Abstract: A method and apparatus for forming a three-dimensional article includes dispensing build material and thermally normalizing predetermined portions thereof at predetermined intervals during construction of the article. The thermal energy may be provided by a heated body advanced adjacent to or in contact with the surface portions. Thermal energy may also be supplied by a radiation source. The thermal normalization may be performed after a predetermined number of successive layers are dispensed. Related methods are also disclosed.

Abstract: An electric control for gas furnaces which controls a two speed main blower fan and an induction draft fan based on inputs from a room thermostat, a high limit and an ignition control including a gas valve. The control has a circuit board having a power supply for providing 24 volts DC current source to drive DC relays and a 5 volt DC power source to power a microprocessor. 24 volt AC input signals are coupled to the input ports of the microprocessor through current limiting resistors and to AC ground through pull down resistors. AC ground is also connected to the IRQ port of the microprocessor. The output ports of the microprocessor are connected to a relay driver which in turn is connected to the relays. Several breakaway tabs in the board provide optional features such as eliminating a normally provided draft delay timing function. Test pads are provided on the board so that the board can be tested during manufacture.

Abstract: An apparatus includes a processor for controlling a build material dispenser and a dispenser positioner to construct a three-dimensional article in successive layers based upon article defining data, and wherein the processor operates the dispenser to dispense a series of bursts of build material at a series of respective target positions as the dispenser is advanced along a predetermined path of travel. Each burst is defined by a plurality of droplets dispensed in relatively rapid succession so that the build material thereof combines at a respective target position. The build material dispenser is preferably a jet including a piezoelectric actuator for ejecting a droplet of build material responsive to a corresponding firing signal. Accordingly, the processor generates a predetermined number of firing signals for the piezoelectric actuator corresponding to a desired number of droplets in each burst. Method aspects of the invention are also disclosed.

Abstract: A dual dispenser dispenses both soap and fragrance for washrooms. The dispenser has a mounting plate for mounting on a surface in the washroom and has a lower support for a box containing a flexible bag of soap with the bag having a flexible tube extending out of the box. A container with a fragrance source is mounted in the top of the box and a fan is located thereabove which is driven by a small motor mounted on an upper support of the mounting plate. A battery is also located on the box adjacent the fragrance container. Switch contacts are in circuit with the motor and the battery for operating the motor and fan when the switch contacts are closed. A cover for the mounting plate has a hand-operated actuating plate which squeezes the tube to dispense soap and closes the contacts to operate the fan when the actuating plate is pushed, thus dispensing both soap and fragrance in a single motion.

Abstract: An electric control for gas furnaces which controls a two speed main blower fan and an induction draft fan based on inputs from a room thermostat, a high limit and an ignition control including a gas valve. The control has a circuit board having a power supply for providing 24 volts DC current source to drive DC relays and a 5 volt DC power source to power a microprocessor. 24 volt AC input signals are coupled to the input ports of the microprocessor through current limiting resistors and to AC ground through pull down resistors. AC ground is also connected to the IRQ port of the microprocessor. The output ports of the microprocessor are connected to a relay driver which in turn is connected to the relays. Several breakaway tabs in the board provide optional features such as eliminating a normally provided draft delay timing function. Test pads are provided on the board so that the board can be tested during manufacture.

Abstract: In the preferred configuration, the assembly is characterized in that the lateral and longitudinal thrust reversing loads exerted on the thrust reversing subassembly are transmitted into the fan duct structure which is arranged to in turn transmit these thrust reversing loads into outer structure to which the jet engine and thrust reversing assembly is mounted. In the preferred form, there are vane means which, with the thrust diverting structure in the thrust reversing position, is positioned in the thrust reversing opening to properly direct flow through the thrust reversing opening. Also in the preferred form, the thrust diverting structure is pivotally mounted to the fan duct structure at a lower location so that the thrust diverting structure rotates with a downward component of motion to the thrust reversing position, so that the thrust diverting opening is directed upwardly.

Abstract: An engine end and thrust reversing assembly comprising an annular thrust diverting structure which in the cruise configuration is a rearward extension of a fan duct cowl structure. For thrust reversal, the thrust diverting structure is swung rearwardly and inwardly about an inboard hinge axis to form a laterally and forwardly directed thrust reversing opening. A transversely curved blocking plate is pivotally mounted about a vertical axis to the fan duct structure, and in the cruise configuration it is positioned adjacent to a forward extension of the thrust diverting structure so as to surround a portion of the exhaust passageway. In the thrust reversing position, the blocking plate is swung to a position where it extends across the exhaust passageway defined by the thrust diverting structure.

Abstract: In the preferred configuration, the assembly is characterized in that the lateral and longitudinal thrust reserving loads exerted on the thrust reversing subassembly are transmitted into the fan duct structure which is arranged to in turn transmit these thrust reversing loads into outer structure to which the jet engine and thrust reversing assembly is mounted.In the preferred from, there are vane means which, with the thrust diverting structure in the thrust reversing position, is positioned in the thrust reversing opening to properly direct flow through the thrust reversing opening. Also in the preferred form, the thrust diverting structure is pivotally mounted to the fan duct structure at a lower location so that the thrust diverting structure rotates with a downward component of motion to the thrust reversing position, so that the thrust diverting opening is directed upwardly.

Abstract: A chordwise extensible wing leading edge system incorporating a rigid contoured panel member which is exposed during forward extension movement of the leading edge slat for closing in the proximity area between said slat and the relatively stationary leading edge portion of the wing, as a function of the forward movement of the slat. A further embodiment utilizes a second panel member so that both the upper and the lower surface contour of the wing airfoil envelope are aerodynamically continuous to complete the contour of the intervening space between the extended position of the slat and the stationary portion of the wing; whereby, this combination results in approaching the merits of wing cambering devices capable of operation at relatively high airspeeds as opposed to landing or take-off airspeeds.

Abstract: A body-braced main landing gear assembly for a commercial airplane includes a set of landing wheels journalled to a shock absorber strut. The shock strut and wheels are swingably attached to the underside of the wing structure by a trunion shaft for lateral as well as fore and aft swinging movement between an extended position wherein the wheels depend downwardly from the wing for taxiing and landing of the airplane and a retracted position wherein the wheels and shock strut are swung inwardly and upwardly into a wheel bay in the airplane fuselage. The shock strut is braced in the extended position by a foldable drag strut and a rigid radius brace. The foldable drag strut is attached at one end to the shock strut and is attached at its opposite end to the fuselage body at a point inward and forward of the trunion shaft. The radius brace is attached at one end to the shock strut and is attached at its opposite end to a point on the fuselage body inward and rearward of the trunion shaft.

Abstract: A supersonic airplane has a fuselage, a wing, a vertical stabilizer, a canard and a pair of turbine engines mounted in the fuselage. Each engine is of relatively simple design with a fixed inlet, a compressor and a turbine with a single drive shaft interconnecting the turbine and compressor. The engine can employ either fixed or variable exhaust nozzle geometry, depending on whether an afterburner is installed. The engine is point designed to provide maximum design thrust at a given intermediate throttle setting when the airplane is being propelled by the engine at a predetermined supersonic cruise Mach number. Maximum allowable thrust at speeds below the predetermined cruise Mach number is achieved without variable geometry air inlets by maintaining the corrected airflow through the engine at a substantially constant value equivalent to the corrected airflow at the predetermined supersonic cruise Mach number.

Abstract: A midwing aircraft employs a unique configuration for mounting three high bypass turbofan engines. All three engines are mounted so that a portion thereof projects forwardly of the leading edge of the airfoil on which they are mounted and so that the chordal plane of the airfoil longitudinally bisects the engine. The exhaust from each of the engines is directed by two nozzles. Internal bifurcators split both the turbine exhaust and the fan exhaust from each of the engines evenly between the two nozzles. A pair of channels in each of the wing mounted engines intercepts a portion of the fan effluent and directs it rearwardly into boundary layer control supply plenums in the wing structure. Valve mechanisms for opening and closing the channels are mounted in the forward portions of the channels. Check valves are also provided in each of the channels to prevent backflow of fluid from the supply plenums into the channels.