear for rotating between lifting and closed positions. When the planetary gear device rotates to the lifting position, the first rod pivots with rotation of the planetary gear device to have a first included angle relative to the casing, and the planetary gear device rotates the driven gear to make the lid have a second included angle relative to the first rod for exposing the target region.

A lid controlling apparatus includes a casing having a target region, a lid, and a rod driving mechanism connected between the casing and the lid. The rod driving mechanism includes a first rod pivoted to the casing, a non-rotatable gear fixed to the casing, a driven gear pivoted to a side of the first rod and connected to the lid, and a planetary gear device pivoted to the side of the first rod and engaged with the non-rotatable gear and the driven gear for rotating between lifting and closed positions. When the planetary gear device rotates to the lifting position, the first rod pivots with rotation of the planetary gear device to have a first included angle relative to the casing, and the planetary gear device rotates the driven gear to make the lid have a second included angle relative to the first rod for exposing the target region.

A lifter device includes: a pinion gear; a rotation control device including: a rotation shaft rotating in synchronization with the pinion gear; a support member supporting the rotation shaft; a rotation drive mechanism configured to rotate the rotation shaft; and a lock mechanism configured to lock rotation of the rotation shaft when an operation handle is in an operation-released state and including: a first tooth; and a second tooth configured to selectively mesh with the first tooth to lock relative rotation of the rotation shaft and the support member; and a speed increasing mechanism provided closer to the rotation shaft than a meshing portion of the first tooth and the second tooth in a rotation transmission path, configured to transmit the rotation of the rotation shaft to one of the first tooth and the second tooth, and configured to speed up the transmitted rotation of the rotation shaft.

A lifter device includes: a pinion gear; a rotation control device including: a rotation shaft rotating in synchronization with the pinion gear; a support member supporting the rotation shaft; a rotation drive mechanism configured to rotate the rotation shaft; and a lock mechanism configured to lock rotation of the rotation shaft when an operation handle is in an operation-released state and including: a first tooth; and a second tooth configured to selectively mesh with the first tooth to lock relative rotation of the rotation shaft and the support member; and a speed increasing mechanism provided closer to the rotation shaft than a meshing portion of the first tooth and the second tooth in a rotation transmission path, configured to transmit the rotation of the rotation shaft to one of the first tooth and the second tooth, and configured to speed up the transmitted rotation of the rotation shaft.