An assembly for reacting a thrust load from an engine, the assembly comprising a frame, a pin, an evener bar, and left and right thrust links. The frame includes an upper pin interface and a lower pin interface. The pin extends through the upper pin interface and the lower pin interface and includes an upper end and a lower end. The evener bar engages the lower end of the pin below the lower pin interface and connects the left and right thrust links to the pin. The pin is configured to react the thrust load at the lower pin interface and the upper pin interface thereby forming a distributed force couple between the lower pin interface and the upper pin interface.

An engine vibration isolation subframe for aircraft includes a forward frame and a forward beam connected to the forward frame. The forward beam includes a first end configured to connect to a first engine and a second end configured to connect to a second engine. An aft frame is disposed aft of the forward frame and includes a first aft beam connected to the aft frame and the first engine and a second aft beam connected to the aft frame and the second engine, where the second aft beam is disposed substantially opposite the first aft beam. At least one forward isolator assembly is connected to the forward frame and at least one aft isolator assembly is connected to the aft frame.

An engine vibration isolation subframe for aircraft includes a forward frame and a forward beam connected to the forward frame. The forward beam includes a first end configured to connect to a first engine and a second end configured to connect to a second engine. An aft frame is disposed aft of the forward frame and includes a first aft beam connected to the aft frame and the first engine and a second aft beam connected to the aft frame and the second engine, where the second aft beam is disposed substantially opposite the first aft beam. At least one forward isolator assembly is connected to the forward frame and at least one aft isolator assembly is connected to the aft frame.

An aircraft including a rear wing attachment, connecting a primary structure of an aircraft pylon to its wing, and including at least one right-hand link connected to the wing by a first right-hand connecting element and to the primary structure by a second right-hand connecting element and configured to react loads oriented parallel to the vertical direction only, at least one left-hand link connected to the wing by a first left-hand connecting element and to the primary structure by a second left-hand connecting element and configured to react loads oriented parallel to the vertical direction only, a shear pin secured to the primary structure and housed in operation in a housing secured to the wing, the shear pin and the housing being configured to react loads oriented in a plane approximately perpendicular to the vertical direction.

An aircraft including a rear wing attachment, connecting a primary structure of an aircraft pylon to its wing, and including at least one right-hand link connected to the wing by a first right-hand connecting element and to the primary structure by a second right-hand connecting element and configured to react loads oriented parallel to the vertical direction only, at least one left-hand link connected to the wing by a first left-hand connecting element and to the primary structure by a second left-hand connecting element and configured to react loads oriented parallel to the vertical direction only, a shear pin secured to the primary structure and housed in operation in a housing secured to the wing, the shear pin and the housing being configured to react loads oriented in a plane approximately perpendicular to the vertical direction.

An aircraft pylon comprising a structure covered by a fairing. The structure includes at least one void bounded by a peripheral edge. The fairing includes at least one removable panel connected to the structure around the void and having an inner face oriented towards the structure. The structure includes at least one seal connected to the structure so as to be slightly compressed against the inner face of the removable panel. The seal extends over at least a lower portion of the peripheral edge so as to retain a fluid located below a sealing horizontal plane while ensuring ventilation beneath the fairing.

An aircraft pylon comprising a structure covered by a fairing. The structure includes at least one void bounded by a peripheral edge. The fairing includes at least one removable panel connected to the structure around the void and having an inner face oriented towards the structure. The structure includes at least one seal connected to the structure so as to be slightly compressed against the inner face of the removable panel. The seal extends over at least a lower portion of the peripheral edge so as to retain a fluid located below a sealing horizontal plane while ensuring ventilation beneath the fairing.

An example of a collapsible pylon for a drone aircraft includes a bore extending through a length of a barrel, a first and a second flex-pin bore formed through a wall of the barrel, a first arm slidably positioned within a first end of the bore, a first flex pin disposed on the first arm to engage the first flex-pin bore, a second arm slidably positioned within a second end of the bore, and a second flex pin disposed on the second arm to engage the second flex-pin bore.

An example of a collapsible pylon for a drone aircraft includes a bore extending through a length of a barrel, a first and a second flex-pin bore formed through a wall of the barrel, a first arm slidably positioned within a first end of the bore, a first flex pin disposed on the first arm to engage the first flex-pin bore, a second arm slidably positioned within a second end of the bore, and a second flex pin disposed on the second arm to engage the second flex-pin bore.

A tailsitter aircraft includes an airframe having first and second wings with first and second pylons extending therebetween, a thrust array attached to the airframe, payloads and payload saddle assemblies coupled to the pylons each configured to secure a respective payload. The thrust array includes propulsion assemblies configured to transition the airframe between a forward flight orientation for wing-borne lift and a VTOL orientation for thrust-borne lift. Each payload saddle assembly includes a latch assembly and a retainer configured to secure the respective payload against a respective pylon. A latch assembly is movable between various positions including an open position and a closed position and is configured to secure the respective payload in the closed position and release the respective payload in the open position. Each latch assembly is configured to move from the closed position to the open position to release the respective payload in the VTOL orientation.