Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

A method of manufacturing a part having an opening for receiving an insert, including forming the opening having an internal surface wherein the internal surface has a polygonal cross-section including a plurality of sides. The polygonal cross-section comprises a polygon having an area larger than a cross-section of the insert, and the sides constrain the insert so as to locate the insert in the opening when the insert is inserted into the opening.

An aircraft engine mounting system to retrofit an aircraft engine from one aircraft type to another in a manner suitable for approved flight. The system includes a circular member having longitudinal securement members extending therefrom to attach the circular member to an inner surface of the fuselage of an aircraft. The circular member in turn has mounting members configured to receive an aircraft engine to retrofit the engine from a first aircraft to a second aircraft.

An aircraft engine mounting system to retrofit an aircraft engine from one aircraft type to another in a manner suitable for approved flight. The system includes a circular member having longitudinal securement members extending therefrom to attach the circular member to an inner surface of the fuselage of an aircraft. The circular member in turn has mounting members configured to receive an aircraft engine to retrofit the engine from a first aircraft to a second aircraft.

A pressure bulkhead assembly support tool configured to hold a pressure bulkhead system is presented. The pressure bulkhead assembly support tool comprises a segmented frame having a substantially circular path. A plurality of circumferential force assemblies restrains the pressure bulkhead system such that a circumferential surface of the pressure bulkhead system with a nominal shape is formed. A plurality of alignment probes holds and positions the pressure bulkhead system relative to the segmented frame.

A pressure bulkhead assembly support tool configured to hold a pressure bulkhead system is presented. The pressure bulkhead assembly support tool comprises a segmented frame having a substantially circular path. A plurality of circumferential force assemblies restrains the pressure bulkhead system such that a circumferential surface of the pressure bulkhead system with a nominal shape is formed. A plurality of alignment probes holds and positions the pressure bulkhead system relative to the segmented frame.

Methods of performing assembly or maintenance on an aircraft, systems for performing desired assembly or maintenance on an aircraft, and mobile work stations useful for such systems and methods, where the mobile work stations include a work platform, including an accessway providing access to the work platform; and a moveable base supporting the work platform with one or more platform jacks that can adjustably raise and lower the work platform.

Methods of performing assembly or maintenance on an aircraft, systems for performing desired assembly or maintenance on an aircraft, and mobile work stations useful for such systems and methods, where the mobile work stations include a work platform, including an accessway providing access to the work platform; and a moveable base supporting the work platform with one or more platform jacks that can adjustably raise and lower the work platform.

Some variations provide a leading-edge heat pipe comprising: (a) an envelope fabricated from a shell material, wherein the envelope includes at least one edge with a radius of curvature of less than 3 mm, and wherein the envelope includes, or is in thermal communication with, at least one heat-rejection surface; (b) a porous wick fabricated from a ceramic or metallic wick material, wherein the porous wick is configured within a first portion of the interior cavity, wherein at least a portion of the porous wick is adjacent to the inner surface, and wherein the porous wick has a bimodal pore distribution comprising an average capillary-pore size from 0.2 microns to 200 microns and an average high-flow pore size from 100 microns to 2 millimeters (the average high-flow pore size is greater than the average capillary-pore size); and (c) a phase-change heat-transfer material contained within the porous wick.

The present disclosure relates to a method of assembling hardpoints in aeronautical structures, and more specifically, the disclosed method allows knowing the relative deviation of the hardpoints and of the positioning elements of the hardpoints with respect to a laser beam emitted by a laser collimator fixed to an adjustable support which can be adjusted in at least two directions in space, and by using a correction algorithm, it is possible to know the displacement necessary for locating the positioning elements such that they are aligned with respect to the hardpoints, the positioning elements in turn being moved as a result of the movement of the driven linear tables in one or in several iterative steps, at which time the position thereof is fixed and they are ready for the rest of the hardpoints to be assembled.