Abstract: A reinforced elastomer attachment joint includes an elastomer section (304) butt bonded to a FIBERGLAS section (332), a boundary line (340) being defined therebetween. One or more fabric plies (338) are embedded within the elastomer (304) and FIBERGLAS (332) sections so as to be capable of transmitting loads from the elastomer section (304) to the FIBERGLAS section (332). The rigid FIBERGLAS section (332) is capable of being drilled and countersunk so as to accomodate fastening means (306) whereby the attachment joint can be secured to basic support structure (302).

Abstract: A yaw control arrangement for tailless aircraft utilizing a plurality of rudder-like surfaces which are normally retracted into the surface of an aircraft wing and extended only momentarily on demand to generate a yawing moment. The surfaces are mounted on a wing surface by hinges which are canted with respect to the free stream flow. In this manner, the extended deployed surfaces are given an angle of attack to the free stream flow to produce a lift force at essentially right angles to the longitudinal axis of the aircraft.

Abstract: An aircraft vertical fin-fuselage structural integration system wherein a plurality of vertical tail fin spars, extending transversely across the fin and fuselage and substantially parallel to the longitudinal axis of the fin, are integrally connected directly to the fuselage pressure bulkhead so as to directly transmit or transfer the vertical fin and horizontal stabilizer empennage loads to the fuselage structural network. The system can be adapted to any type of aircraft, and in the case of an aircraft of the BOEING 727 class, the spars accommodate the air intake S-duct operatively associated with the craft's rear engine housed within the rearwardmost portion of the fuselage. The spars also have their lateral configurations fabricated so as to match the fuselage loft lines.

Abstract: A seat structure includes a flexible canvas seat bottom portion (14) and a flexible canvas seat back portion (12). A horizontally disposed, transversely extending beam member (58) is rotatably disposed above the seat bottom portion (14) and is operatively connected to the lower end of the seat back portion (12). The beam member (58) is movable between two positions 90.degree. apart such that when the beam member (58) is disposed in its first position, the beam member (58) effectively defines a support shelf or platform projecting forwardly of the seat back portion (12) and is therefore capable of supporting parachute packs borne by parachuting personnel seated within the seat structure. The seat back portion (12) is also disposed in a slackened state at such time so as to accommodate the depth of the parachute packs.

Abstract: An integrated power plant installation system for underwing high-bypass mid-length fan air duct core-mounted engines readily permits disconnection of the entire powerplant at the wing thereby virtually eliminating the necessity of disconnecting the engine and complex systems per se from the support strut when engine replacement or removal proves necessary. Excessive congestion within the vicinity of the strut box structure is eliminated by disposing the engine accessories, and auxiliary equipment and system lines, within the lower quadrant of the powerplant assembly in both a laterally and longitudinally distributed array. Potential catastrophic fire hazards within the nacelle are substantially eliminated by routing the fluid lines and electrical conduits axially aft and upwardly around the circumference of the engine within the nozzle section of the powerplant aft of all rotating discs.

Abstract: An adjustable litter support assembly includes fittings on each stanchion to engage conventional hold-down fixtures on the floor of an aircraft. The stanchions are further supported by interconnectable connecting links carried near the top of each stanchion. Connecting straps also extend from near the top of each stanchion to a floor fitting near the bottom of the other stanchion of each pair. Litter support arms are adjustably connected to each stanchion and carry locking straps for detachably holding a litter thereon.

Abstract: A cargo restraint and delivery system for an aircraft having a cargo-receiving and delivery opening for cargo secured to pallets. The cargo is moved backwardly and out of the rear cargo-delivery opening under either the pull of the parachute when the aircraft is airborne or by the force developed by the rapid acceleration of the aircraft for combat off-loading of cargo onto the ground. One of two spaced-apart guide rails for the pallets supports locks to releasably hold the pallets. A logistics control includes a lever at a loadmaster station to move a logistics control cable extending along the rail supporting the locks to move them into a first position where the pallet locks will release the pallets for movement either forward or aft of the aircraft and a second position where the pallet locks will prevent either forward or aft movement of a pallet.

Abstract: A winch cable driven retrieval apparatus for retracting static lines slidably mounted on a fixed anchor cable or the like, wherein a retrieval spool is slidably mounted on the anchor cable and is attached to a winch cable through a pair of attachment members extending from opposite sides of the spool. The points of attachment are carefully chosen such that an imaginary line extending therebetween intersects the anchor cable and preferably the centerline of the anchor cable.

Abstract: Compressed air is directed through an inert gas generator which removes oxygen to produce a nitrogen enriched, combustibly inert air or gas. The converter is sized to only meet the relatively low flow rate requirements of the system during which times the combustibly inert air or gas is delivered directly to a utilization site. The system further includes a high pressure storage container in which a pressurized precharge of the combustibly inert air or gas is stored. Combustibly inert air is released from such high pressure storage container for providing the higher flow rate requirements of the system. The system may be used aboard an aircraft for inerting fuel tanks. It may include a separate compressor for filling the high pressure storage container.

Abstract: An aerial cargo delivery system for aircraft having a rear cargo receiving and delivery opening. Cargo bundles, guided between parallel guide rails on the aircraft floor, are restrained by fore and aft restraint straps during normal flight conditions. The aft restraint straps are provided with electrically-actuated release latches which effectively sever the aft straps to permit cargo bundles to pass out of the rear opening when the aircraft is in a nose-up attitude.

Abstract: An inlet duct of generally rectangular configuration for supersonic aircraft in which a normal shock is produced in close proximity to the forward lip of the lower duct wall, and in which variable area sideplate openings are provided just upstream of the normal shock to achieve boundary layer control for the normal shock-boundary layer interaction during on-design operation and increasing flow area for spillage as the normal shock is moved forward during off-design operation.

Abstract: The system includes two parallel rails, multiple airdrop/logistics locks mounted by one rail, and multiple forward restraint mechanisms mounted by the other rail opposite alternate airdrop/logistics locks. Two drawbars are connected to and provide remote operation of the airdrop/logistics locks and the forward restraint mechanisms, respectively. The airdrop/logistics locks additionally are operable locally. Each airdrop/logistics lock includes a movable detent and a force responsive release assembly which releases the detent from an extended locking position upon attainment of a predetermined threshold force in the aft direction. The release assembly includes a fuse and a contractible cartridge assembly connected to the detent such that movement of the detent toward a release position will cause the cartridge to contact.

Abstract: The system includes an inertial body on which is mounted a mirror, which together are mounted for rotation by a gimbal bearing element. The gimbal bearing element is part of a base system which further includes a light beam source, such as a laser. The mirror is positioned on the inertial body so that it is at an angle of 45.degree. relative to the axis of the gimbal bearing element. The inertial body, which can be represented by a dumbbell-shaped equivalent mass, is oriented so that the path of the light beam from the light source is coincident with the gimbal axis, i.e. such that the light beam strikes the mirror. A yaw-like disturbance, i.e. a rotational vibration about the Z coordinate axis, affecting the base system, and hence the light beam source and gimbal bearing element as well, is converted into a rotational movement of the inertial body and the mirror about the axis of percussion, which, in the embodiment shown, causes a rotation of the reflected beam about the Y coordinate axis.

Abstract: A servovalve of the type wherein changes in two primary control pressures, as determined by a primary stage valve, positions a secondary output control valve. The primary stage valve is in the form of two nozzles which direct fluid jets against opposite sides of a rotatable cylinder such that the back pressures from the two jets, which control the position of the secondary output control valve, can be varied as the cylinder rotates. The cylinder is driven by a stepper motor which, in turn, can be controlled by the output of digital computer apparatus.

Abstract: A lightweight cargo container and the fittings for the construction of same are disclosed. One fitting is an extrudable side rail member which connects the container side walls to the bottom wall or floor. Another fitting is a two-part, lightweight, protective corner block which provides attachment points for handling and permits simple replacement of the exposed portion thereof, in the event of damage.

Abstract: A jet engine having its turbine section and exhaust nozzles particularly arranged to alleviate noise. There is a forward turbine section positioned in a first passageway to receive all or substantially all of the gaseous discharge from the combustion section of the jet engine. There are second and third coannular passageways positioned downstream of the first passageway, with the second passageway being positioned radially inwardly of the third passageway. A second turbine stage is positioned in the second inner passageway to receive a portion of the gaseous flow from the first passageway so as to be driven thereby, with the first portion of gaseous flow being discharged at a relatively low velocity at a radially inward location. A second portion of the gaseous flow passes from the first passageway to the third passageway and is discharged at a relatively high velocity in a generally annular pattern radially outward of the flow of the first portion of the gaseous flow.

Abstract: A tow plate including a retention assembly and a removable clevis assembly made up of a main clevis member and a drogue clevis member engageable with the main clevis member. A first latch mechanism latches the main clevis member to the retention assembly. A second latch mechanism latches the drogue clevis member to the main clevis member. To effect force transfer, the entire clevis assembly is released by unlatching the main clevis member from the retention assembly, with the drogue clevis member latched to the main clevis member. To effect drogue jettison, the drogue clevis member alone is released by unlatching it from the main clevis member, while the main clevis member remains latched to the retention assembly.

Abstract: Method and apparatus for reducing jet noise in a turbofan engine by causing internal mixing of fan and primary air to reduce the maximum velocity of gases at the nozzle exit plane by creating a particular type of vortex flow at a distance of at least one nozzle diameter forward of the nozzle exit plane. In one preferred embodiment for a JT8D engine an array of eight roll-top vortex generators are provided on each side of the splitter wall between fan and primary flows, and a tail cone is disposed in the primary exhaust downstream of the vortex generators.