During landing and rejected-takeoff flight phases, aircraft drag is a useful force to supplement braking and reduce stopping distance. During descents, aircraft drag is a useful force in steepening flight path angle and achieving higher rates of vertical descent speed at a trimmed forward flight speed in unaccelerated flight. A flight control system is detailed herein that deflects opposing flight control components in a symmetric fashion to increase aircraft drag, while maintaining controllability.

Aircraft, auto speed brake control systems, and methods for controlling drag of an aircraft are provided. In one example, an aircraft includes an aircraft structure. A drag device is operatively coupled to the aircraft structure between a stowed and a deployed position and/or an intermediate deployed position. A speed brake controller is in communication with the drag device to control movement. An autothrottle-autospeedbrake controller is in communication with the speed brake controller and is configured to receive data signals. The autothrottle-autospeedbrake controller is operative to direct the speed brake controller to control movement of the drag device between the stowed position and the deployed position and/or the intermediate deployed position in response to at least one of the data signals.

Reactive spoilers for aircraft and associated methods. In one embodiment, a wing of an aircraft includes a leading edge, a trailing edge, and an upper surface and a lower surface between the leading edge and the trailing edge. The wing further includes a reactive spoiler disposed on the upper surface between the leading edge and the trailing edge. The reactive spoiler comprises one or more turbines configured to raise in relation to the upper surface into an airflow passing over the upper surface, and to reduce lift of a wing section behind the turbines. The turbines are configured to convert kinetic energy from the airflow into electrical energy.

Reactive spoilers for aircraft and associated methods. In one embodiment, a wing of an aircraft includes a leading edge, a trailing edge, and an upper surface and a lower surface between the leading edge and the trailing edge. The wing further includes a reactive spoiler disposed on the upper surface between the leading edge and the trailing edge. The reactive spoiler comprises one or more turbines configured to raise in relation to the upper surface into an airflow passing over the upper surface, and to reduce lift of a wing section behind the turbines. The turbines are configured to convert kinetic energy from the airflow into electrical energy.

A system for detecting and controlling the position of a spoiler of an aircraft wing is described herein comprising: a hydraulic actuator having a piston rod operably connected to the spoiler, the piston rod being moveable between a retracted position, a neutral position and an extended position; and means for providing power to said hydraulic actuator; and a mechanical device for detecting whether the piston rod is in the retracted position, the neutral position or the extended position; and means, operatively connected to the mechanical device, that is configured to provide a change in a load applied to said hydraulic actuator, wherein said means is configured to change said load based on whether said piston rod is detected as being in said retracted position or said extended position.

A seal is provided. The seal includes a seal panel having lateral sides. The seal also includes a seal locking mechanism coupled to the seal panel. The seal locking mechanism is configured to resiliently move, under impetus of an actuator, between an unbowed position of the seal locking mechanism and a bowed position of the seal locking mechanism.

An aircraft includes a fuselage having a wing profile. An apparatus for thrust reversal is disposed on the tail of the aircraft. Air feed takes place from the outside, by way of a braking flap with an air intake channel and/or from a propelling machine.

An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The panel trailing edge portion is pivotably coupled to a vehicle body. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to pivot the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is pivoted away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.

An improved aircraft system is provided. The improved aircraft system comprises an adjustable vortices device that may be attached to an aircraft to create various vortices effects, which increase take-off weight and improve low-speed handling of the aircraft. The adjustable vortices device comprises a linear actuator, a pivot mechanism, and a vortex generator. The pivot mechanism is operably connected to the linear actuator in a way such that the translational energy of the linear actuator causes the pivot mechanism to rotate about a central axis. The vortex generator is moveably attached to a surface of the aircraft and coupled to the pivot mechanism in a way such that rotating the pivot mechanism causes the vortex generator to rotate about a central axis, which alters the angle the vortex generators move through the air.

An improved aircraft system is provided. The improved aircraft system comprises an adjustable vortices device that may be attached to an aircraft to create various vortices effects, which increase take-off weight and improve low-speed handling of the aircraft. The adjustable vortices device comprises a linear actuator, a pivot mechanism, and a vortex generator. The pivot mechanism is operably connected to the linear actuator in a way such that the translational energy of the linear actuator causes the pivot mechanism to rotate about a central axis. The vortex generator is moveably attached to a surface of the aircraft and coupled to the pivot mechanism in a way such that rotating the pivot mechanism causes the vortex generator to rotate about a central axis, which alters the angle the vortex generators move through the air.