Abstract: In a first assembly step a coolant liner is formed having an outside surface. A plurality of coolant channels are formed on the outside surface. At least two inner conformal throat support sections and at least two outer conformal throat support sections are formed. The two inner conformal throat support sections are formed around the outside surface of the coolant liner to form a closed inner conformal throat outside surface. The inner conformal throat support sections are joined at inner throat seam lines. At least two outer conformal throat support sections are assembled around the closed inner conformal throat outside surface so as to cover the inner throat seam lines, to form a liner throat support assembly. An inlet manifold and an outlet manifold are assembled around the liner throat support assembly to form a hot isostatic press (HIP) assembly. A HIP'ed assembly is formed by HIP'ing the HIP assembly.

Abstract: A satellite location determination system for a constellation of satellites includes a plurality of optical transceivers. Each optical transceiver is associated with a respective satellite and includes an optical synthesizer, transmission conditioning optics, a telescope assembly, reception conditioning optics, and an optical to electronic signal converter. The optical synthesizer produces phase-coherent optical laser pulses. The transmission conditioning optics appropriately conditions the characteristics of the phase-coherent optical laser pulses. The telescope assembly receives an output of the transmission conditioning optics and transmits an optical transceiver output into space for reception by an optical transceiver associated with another of the satellites. The telescope assembly also receives an optical transceiver output from another of the satellites. Reception conditioning optics appropriately conditions the characteristics of the optical transceiver output received from another of the satellites.

Abstract: A hidrogen detection system (14) includes a hydrogen sensor(16) that detects contamination within a reaction member and generates a hydrogen contamination signal. A surface spectroscopic system (18) is operational in conjuction with the hydrogen sensor (16) and determines contamination of the hydrogen sensor (16) and generates a sensor contamination signal. A controller (20) is electrically coupled to the hydrogen sensor (16) and the surface spectroscopic system (18) and compares the hydrogen contamination signal to the sensor contamination signal and generates a corrected hydrogen contamination signal.

Abstract: An ignition isolating interrupt control circuit (52) includes a main transition circuit (90) isolating a first activation circuit (84) from an ignition circuit (114). The main transition circuit (90) includes a source terminal (93) that is electrically coupled to and receives a first source power from the first activation circuit (84). An input terminal (106) is electrically coupled to a second activation circuit (88) and receives an activation signal. An output terminal (138) is electrically coupled to the ignition circuit (114) and receives and supplies the first source power to the ignition circuit (114) in response to the activation signal. A power source monitor cutoff circuit (112) including a comparator is electrically coupled to the first activation circuit (84) and to the ignition circuit (114) and disables the ignition circuit (114) when a source voltage level is less than a predetermined voltage level.

Abstract: A solar receiver system (10) has a solar receiver (12) that receives sun rays (14) directed thereto. The receiver (12) has a heat pipe (26) having working fluid (38) therein. The first end (28) of heat pipe (26) and a second end (30) form a respective first condenser (32) and a second condenser (34). An evaporator portion (36) is disposed between the ends (28,30). The first end (28) has an air manifold (42) therearound. The second end has a liquid manifold (48) therearound. The heated air from the air manifold (42) is provided to a power generation device (22). The power generation device (22) receives heated air from the air manifold (42) which is expanded in a turbine (68) to extract mechanical work therefrom. The turbine (68) may be coupled to a generator (78) for generating electrical power in response to the mechanical energy.

Abstract: An apparatus and method for controlling contrast for a liquid crystal display (“LCD”), especially active-matrix LCDs, while receiving large dynamic range video data to be displayed to the user by the LCD. Contrast settings of the LCD correspond to a single look-up table from a set of different and multiple look-up tables rather than using the contrast setting of the LCD to select different voltage values from a single look-up table. The values of the reference voltages of the LCD are varied so that all shades of gray are available with each contrast selection resulting in a high image quality and a high contrast.

Abstract: A dual pivot expandable lavatory for use in limited spaces such as on an airplane. The lavatory may be positioned proximate the doorway area of the airplane, and is provided with a primary and a secondary pivotable module. Each module is pivotably attached to a stationary assembly conventionally affixed to the ceiling and floor of the airplane. During take-off and landing both modules are locked, by means of a locking system, in a stowed position within the stationary assembly. During routine flight, the locking system is unlocked and both modules are pivoted into a deployed position within the doorway area. A flight attendant's seat may be affixed to the exterior of the primary module. If the seat is used, an additional support foot is affixed to the primary module to accommodate the additional loading on the lavatory.

Abstract: An improvement in an airplane mounted aerial refueling boom wherein the boom assembly mounting permits motion about three axes. A first pivot attached to the fuselage of the airplane provides for radial or azimuth motion of the boom about a vertical or yaw axis of rotation essentially normal to the air stream. The second axis of motion, the pitch axis, is located below the airplane fuselage and perpendicular to the yaw axis so that the pitch axis rotates with any yaw motion of the boom and allows vertical displacement of the boom. Vertical and yaw displacement takes place in a conventional fashion. The third axis of motion, the roll axis, is located in-plane with and perpendicular to the pitch axis. This roll axis is coincident with the longitudinal centerline of the boom structural tube and a helical rotary actuator that produces a commanded roll motion as a function of pitch and yaw motion of the boom assembly.

Abstract: A lockable turnbuckle assembly having a locking mechanism that can be used in limited space applications. The present invention pertains to a turnbuckle that is adjustable and lockable using a single hand and does not require the use of tools.

Abstract: A method and apparatus for reducing noise produced by the airframe of an airplane in flight. The present invention provides a smooth, continuous, arcuate surface, such as a rounded edge cap, for the lateral surface of any airplane flap exposed to fluid having relative motion with respect to the airplane. Tests indicate that a rounded flap edge cap made in accordance with the present invention is effective in attenuating noise levels in the middle and high frequency range, i.e., between about 500 to about 10000 Hz.

Abstract: An adaptive wind tunnel wall system for minimizing aerodynamic wall interference for slotted or perforated wall test sections. In the present invention, a plurality of continuous or segmented flexible strips may be deflected by a number of actuators to control fluid flow from the test section to a plenum or plena surrounding the test section. The actuators move the continuous or segmented strips toward and away from the slotted or perforated test section walls along the length of the test section to easily change wall crossflow resistance.

Abstract: A cargo handling system rollout stop assembly, which allows a movable object to freely pass over it in a first or inboard direction but obstructs passage of that object in the opposite or outboard direction. The stop assembly comprises a frame and at least one arm assembly rotatably mounted in the frame. The arm assembly normally extends in an upright position in the path of the movement of the object and is capable of slight translation in the first direction. The arm assembly has a straight or linear camming surface all of whose centerline points are equidistant from the axis of rotation of the arm assembly. When the camming surface engages the object moving in the first direction, the arm assembly is translated slightly in the first direction and rotated downwardly out of the path of the object. A dog clutch assembly releasably connects the arm assembly to the frame.

Abstract: A quickly releasable stowage bin 108 mountable on one or more support panels 110, 110', or 110", affixed to the interior of an aircraft 100. In the installation of a single stowage bin 108, quickly releasable mounting mechanisms 146, and 158, 160, and 168, respectively affix the upper and lower portion of the stowage bin 108 to the upper and lower portion of a support panel or panels. Each support panel 110, 110', and 110" are initially aligned in the factory whereby a conversion of the aircraft 100 from freighter mode to full or partial passenger mode, results in a rapid, easy, secure, and quality installation of each stowage bin 108. The quickly releasable mounting mechanisms 146, and 158, 160, and 168, also facilitate the rapid and easy removal of each stowage bin 108 from within a compartment of the aircraft 100 during conversion of that compartment from passenger mode to freighter mode.

Abstract: A highly tapered wing tip extension added to the tip of an existing swept, trapezoidal airplane wing for reducing high speed drag significantly. A smaller, highly swept, extension does not require a leading edge device to protect against low speed stall. A larger, less swept, extension requires a tapered slat for which two mechanisms are presented. The principles of the present invention are also applicable to the design of new aircraft.

Abstract: Actuation and support mechanisms for wing trailing edge flap systems wherein each flap system has a streamwise or chordwise pair of geometrically similar flap support assemblies. Each of the flap support assemblies has a chordwise aligned cantilever support beam fixedly attached to wing structure. The beam incorporates multiple cam tracks for providing guidance and support to a movable dual carriage assembly upon which a wing trailing edge flap assembly is mounted. The dual carriage assembly comprises a fore-carriage which is articulatably connected to an aft-carriage. The wing trailing edge flap assembly is mounted upon the aft-carriage. Both the fore-carriage and the aft-carriage are individually supported by rollers constantly engaging a separate cam track for each of said carriages. For actuation of the dual carriage assembly and the wing trailing edge assembly mounted thereon, a ball screw drive mechanism is incorporated between the cantilever beam and the dual carriage assembly.

Abstract: A releasable tool holder (75) for quickly interchanging tools usable by a conventional robot (50) having one or more articulatable arms (60, 65, 70). The tool holder (75) is mounted to an arm (70) of the robot (50) and is provided with a plurality of variable fulcrum clamping levers (110) capable of engaging a surface (215) of a ring (205) mounting a preselected tool. A fluid motor (95) is connected to a translatable center link (105) that is pivotably attached to the variable fulcrum clamping levers (110) whereby when the motor (95) causes the link (105) to translate, the variable fulcrum clamping levers (110) engage the surface (215) of the tool mounting ring (205). A novel tool mounting ring (205) and a releasable fluid coupling (125) are also provided.

Abstract: An inverted cutter or a backspotfacer 100 having indexible, lockable, rotatable carbide cutter inserts 120 whereby in use an operator can reposition the inserts 120, as necessary, to assure a sharp cutting edge 175.

Abstract: A hand tool (20) useful in the repair of bodies having complex, compound curved surfaces. The tool (20) comprises an adjustable arm (40) mountable at one of its ends to a damaged surface area (15). The other end of the arm (40) is provided with a gimbal mount (50) supporting a cutter assembly (45) and a gripping ball (60) for rotating the tool (20) during use. The gimbal mount (50) and a plurality of orthogonally disposed springs 190 provides a means to ensure that the cutter assembly (45) can follow the contour of the surface area 5 and will be substantially perpendicular to the surface area (15) as the tool (20) is being rotated. A guide (55) provides additional forces to urge the cutter assembly (45) into a position substantially perpendicular to the surface area (15).

Abstract: Apparatus for removing or deflecting surface debris (D) from the moorage site of, e.g., a hydrofoil watercraft (5) having a water-jet propulsion system. Debris (D) is diverted away from the hull inlet (72) of the propulsion system and/or cooling water inlets and/or positions proximate the craft (5) which may interfere with the operation of a forward and an aft strut assembly (15,20) by means of a catamaran pontoon (95). The pontoon (95) is provided with an open-ended debris-conducting channel (100) into which surface debris (D) is guided by a pair of fixed debris guides (105B, 105F). A plurality of elevated stand-offs (115) are supported by the pontoon (95) precluding damage to the craft (5) and the accumulation of surface debris (D) proximate the craft (5). Optionally, retractable debris guides (120B, 120F) may be pivotably attached to the guides (105B, 105F) affording the moorage site greater isolation from surface debris (D).