An aircraft fairing includes a fairing body having an exterior fairing wall and at least one wheel bin. The at least one wheel bin has a side wall extending from an opening in the exterior fairing wall to an end wall. The side wall and the end wall define a cavity of the at least one wheel bin in fluid communication with the opening in the exterior fairing wall. An acoustic resonator is mounted to an outer surface of the side wall of the at least one wheel bin and is in fluid communication with the cavity. The acoustic resonator has a resonant frequency substantially similar to a cavity modal frequency of the at least one wheel bin at an aircraft flight condition.

The present disclosure provides an insert that includes a locking mechanism that may either be formed integrally to the component or attached separately to the insert body. The top of the locking mechanism is offset from the first surface by an offset distance to enable the insert to be coupled to a recess of a component such as an aircraft component. An aperture formed in a top surface of the first portion is configured to allow additional elements to be coupled to the aircraft component. The coupling of the insert to the aircraft component is further promoted by a compression mechanism that forces the locking mechanism to couple to an overhang portion of the top layer after the force applied to the insert once it is positioned in the recess is removed, such that the top surface of the insert is co-planar with an outermost surface of the aircraft component.

The present disclosure provides an insert that includes a locking mechanism that may either be formed integrally to the component or attached separately to the insert body. The top of the locking mechanism is offset from the first surface by an offset distance to enable the insert to be coupled to a recess of a component such as an aircraft component. An aperture formed in a top surface of the first portion is configured to allow additional elements to be coupled to the aircraft component. The coupling of the insert to the aircraft component is further promoted by a compression mechanism that forces the locking mechanism to couple to an overhang portion of the top layer after the force applied to the insert once it is positioned in the recess is removed, such that the top surface of the insert is co-planar with an outermost surface of the aircraft component.

An unmanned aerial vehicle capable of VTOL operation can include: a vehicle body defining longitudinal and transverse directions and opposing longitudinal sides; a first support boom coupled to the vehicle body at a first transverse axis and extending outwardly from the opposing longitudinal sides; a second support boom coupled to the vehicle body at a second transverse axis positioned rearward from the first transverse axis and extending outwardly from the opposing longitudinal sides; a plurality of electric motors coupled to a one of the first and second support booms, at least two electric motors of the plurality of electric motors positioned on each of the first and second support booms, a rotation axis of each of the at least two electric motors coupled to the second support boom offset in a transverse direction from a rotation axis of each of the at least two adjacent electric motors coupled to the first support boom; a plurality of rotors; and a propulsion system.

An unmanned aerial vehicle capable of VTOL operation can include: a vehicle body defining longitudinal and transverse directions and opposing longitudinal sides; a first support boom coupled to the vehicle body at a first transverse axis and extending outwardly from the opposing longitudinal sides; a second support boom coupled to the vehicle body at a second transverse axis positioned rearward from the first transverse axis and extending outwardly from the opposing longitudinal sides; a plurality of electric motors coupled to a one of the first and second support booms, at least two electric motors of the plurality of electric motors positioned on each of the first and second support booms, a rotation axis of each of the at least two electric motors coupled to the second support boom offset in a transverse direction from a rotation axis of each of the at least two adjacent electric motors coupled to the first support boom; a plurality of rotors; and a propulsion system.

Disclosed is a take-off and landing station (1) for a flying vehicle (2) for transporting people and/or loads, which flying vehicle takes off and lands vertically and comprises a flight module (3), having a plurality of drive units (17) arranged on a supporting framework structure (16) of the flight module (3), and a transportation module (4), which can be coupled to the flight module (3). The take-off and landing station (1) comprises a holding apparatus (21) having a plurality of gripper elements and support elements (11) for supporting, fixing and/or orienting the supporting framework structure (16) during take-off and landing of the flying vehicle (2) or the flight module (3).

Disclosed is a take-off and landing station (1) for a flying vehicle (2) for transporting people and/or loads, which flying vehicle takes off and lands vertically and comprises a flight module (3), having a plurality of drive units (17) arranged on a supporting framework structure (16) of the flight module (3), and a transportation module (4), which can be coupled to the flight module (3). The take-off and landing station (1) comprises a holding apparatus (21) having a plurality of gripper elements and support elements (11) for supporting, fixing and/or orienting the supporting framework structure (16) during take-off and landing of the flying vehicle (2) or the flight module (3).

There is provided a method of mounting equipment to an aircraft having an empennage. The method comprises mounting equipment to a mounting structure for mounting to the aircraft; removing an access panel from the outer skin of the empennage of the aircraft to reveal an access panel opening into the empennage; and attaching the mounting structure to or within the access panel opening such that at least a portion of the equipment extends beyond the outer skin of the empennage. The shape of the mounting structure at least partly conforms to the shape of the access panel opening. The method also comprises covering the mounting structure and the equipment mounted thereon with a cover, and attaching the cover to the mounting structure or the empennage. An assembly, structure, tailplane and aircraft are also provided.

There is provided a method of mounting equipment to an aircraft having an empennage. The method comprises mounting equipment to a mounting structure for mounting to the aircraft; removing an access panel from the outer skin of the empennage of the aircraft to reveal an access panel opening into the empennage; and attaching the mounting structure to or within the access panel opening such that at least a portion of the equipment extends beyond the outer skin of the empennage. The shape of the mounting structure at least partly conforms to the shape of the access panel opening. The method also comprises covering the mounting structure and the equipment mounted thereon with a cover, and attaching the cover to the mounting structure or the empennage. An assembly, structure, tailplane and aircraft are also provided.

A flow management system for delivering air to a heat load of an aircraft includes a cover having an opening for receiving and directing an airflow, and a duct defining a non-linear fluid flow path. The fluid flow path operably couples the opening and the heat load. A configuration of the fluid flow path reduces a velocity of the airflow therein while minimizing a pressure drop of the airflow.