Abstract: A reactor having a top to bottom design configuration capable of being operated in an up flow or down flow configuration with equal ease, where the reactor includes a plurality of tubes optionally housed within a shell and includes top and bottom screen assemblies capable of retaining a catalyst within the tubes, while permitting reactants and products to flow through them.

Abstract: A process for preparing trichlorosilane by reacting silicon with hydrogen chloride, or silicon tetrachloride with hydrogen in the presence of silicon, and catalysts where the silicon and catalysts are laminated together and reduced in particle size prior to reaction.

Abstract: The invention relates to a method for receiving and/or transporting substrates, wherein, by means of at least one sensor, a deviation of the position of a substrate, in particular of a substrate arranged in a slot of a container, is detected at least with respect to one degree of freedom and a movement course of at least one receiving device and/or transporting device is determined with the inclusion of said deviation.

Abstract: A method for holding and orienting a wafer having an alignment feature, the method includes gripping a wafer with an end effector attached to an end of a robot arm, the end effector including a gripping mechanism which includes a first contacting member, a second contacting member, and a drive element, and wherein gripping includes increasing and decreasing the space between the first and second contacting members, the method also including rotating the wafer about an axis that is perpendicular to the plane of the wafer and sensing the alignment feature on the wafer as the gripping mechanism rotates the wafer.

Abstract: An apparatus for holding and orienting a wafer having an alignment feature, and including a movable robot arm; and an end effector attached to an end of the robot arm, the end effector including a gripping mechanism which during operation both holds the wafer and rotates it about an axis that is perpendicular to the plane of the wafer and a sensing element for detecting the alignment feature on the wafer as the gripping mechanism rotates the wafer past the sensing element.

Abstract: A rotatable slotted cylinder (RSC), partially embedded within the contours of a tail surface, such as an aircraft tail airfoil, serves as a force-producing element in a closed-loop active control system for buffet alleviation. A longitudinal axis of the RSC runs spanwise to the airfoil at or near the three-quarter chord location. In a so-called "home" position, the RSC projects as two small spanwise humps out of opposite sides of the tail surface. By active feedback control using a buffet response signal measured by an accelerometer, the RSC rotates up to .+-.45.degree. maximum deflection from the home position, thus allowing free stream air to flow through the airfoil, thereby creating lift forces for the active alleviation of the buffet response on the tail surface. An alternate embodiment of the invention places the RSC and a drive motor assembly outside of and adjacent to the tail surface near the airfoil quarter chord station.

Abstract: Higher harmonic control (hereinafter HHC) of helicopter rotor blade vibrations is provided by an actively controlled, rotatable, slotted cylinder which is mounted at an outboard section of each blade. Continuous rotation of each cylinder about its longitudinal axis produces a periodic aerodynamic force on the blade at a frequency of twice the rotational frequency of the cylinder. The amplitude of force is controlled by the size of a slot opening in the cylinder while the rotational speed of the cylinder is synchronized to run at a multiple of the speed of a rotor blade drive shaft. The amplitude and phase of the HHC force is regulated, either manually or by active feedback control, to minimize any vibratory load transmitted to the airframe through the rotor blade drive shaft. A significant advantage offered by this concept relative to other HHC methods, such as high-frequency blade pitch motions actuated either by the swash plate or by moveable tabs at the blade trailing edge, is its low power requirement.

Abstract: An automatic transducer selection system for fluid pressure measurement functions by using two or more transducers with different ranges of accuracy and also by incorporating comparator circuitry which automatically selects the transducer reading nearer to full scale. An electronic signal or output from the comparator is preferably nested such that a continuous voltage is generated in accordance with the fluid pressure being measured, thus making the system appear to function as a single transducer with a wide range of accuracy.

Abstract: A superagile tactical fighter aircraft and a method of flying it are disclosed. The superagile aircraft is characterized by articulatable air inlets, articulatable exhaust nozzles, highly deflectable canard surfaces, and control thruster jets located around the nose of the fuselage, on the top and bottom surfaces of the propulsion system near the exhaust nozzles, and on both sides of at least one vertical tail. The method of operating the superagile aircraft comprises the step of articulating the air inlets and exhaust nozzles, deflecting the canard surfaces, and vectoring the thruster jets so that supernormal flight is attained. Supernormal flight may be defined as flight at which the superagile aircraft operates at an angle of attack much greater than the angle of attack which produces maximum lift. In supernormal flight, the superagile aircraft is capable of almost vertical ascents, sharp turns, and very steep descents without losing control.

Abstract: A flutter exciter induces vibration either for actual aircraft flight testing or for wind tunnel model testing. The basic flutter exciter unit is a pair of rotatable concentric cylinders mounted on either a fixed vane or an aircraft wing or a tail surface. Each cylinder has a slot which allows the air flow to pass therethrough. By rotating the cylinders together, oscillating air pressures are induced on the fixed vane or the aircraft surface to which the cylinders are attached. The cylinders may be mounted at a trailing edge of either the fixed vane or the aircraft wing, to any tail surface, or on any other lifting surfaces of the aircraft itself. Thus, because the flutter exciter can be made as a completely self-contained unit, it may be simply mounted to any suitable hard point on either the test model or the aircraft. The power required to rotate the slotted cylinders is minimal, thus allowing the use of a low wattage motor.

Abstract: Tilting the stabilizer at an extreme angle to the fuselage, with leading edge down, and controlling and varying engine thrust comprise a method for all-axis control of a generally conventional aircraft in ultra deep stall. The method is effective in recovery from unstable and unusual flight attributes and in landing emergencies; the aircraft may land in the ultra deep stall configuration or conventional flight may be resumed. So-called flying wing aircraft, where pitch control surfaces are incorporated with the trailing edge of the primary lift surface, are also controllable in ultra deep stall by the method of this invention.

Abstract: An automatic transducer selection system for fluid pressure measurement functions by using two or more transducers wtih different .Iadd.measurement .Iaddend.ranges .[.of accuracy.]. and also by incorporating comparator circuitry which automatically selects the transducer reading nearer to full scale. An electronic signal or output from the comparator is preferably nested such that a continuous voltage is generated in accordance with the fluid pressure being measured, this making the system appear to function as a single transducer with a wide .Iadd.measurement .Iaddend.range of .Iadd.high .Iaddend.accuracy.

Abstract: A superagile tactical fighter aircraft and a method of flying it are disclosed. The superagile aircraft is characterized by articulatable air inlets, articulatable exhaust nozzles, highly deflectable canard surfaces, and control thruster jets located around the nose of the fuselage, on the top and bottom surfaces of the propulsion system near the exhaust nozzles, and on both sides of at least one vertical tail. The method of operating the superagile aircraft comprises the step of articulating the air inlets and exhaust nozzles, deflecting the canard surfaces, and vectoring the thruster jets so that supernormal flight is attained. Supernormal flight may be defined as flight at which the superagile aircraft operates at an angle of attack much greater than the angle of attack which produces maximum lift. In supernormal flight, the superagile aircraft is capable of almost vertical ascents, sharp turns, and very steep descents without losing control.