Abstract: The invention comprises an all gear mechanism for a continuously variable transmission that provides a wide range of output speeds and torques. The Basic element of the transmission is a floating gear assembly which relates output speed to input speed. The floating gear assembly can either comprise a floating gearbox or a floating gear arrangement incorporated into a differential assembly with idler gears. Various controlling mechanisms are shown and described which include first and second mechanical feedback loops. With these speed control systems, the output gear ratio can be made to change either linearly to geometrically to produce a desired output speed and torque.

Abstract: The invention comprises a borescope plug for sealing a borescope inspection port on a turbine engine having a fluid flowpath and multiple casings. The borescope plug comprises a plug body having an interlocking drive interface, a plunger portion positioned for sliding coaxial movement relative to the plug body and spring means engaging both the plug body and the plunger. The spring means presses the plunger towards a fully extended position relative to the plug body. The plunger comprises a fixedly attached tip portion shaped to conform with the fluid flowpath. Key means is provided for aligning the tip to conform with the fluid flowpath and the tip is cooled with a cooling airflow.

Abstract: An apparatus for stopping a rotating antenna shaft at a distinct position intermediate two end stop positions 23, 24. Paddle 12 on the rotating shaft 21 cooperates with intermediate stop assembly 26 to arrest bi-directional shaft rotation at an intermediate point when such stopping is desired, the intermediate stop assembly being activated by springs 38, 39 and deactivated by action of solenoids 30, 31.

Abstract: The invention comprises an interferometric load sensor, or force balance 10 which utilizes etalons 12, 14 to form a reflective cavity 16. A fringe pattern is formed in cavity 16 by light from laser source 26. One of the etalons (14) is mounted to a section 20 that is sensitive to the application of a force 22. Flexing of cantilever 24 due to application of force 22 on section 20 changes the air gap wedge angle between the etalons 12, 14 and thereby shifts the fringe field formed in cavity 16. The shift in the fringe field is observed by light detectors 30, 32.

Abstract: The invention comprises a boltless turbine nozzle and nozzle support assembly that includes a turbine nozzle mounting flange seated in a nozzle seat forming a part of the nozzle support. Pins are used for affixing the nozzle mounting flange to the nozzle support seat and baffles are provided for maintaining the pins in their desired locations. A retaining ring is preferrably used to retain the baffles adjacent to the pins. A pressure actuated pliable seal is affixed to the turbine nozzle adjacent to the nozzle seat in order to provide an air seal across the completed assembly.

Abstract: A bimetallic leaf seal 40 for forming an air seal between adjacent structures (38, 42). The bimetallic seal 40 comprises two metallic layers 46, 48 having different coefficients of thermal expansion. The seal moves in a preferred direction upon the application of heat to form an air seal upon the application of heat.

Abstract: The invention comprises a combination boundary layer control system that utilizes both suction and cryogenic wall cooling to reduce aircraft drag. The invention is particulary useful in circumstances where liquid hydrogen or other cryogenic fuels are used to operate the aircraft.In the preferred embodiment of the invention, a network of D-tube ducts are provided that are fluidly connected to a cryogenic fluid source. These cryogenic fluid ducts are selectively fed cryogenic fluid to reduce aircraft surrface temperature and promote adhesion of boundary layer air to the aircraft. An air duct system is also provided to apply suction to the aircraft surface in order to remove the boundary layer at low altitude. The suction is applied by means of a multitude of minute holes in the aircraft skin which are fluidly connected to the air duct system.

Abstract: A variable guide vane 12 bushing assembly 10 which features means that prevents bushing rotation. A bushing 16 comprises flats 16b on its outer sleeve, the flats interlock with race track shaped holes 20a on a tab-lock washer 20. The tab-lock washer spans two or more adjacent vane stems (12,14) and thus is not susceptible to rotation. A retainer 24 and the vane arm 26 assemble on top of the tab-lock washer to complete the assembly.

Abstract: The invention comprises a semiconductor laser 10 having an attached etalon 18 which imposes two additional reflective cavity resonance conditions on a laser diode 12. The etalon has partially reflective front surface 26 and an inner surface 24 which act in conjunction with the internal cavity of the laser diode 12 to reduce side mode emission from the laser. This results in laser emission of a single dominant mode, i.e., a single discrete wavelength of coherent light, from surface 22.

Abstract: The invention comprises a mounting assembly for supporting the turbine outer casing duct adjacent to the turbine frame. Multiple support posts are mounted to the turbine frame and a roller means is rotatably attached to each support post. The roller means are aligned to rotate on a contact surface of the outer casing duct. Movement of the rollers on the contact surface is caused by the relative movement of the turbine frame and outer casing duct.

Abstract: All silicon electrooptic devices for modulating and switching of guided light have been developed using the silicon-on-insulator approach. Generally, p-n junctions are formed in a silicon waveguide to selectively modulate and direct light by carrier refraction. An electrooptic phase modulator and several 2.times.2 electrooptic switches are described. The devices are particularly useful for manipulating light signals in the 1.3-1.6 micron range.

Abstract: A flap system for deploying high lift flaps on short takeoff and landing aircraft. The flap system utilizes an activating mechanism 27 that is used to extend a flap 12, a vane 22 and a spoiler 18 for maximum lift. The mechanism 27 utilizes relatively few linkage pieces and attached to the flap at single pivot points 44. The flap is supported by an actuator 46 and flap hinge support bracket 30. Increased mechanism rigidity and single pivot mountings allow use of roller 75 and track 74 guides at flap ends 78, 80 to smoothly guide flap movement and provide a fail-safe in case of pivot mounting failure. Spherical bearings 86 are utilized for mounting of rollers 75 and actuators 46, 60 in order to compensate for misalignment of the flap 12 and the flap mechanism 27 when used with tapered flaps on swept wing aircraft. The spoiler 22 is joined by a guide link 62 that adjusts spoiler position with flap 12 movement in order to maximize lift. The spoiler can also be used conventionally by activation of actuator 60.

Abstract: A method and apparatus for die forming metal sheets and extrusions 20 which utilizes recycleable die blocks 16. The die blocks are cast in an adjustable mold box 12. A pivotable dam member 14 is used to set angles on a surface 16a of the cast die blocks. Adjusting the pivotable dam 14 permits the casting of a variety of die blocks for introducing a variety of angled joggles in the metal sheets and extrusions. Relatively low melting temperature material is used for the castings.

Abstract: A real time autocollimator 10 for measuring parallelism of two surfaces 12, 14. The autocollimator uses a laser 16 to provide light to first and second beam splitters 20, 22. Second beam splitter 22 directs dissimilarly polarized light to each surface 12, 14. This light is reflected to, then recombined by the second beam splitter prior to being redivided by a third beam splitter for comparison at quadrant detectors 30, 32.

Abstract: A portable microform reader 10 comprising a foldable frame 12. The frame includes a view screen 14 and a microform holder 18. A microform 38 is illuminated by a light package 80 and an image of a portion of the microform 38 is projected through pick up lens 48. A fiber optic cable 22 carries the image from the objective lens 48 to a focusing lens 52 which projects a magnified image onto the view screen 14. Pickup lens assembly 20 is moved manually to view different areas of the microform.

Abstract: An air seal assembly 10 for a gas turbine engine comprising a full ring cover plate 20 and seal segment 14 attached to impingement boxes 18. The impingement boxes have counter mounted hooks 24, 26 that interlock with a turbine flange 22 and cover plate 20 to secure the seal assembly 10. Holes 36 in the impingement boxes 18 direct cooling air to the entire backside 38 of seal 14. Seals 14 are mounted to the impingement boxes 18 by pedestals 40 that are positioned to enhance seal flexibility since axial edges are unrestrained.

Abstract: An electrically controlled integrated optical switch having a body made up entirely of crystalline silicon. More specifically, the body has a pair of channel waveguides intersecting in an X-like configuration forming therein an intersection crossover region. A first electrode is positioned on the intersection crossover region and a second electrode is positioned on the bottom of the body opposite the intersection crossover region. A controllable current/voltage source is electrically connected to the electrodes in order to alter the index of refraction of the intersection crossover region by carrier injection in order to selectively switch optical signals between diverging waveguides.

Abstract: A fiber optic device 50 designed to steer the radiation beam of a phased-array antenna 10 has been demonstrated. A radio frequency (RF) signal is generated via photomixing at the output of a single-mode fiber optic interferometer. The phase of the electrical signal is shifted over several cycles in direct proportion to a voltage applied to an optical modulator 34, 60. The modulator consists of a Pockels-type optical phase modulator located in one arm of the heterodyne interferometer. Rapid changes in RF phase are feasible. A miniature low-voltage version of the device 50, 72, based upon integrated optics, has been devised.

Abstract: A heat shield assembly 10 for attachment to an afterburner liner 18. The heat shield assembly 10 comprises a clamp 14 and an optional support bracket 16 which hold a carbon-carbon panel 12 adjacent to the liner 18. The carbon-carbon panel shields a damaged area 20 of the liner in order to extend the liner's service life.

Abstract: A method and apparatus 10 for rapid optical phasing of optical devices utilizing white light interference fringe finding. The apparatus comprises a white light source 12, a beam splitter 18, a scanning mirror 20 and a stationary reflective surface 24. The scanning mirror 20 is moved in piston while reflected light is observed in an electro-optic sensor 32 at a receiver 28. A nulled pattern has been previously established at the receiver 28. An electrical signal from the electro-optic sensor is mounted at amplification and recording means 34 to identify variations in reflected light intensity that are caused by white light fringes. White light fringes only occur at zero optical difference, i.e. when the scanning mirror and stationary reflected surface are in phase.