Abstract: A wing (5) for an aircraft (1) and include a fixed wing (7), a high lift system (9) including a high lift surface (27) movably mounted to the fixed wing (7), and a high lift actuation system (29) for moving the high lift surface (27) relative to the fixed wing (7) between a retracted position and at least one deployed position, a foldable wing tip portion (11) mounted to the fixed wing (7) pivotally about an axis of rotation (35) between an extended position and a folded position, a tip actuation unit (13) for moving the foldable wing tip portion (11) between the extended position and the folded position.

Abstract: The current invention relates to novel platinum(II) based organometallic materials. These materials show high emission quantum efficiencies and low self-quenching constant. Also provided are high efficiency, green to orange emitting organic light-emitting diode (OLED) that are fabricated using platinum(II) based organometallic materials as the light-emitting material. The organometallic materials of the invention are soluble in common solvents; therefore, solution process methods such as spin coating and printing can be used for device fabrication. The devices fabricated from these materials show low efficiency roll-off.

Abstract: The vertical takeoff and landing unmanned aerial vehicle includes a pair of selectively rotatable ducted fans and a selectively rotatable thrust vectoring nozzle providing vertical takeoff and landing for an unmanned aerial vehicle or a similar type of aircraft. A pair of fixed forward-swept wings are mounted on a rear portion of a fuselage, and a pair of canards are mounted on a top end of a forward portion of the fuselage. The pair of ducted fans are respectively mounted on free ends of the pair of canards, and are selectively rotatable about an axis parallel to a pitch axis of the fuselage. An engine is mounted in the rear portion of the fuselage, and a thrust vectoring nozzle is mounted on the rear portion of the fuselage for directing thrust exhaust from the engine. The thrust vectoring nozzle is selectively rotatable about an axis parallel to the pitch axis.

Abstract: An aeroplane comprising a fuselage elongated in a longitudinal direction of the aeroplane is provided. The aeroplane includes a wing attached to the fuselage in a midsection of said fuselage in the longitudinal direction, such that part of the fuselage extends forward of the wing toward a front extremity of the fuselage, and part of the fuselage extends from the rear of the wing toward a rear extremity of the fuselage. A rear fuselage section includes at least one engine attached to the fuselage and located to the rear of the wing. The one or more engines attached to the fuselage are attached in a rear position such that only parts of the aeroplane located in a projection space of the one or more engines attached to the fuselage and the rear fuselage does not include any aerodynamic surfaces intended to assure stability and/or aerodynamic control of the aeroplane.

Abstract: A compound motion structure (3) for connection between two surfaces comprising a first arm (5) and a second arm (7) swingable coupled together through a first hinge connection (13), a first surface (35) coupled to an opposite end of the first arm via a second hinge connection, a second surface (39) coupled to an opposite end of the second arm via a third hinge connection, the first arm (5) and the second arm (7) being movable thereby resulting in a compound motion of one or both surfaces.

Abstract: An aircraft control system is presented. The system includes a wing including a flap track, and a shuttle connected to the flap track and configured to slide along a length of the flap track. The system includes a flap panel pivotally attached to the shuttle at a flap pivot. The flap panel is configured to rotate about the flap pivot. When the shuttle is deployed along a length of the flap track, the shuttle is configured to prevent rotation of the flap panel about the flap pivot, and when the shuttle is withdrawn into a stowed position, the shuttle is configured to allow the flap panel to rotate about the flap pivot.

Abstract: Described are novel platinum (II) containing organometallic materials. These materials show green to orange emissions with high emission quantum efficiencies. Using the materials as emitting materials; pure green emitting organic light-emitting diodes can be fabricated. Since the novel platinum (II) containing organometallic materials are soluble in common solvents, solution process methods such as spin coating and printing can be used for device fabrication.

Abstract: A fault-tolerant actuating system with at least one flap, adjustable on a respective wing of an aircraft, and with a control and monitoring device, includes: drive devices that are functionally connected to the control and monitoring device, with one of these drive devices in each case being associated with a flap, where each flap in each case is associated with a drive device, in each case including: two drive motors, two brake mechanisms, where each drive motor is associated with a brake mechanism for stopping rotation of the output of the respective drive motor, a differential that couples the outputs of the aforesaid to the aforesaid in a summing manner, an output shaft for coupling the output of the differential to drive connections, and a differential lock that is functionally connected to the control and monitoring device, which differential lock is coupled to the control and monitoring device in this manner, where each of the brake mechanisms as well as the differential lock can be operated by way of

Abstract: A control input system is provided. The system includes a pair of control columns that are selectively interconnected such that manipulation of one of the control columns is translated to the other one of the control columns. The system includes a disconnect arrangement for each of the degrees of freedom (pitch and roll) of the system that operably disconnects the two control columns such that the two control columns can operate independently such as in the event of failure of one of the control columns. The system may also include a discontinuous force profile for a restoring force mechanism that provides tactile feedback to the pilots simulating resistance provided by control surfaces of the aircraft. The system may also include an autopilot lockout mechanism that increases the force profile experienced by the pilots when autopilot mode is entered.

Abstract: Vehicle control systems and methods for sizing such systems are disclosed. In one embodiment of the invention, an actuator mechanism capability is selected, at least one operating requirement is selected, and the required number, size, and locations of a plurality of control surfaces needed to satisfy the at least one operating requirement are determined. In another embodiment, a set of control laws is selected, at least one operating requirement is selected, and the number size, and location of a plurality of control surfaces needed to satisfy the at least one operating requirement are determined.

Abstract: Improved miniature trailing edge effectors for aerodynamic control are provided. Three types of devices having aerodynamic housings integrated to the trailing edge of an aerodynamic shape are presented, which vary in details of how the control surface can move. A bucket type device has a control surface which is the back part of a C-shaped member having two arms connected by the back section. The C-shaped section is attached to a housing at the ends of the arms, and is rotatable about an axis parallel to the wing trailing edge to provide up, down and neutral states. A flip-up type device has a control surface which rotates about an axis parallel to the wing trailing edge to provide up, down, neutral and brake states. A rotating type device has a control surface which rotates about an axis parallel to the chord line to provide up, down and neutral states.

Abstract: Systems and methods for implementing control linkages that may be employed to produce synchronous motion in two adjacent controlled devices controlled by a common input. In one example implementation, a semi-rigid modified constant velocity (CV) joint control linkage may be provided that is laterally self-stabilizing. The modified constant velocity CV joint control linkage may include an input push rod assembly that is self-aligning, deflectable and of an adjustable length. The CV joint may be configured with a central cage that is allowed to skew to allow for alignment of the controlled devices.

Abstract: An apparatus for actuating a control surface includes a first spur gear; a first drive assembly engaged with the first spur gear; a second spur gear; and a second drive assembly engaged with the second spur gear. The apparatus further includes a gear assembly engaged with the first spur gear and the second spur gear and adapted to be coupled with the control surface.

Abstract: This invention is a servo mounting system, which allows a servo with a rotating output shaft to directly power an aircraft control surface. A specially designed servo mount securely positions the servo with the central axis of its rotational output shaft on, and axially aligned with, the hinge line of the control surface it drives. The servo shaft and servo body are directly connected to the airframe and control surface, thereby conserving rotational motion while driving control movement. Electronic means are then used to control the neutral point and the limit of travel of the servo. The system eliminates lost motion without generating adverse linear loads within the drive assembly.

Abstract: The present invention is structured such that lift control apparatus such as flaps and flaperons operate in association with elevator operation performed by a pilot. Lift control conforming to elevator operation by the pilot is performed.

Abstract: A flaperon operating device having a center pulley and a slider supported on a center shaft. When the center pulley and the slider are rotated about the center shaft, left and right driving pulleys are rotated in the same direction, whereby left and right flaperons are operated in opposite directions to provide aileron functions. When the slider is slid rearwards on the center shaft by an actuator, the left and right driving pulleys are rotated in opposite directions, whereby both the left and right flaperons are lowered to provide flap functions. If the left and right flaperons are lifted or lowered by a very small angle in the same phase by the actuator, boundary layers on main wings can be controlled to reduce the drag.

Abstract: A rotor aircraft has an adjusting mechanism that controls the sensitivity of the control stick relative to fore and aft tilt of the rotor. The control stick is pivotable between fore and aft directions as well as laterally about a control stick pivot point. A rotor linkage is connected between the control stick and the rotor rotor head. The rotor linkage assembly tilts the rotor head in response to tilting movement of the control stick. The linkage assembly has a control point that rotates at a radius about the control stick pivot point. An adjusting member located between the control stick and the linkage assembly can be moved to change the radius of the control point to the control stick pivot point. The change in radius corresponds to the amount of tilt that the rotor head make while the control stick moves between full aft and full forward positions. The control stick also controls ailerons and a horizontal stabilizer but these control services are not affected by the adjusting member.

Abstract: In accordance with the present invention, there is provided an aerodynamic control device for use with an aerodynamic lifting member. The lifting member is defined by a horizontal reference plane disposed therethrough. The control device is provided with at least one support rotor extending from the lifting member. The support rotor is sized and configured to rotate about a rotor axis of rotation which is disposed generally parallel to the horizontal reference plane. The support rotor has an inboard segment which is disposed along the rotor axis of rotation and in rotational communication with the lifting member. The support rotor has an outboard segment disposed off-set from the rotor axis of rotation. The control device is further provided with a control device body which is engaged with the outboard segment of the support rotor. The control device body is sized and configured to translate generally orthogonal to the horizontal reference plane in response to rotation of the support rotor.

Abstract: A short take off and landing (STOL) aircraft is optimized for STOL performance and flight at minimum airspeed. The aircraft includes leading edge wing slats that are extended and retracted under the direct manual control of the pilot. The aircraft further includes an aileron/flap mixing mechanism that automatically droops the ailerons when the flaps are lowered. A flap bellcrank, which pivots to lower the flaps, carries a pair of pulleys. Aileron control cables, that actuate an aileron bellcrank to raise and lower an aileron, are threaded around and between the two pulleys. When the flap bellcrank pivots to lower the flap, the pulleys vary the positions of the aileron control cables relative to each other to pivot the aileron bellcrank and thereby lower the aileron. The aileron control cables remain independently movable to maintain pilot control over the bank and roll of the aircraft.

Abstract: The present invention discloses an aircraft control system having simultaneously controllable rear aileron/elevators and a retractable body flap for longitudinal stabilization. The aileron/elevators are airfoils comprising the complete horizontal tail plane. Control arms for the rear aileron/elevators are capable of pivotal movement about the longitudinal axis of the aircraft while the aileron/elevators are secured to the control arms by axles pivotal about the lateral axis of the airfoil, for directional control. With two degrees of rotational movement, the aileron/elevators are capable of maneuvering the aircraft in all three axes, providing a much simpler mechanism than the conventional control surfaces. Added safety is accomplished by removing lateral control from the wings. Weight savings and reduced drag also result from eliminating the vertical stabilizer and rudder and consolidating the controls for both ailerons and elevators of conventional aircraft.

Abstract: A short take off and landing (STOL) aircraft is optimized for STOL performance and flight at minimum airspeed. The aircraft includes leading edge wing slats that are extended and retracted under the direct manual control of the pilot. The aircraft further includes an aileron/flap mixing mechanism that automatically droops the ailerons when the flaps are lowered. A flap bellcrank, which pivots to lower the flaps, carries a pair of pulleys. Aileron control cables, that actuate an aileron bellcrank to raise and lower an aileron, are threaded around and between the two pulleys. When the flap bellcrank pivots to lower the flap, the pulleys vary the positions of the aileron control cables relative to each other to pivot the aileron bellcrank and thereby lower the aileron. The aileron control cables remain independently movable to maintain pilot control over the bank and roll of the aircraft.

Abstract: A hydraulic actuation system for an aircraft control surface such as an elevon. A pair of spaced pivot points are provided to alternately rotate the control surface either clockwise or counterclockwise.

Abstract: A light-duty multipurpose aeroplane has a fuselage having a cabin at its center, a tail portion with a pusher propeller in a ring and a front portion with an all-swiveling horizontal "canard" type empennage. The wings of the aeroplane are articulated with low-mounted and high-mounted wing segments with opposite sweeps. The tips of the wing segments are connected with arrow-shaped pylons provided with heading control rudders.

Abstract: An autogyro has a teetering semi-rigid rotary wing with rigid rotor blades. The angle of attack (blade pitch) of the rotor blades is fully adjustable in flight continuously over an operational range, and varies along the blade length. A prerotator rotates the rotor blades up to takeoff speed at minimum drag, no lift and optimum engine efficiency. Engine power is disconnected from the rotor blades and their angle of attack is changed for optimum lift to facilitate smooth vertical takeoff. Rotor blade pitch is likewise adjusted during vertical landing. In flight, rotor blade angle of attack is varied to adjust autorotation, lift and drag at any flight airspeed. On the ground, the rotary wing is braked to prevent rotation.The autogyro may roll, pitch, or yaw, with complete independence of blade pitch with respect to all other relative motions. The pedals have disproportionate forward and backward motions. The autogyro has retractable gear capable of fail-safe gear-up landing.

Abstract: A spoileron control mechanism is shown which provides for separate or simultaneous braking and rolling of the aircraft through operation of spoilers located on the wings. The control mechanism includes a base to which is mounted two pivot brackets 2. Pivotally mounted to the base are two bell cranks 3 to which are connected via cables 15 to the spoiler. The bell cranks are pivoted in a scissors like fashion by connection via arms 7 to slotted plates 5 that are also pivoted side to side by a control stick 13 which causes the bell cranks to operate the spoilers in a differential fashion for roll control. The bell cranks are further actuated by a lever 10 which causes a cam bar 8 to act on the arms 7 pivoting the bell cranks and causing the spoilers to be actuated simultaneously for braking of the aircraft.

Abstract: A flap (22) carries a guide roller (24) at each of its ends. Each guide roller (24) travels within a fore and aft track (28) positioned immediately endwise outwardly of its end of the flap (22). The flap (22) is extended and retracted by means including a reaction link (36) and a two-way linear actuator (38). The actuator (38) and the reaction link (36) are pivotally connected at their forward ends to the outer end of a bell crank arm (34), for pivotal movement about a common axis (40). At its rearward end the actuator (38) is pivotally attached to the flap at a location (44) offset above the roller (24). The reaction link (36) is pivotally attached at its rearward end to the flap (22) at a location (42) offset below the roller (24). Rotation of the bell crank arm (34) alone will result in the flap (22) being translated rearwardly and rotated downwardly, i.e. Fowler flap movement. Extension or retraction of the actuator (38) will cause a rotation of the flap (22) about the axes (26) of the rollers (24).

Abstract: An empennage assembly for supersonic aircraft includes longitudinally and rearwardly extending booms (12) mounted upon the wings (16) or fuselage of the aircraft. The booms (12) include aft rotatable sections (22) upon which are mounted larger (18) and smaller (20) tail surfaces. The boom sections (22) are angularly rotated through angular displacements .theta. such that the dispositions of the tail surfaces (18, 20) are interchanged between their dispositions during low subsonic and high supersonic flight conditions. In this manner, the directional and longitudinal aerodynamic static stability components of the aircraft are rendered substantially constant at an optimum low or near-neutral level of stability in order to enhance the flight maneuverability capabilities of the aircraft throughout the subsonic, transonic, and high supersonic speed ranges.

Abstract: The invention is an improved flight control system for aircraft. The improved flight control system mixes or blends several flight control movements into a unified operation. The flight control mixing system of this invention combines the functions of standard ailerons (a roll and lateral control device) with standard flaps (a lift control device) on aircraft into a single control device, referred to herein as flaperons. The improved system can also be used on tailess or flying wing type aircraft to combine the functions of standard ailerons with the elevator functions (a nose up or down pitch control device) into a single control device, referred herein as elevons. The improved system is also applicative to V-tail type aircraft for controlling the elevators in a similar single control operation, herein referred to as ruddervators.

Abstract: An ultralight aircraft has a single stick three-axis aerodynamic control, twin engined power control, wing- and tail-mounted ailerons, an inverted V-tail and wide span wings with upturned tips.

Abstract: An actuation system for rotating a control surface mounted on an aircraft airfoil, the control surface being rotatable about a first axis at an acute angle to the longitudinal axis of the aircraft is disclosed. The invention comprises a first crank having a first end and a second end pivotally mounted to the airfoil and rotatable about a spanwise second axis substantially perpendicular to the longitudinal axis of the aircraft. A second crank is pivotally mounted at its first end to the first crank and is rotatable about a third axis which is substantially perpendicular to the second axis. The second end of the second crank is pivotally mounted to the control surface. The second end of the second crank is rotatable about a fourth axis substantially perpendicular to the second and third axes. An actuator, substantially aligned with the longitudinal axis of the aircraft, is coupled to the airfoil and to the first end of the first crank.