A load testing apparatus can include a plurality of vertical load structures arranged on a flight control surface to provide torque on the control surface and reacted by a control rod of the flight control surface. The load testing apparatus can also include a plurality of fore/aft load structures arranged to provide tensile and/or compressive force in a direction intersecting a hinge line of the flight control surface. Each of the plurality of fore/aft load structure can include a first rubber pad having a surface extending in a first plane that is arranged to contact a lower surface of the flight control surface. Each of the plurality of fore/aft load structures can also include a first rubber pad having a surface extending in a second plane that is arranged to contact an upper surface of the flight control surface, wherein the first plane and the second plane are non-parallel planes.

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 system for providing active flow control in an aircraft having a gas turbine engine. The system includes an environmental control system that includes a cabin blower system having a compressor operable to compress a fluid delivered by a fan section of the gas turbine engine to generate a pressurised fluid for use by the environmental control system. The environmental control system is fluidicly connected to an active flow control system via a fluid supply line, for allowing the pressurised fluid generated by the compressor to be supplied to the active flow control system so that it can be ejected from the aircraft across an exterior surface of a movable control element of the aircraft.

A system for providing active flow control in an aircraft having a gas turbine engine. The system includes an environmental control system that includes a cabin blower system having a compressor operable to compress a fluid delivered by a fan section of the gas turbine engine to generate a pressurised fluid for use by the environmental control system. The environmental control system is fluidicly connected to an active flow control system via a fluid supply line, for allowing the pressurised fluid generated by the compressor to be supplied to the active flow control system so that it can be ejected from the aircraft across an exterior surface of a movable control element of the aircraft.

An aircraft motor includes a bearing assembly including a first plurality of rotor alignment magnets; a magnet support structure fixedly mounted on a shaft of the motor in a spaced apart relation to the bearing assembly, the magnet support structure including a second plurality of rotor alignment magnets such that when the vertical thrust engine is disengaged, attraction between the first and second rotor alignment magnets causes the magnet support structure to rotate relative to the bearing assembly to an alignment position defined by the relative placement of north and south poles of the first and second plurality of rotor alignment magnets.

An aircraft motor includes a bearing assembly including a first plurality of rotor alignment magnets; a magnet support structure fixedly mounted on a shaft of the motor in a spaced apart relation to the bearing assembly, the magnet support structure including a second plurality of rotor alignment magnets such that when the vertical thrust engine is disengaged, attraction between the first and second rotor alignment magnets causes the magnet support structure to rotate relative to the bearing assembly to an alignment position defined by the relative placement of north and south poles of the first and second plurality of rotor alignment magnets.

Fixed-wing short-takeoff-and-landing aircraft and related methods. The aircraft comprise an airframe comprising a rear wing assembly and a forward wing assembly positioned forward of the rear wing assembly, a rear plurality of blowing rotor assemblies operatively coupled to the rear wing assembly that are configured to blow air across the rear wing assembly to induce lift in the rear wing assembly, and a forward plurality of blowing rotor assemblies that are operatively coupled to the forward wing assembly and configured to blow air across the forward wing assembly to induce lift in the forward wing assembly. The methods comprise inducing lift in a forward wing assembly by blowing air across the forward wing assembly with a forward plurality of blowing rotor assemblies and inducing lift in a rear wing assembly by blowing air across a rear wing assembly with a rear plurality of blowing rotor assemblies.

Fixed-wing short-takeoff-and-landing aircraft and related methods. The aircraft comprise an airframe comprising a rear wing assembly and a forward wing assembly positioned forward of the rear wing assembly, a rear plurality of blowing rotor assemblies operatively coupled to the rear wing assembly that are configured to blow air across the rear wing assembly to induce lift in the rear wing assembly, and a forward plurality of blowing rotor assemblies that are operatively coupled to the forward wing assembly and configured to blow air across the forward wing assembly to induce lift in the forward wing assembly. The methods comprise inducing lift in a forward wing assembly by blowing air across the forward wing assembly with a forward plurality of blowing rotor assemblies and inducing lift in a rear wing assembly by blowing air across a rear wing assembly with a rear plurality of blowing rotor assemblies.

A method for manufacturing an aerodynamic structure including a first panel having an aerodynamic face, as well as a second reinforced panel. The method includes a step of stamping the second panel to obtain at least one raised shape which is recessed on the second face, and a step of joining the first and second panels by pressing them against each other outside the at least one raised shape. An aerodynamic shape is obtained using this method.