Abstract: Systems, methods, and apparatuses for the direct mount of secondary payload adapters to a truss structure common to a space vehicle payload adapter are disclosed herein. In one or more embodiments, a method for reacting loads into a space vehicle payload adapter comprises reacting, by more than two interstitial rings of the space vehicle payload adapter, the loads created by secondary payloads mounted onto the space vehicle payload adapter, into a truss structure of the space vehicle payload adapter. The method further comprises reacting, by struts of the truss structure, the loads to a forward ring and an aft ring of the space vehicle payload adapter. In one or more embodiments, the reacting of the loads maintains high frequency (e.g., greater than (>) thirty (30) gigahertz (GHz)) modes for the space vehicle payload adapter.

Abstract: Tooling for clocking dual eccentric bushings of a clevis so that the clevis and a lug can be pinned together, comprises a pin and a sleeve. The pin comprises a pin cylindrical portion, a plate-engagement portion, and a stop surface. The sleeve comprises a sleeve cylindrical outer surface and a sleeve interior channel that has an interior-channel central axis, which is parallel to and offset from a sleeve-cylindrical-outer-surface central axis. The pin cylindrical portion is configured to be received by the sleeve interior channel with a slip fit. The tooling further comprises a squaring plate that comprises a squaring-plate abutment surface, configured to contact the stop surface, and a squaring-plate opening configured to receive the plate-engagement portion of the pin with a slip fit.

Abstract: Tooling for clocking dual eccentric bushings of a clevis so that the clevis and a lug can be pinned together, comprises a pin and a sleeve. The pin comprises a pin cylindrical portion, a plate-engagement portion, and a stop surface. The sleeve comprises a sleeve cylindrical outer surface and a sleeve interior channel that has an interior-channel central axis, which is parallel to and offset from a sleeve-cylindrical-outer-surface central axis. The pin cylindrical portion is configured to be received by the sleeve interior channel with a slip fit. The tooling further comprises a squaring plate that comprises a squaring-plate abutment surface, configured to contact the stop surface, and a squaring-plate opening configured to receive the plate-engagement portion of the pin with a slip fit.

Abstract: A raceway system and method within an internal cabin of an aircraft include a plurality of routing modules that are coupled together. Each of the plurality of routing modules includes a main housing that routes one or more transferring components to one or more monuments within the internal cabin. A raceway system and method for an aircraft includes a transferring component attachment system that includes a plurality of transferring component support struts, and one or more transferring components coupled to the plurality of transferring component support struts.

Abstract: Systems, methods, and apparatuses for the direct mount of secondary payload adapters to a truss structure common to a space vehicle payload adapter are disclosed herein. In one or more embodiments, a method for reacting loads into a space vehicle payload adapter comprises reacting, by more than two interstitial rings of the space vehicle payload adapter, the loads created by secondary payloads mounted onto the space vehicle payload adapter, into a truss structure of the space vehicle payload adapter. The method further comprises reacting, by struts of the truss structure, the loads to a forward ring and an aft ring of the space vehicle payload adapter. In one or more embodiments, the reacting of the loads maintains high frequency (e.g., greater than (>) thirty (30) gigahertz (GHz)) modes for the space vehicle payload adapter.

Abstract: Systems and methods are provided for eccentric bolt. One embodiment is an eccentric bolt to secure a clevis and lug fitting. The eccentric bolt includes a head and a shank. The shank includes multiple shank sections that successively decrease in diameter in an axial direction from the head toward a tail end of the shank. One of the shank sections is an eccentric shank section that is off-center with respect to a center axis of the shank. The eccentric shank section is configured to engage the lug prior to engagement of concentric shank sections with the clevis. While the eccentric shank section is engaged with the lug, the shank is configured to rotate to align the concentric shank sections with the clevis, and to insert through the clevis and lug fitting to compensate for misalignment of the clevis and lug fitting.

Abstract: A radome assembly of an aircraft includes a shell having an elongated shape wherein the shell defines a first opening having a diameter of a first dimension and is positioned within a first end portion of the shell. The shell defines a second opening having an elongated shape which extends along a length of the shell and has a second dimension which is greater than the first dimension. First fastener extends through the first opening and is engaged with a first surface associated with a first structural element and resists movement of the shell and the first structural element relative to one another. Second fastener extends through the second opening and is engaged with a second surface associated with the first structural element such that the shell is moveable along the length of the shell relative to the first structural element.

Abstract: A raceway system and method within an internal cabin of an aircraft include a plurality of routing modules that are coupled together. Each of the plurality of routing modules includes a main housing that routes one or more transferring components to one or more monuments within the internal cabin. A raceway system and method for an aircraft includes a transferring component attachment system that includes a plurality of transferring component support struts, and one or more transferring components coupled to the plurality of transferring component support struts.

Abstract: A raceway system and method within an internal cabin of an aircraft include a plurality of routing modules that are coupled together. Each of the plurality of routing modules includes a main housing that routes one or more transferring components to one or more monuments within the internal cabin. A raceway system and method for an aircraft includes a transferring component attachment system that includes a plurality of transferring component support struts, and one or more transferring components coupled to the plurality of transferring component support struts.

Abstract: A raceway system and method within an internal cabin of an aircraft include a plurality of routing modules that are coupled together. Each of the plurality of routing modules includes a main housing that routes one or more transferring components to one or more monuments within the internal cabin. A raceway system and method for an aircraft includes a transferring component attachment system that includes a plurality of transferring component support struts, and one or more transferring components coupled to the plurality of transferring component support struts.

Abstract: A mounting system for mounting an external structure to an aircraft includes a plurality of first mounting structures coupled to the aircraft and at least one link coupled to each first mounting structure of the plurality of mounting structures. The mounting system also includes a second mounting structure positioned proximate the at least one link, wherein the second mounting structure includes at least one aperture defined therein. An eccentric bearing is positioned in the at least one aperture and is configured to couple the second mounting structure to the at least one link. The eccentric bearing includes a bore extending therethrough that is offset from an axial center of the eccentric bearing.

Abstract: A radome assembly of an aircraft includes a shell having an elongated shape wherein the shell defines a first opening having a diameter of a first dimension and is positioned within a first end portion of the shell. The shell defines a second opening having an elongated shape which extends along a length of the shell and has a second dimension which is greater than the first dimension. First fastener extends through the first opening and is engaged with a first surface associated with a first structural element and resists movement of the shell and the first structural element relative to one another. Second fastener extends through the second opening and is engaged with a second surface associated with the first structural element such that the shell is moveable along the length of the shell relative to the first structural element.

Abstract: A radome includes a shell defining an internal volume. A track is coupled to the shell, and the track allows the shell to move axially between an open position and a closed position. A support structure is coupled to the shell, and the support structure moves from a collapsed position to an expanded position.

Abstract: A mounting system for mounting an external structure to an aircraft includes a plurality of first mounting structures coupled to the aircraft and at least one link coupled to each first mounting structure of the plurality of mounting structures. The mounting system also includes a second mounting structure positioned proximate the at least one link, wherein the second mounting structure includes at least one aperture defined therein. An eccentric bearing is positioned in the at least one aperture and is configured to couple the second mounting structure to the at least one link. The eccentric bearing includes a bore extending therethrough that is offset from an axial center of the eccentric bearing.

Abstract: A radome includes a shell defining an internal volume. A track is coupled to the shell, and the track allows the shell to move axially between an open position and a closed position. A support structure is coupled to the shell, and the support structure moves from a collapsed position to an expanded position.