Abstract: A structural interlock (40) for inhibiting relative rotation between mating elements (20, 42) characterized by a plurality of grooves (50) being formed in one of the mating elements, and a mechanism (60) for producing a nominal contact pressure on the contact area (A.sub.1 thru A.sub.8) between the mating element, which contact pressure elastically deforms the other of the mating elements into the grooves (50), and is less than the material yield strength of either of the mating elements. In the preferred embodiment, the grooves (50) are radially oriented and an applied compressive load produces a nominal contact pressure which is about 80% of the material yield strength.

Abstract: A turning vane arrangement (30) for an IR suppressor having a duct (32) adapted for receiving a primary flow PF of engine exhaust. The turning vane arrangement (30) is operative to direct a pressurized secondary flow PSF of low temperature gaseous fluid into the primary flow of engine exhaust for reducing the IR energy thereof. The turning vane arrangement (30) includes at least one turning vane (50) situated in the duct (32) and is characterized by a trailing edge (50.sub.TE) that defines an exhaust nozzle (52). The exhaust nozzle (52) is adapted for being disposed in fluid communication with a flow source (54) which produces the pressurized secondary flow PSF. The exhaust nozzle may include a plurality of adjoined lobes (60.sub.R, 60.sub.A or 60.sub.P) for rapidly and thoroughly admixing the primary and pressured secondary flows PF, PSF.

Abstract: A multi-stage mixer/ejector (20) having at least one exhaust nozzle (24 or 28) which includes inlet conduit adapted for receiving a primary flow PF of engine exhaust and a plurality of adjoined lobes (30) integrally formed in combination with the inlet conduit. The adjoined lobes (30) of the exhaust nozzle (24 or 28) are characterized by a first and second plurality of penetrating lobes (60, 62 or 70, 72) which are axially staggered with respect to each other and which are adapted for admixing low-temperature gaseous fluid with the high-temperature exhaust. In the preferred embodiment, at least one of the plurality of penetrating lobes (60 or 62, 70 or 72) extends into a core region (CR) of the exhaust nozzle (24 or 28) to effect thorough mixing of the low temperature gaseous fluid with the engine exhaust.

Abstract: A method for manufacturing a fiber optic terminus (10) having an optical fiber (12) disposed within and supported by a ferrule assembly (22). The method includes the steps of: stripping a fiber optic cable (8) to expose the optical fiber (12), bonding the stripped-end of the fiber optic cable (8) to a ferrule assembly (22), cleaving the optical fiber (12) in close proximity to a face surface (28) of the ferrule assembly (22), polishing the cleaved-end of the optical fiber (12) to achieve a terminus end profile, and inspecting the polished-end of the optical fiber (12) to determine whether the terminus end profile conforms to predefined acceptance criteria.

Abstract: An exhaust nozzle (24 or 28) operative to suppress the InfraRed (IR) signature radiated from the high-temperature exhaust of an engine (12) which exhaust nozzle (24 or 28) includes an inlet conduit adapted for receiving the high-temperature engine exhaust and a plurality of adjoined lobes (30) integrally formed in combination with the inlet conduit. The adjoined lobes (30) are characterized by a first and second plurality of penetrating lobes (60, 62 or 70, 72) which are adapted for admixing low-temperature gaseous fluid with the high-temperature exhaust and which are axially staggered with respect to each other. In the preferred embodiment, at least one of said plurality of penetrating lobes (60 or 62, 70 or 72) extends into a core region (CR) of the exhaust nozzle (24 or 28) to effect thorough mixing of the engine exhaust with the low temperature gaseous fluid. Various embodiments of such exhaust nozzle (24 or 28) are described in the context of a multi-stage mixer/ejector (20).

Abstract: A monolithic structural member (10) operative for reacting steady and vibratory bending moment loads M about an applied loads axis X and having a specially configured cross-sectional configuration for providing improved flaw tolerance. The cross-sectional configuration (10) includes a central connecting element (18) and at least one pair of structural ribs (14a, 14b) being integrally formed with the central connecting element (18) and projecting outwardly thereof. The structural ribs (14a, 14b) are, furthermore disposed in the tensile field produced by the steady portion of the bending moment loads M and are proximal to the centroid C.sub.T of the cross-section (10). The cross-sectional configuration (10) defined by the structural ribs and connecting element produces a partial inertia ratio I.sub.X /I.sub.Y greater than or equal to 1.0, which partial inertia ratio I.sub.X /I.sub.Y has the advantageous effect of retarding or arresting crack propagation in the structural member (10).

Abstract: A vibration isolator (20) operative for reducing vibration active on a main rotor (12) of a rotorcraft. The vibration isolator (20) includes a hub attachment fitting (22) secured in combination with the main rotor (12) and a spring-mass system (24) mounting to and rotating with the hub attachment fitting (22). The vibration isolator (20) is characterized by the spring-mass system (24) having a fairing (44) operative to aerodynamically contour the spring-mass system (24) while providing a portion of the working mass thereof. Other features of the vibration isolator include adapting the hub attachment fitting (22) to accept hub-mounted rotor systems (36), provide access to the rotor hub mounting attachment (34), and provide a motion limiting portion (74) for reducing loads acting on the spring-mass system (24).

Abstract: A method for manufacture of a fiber reinforced composite spar for a helicopter rotor blade including upper and lower sidewall regions and forward and aft conic regions. Constant width crossplies and unidirectional plies are stacked and arranged to form crossply and unidirectional laminates. The composite spar is manufactured via a vacuum forming technique which includes forming the composite laminates directly over an inflatable mandrel assembly. Regarding the latter method, a spar forming apparatus is used to position and manipulate the mandrel assembly as composite laminates are laid. The spar forming apparatus includes first and second pedestal supports being suitably configured so as to facilitate formation of the butt joints in the conic regions of the composite spar.

Abstract: A landing gear/tail skid having at least two pivot axes (22, 24) which are subject to relative motion in response to impact loads acting on the landing gear/tail skid (10) and a contact arm (18) disposed in combination with pivot axes (22, 24). The cartridge assembly (20) includes a housing member (30) having and internal chamber (38) and a telescoping piston assembly (40) mounting within the internal chamber (38) wherein the end portions of each are disposed in combination with one of the pivot axes (22, 24). The housing member (30) and piston assembly (40), in combination, define opposed bearing surfaces (36s, 46s) which act on an energy absorbing means (50) disposed within the internal chamber (38) and intermediate the opposed bearing surfaces (36s, 46s). The energy absorbing means (50) is operative, in response to impact loads coupled thereto by the opposed bearing surfaces (36s, 46s), to react impact loads below a threshold is value without change in its critical dimension (L.sub.

Abstract: A fuel intake device (20) for a fuel system (10) having a fuel tank (14) for containing a supply of fuel (16) and an internal fuel feed line (18) which is disposed internally of the fuel tank (14). The fuel intake device (20) is operative to provide uninterrupted fuel flow in icing conditions and is characterized by a flexible fuel filter (40) having a plurality of primary flow apertures (42) apertures therein for facilitating a primary flow P.sub.F of fuel therethrough, a bypass means (50) for providing a secondary flow S.sub.F of fuel to the internal fuel feed line (18) when an accumulation of ice (80) restricts the primary flow P.sub.F of fuel through the primary flow apertures (42), and force bias means (60) for rapidly reconfiguring the flexible fuel filter (40) for forcibly shedding the accumulation of ice (80), thereby restoring the primary flow P.sub.F of fuel.

Abstract: An inertial mass (50) for a vibration isolator (20) having an attachment fitting (22) adapted for rotation about an axis (16) and a spring (40) adapted for rotation with the attachment fitting (22). The inertial mass (50) is characterized by a pair of segments (52) each having a generally Z-shaped cross-sectional configuration. More specifically, each segment (52) defines a central web (54), a first leg (56) projecting radially inboard of the central web (54) and a second leg (58) projected radially outboard of the central web (54). The first and second legs (56, 58) are integral with the central web (54) and the second legs (58) are adjoined along a mating interface (I) to define the assembled inertial mass (50). As assembled, the inertial mass (50) is adapted for being mounted in combination with the spring (40) of the vibration isolator (20).

Abstract: A method for making a honeycomb core composite article includes forming a honeycomb core (24) and a precured composite skin (20) having a core edge (32) and a restraint edge (30), respectively. The precured composite skin (20) is placed in combination with a rigid mold member having a mold surface (12s) and the honeycomb core (24) is mated with the precured composite skin (20) to form a mated subassembly (36). An uncured composite skin (22) is laid over the mated subassembly (36) such that a peripheral portion (44) of the uncured composite skin (22) extends beyond the restraint edge (30) by a distance X and such that the peripheral portion (44) is in superposed abutting engagement with the mold surface (12s). The honeycomb core (24), the precured composite skin (20) and the uncured composite skin (22) define a composite lay-up (10) over which a vacuum bag (14) is disposed.

Abstract: An emergency egress system (10) for facilitating emergency egress of passengers/crewmembers from an aircraft (4), which egress system (10) includes an egress panel (12), a panel frame (14) disposed about the egress panel (12) and a weather strip (16) defining back-to-back channels (18) for accepting the peripheral edges (12.sub.E, 14.sub.E) of the egress panel (12) and the panel frame (14). Furthermore, the emergency egress system (10) includes a plurality of retention devices (30) disposed about the periphery of the egress panel (12) for laterally retaining the egress panel (12) with respect to the panel frame (14) in a normal operating mode, a cam (80) operative to forcibly urge a portion of the weather strip (16) out of engagement with one of the peripheral edges (12.sub.E, 14.sub.E) and an actuation device (50) operative to sequentially disengage at least one of the retention devices (30) and actuate the cam (80) in an emergency operating mode.

Abstract: A coil spring (10) for an overrunning spring clutch assembly wherein the coil spring (10) includes a crossover coil (20) having a longitudinal crossover gap (24) formed therein, and a dynamic balance weight (40) secured in combination with one of the internally opposed surfaces (24s) of the longitudinal crossover gap (24). The dynamic balance weight (40) is configured such that, when assembled in combination with a central arbor (32) and coaxial clutch members (34) of the overrunning spring clutch assembly, the dynamic balance weight (40) is spaced apart from the central arbor (32) and each of the clutch members (34). Furthermore, the dynamic balance weight (40) is fabricated from a material having a density .rho..sub.BW which is greater than the density .rho..sub.CC of the base material from which the crossover coil (20) is fabricated.

Abstract: An isolated ring gear (60) for a planetary gear drive system (12), which isolated ring gear (60) is operative transferring torque loads and reducing the transmission of high frequency vibrations from the planetary pinions (36) of the drive system (12) to an adjacent support (50). The isolated ring gear (60) includes and inner ring segment (62), an outer ring segment (64) and a plurality of spring elements (66) disposed between and integrally formed with the inner and outer ring segments (62, 64). The inner ring segment (62) has a plurality of gear teeth (62.sub.T) for being disposed in intermeshing combination with the teeth (3b.sub.T) of the planetary pinions (36) and the outer ring segment (64) is rigidly affixed to the adjacent support structure (50).

Abstract: A method for manufacturing precision gears (10) including an initial step of providing a shaped workpiece (30.sub.S) defining a plurality of gear teeth (12) and, furthermore, defining a tooth space surface (68) defined by and between adjacent gear teeth (12). Next, a masking tool (60) is assembled in combination with the shaped workpiece (30.sub.S), which masking tool (60) includes a flexible back-plate (64) and plurality of compliant masking segments (62) bonded to and integrated by the flexible back-plate. Each of the compliant masking segments (62) defines a surface geometry (66) which is substantially complementary to the tooth space surface (68), and adjacent compliant masking segments (62) define an open-ended channel (70) therebetween. As assembled, the compliant masking segments (62) are forcibly urged into superposed engagement with the tooth space surfaces (68). In a subsequent step, a layer of masking material (28) is deposited on exposed surfaces of the shaped workpiece (30.sub.

Abstract: A mounting arrangement (60) for coupling a control rod (38) to a stationary swashplate member (32) of a helicopter swashplate assembly (30) wherein the mounting arrangement (60) is characterized by a specially configured stationary swashplate member (32) and a trunnion fitting (62) for mounting in combination therewith. More specifically, the stationary swashplate member (32) includes a horizontal web (74) disposed between an inner ring segment (72.sub.IR) and an outer ring segment (72.sub.OR), wherein the horizontal web (74) includes an aperture (78) and defines a mounting surface (74.sub.S). The trunnion fitting (62) includes a base (64) defining a mounting surface (64.sub.S) and a pair of mounting ears (66) having aligned apertures (66.sub.O). The mounting surface (64.sub.S) of the trunnion fitting (62) engages the mounting surface (74.sub.S) of the horizontal web (74) such that the mounting ears (66) are disposed through the aperture (78) of the horizontal web (74).

Abstract: A retention subassembly for FI threaded fastener assemblies, which retention subassembly is operative to limit the torque, and consequently, the loads acting on the FI threaded fastener assembly and/or on the components coupled thereby. The retention subassembly includes a cage assembly and a Floating Threaded (FT) insert disposed within an internal chamber of the cage assembly. Furthermore, the FT insert includes a threaded bore for accepting a threaded fastener of the FI threaded fastener assembly. The retention subassembly further comprises a first torque reacting means for reacting torque when the threaded fastener is caused to engage the threaded bore, a means for disengaging the first torque reacting means in response to a threshold magnitude of torque, and a second torque reacting means for reacting torque when the threaded fastener is caused to disengage the threaded bore.