Disclosed and described herein are embodiments of an articulated utility pole that facilitates repair and/or reinstallation in the event of damage to the pole caused by wind loading (e.g., storms), trees or other items striking the utility lines, collisions with the poles, and the like. Also disclosed herein are methods of repairing and/or re-installing the articulated utility pole. Further disclosed herein are components for fabricating an articulated utility pole.

A breakaway threaded fastener is provided. The fastener has a stud, a pin, and a cap. The stud has a hollow cavity with a closed end, an open end, a wall, and an outer surface. The outer surface has an external thread. The pin is in the hollow cavity. The pin has a first end at the closed end of the stud and a second end extending above the open end of the stud. The cap has another hollow cavity with a closed end, an open end, and an internal thread. The cap is threadably engaged to the open end of the stud via the internal and external threads so that the second end of the pin abuts the closed end of the cap.

A composite laminate for connection to at least one attachment component in a load-introduction joint, said composite laminate comprising an opening that is adapted to receive a load-introduction component of said load-introduction joint, wherein a prefailure indication element is provided in the region of said opening, said prefailure indication element being modifiable by said load-introduction component in a prefailure mode of said load-introduction joint for indication of an impending function-affecting failure of said composite laminate. The invention is further related to a corresponding load-introduction component.

A propeller shaft assembly comprises a first rotary component having a first splined portion and a first engaging surface arranged transverse to a longitudinal axis of the first rotary component and spaced from the first splined portion and a second rotary component having a second splined portion configured to engage the first splined portion. The second splined portion defines a second engaging surface arranged transverse to the longitudinal axis of the first rotary component. A shear component is disposed between the first engaging surface of the first rotary component and the second engaging surface of the second rotary component. The shear component forms a crash feature of the propeller shaft assembly configured to shear at an edge of the second engaging surface when the first shear component is compressed between the first engaging surface and the second engaging surface.

Separation device assemblies are provided. The assemblies include a first plate defining respective contact surfaces and engagement surfaces and a second plate defining a respective contact surfaces and engagement surfaces. A fracture groove is located on separation walls of the first and second plates. A first end member, a second end member, and the separation wall of the first plate define a first plate expansion device channel and the second plate defines a similar second plate expansion device channel. When assembled, the first plate and the second plate form an expansion device cavity and the first and second plates form a frangible joint. The respective engagement surfaces are configured to engagement with receiving channels of attachable mounting devices.

An assembly is provided that includes a first mount, a second mount and a fuse pin. The first mount is configured with a first aperture. The second mount is configured with a second aperture. The fuse pin is mated with the first aperture and the second aperture. The fuse pin connects the first mount and the second mount together. The fuse pin has an axis, and is configured with a plurality of slots arranged circumferentially about the axis. A first of the slots has a length measured along the axis. The second mount has a thickness measured along the axis at an interface between the fuse pin and the second mount. The length is greater than the thickness.

A composite laminate for connection to at least one attachment component in a load-introduction joint, said composite laminate comprising an opening that is adapted to receive a load-introduction component of said load-introduction joint, wherein a prefailure indication element is provided in the region of said opening, said prefailure indication element being modifiable by said load-introduction component in a prefailure mode of said load-introduction joint for indication of an impending function-affecting failure of said composite laminate. The invention is further related to a corresponding load-introduction component.

A pin assembly includes: a resin pin; and a collar fitted to a round shaft portion of the resin pin and having higher hardness than the resin pin. The round shaft portion is sheared to cancel connection between a first plate and a second plate upon secondary collision of a vehicle. The collar includes an end face received by a reception surface of the second plate, and shears the round shaft portion in a shear plane along the end face upon the secondary collision. The round shaft portion includes a hollow hole. An inner circumference of the hollow hole includes a straight portion which has a generating line parallel to an axial direction of the round shaft portion and which is traversed by a plane including the end face of the collar.

A cable-barrier system that includes an anchor-body and terminal post which receive and retain one or more anchor-cables and are anchored to a footing to counter balance the force applied to the anchor body by one or more barrier-cables. The system also allows for the release of the anchor-cables during a collision by a vehicle.

Frangible fasteners with flexible connectors for unmanned aircraft, and associated systems and methods are disclosed. A representative aircraft includes a fuselage portion, a wing portion, a winglet carried by the wing portion, and a frangible fastener coupling the winglet portion to the wing portion. The frangible fastener can include an outer body with a first portion in contact with the wing portion, a second portion in contact with the winglet portion, and a frangible portion between the first and second portions. A flexible member is positioned at least partially within the outer body and is connected to the first portion so as to extend through and out of the second portion. A stop element is carried by the flexible member.