Abstract: An omnidirectional pressure sensing head includes a rotatable hub; a channel extending through the hub having an inlet and an outlet; and a single pressure sensing port in the hub disposed in the channel between the inlet and outlet for sensing the dynamic pressure of the fluid through the channel which is a function of the speed of the hub through the fluid and the rotational speed of the hub.

Abstract: An omnidirectional speed sensing system includes a rotatable member; a channel supported by the rotatable member and having an inlet and an outlet; a single pressure sensing port in the system disposed the channel between the inlet and the outlet for sensing the dynamic pressure of the fluid flow through the channel which pressure is a function of the rotational speed of the rotatable member and the velocity of the rotatable member through the fluid; transducer means responsive to the pressure at the sensing port for producing a pressure signal; means responsive to the pressure signal for extracting the first harmonic of the pressure signal; and means responsive to the magnitude and phase of the first harmonic of the pressure signal for indicating the velocity and direction of the sensed speed.

Abstract: A microprocessor receives sensor signals and produces signals proportional to total, longitudinal and lateral air speed. An omnidirectional air speed sensor uses pressure samplers on a rotating arm to produce a sinusoidal pressure differential signal related to air speed. An interrupter disc rotating with the arm periodically exposes an opto-electric sensor to light to produce a pulse phase reference signal. In one embodiment, the pulse signal operates a first ramp generator to produce an arm RPM signal and operates a second ramp generator in conjunction with the sinusoidal signal to produce an azimuth reference signal. The RPM and azimuth signals are fed to a processor to resolve the air speed into longitudinal and lateral components. In the preferred embodiment, the processor receives the pulse signal and produces a pair of out-of-phase square wave signals which control chopper modulators which demodulate the sinusoidal signal to produce signals proportional to lateral and longitudinal speed.

Abstract: A temperature sensor for mounting on a mast of a helicopter has a heat sensor positioned within a central openining in a radially finned heat exchanger. The heat sensor and heat exchanger are spaced rearward from the mast on a tubular sensor support. Long wires helically coiled within the sensor support connect the sensor and terminals on a bracket soldered to the mounting base. The rearward mounting of the heat sensor and the spacing of the heat exchanger and sensor from the mast on the sensor support and the coiling of a long wire within the sensor support between the sensor and terminals on the base and the filling of the sensor support with polyurethane foam resin ensure that the sensor senses air temperature remote from its base and does not sense temperature of the element on which the base is mounted.

Abstract: An omnidirectional airspeed indicator has a plate with a window and a fixed horizontal bar across the window. A drum with graduations and numerical indications of speed and forward and rearward direction and with a safe flight envelope indication and safe engagement and disengagement indication rotates within the window so that the horizontal bar points to the forward and rearward speeds. A vertical bar moves between a drum and the window to indicate lateral speeds. Vectoral sum of speed is presented in digits at the top of the window. A rearward flight warning light is mounted beneath the window and a high speed warning flag appears in the window when maximum safe speeds are approached. Triangles at the lateral edges of the window cause the vertical bar to appear as a broken line when maximum lateral indications are approached or exceeded. Rate of climb is indicated by a pointer beside the window. A selector switch lights air density in the digital display.

Abstract: A flight simulator instrument trainer has operational controls and instruments similar to a conventional aircraft. An AC driven position simulator moves a simulated station position according to simulated power, attitude, flap condition direction and distance traveled to control simulated ADF, ILS and VOR instruments. Angularly offset phases are generated and are provided to potentiometers on directional instruments. Wipers on the potentiometers move with simulated direction indicators. Signals from the wipers are fed to other devices, and phases are compared with one of two ninety degree offset reference phases. The latter are shifted according to simulated flight characteristics, and the thus-varied output of the phase comparators are used to drive instruments and to shift angle position accumulators and distance position accumulators.

Abstract: A flight simulator instrument trainer has operational controls and instruments similar to a conventional aircraft. An AC driven position simulator moves a simulated station position according to simulated power, attitude, flap condition direction and distance traveled to control simulated ADF, ILS and VOR instruments. Angularly offset phases are generated and are provided to potentiometers on directional instruments. Wipers on the potentiometers move with simulated direction indicators. Signals from the wipers are fed to other devices, and phases are compared with one of two ninety degree offset reference phases. The latter are shifted according to simulated flight characteristics, and the thus-varied output of the phase comparators are used to drive instruments and to shift angle position accumulators and distance position accumulators.

Abstract: An omnidirectional cockpit display has perpendicular bars independently moving across a plate for providing indications of speed in lateral, forward and rearward directions. A zero point is centered between lateral edges of the plate and is displaced vertically from the center of the plate to provide greater speed indications in a forward direction than in a rearward direction. A safe flight envelope is indicated on the plate, extending around the zero point in lateral and rearward directions and extending toward the edges of the plate in the forward flight direction. Indicator scales are mounted along edges of the plate, and pointers move along the scales to indicate vector sum of component speeds, and density altitude. Other scales and pointers indicate ground speed in orthogonal directions, while the crossbars indicate air speed in those directions. Other peripheral scales and pointers indicate directional control position, collective thrust control position, rate of climb and rate of closure.

Abstract: Power required curves for ratios of helicopter weight to air density ratio form a background over which move perpendicular bars representing air speed and engine torque. The intersection of the relatively movable bars indicates which power required curve the helicopter is operating on. An area to the right and above that curve represents power margin available for maneuvering. A knob positions a mask over a portion of the background to indicate the actual maximum power limitation of the helicopter. A maximum power setting is varied according to ambient pressure and temperature. A minimum speed warning is produced by comparing air speed and engine torque. A rapid descent automatically raises the minimum speed warning.