Recessed lift spoiler assembly for airfoils

A spoiler assembly engageable to an airfoil for reducing lift of the airfoil, the airfoil defining an airfoil body, an airfoil outer surface and an airfoil inner surface, the airfoil outer surface defining first and second spoiler apertures formed therein, the spoiler assembly comprising:

• first and second spoilers, each spoiler being translatably connected to the airfoil inner surface adjacent a first portion of an associated spoiler aperture, each spoiler defining a spoiler upper surface and a spoiler lower surface, the spoiler upper surface being substantially the same size and shape as the associated spoiler aperture;
• first and second spoiler shrouds, each shroud being connected to the airfoil inner surface and extending within the airfoil body about at least a portion of an associated spoiler aperture;
• and
• first and second spoiler activating mechanisms, each spoiler activating mechanism being secured to the airfoil inner surface and connected to an associated spoiler lower surface, the spoiler activating mechanisms being translatable into the spoiler shrouds to reduce lift of the airfoil by translating the spoilers between a first position, wherein the spoiler upper surfaces are both substantially flush with the airfoil outer surface, and a second position, wherein the spoiler upper surfaces are both recessed within the shroud, thereby reducing lift of the airfoil.

A method of reducing the descent angle of an aircraft defining an aircraft body, an aircraft outer surface and an aircraft inner surface, the aircraft outer surface defining first and second apertures formed therein the method comprising:

• forming first and second spoiler apertures in the aircraft outer surface, the spoilers each defining an upper surface;
• connecting a translatable spoiler to the aircraft inner surface adjacent each of the spoiler apertures, the spoilers being substantially the same size and shape as the spoiler apertures;
• and
• reducing the lift of the aircraft by translating the spoilers between a first position wherein the spoilers are substantially flush with the aircraft outer surface, to a second position wherein the spoilers are at least partially recessed within the aircraft body, thereby increasing the descent angle of the aircraft.

An unmanned aerial vehicle (UAV), the UAV defining a UAV blended wing body, a UAV outer surface, a UAV inner surface, a UAV upper surface and ailerons disposed along a trailing edge of the UAV outer surface, the UAV upper surface defining first and second spoiler apertures formed therein, the UAV comprising:

• a spoiler assembly for reducing lift of the UAV, the spoiler assembly including:
• first and second spoilers disposed along the UAV upper surface upstream of the ailerons, each spoiler being translatably connected to the UAV inner surface adjacent a first portion of an associated spoiler aperture, the spoilers each defining a spoiler upper surface and a spoiler lower surface, the spoiler upper surfaces being substantially the same size and shape as the spoiler apertures;
• first and second spoiler shrouds, each spoiler shroud being disposed within the UAV blended wing body about at least a portion of an associated spoiler aperture;
• and
• first and second spoiler activating mechanisms disposed within the UAV, each spoiler activating mechanism being disposed within the UAV blended wing body and connected to an associated spoiler lower surface, the spoiler activating mechanisms being operative to increase the descent angle of the UAV by translating the spoilers from a first position, wherein the upper surfaces of the spoilers are substantially flush with the UAV outer surface, to a second position, wherein the spoiler upper surfaces of the spoilers are recessed within the UAV blended wing body to form a cavity within the UAV blended wing body, the cavity being substantially defined by the shroud and the upper surface of the spoilers.