Abstract: A collision damage prevention system is disclosed which may be installed on many standard powered mobility vehicles for handicapped persons. The system includes an array of one or more sensors placed around the periphery of the powered mobility vehicle, a switch for each sensor, and a central control module which receives input from the switches, turns the vehicle off and/or applies braking power to prevent damage from a collision. The system then prompts the operator to acknowledge the collision and guides the operator into the appropriate direction to move the vehicle's controls in order to move away from the object collided with.

Abstract: A collision damage prevention system is disclosed which may be installed on many standard powered mobility vehicles for handicapped persons. The system includes an array of one or more sensors placed around the periphery of the powered mobility vehicle, a switch for each sensor, and a central control module which receives input from the switches, turns the vehicle off and/or applies braking power to prevent damage from a collision. The system then prompts the operator to acknowledge the collision and guides the operator into the appropriate direction to move the vehicle's controls in order to move away from the object collided with.

Abstract: An aircraft flight mode selector assembly utilizes computer-generated menus and soft wired bezel keys to enable the use of a greater number of flight modes to be accessed in a smaller space than is presently possible with a flight mode selector consisting solely of conventional dedicated switches, switch indicator lights, and hard wired selector panel assemblies. Serial bus connections between the flight mode selector assembly and the flight control computer in the aircraft reduce the amount of wiring needed for the flight mode selector assembly, as compared to present protocol which utilizes dedicated wiring for each dedicated switch in the aircraft flight mode selector. The use of computer-generated displays and menus permits easy expansion of the flight mode selector assembly without the need to add additional switches and switch indicator lights.

Abstract: A vertical performance limit compensator is provided for a rotary wing aircraft. The compensator modifies a vertical velocity command signal for the aircraft's autopilot. The vertical velocity command signal represents a desired vertical velocity for the aircraft, and results in an associated engine power demand. Existing engine power remaining beyond that required for level flight is excess engine power. An engine performance signal is provided as an indication of an engine power demand that exceeds the excess engine power. A compensated vertical velocity command signal having a magnitude lower than the vertical velocity command signal is provided in response to the vertical velocity command signal and the presence of the engine performance signal.

Abstract: A steam trap test station includes a body connected to a source of steam, a steam trap and an object to be heated by steam. A rotor fixed for rotation in the body. The body having porting walls defining body ports, and the rotor has porting walls defining rotor ports. The body and rotor ports are adapted and arranged such that an "ON" mode is provided wherein steam passes through the station from the source of steam through the steam trap to the object to be heated. A "TEST OUTLET" mode being first reached when the rotor is turned in a first direction from the "ON" mode wherein an outlet max be tested for leakage. A "TEST INLET" mode is second reached when the rotor is turned in the first direction from the "ON" mode wherein inlet media may be tested. A "BYPASS & VENT" mode is first reached when the rotor is turned in a second direction from the "ON" mode wherein the steam trap is bypassed and vented.

Abstract: A single-handled manifold for connecting a differential pressure transmitter to a source of differential pressure is provided. The manifold includes a body wherein a rotor is mounted for combined axial and rotary motion. Automatic sequencing of the various functions is provided by way of a single handle with multiple selectable positions.

Abstract: A control system, having an input command signal and driving a prime mover, is provided with variable magnitude and/or rate input signal limiting that is adjusted by maps 68,70,72,74 which set the limits for a variable magnitude limiter 14 and a variable rate limiter 22 as a function of the prime mover rate. The limiting is adjusted dynamically as the prime mover rate changes. When the prime mover enters an undesirable operating condition, the maps only limit the command signal in the direction of such condition. The adjustable limiting is enabled or disabled based on the position, rate, and/or acceleration of the prime mover.

Abstract: A helicopter flight control system includes an automatic turn coordination system which provides a coordinating yaw command signal to the tail rotor of the helicopter. The system stores on command a trim attitude (e.g., signals indicative of bank angle, lateral ground speed, and lateral acceleration) about which automatic turn coordination is provided, thus providing the pilot with automatic turn coordination about attitudes other than wings level.

Abstract: A helicopter flight control system includes a model following control system architecture to control helicopter response about the yaw axis. The control system processes information from a variety of helicopter sensors in order to provide an output command signal to the tail rotor. Yaw control is accomplished by applying a force on a sidearm controller which provides a yaw axis command signal that is used to schedule a desired yaw rate of change. The lateral acceleration and airspeed signals are used to compute a synthesized yaw rate signal which is compared against the desired yaw rate of change, thus allowing the pilot to control lateral acceleration when he applies force on the sidearm controller.

Abstract: A manifold for a differential pressure transmitter for a fluid conveying pipeline is provided. Valves are arranged to provide automatic sequencing for service functions.

Abstract: Apparatus for connecting a conduit to an equipment opening having damaged female threads includes a body, an annular packing ring and a packing follower. The packing ring is formed of an extrudable, non-resilient packing material. The body and the packing follower are threaded to engage the female threads of the equipment opening. The packing ring is compressed and extruded into the damaged threads by relative rotation of the body and packing follower.

Abstract: A transmitter/manifold with integral transducer for measuring the differential pressure of a fluid conveying pipeline is provided. Valves are arranged to provide automatic sequencing for service functions. Means for heating the transmitter/manifold is provided. Interface modules are provided to provide for adaptability to a variety of user requirements. A sealing arrangement for interface modules is also provided.

Abstract: An arrangement for controlling the position of a movable member, especially an aircraft control surface member, includes an operational amplifier and a capacitor connected in parallel to the amplifier. The control arrangement further includes a detector which detects the restoration of the supply of electric power following its interruption and generates a limited-duration pulse. This pulse is then used to close a switch, which is interposed between an input terminal of the capacitor and the ground, for the duration of this pulse, so that the capacitor is charged much more rapidly than otherwise. The output signal of the combination of the operational amplifier and the capacitor is supplied to an actuator for the movable member so that the extent of excursion of the movable member out of its desired position after the electric power supply has been restored is minimized.

Abstract: A method of and an arrangement for controlling the operation of a reversible D.C. electric motor including a winding having two ends each of which is connected to both the positive and negative terminals of an electric current source through respective control switches that can be selectively closed and opened in response to command signals to apply voltage differentials across the winding with attendant electric current flow through the winding in one or the opposite direction for operating the electric motor in one or the other of its senses of rotation with intervening rotation sense reversals utilize the original command signals for determining when the sense of rotation reversal would result in an excessive electric current flow through the winding.

Abstract: Pilot workload is reduced in a helicopter having a force-type, multi-axis sidearm control stick by providing a displacement-type control stick for collective blade pitch control. Either stick may be used by the pilot. When the force-type stick is employed, a trim system causes the displacement-stick to track a collective position command signal which is provided to the blade actuators. Changeover of control to the displacement-type control stick is accomplished either with a switch, or by moving the collective-type control stick. The signals associated with each control stick are alternately faded in and out to assure a smooth transition when collective control is switched over from one to the other.

Abstract: A heading trim reference system provides beep commands indicative of a desired heading/attitude change to the roll channel of an AFCS as roll commands at slow speed in a conventional manner, and to the yaw channel as yaw commands at cruise speed. At cruise speed, the yaw synchronizing integrator responds to the beep commands and provides an error signal to existing turn coordination logic to turn the aircraft.

Abstract: The directions of travel of an inner and an outer loop actuator are monitored for movement in opposite directions within selected ranges and the outer loop actuator is disabled under selected conditions. These conditions may include movement of both the inner and outer loop actuators in opposite directions, any one of which has been detected moving at a rate greater than a selected rate or to a position outside a selected range. The invention is particularly suited for an aircraft trim actuator shutdown monitor system.

Abstract: An aircraft automatic flight control system (AFCS) includes a pair of fast, limited authority inner loop actuators responsive to signals indicative of aircraft attitude or other flight parameters such as airspeed, the inner loop being recentered by an outer loop actuator responsive to attitude or other aircraft parameter-indicating signals (54,55). Commands applied to the outer loop are applied in a lagged fashion in opposite direction so as to drive the inner loop actuators back toward the center of their authority. The rate of response of the outer loop is adaptive in response to magnitude of inner loop input (101, FIG. 2). A pitch bias command is provided to the inner loop as a function of airspeed multiplied inversely with collective pitch, and as a function of the rate of change of collective stick position, so as to provide a positive static pitch trim gradient and decouple collective pitch from the longitudinal cyclic pitch channel.

Abstract: A steam trap test station includes a body connected to .[.a source of steam.]. .Iadd.an inlet for steam and condensate from an object to be heated by steam.Iaddend., a steam trap and .[.an object to be heated by steam.]. .Iadd.a condensate outlet.Iaddend.. A rotor .Iadd.is .Iaddend.fixed for rotation in the body. The body .[.having.]. .Iadd.has .Iaddend.porting walls defining body ports, and the rotor has porting walls defining rotor ports. The body and rotor ports are adapted and arranged such that an "ON" mode is provided wherein steam .Iadd.and condensate .Iaddend.passes through the station from the .[.source of steam.]. .Iadd.inlet .Iaddend.through the steam trap to the .[.object to be heated.]. .Iadd.outlet.Iaddend.. A "TEST OUTLET" mode .[.being.]. .Iadd.is .Iaddend.first reached when the rotor is turned in a first direction from the "ON" mode wherein .[.an.]. .Iadd.the .Iaddend.outlet .[.max.]. .Iadd.may .Iaddend.be tested for leakage.