Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Abstract: A multiple pre-orifice apparatus for a sprayer nozzle body with an upper end connected to a liquid source, a nozzle tip releasably mounted at a lower end thereof, and a channel between the upper and lower ends of the nozzle body. The apparatus comprises a sleeve assembly comprising a sleeve closed at an upper portion thereof by a top orifice plate defining a top orifice, and closed at a lower portion thereof by a bottom orifice plate defining a bottom orifice such that a sleeve turbulence chamber is formed between the top and bottom orifice plates. The sleeve assembly is secured in the channel such that a nozzle turbulence chamber is formed between the bottom orifice plate and the nozzle tip. The area of the flow opening in the nozzle tip is greater than the area of the top orifice which is greater than the area of the bottom orifice.

Abstract: A calibration system is disclosed. The calibration system includes a waveform generator configured to generate a periodic waveform and a control circuit in signal communication with the waveform generator. The control circuit includes an analog-to-digital converter configured to convert the periodic waveform to digital values and an electronic device in signal communication with the analog-to-digital converter. The electronic device is configured to verify calibration of (1) timing of the control circuit and (2) voltage levels of the control circuit based on the periodic waveform.

Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Abstract: A multiple pre-orifice apparatus for a sprayer nozzle body with an upper end connected to a liquid source, a nozzle tip releasably mounted at a lower end thereof, and a channel between the upper and lower ends of the nozzle body. The apparatus comprises a sleeve assembly comprising a sleeve closed at an upper portion thereof by a top orifice plate defining a top orifice, and closed at a lower portion thereof by a bottom orifice plate defining a bottom orifice such that a sleeve turbulence chamber is formed between the top and bottom orifice plates. The sleeve assembly is secured in the channel such that a nozzle turbulence chamber is formed between the bottom orifice plate and the nozzle tip. The area of the flow opening in the nozzle tip is greater than the area of the top orifice which is greater than the area of the bottom orifice.

Abstract: A multiple pre-orifice apparatus for a sprayer nozzle body with an upper end connected to a liquid source, a nozzle tip releasably mounted at a lower end thereof, and a channel between the upper and lower ends of the nozzle body. The apparatus comprises a sleeve assembly comprising a sleeve closed at an upper portion thereof by a top orifice plate defining a top orifice, and closed at a lower portion thereof by a bottom orifice plate defining a bottom orifice such that a sleeve turbulence chamber is formed between the top and bottom orifice plates. The sleeve assembly is secured in the channel such that a nozzle turbulence chamber is formed between the bottom orifice plate and the nozzle tip. The area of the flow opening in the nozzle tip is greater than the area of the top orifice which is greater than the area of the bottom orifice.

Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Abstract: The invention describes a novel system for measuring short distances using the propagation time of radio signals between at least one interrogation unit and a transponder, whereby a disturbance of the transponder's response signal by its own request signal is excluded by means of a highly precise delay of the request in the transponder. The delay is realized with quartz accuracy and the necessary precision in that it takes place in a digital or analog register chain, whose register clock is kept phase synchronous with the interrogation signal, that a variable delay of the interrogation signal takes place in the interrogation unit and that this delay is adjusted by one register clock period at the synchronous time preferably by means of a binary search by means of the recognizable jump of the total running time-round trip.

Abstract: A multiple pre-orifice apparatus for a sprayer nozzle body with an upper end connected to a liquid source, a nozzle tip releasably mounted at a lower end thereof, and a channel between the upper and lower ends of the nozzle body. The apparatus comprises a sleeve assembly comprising a sleeve closed at an upper portion thereof by a top orifice plate defining a top orifice, and closed at a lower portion thereof by a bottom orifice plate defining a bottom orifice such that a sleeve turbulence chamber is formed between the top and bottom orifice plates. The sleeve assembly is secured in the channel such that a nozzle turbulence chamber is formed between the bottom orifice plate and the nozzle tip. The area of the flow opening in the nozzle tip is greater than the area of the top orifice which is greater than the area of the bottom orifice.

Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Abstract: A nozzle mounting and control system for use in sprayers comprising multiple sets of nozzles mounted in the operating position on a sprayer boom. Control valves are operable to select which sets of nozzles are operating at any given time. The valves may be remote controlled and may further incorporate a rate controller to maintain a chosen application rate as speed varies. This application rate may be varied conveniently. The rate controller may be a present rate controller such as measures the speed and total fluid volume delivered and then adjusts the pressure to maintain the application rate, or may be a novel rate controller which measures the speed and fluid pressure and then adjusts the pressure to maintain the application rate. Either rate controller would operate the control valves to select the proper combination of operating nozzles in addition to adjusting the pressure.

Abstract: A nozzle fluid supply system for use in sprayers that combines the modular advantages of a dry boom system with the high capacity of a wet boom system. Pressurized fluid is carried by rigid tubes connecting adjacent nozzle holding members attached to the sprayer. A two-part nozzle holding member is disclosed for attachment to a dry boom bracket through a hole therein. The combination of the short rigid tubes and two-part nozzle holding member provide a modular system with interchangeable parts.

Abstract: In a metallic sheathed electric heating element assembly having a resistance element, a sheath surrounding the resistance element, pulverulent electrically insulating material within the sheath and surrounding the resistance element, the insulating material being tightly compacted and extending within the sheath short of an open end thereof, and a terminal pin electrically and mechanically connected to an end of the resistance element within the compass of the sheath, the terminal pin is made in two parts, an inner part to which the resistance element is connected, and an outer part spaced from the inner part, and a thermal switch or cut off electrically connected to and in series between the inner and outer parts of the pin within the sheath but spaced toward the open end from the compacted insulating material, the thermal switch being in good thermal contact with the inner part of the terminal pin.

Abstract: A water heater with a plastic tank is provided with an electric immersion heating element assembly having a mounting plug in which is mounted a sheathed heating element having two generally parallel legs and a bight portion. A well projects from the mounting plug along and substantially parallel to the legs in heat exchange relation therewith and contains a thermal cutoff adapted to be electrically connected in series with the first end of a two-ended electric resistance element in the sheathed heating element. A thermally conductive bridge mechanically and thermally connects the legs of the sheathed heating element to the well. The legs of the sheathed heating element are bent back upon themselves and a bracket, connected to the two reaches of at least one leg, permits relative axial movement but prevents lateral movement of the reaches of the legs with respect to one another. The mounting plug is made of solid copper or copper alloy, as is the sheath and well.