Mini-spoilers for enhancing the effectiveness of lateral-control surfaces of aircraft wings are described. An example aircraft includes a wing, a lateral-control surface, and a mini-spoiler. The lateral-control surface is movably coupled to the wing. The lateral-control surface is movable between a neutral position, a first upward deflected position, and a second upward deflected position extending beyond the first upward deflected position. The mini-spoiler is located on or forward of the lateral-control surface. The mini-spoiler is movable between a retracted position and a deployed position. The mini-spoiler is configured to be moved from the retracted position to the deployed position based on the lateral-control surface being moved from the neutral position to or toward the first upward deflected position.

Mini-spoilers for enhancing the effectiveness of lateral-control surfaces of aircraft wings are described. An example aircraft includes a wing, a lateral-control surface, and a mini-spoiler. The lateral-control surface is movably coupled to the wing. The lateral-control surface is movable between a neutral position, a first upward deflected position, and a second upward deflected position extending beyond the first upward deflected position. The mini-spoiler is located on or forward of the lateral-control surface. The mini-spoiler is movable between a retracted position and a deployed position. The mini-spoiler is configured to be moved from the retracted position to the deployed position based on the lateral-control surface being moved from the neutral position to or toward the first upward deflected position.

Systems and methods for controlling a fixed-wing aircraft during flight are disclosed. The aircraft comprises first and second flight control surfaces of different types. The method comprises determining that a pilot command of the first flight control surface will excite a structural flexible mode of the aircraft and then executing the pilot command of the first flight control surface in conjunction with a command of the second flight control surface to mitigate the effect of the excitation of the structural flexible mode of the aircraft.

Systems and methods for controlling a fixed-wing aircraft during flight are disclosed. The aircraft comprises first and second flight control surfaces of different types. The method comprises determining that a pilot command of the first flight control surface will excite a structural flexible mode of the aircraft and then executing the pilot command of the first flight control surface in conjunction with a command of the second flight control surface to mitigate the effect of the excitation of the structural flexible mode of the aircraft.

A camber adjustment system for a wing of an aircraft includes a droop panel that is configured to moveably couple to a portion of the wing, a flap, a cam rod moveably coupled to the droop panel, a bell crank cam arm moveably coupled to the flap, and a jackscrew interface between the cam rod and the bell crank cam arm. The droop panel is configured to move in response to movement of the flap via the jackscrew interface.

A camber adjustment system for a wing of an aircraft includes a droop panel that is configured to moveably couple to a portion of the wing, a flap, a cam rod moveably coupled to the droop panel, a bell crank cam arm moveably coupled to the flap, and a jackscrew interface between the cam rod and the bell crank cam arm. The droop panel is configured to move in response to movement of the flap via the jackscrew interface.

A spoiler mechanism for an aircraft includes a spoiler fore-section and a spoiler aft-section. The spoiler fore-section includes a forward end configured to couple to a wing structure of an aircraft and a hinge end. The hinge end includes a first hinge coupling and a first retainer portion. The spoiler aft-section includes a second retainer portion and a second hinge coupling coupled to the first hinge coupling of the spoiler fore-section. The first retainer portion and the second retainer portion are configured to engage one another when the spoiler aft-section is aligned with the spoiler fore-section, and the first retainer portion and the second retainer portion are configured to disengage from one another responsive to the spoiler aft-section pivoting upward relative to the spoiler fore-section.

A spoiler mechanism for an aircraft includes a spoiler fore-section and a spoiler aft-section. The spoiler fore-section includes a forward end configured to couple to a wing structure of an aircraft and a hinge end. The hinge end includes a first hinge coupling and a first retainer portion. The spoiler aft-section includes a second retainer portion and a second hinge coupling coupled to the first hinge coupling of the spoiler fore-section. The first retainer portion and the second retainer portion are configured to engage one another when the spoiler aft-section is aligned with the spoiler fore-section, and the first retainer portion and the second retainer portion are configured to disengage from one another responsive to the spoiler aft-section pivoting upward relative to the spoiler fore-section.

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.

Mini-spoilers for enhancing the effectiveness of lateral-control surfaces of aircraft wings are described. An example aircraft includes a wing, a lateral-control surface, and a mini-spoiler. The lateral-control surface is movably coupled to the wing. The lateral-control surface is movable between a neutral position, a first upward deflected position, and a second upward deflected position extending beyond the first upward deflected position. The mini-spoiler is located on or forward of the lateral-control surface. The mini-spoiler is movable between a retracted position and a deployed position. The mini-spoiler is configured to be moved from the retracted position to the deployed position based on the lateral-control surface being moved from the neutral position to or toward the first upward deflected position.