Abstract: A method and apparatus for retrieving an aircraft in a confined space involves hanging a cable, for example from a kite or mast, across the aircraft's flight path. The aircraft approaches the cable in steady forward flight, and may strike the cable at any point on the wing, fuselage, or other leading surface. The cable then slides along the airframe as the aircraft moves forward, until it is intercepted by a hook attached to the wing tip or other convenient location. The hook captures the cable, and prevents further sliding; the cable then pulls the aircraft to a stop. Compliance of the cable, optionally combined with compliance of the cable suspension, provides acceptably gradual deceleration. The aircraft is left suspended in mid-air, and is then winched or slid to the base of the cable or other convenient retrieval point.

Abstract: The improved helicopter anti-icing and deicing system and method includes mounting an airfoil shaped manifold transversely of the helicopter and filling the manifold with anti-icing or deicing fluid which is not under sufficient pressure to spray outwardly from the manifold. Instead, the rear edge of the manifold is provided with small, spaced openings which cause fluid droplets to form along the rear edge of the manifold and to then drop downwardly by gravity. The helicopter is positioned above a power line with the power line extending in the direction of the helicopter longitudinal axis and droplets are caused to exit the manifold as the helicopter flies along the power line.

Abstract: A wing fold actuation system (24) is provided for folding an outboard wing section (18) relative to an inboard wing section (16) between a deployed position (20) and a stored position (22). The system (24) includes an actuator (26) in the form of a geared rotary actuator (30) in combination with a four-bar linkage (32). A locking mechanism (28) is provided to lock the outboard wing section (18) in the deployed position (20), and includes a catch on the outboard wing section (18) that is engageable with a rotary latch (42) on the inboard wing section (16). A timing transmission (46) connects the rotary actuator (30) with the rotary latch (42) to time the rotation of the rotary latch (42) with respect to the movement of the outboard wing section (18) between the deployed and stored positions (20,22).

Abstract: To provide aerodynamic continuity between the front part, pivoting with the rotor, and the stationary rear part of a pod housing an engine for driving the rotor, a curved cowl curved about the pivot axis extends the rear edge of the bottom cowling of the front part to join this rear edge to the front edge of a bottom cowling of the stationary rear part, in helicopter mode, and a flap swivel-mounted on the top cowling of the front part joins this latter to the top cowling of the stationary rear part, onto which this flap is folded, in helicopter mode.

Abstract: A fitting for anchoring an aircraft seat to a track mounted to the floor of the aircraft is provided. The fitting is removably mounted to the seat and includes a generally rectangular elongate base having flange-like extensions running longitudinally thereof. The base has symmetric slide bearings affixed thereto, one at each end thereof, and overlaying the base, dimensioned so that the base with attached bearings is slidably insertable into the slot of the track. When the seat is mounted to the track, the symmetric bearings are in contact with the upper inside surfaces of the slot within the track, providing relative ease of slidable movement thereof when required.

Abstract: A vibration-preventing tail wheel assembly prevents an aircraft tail wheel from shimmying during the takeoffs and landings. The unit retrofits and mounts between the aircraft tail spring and the original equipment tail wheel fork. A rigid hub assembly comprising a sleeve-like, central hub is rotatably coupled to the spindle assembly. The spindle assembly has a mounting flange connected to the aircraft tail wheel fork. A rigid arm projecting from the hub is bolted to the tail spring. The spindle assembly comprises a rigid sleeve coaxially extending from a mounting flange through and within the hub assembly. A pair of bearing assemblies fitted within suitable recesses on opposite ends of the central hub contact a special bushing.

Abstract: A mechanical dereefer comprises a frame having a housing end with a joining wall and spaced plates extending from the joining wall to define a L shaped bifurcated end. A latch is mounted between the plates for pivotal movement between a capture position, wherein a reefing line end is held, and a release position, wherein the reefing line end is released. The latch is maintained in the capture position by engagement with a latch lock slidable through an aperture in the joining wall to a projected position. The latch lock is maintained against a bias in the projected position by the engagement of an elbow link and a trigger link each pivotally mounted within the frame housing end. The trigger link may be actuated out of engagement with the elbow link either manually or by a trigger device.

Abstract: An apparatus for rigidly interlocking a control stick and the rudder pedals of an aircraft is provided for protecting the control surfaces of the aircraft operated by the control stick and the rudder pedals against wind loads. The apparatus comprises a control stick clamp assembly rigidly connected to one end of a first lever arm and a rudder pedal retaining assembly rigidly connected to another end of the first lever arm. A second lever arm has one end connected to the rudder pedal retaining assembly. The second lever arm is moveable between a collapsed position and an extended position wherein the distal end of the second lever arm is engageable with a support surface such that the second lever arm is able to support the rudder pedal retaining assembly in engagement with each of the rudder pedals and thereby cause, upon the control stick clamp assembly being secured to the control stick, the first lever arm to support the control stick in a selected position.

Abstract: An active flaperon assembly for a wing includes a sheet of flexible material deployed near an intersection between a primary lift surface of a wing and the surface of a flap. The sheet is mechanically linked to the flap such that it is withdrawn from and extended into the air flow over the wing, the extent of projection varying as a function of the downward deflection of the flap. An actuator generates mechanical oscillations in the sheet.

Abstract: A blast shell is launched as a defense against an attacking tail fin-stabilized projectile, such as in particular a KE penetrator, from an object which is to be protected. Gas fumes and a reaction pressure blast wave from a fired blast warhead of the shell act principally on the tail region of the attacking projectile and thereby deflect the latter from a trajectory in the attack direction so that the object under attack is either missed or at least is not hit in a head-on direction, thereby reducing the effectiveness of the attacking projectile.

Abstract: A modular rack unit for use in a vehicle such as a coach consisting of an outer shell (2) and an inner shell (9). The inner shell (9) acts as a shelf for luggage and defines with the outer shell (2) an air conduit (5). The rack unit is secured to the vehicle by means of pillars (14) and two longitudinally extending brackets (18, 19). Each bracket defines with the engaging edges of the outer and inner shells respectively labyrinthine passages for the escape of any air from the air conduit (5).

Abstract: A basket for supporting equipment between a pair of laterally spaced-apart parallel overhead cables. The basket is provided in the form of a top open container insertable between the overhead cables. A carrying member engageable with a helicopter arm is provided for allowing the basket to be selectively transported between and away from the overhead cables. A pair of wing-like members extend laterally outwardly from opposed side walls of the container for resting on the overhead cables once the basket has been lowered to a suspended position between the overhead cables.

Abstract: A release fitting for releasably holding at least one line to at least one item, the release fitting having a first body part, a second body part, and a third body part, the first and second body parts pivotably secured to the third body part, a bolt with a first bolt portion connected to a first portion of the first body part and a second bolt portion connected to a first portion of the second body part, at least one pin suitable for attaching thereto the at least one line, the first body part having a recess for releasably receiving an end of the pin, the bolt initially holding apart the first portion of the first body part and the first portion of the second body part to thereby maintain a second pin end in the recess, the third body part connected to the at least one item, bolt cutter apparatus for selectively cutting the bolt to release the at least one line from the pin.

Abstract: Referring to FIG. 2, disclosed is an aircraft compound no-back/offset gearbox (2) with an integral load proportional safety (no-back) brake (50). The four gears are all 16 diametral pitch, involute external spur gears with 20 degree standard pressure angles. The two gear stages are interconnected with a mechanical fuse or shearout (40) designed to fail under excess shear loads and protect components downstream of the input shaft (10) from excess torque in the event of a system jam. The shearout (40) is essentially a quill shaft with external splines at both ends and an hourglass-shaped shear neckdown in the middle. The purpose of the no-back brake (50) is to prevent air loads from causing slat movement in the event of a torque tube disconnect. Referring to Figure, the no-back consists of a set of ball ramp (22) and brake plate components connected to the gearbox's output shaft.

Abstract: The wing movement has a gearbox, a reference gear extending through the gearbox and being movably mounted to the gearbox, an input shaft extending through the reference gear and into the gearbox and first and second output shafts movably extending from the gearbox at right angles with the input shaft. There is also provided a motor having a drive shaft connected to the input shaft of the gearbox for rotation of the input shaft. A bracket is connected to the motor base and to the reference gear for retaining the reference gear to the motor base, with an axis of the reference gear in alignment with the drive shaft of the motor. A gearing system is mounted inside the gearbox for rotating the first and second output shafts one full turn in opposite directions relative to each other, upon a rotation of the input shaft one full turn, and for rotating the gearbox one full turn about the reference gear upon a rotation of the first and second output shafts one full turn.

Abstract: An aircraft engine has opposite front and rear ends, extends in a longitudinal direction between the front and rear ends, and defines a longitudinal axis that extends between the front and rear ends. The aircraft engine includes a reference portion, and right and left cowls that extend arcuately at least partially around the longitudinal axis of the aircraft engine. The cowls are operative for covering at least a portion of the reference portion. Each cowl is movably mounted in relation to the reference portion so that the cowls move both radially away from the longitudinal axis and in the longitudinal direction as the cowls are moved from a closed configuration to an open configuration. Further, the cowls move both in the longitudinal direction and radially toward the longitudinal axis as the cowls are moved from the open configuration to the closed configuration.

Abstract: A pistol comprises a butt containing a trigger mechanism and a barrel slide which can be displaced in the longitudinal direction, the trigger being guided in the upper part of the butt. In order to permit rapid, simple and reliable locking and unlocking, a locking pin is guided so that it can be displaced and rotated in a lateral transverse hole in the butt. The locking pin protrudes into the path of the trigger in the locked condition. A compression spring acts on the locking pin in the unlocked position and the locking pin has a head which interacts in bayonet fashion with an enlarged portion of the hole so that two different angular positions of the locking pin correspond to the locked and unlocked positions are selected.

Abstract: A video camera mounting system for a firearm, such as a rifle or a shotgun, to simultaneously video a target at the time of the “kill”. The system includes a video mounting assembly that incorporates a shock absorbing mechanism to protect the video camera against the recoil of the firearm, and a pivotally mounted platform to finely adjust the video camera toward the target.