Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) (24, 25) with a belt drive system (84, 99) for turning wing-situated propellers (8, 9); compound landing gear integrating ski (29, 114), pontoon and wheel (18, 19, 21) subcomponents; pivotal mounting armatures (6, 7) for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure (14, 15) featuring extendable wing panels (4, 5) that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.

Multi-purpose aircraft

Systems and methods for controlling aircraft flaps and spoilers are disclosed. Systems (200) in accordance with some embodiments -include- a wing (210) having a trailing edge (211) , and a flap (220) positioned at least partially aft of the wing trailing edge (211) and being deployable relative to the wing (210) between a first flap position and a second flap position by operation of a first actuator. A spoiler (230) can be positioned at least proximate to the trailing edge (211) and can be movable among at least three positions, including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing (210) , a second spoiler position deflected downwardly from the first, and a third spoiler position deflected upwardly from the first. A second actuator (231) can be operatively coupled to the spoiler to move the spoiler among the first, second and third spoiler positions in a manner that is mechanically independent of the motion of the flap. independent of the motion of the flap.

Systems and methods for controlling aircraft flaps and spoilers

A highly tapered wing tip extension added to the tip of an existing swept, trapezoidal airplane wing for reducing high speed drag significantly. A smaller, highly swept, extension does not require a leading edge device to protect against low speed stall. A larger, less swept, extension requires a tapered slat for which two mechanisms are presented. The principles of the present invention are also applicable to the design of new aircraft.

High taper wing tip extension

A wing leading edge high-lift generating device in the form of a spanwise slat segment having both an upper and a lower surface, faired into an airfoil configured leading edge of a relatively stationary portion of the wing therebehind and movable with respect thereto by a downwardly extending hinge arm pivotally related to a downwardly extending hinge bracket from the wing within a fairing structure which also includes an actuator between the hinge arm and bracket for biasing the hinge arm connected to the leading edge device away from and downwardly with respect to the hinge bracket of the wing about the pivotal connection therewith. Further, the wing leading edge slat device has a large cavity formed between the upper and lower surfaces thereof, which cavity is readily adaptable for the insertion of a large duct for blowing pressurized air through a nozzle and an aerodynamic slot formed between the leading edge slat and the relatively stationary airfoil configured leading edge of the wing therebehind when the leading edge slat is moved outwardly and downwardly. In another embodiment the leading edge slat has its movement guided by an extendable track.

Wing leading edge high lift device

Trailing edge devices configured to carry out multiple functions, and associated methods of use and manufacture are disclosed An external fluid flow body (eg, an airfoil) configured in accordance with an embodiment of the invention includes a first portion and a second portion, at least a part of the second portion being positioned aft of the first portion, with the second portion being movable relative to the first portion between a neutral position, a plurality of upward positions, and a plurality of downward positions A guide structure can be coupled between the first and second portions, and an actuator can be operatively coupled between the first and second portions to move the second portion relative to the first portion In one embodiment, a flexible surface can track the motion of the second portion and can expose a gap at some positions In another embodiment, a controller can be coupled to the actuator and can be configured to direct the actuator to move the second portion to a high lift setting, a high drag setting, a roll setting, and a trim setting In yet another embodiment, trailing edge devices on an airfoil can have scaled, mechanically similar guide structures

Multi-function trailing edge devices and associated methods

A mechanism is provided for both extending the chord of a wing by more than seventy percent and for increasing the camber of the wing without creating the high pitching moment characteristics of conventional high lift wing systems. These advantageous capabilities are accomplished by constructing forward and aft wing sections which cover the wing box beam and form a high wing loading cruise flight wing. The sections can be extended and deflected to uncover the wing box beam and form a greatly increased area to lower the wing loading and an increased camber with low pitching moment to provide high lift for short take-off and landing.

T Gardner Hill

Papers

Variable area, variable camber wing for aircraft