Abstract: Apparatus and process for the installation of collars and/or nuts on fasteners, particularly in the aerospace industry. The apparatus includes an industrial base robot supporting a mounting base carrying a gimbal and rotary drive for a lightweight sensing robot with a fastening/torque tool. The sensing robot operates to align and position a spin preventing projection such as a hex key in a fastener end and a rotatable socket to torque a nut or collar onto the fastener held against rotation. The related process is accomplished by sensors in conjunction with the sensing robot aligning the hex key with a recess in the fastener end, inserting the key into the fastener to hold it against rotation, and spinning a nut or collar onto the fastener. A wrenching component is sheared from the nut and removed after the nut or torque is applied.

Abstract: A monolithic optical absorber and methods of making same. The monolithic optical absorber uses an array of mutually aligned carbon nanotubes that are grown using a PECVD growth process and a structure that includes a conductive substrate, a refractory template layer and a nucleation layer. Monolithic optical absorbers made according to the described structure and method exhibit high absorptivity, high site densities (greater than 109 nanotubes/cm2), very low reflectivity (below 1%), and high thermal stability in air (up to at least 400° C.). The PECVD process allows the application of such absorbers in a wide variety of end uses.

Abstract: A monolithic optical absorber and methods of making same. The monolithic optical absorber uses an array of mutually aligned carbon nanotubes that are grown using a PECVD growth process and a structure that includes a conductive substrate, a refractory template layer and a nucleation layer. Monolithic optical absorbers made according to the described structure and method exhibit high absorptivity, high site densities (greater than 109 nanotubes/cm2), very low reflectivity (below 1%), and high thermal stability in air (up to at least 400° C.). The PECVD process allows the application of such absorbers in a wide variety of end uses.

Abstract: YAn aircraft leading edge slat is biased when at an extended location toward a first position wherein the trailing edge of the slat is a predetermined distance from the wing upper surface. The slat is pivotable to a second position, when aerodynamic forces acting on the wing overcome the biasing force, wherein the slat trailing edge is pivoted upward and forward, and the distance between the slat trailing edge and the wing upper surface is increased. The slat is retracted and extended by a drive track which is supported inside the wing by upper rollers located chordwise within the wing cavity, a lower front roller, and a pair of roller rings rotatably mounted at opposite sides of a rotary actuator pinion gear. The pinion gear engages the drive track and moves the slat between the extended and retracted positions.

Abstract: A leading edge/anti-icing assembly for an airfoil comprising a leading edge slat having a nose section defining a heat exchange chamber. Anti-icing air directed into the heat exchange chamber flows rearwardly through the slat so as to have a deicing function, and is then discharged in a rearward direction from the trailing edge of the slat. Thus, the anti-icing air not only performs an anti-icing function over the upper surface of the slat, but also contributes to anti-icing over the upper surface portion of the main wing rearwardly of the trailing edge of the slat.

Abstract: A variable camber leading edge device having a movable nose section and an upper flexible panel extending rearwardly from the nose section. To move the nose section between its upper cruise position and a high lift downwardly deflected position, there is attached to the nose section a generally arcuate cam track, having its forward and rear portions curving upwardly. The cam track is constrained to move in a generally arcuate path, but with a movable center of rotation, and is driven by a gear engaging a radially outward rear portion of the track.

Abstract: A leading edge wing slat having a movable nose portion wherein the nose portion leading edge moves relative to the slat frame in a downward and rearward direction when the slat is extended. This causes an intermediate flexible upper skin panel attached between the nose portion and a rigid rear portion of the slat to have its curvature increased thereby increasing the camber of the upper surface of the slat. During retraction of the slat, the nose portion leading edge moves upward and rearward relative to the slat frame decreasing the curvature of the intermediate flexible upper skin panel. The nose portion includes a cam plate having cam slots which are engaged by rollers rotatably connected to the slat frame. Extension of the slat causes the cam plate as programmed by the cam slots to move the nose portion relative to the slat frame to achieve the desired slat camber.

Abstract: A variable-camber airfoil includes a four-bar linkage camber altering mechanism and a flexible panel in the lower skin of the airfoil. A flexible upper skin extends from the upper end of a front spar assembly to the upper end of a nose structure of the airfoil. A rotary actuator is mounted forward of the front spar assembly within the cavity of the airfoil, and is used to actuate the camber altering mechanism. A main drive arm, which acts as a link in the camber altering mechanism, extends forwardly from the rotary actuator. To actuate the camber altering mechanism, the main drive arm is rotated downwardly and rearwardly through an arcuate path in a vertical chordwise plane. The main drive arm pulls downwardly on first and second links, which, due to the kinematics of the four-bar linkage, causes the nose structure to rotate and move downwardly and rearwardly in a manner that will produce the desired aerodynamic curvature in the flexible upper skin.

Abstract: A variable camber leading edge device having a movable nose section and an upper flexible panel extending rearwardly from the nose section. To move the nose section between its upper cruise position and a high lift downwardly deflected position, there is attached to the nose section a generally arcuate cam track, having its forward and rear portions curving upwardly. The cam track is constrained to move in a generally arcuate path by means of two spaced pair of rollers, and it is driven by a pinion gear engaging an upwardly facing middle portion of the track.

Abstract: An actuation and extension mechanism for aerodynamically high-lift devices such as a wing leading edge slat or a wing trailing edge flap; wherein an aerodynamic panel is connected to one end of an extendible track member that is supported and guided by its other end through rollers fixedly mounted to wing rib structure. The track member incorporates a separate rack gear segment internally thereof as part of the extension or retraction mechanism and this combination of track and gear segment provides the primary support and drive means to the high-lift device, without compromising the structural strength, safety, or operational reliability of said combination.

Abstract: An actuation and extension mechanism for aerodynamic high-lift devices such as a wing leading edge slat or a wing trailing edge flap; wherein an aerodynamic panel is connected to one end of an extendible track member that is supported and guided by its other end through rollers fixedly mounted to wing rib structure. The track member incorporates a cable and drum arrangement as part of the extension or retraction mechanism; and this combination of track, cable and drum provides the primary support and drive means for the high-lift device without compromising the structural strength or the stress safety of said combination.

Abstract: Dual flap sections are supported by linkage, first for chordwise movement of the forward flap section rearwardly from the wing and for chordwise movement of the rear flap section rearwardly from the forward flap section, and then for tilting of the two flap sections conjointly to increase their angle of incidence relative to the wing. The forward flap section is supported by motion-amplifying compound linkage for effecting chordwise movement of the forward flap section relative to the wing, and the rear flap section is supported by motion-amplifying compound linkage from the forward flap section for effecting chordwise movement of the rear flap section relative to the forward flap section. Control mechanism for both motion-amplifying compound linkages is connected to the wing and is movable first to actuate the linkages primarily for shifting the two flap sections chordwise rearwardly from the wing and then primarily to tilt the foward and rear flap sections conjointly to increase their angle of incidence.

Abstract: A pair of motion-amplifying flap linkages connected externally to the undersurface of a tapered planform airfoil and being spaced apart spanwise thereof for a combined pseudo conical extension movement of a tapered-chord flap section. The pair of flap linkage mechanisms conjointly first extending the tapered chord flap section chordwise of the airfoil and then rotatably tilting the flap to increase its angle of incidence, such that the chordwise length of movement and rotation of the flap, is proportional to the length of the airfoil chord at that cross-section of the airfoil; and approximates a conic motion of the flap relative to the airfoil.

Abstract: A variable camber leading edge flap and linkage mechanism for allowing two different extended operating positions of the flap, i.e. a landing position whereat an aerodynamic slot is formed between the aft edge of the flap and the fixed leading edge of the wing, coupled with a relatively steep flap angle relative to the wing chord plane; and a take-off position whereat the aerodynamic slot is closed and the flap angle is less than at the landing position. Also, a pair of cam mechanisms are interposed between linkages and sequenced in their operating functions to alternately restrain and release certain of the linkage members in order to open or close the aerodynamic slot and change the flap angle in a manner that insures that air loads acting on the variable camber flap do not cause linkage oscillation and flap instability.

Abstract: A variable camber apparatus for the leading and/or trailing edge of an airfoil that is operable for lift variation at high airspeeds of a jet aircraft such as for maneuvering of fighter aircraft. The cambering apparatus comprises an upper surface flexible skin panel which is supported along its inner edge by a wing spar assembly and along its outermost edge, by an airfoil edge forming structure. A hinged rib member, through a kinematic linkage mechanism associated between itself and the structure at the outermost edge of the airfoil section, bends and torsionally twists the airfoil edge forming structure about a relative spanwise axis.

Abstract: A variable camber apparatus for the leading and/or trailing edge of an airfoil that is operable for lift variation at high airspeeds of a jet aircraft such as for maneuvering of fighter aircraft. The cambering apparatus comprises an upper surface flexible skin panel which is supported along its inner edge by a wing spar assembly and along its outermost edge, by an airfoil edge forming structure. A hinged rib member, through a kinematic linkage mechanism associated between itself and the structure at the outermost edge of the airfoil section, bends and torsionally twists the airfoil edge forming structure about a relative spanwise axis.

Abstract: A variable camber apparatus for the leading and/or trailing edge of an airfoil that is operable for lift variation at high airspeeds of a jet aircraft such as for maneuvering of fighter aircraft. The cambering apparatus comprises an upper surface flexible skin panel which is supported along its inner edge by a wing spar assembly and along its outermost edge, by an airfoil edge forming structure. A hinged rib member, through a kinematic linkage mechanism associated between itself and the structure at the outermost edge of the airfoil section, bends and torsionally twists the airfoil edge forming structure about a relative spanwise axis.

Abstract: An aircraft wing for use in a STOL aircraft incorporating upper surface blowing engines employs trailing edge flaps, including a main flap segment and an aft flap segment. The flaps are mounted on and externally hinged below the wing for movement between a retracted position and a plurality of extended positions. The main flap segment is hinged to its support for pivotal movement about a spanwise axis. The main flap segment is in a first position when retracted and normally remains in that position as the flaps are extended. When the flaps are extended and the main flap segment is in the first position, the upper airfoil surfaces of main flap segment and the aft flap segment form a smooth, continuous upper surface that extends downwardly and rearwardly from the upper airfoil surface of the wing.

Abstract: An extendable fairing for use between two aerodynamic surfaces (e.g., the engine nacelle and wing leading edge flap) of an aircraft is disclosed. The illustrated embodiment of the invention comprises a fixed fairing section, extending outwardly from an engine nacelle, and an extendable fairing section, housed within the fixed fairing section. During cruise, when the flaps are withdrawn, the extendable fairing section is withdrawn. During takeoff and landing, or other conditions when the leading edge flaps are extended, the extendable fairing section is extended and fills the gap between the fixed fairing section and the leading edge flap.

Abstract: A variable camber apparatus for the leading edge of an airfoil that is operable for lift variation at high airspeeds of a jet aircraft such as for maneuvering of fighter aircraft. The cambering apparatus comprises an upper surface flexible skin panel which is supported along its inner edge by a wing spar assembly and along its outermost edge, by an airfoil edge forming structure. A hinged rib member, through a kinematic linkage mechanism associated between itself and the structure at the outermost edge of the airfoil section, bends and torsionally twists the airfoil edge forming structure about a relative spanwise axis.