Abstract: An apnea monitor and alarm for monitoring the breathing of an individual and for sounding an alarm in response to an interruption in the cyclical rhythm of breathing is disclosed. The monitor and alarm includes a respiration detector, an alarm and a signal processor and analyzer. The signal processor and analyzer is programmed to arm the alarm after a preselected time of cyclical breathing. The signal processor and analyzer is also programmed to sense an interruption in the breathing cycle and to actuate the alarm after a preselected period of interrupted breathing. The monitor and alarm may also include a deactivation system that recycles the program back to an initial part of the program so that the alarm is once again armed after a preselected time of continuous breathing.

Abstract: An airborne power control system for automatically controlling the power of an aircraft during landing is disclssed. The system includes a computer and a minimum airspeed program as a function of altitude. A radio altimeter or the like senses the instantaneous altitude of the aircraft while a pitot tube or the like measures indicated airspeed. A computer and program compare programmed airspeed with actual airspeed for a given altitude. And, a servomotor is provided for decreasing engine thrust where the actual airspeed exceeds the programmed airspeed at any given altitude. An inhibitor inhibits the decrease in engine thrust if the airspeed drops below the programmed airspeed.

Abstract: An engine synchronization system for a pair of turbo jet engines in a twin jet aircraft includes a subsystem for selecting a power output, a signal generator for producing a first output signal in response to the speed of a first engine and a signal generator for producing a second output signal in response to the speed of a second engine. The system also includes a selector for selecting the fan speed or compressor speed of the engines as a control. The system incorporating an averaging device for calculating the average of the engine speeds and causing the servo driven throttle controller to retard the faster and advance the slower throttles toward the average. The engine synchronization system also includes a split shaft assembly including first and second output shafts which are disposed on a common axis. Each of the output shafts is locked to a servo motor and are free to rotate with respect to one another.

Abstract: A propulsion system or aircraft engine for a helicopter or other aircraft includes an aerodynamic pod with a forward facing inlet for receiving a flow of ram air and a rearwardly facing exhaust or outlet. The system also includes a vertical shaft and one or more rotatable turbine assemblies mounted on the vertical shaft. Each of the turbine assemblies includes an inner compressor section having a plurality of blades with a first pitch and an outer turbine section having a plurality of blades at a reverse pitch. The compressor and turbine sections both forming part of a single disk or wheel. The system also includes a fuel injector for injecting fuel into the combustion chamber and an igniter for igniting the fuel air mixture within the chamber. A housing or channel directs the ram air through an angle of about 90° and through the compressor section and into the combustion chamber.

Abstract: An airborne power line detector and warning system includes a low frequency radio and antenna for detecting an AC signal of about 50 to 60 hertz. The system also includes a subsystem for producing a unique audio signal such as a series of clicks for warning a pilot that he is flying close to one or more power lines. In addition, the system includes a mute feature for muting the audio signal and replacing it with a visual signal. Finally, the system includes a gain sensor for replacing the audio signal at any time that the helicopter reduces its distance to a power line. An airborne power line detection and warning system which includes a second system or back up system is also disclosed. That system includes a GPS receiver and GIS data base to position a helicopter with respect to a power line grid and sound an alarm when the helicopter approaches a power line.

Abstract: A pilot warning system is disclosed for a helicopter having a main rotor rotatable about a yaw axis, a fuselage connected to the main rotor and having a tail boom with a controllable force mechanism to counter-act the torque exerted on the fuselage by rotation of the main rotor. The pilot warning system acts on foot pedals operatively connected to the controllable force mechanism, with the pedal movement controlling the amount of force exerted by the controllable force mechanism on the tail boom to the control the orientation of the helicopter fuselage about the yaw axis. A position sensing device senses the location of at least one of the foot pedals between its first and second positions, and a warning indicator operatively connected to the position sensing device provides a warning to the pilot when the sensed foot pedal reaches a predetermined distance from one of the first and second positions.

Abstract: A two-stage alarm for a rotary wing aircraft, such as a helicopter which operates on a collective control arm. A moveable mass or weight is operatively connected to the collective control arm. The moveable weight may be of a reciprocating type or a rotor driven mass which is mounted eccentrically for rotation about an axs which is spaced from the center of gravity of the weight. In the latter case, a D.C. motor spins the weight rapidly about the axis at a first speed to produce a shaking action to the collective control arm as a warning of an approaching danger. The weight is moved more rapidly to produce a much more noticeable action at a second frequency, or at an increased amplitude as a warning of a more imminent or serious condition which requires immediate action.

Abstract: A device for indicating that an airplane has reached a safe speed in the presence of headwinds for initiating take-off rotation. The device senses the true ground speed of the airplane and converts the true ground speed into an "indicated ground speed" in accord with the relationship between true air speed and indicated air speed for the airplane. The device subtracts the indicated ground speed from the indicated air speed of the airplane to determine the amount of the headwind and, whenever the headwind exceeds a preselected margin, the device increases the value of the safe minimum indicated air speed for initiation of take-off by any excess of the headwind over the preselected margin. The device then directs the flight director to initiate take-off rotation when the indicated air speed of the airplane equals or exceeds the adjusted minimum indicated air speed.

Abstract: A helicopter includes a rotor tip jet engine which combines ram compression and centrifugal compression to increase the thrust. A first flow of fuel is dispersed in the ram air and is carried into a combustion area of the engine. A separate flow of fuel is injected into the centrifugally compressed air before the fuel air mixture enters the combustion area. For helicopters and other applications, the ram jet engine combines ram air and a separate mass of compressed air which is directed into the combustion area for increased thrust. A regulator or control mechanism is also provided for regulating the quantity of compressed air which is added. The regulator or control mechanism may also be used to cut off or stop the addition of the separate mass of compressed air.

Abstract: An airspeed and direction indicating system for an aircraft of the rotary wing type includes a vertical accelerometer for monitoring the up and down movement of an outer portion or tip of the rotary wing. The vertical accelerometer produces a generally sinusoidal signal in response to the up and down movement of the wing tip as it rotates about an axis. The amplitude of the signal corresponds to the airspeed and the phase angle indicates direction. Suitable readouts display the information for consideration by a pilot.

Abstract: An aircraft control mechanism for a speed brake includes a shaft, an outer sleeve surrounding the shaft and a sprag clutch. The mechanism also includes input and output elements and a control element with the input element tied to the outer sleeve. The control element is tied to the shaft and the output is operatively connected to the output of the clutch. A control cable is connected to the output for moving a speed brake between a first and a second position. A manual input actuates the control element of the clutch. An automatic input is connected to the outer sleeve through a torsional dampening device which minimizes chatter or sticking due to high forces which are required to extricate the sprag clutch from a relatively high racked-in load.

Abstract: A continuously monitored battery operated power supply for maritime applications includes four batteries which form a parallel connected pair of banks in which the cells in each bank are series connected to each other. A Wheatstone bridge circuit connects a midpoint between the plurality of cells in the first bank of battery cells and a midpoint between the plurality of cells in the second bank of batteries. The circuit also includes a volt meter for indicating a voltage change due to the degeneration of a cell when the voltage change exceeds a predetermined value.

Abstract: An auto throttle system for FAYDEC equipped aircraft includes a remote friction element which is separated from a pilot's console. The system also includes an auto throttle control and a manual throttle control which are mechanically coupled through the friction element. The friction element provides the "feel" of a cable operated throttle system and allows a pilot to manually override the auto throttle without a significant change in the torque required to advance or retard the throttle. The system also includes a servo motor, gear drive and shaft with the friction element disposed on the shaft. A mechanical coupling connects the shaft and the manual control so that any changes caused by the auto throttle cause a corresponding change in a pilot's manual throttle control.

Abstract: An aircraft control system for computing a yaw compensated angle of attack is disclosed. The system includes an angle of attack sensor for generating a signal which represents an aircraft's angle of attack as determined by an angle of attack vane and a transverse accelerometer for generating a signal in response to the lateral acceleration of the aircraft. A summing device sums the two signals to thereby provide a yaw compensated angle of attack signal. The system may also include a rudder deflection sensor for generating a signal which represents the deflection of an aircraft's rudder. The rudder deflection signal is then subtracted from the yaw compensated angle of attack in the summing device. A stall warning system incorporating the yaw compensation system includes a stall warning computer for comparing the yaw compensated angle of attack signal to a predetermined value.

Abstract: A method for placing a surcharge on telephone solicitations including the steps of providing a local telephone number to a customer for accessing a call from an originating caller and identifying the originating caller's telephone number, as for example, by conventional caller identification systems. The method also includes the steps of advising the caller of the surcharge and providing an opportunity to complete the call by accepting the surcharge or terminating the call without charge. For example, the subscriber's equipment may incorporate an automatic answering system including voice responsive functions and call forwarding. The method also includes the steps of billing the caller for the surcharge and crediting a portion of that charge to the customer's account.

Abstract: A vane-type forward fuselage mounted angle of attack sensor having an internal force relief feature is disclosed. The sensor includes a cam surface having a first portion which defines a segment of a circle, a second portion which defines a curve with a decreasing radius and a shoulder portion between the first and second portions. A cam follower and spring biasing member act as a stop to limit the angular displacement of the vane and as an override to protect the vane against breakage and to automatically return the vane to an operational position after an override.

Abstract: An integral turbo jet/ram jet propulsion system has co-axial forward and rear portions and includes a converging supersonic compression chamber and an inlet in the forward portion for directing air into the supersonic compression chamber. A diverging subsonic compression chamber is disposed rearwardly of the supersonic compression chamber. An inlet sonic throat connects the supersonic compression chamber and the subsonic compression chamber and directs a flow of air from the supersonic compression chamber through the throat and into the subsonic compression chamber. A high by-pass turbo jet engine is disposed adjacent to the subsonic compression chamber for heating and expanding the air which passes into the engine. A subsonic expansion exhaust chamber and supersonic expansion exhaust chamber are disposed rearwardly of the engine with an exhaust sonic throat between the two.

Abstract: A navigational system for determining and displaying the position of a vessel on a navigational chart includes an optical projection system for establishing first and second reference points on the chart. The system also includes a computer and a keyboard or the like for entering the longitudinal and latitudinal coordinates of the first and second reference points in the computer. A GPS or Loran receiver is also tied into the computer so that the present position of the vessel can be projected onto the chart.

Abstract: An aerodynamic vane is mounted on the fuselage of an aircraft for purposes such as sensing the angle of attack of an aircraft. The vane is attached to a fuselage mounting hub by means of a deformable hinge member and a weakened linear portion of the vane which is designed to give way under the force of impact of an object striking the vane. Should an object such as a bird strike the vane, the vane will separate from the hub along the weakened linear portion without the main body of the vane shattering. The hinge member, while it will deform under the impact, retains the vane to the fuselage so that it cannot fly into the engine or otherwise cause damage to the aircraft.

Abstract: A supersonic aircraft includes an internal passageway, an articulated intake structure and an articulated exhaust structure which is connected to the intake structure by the passageway. The articulated intake structure defines an opening having a cross-section which is essentially equal to the cross-section of the aircraft's fuselage when configured for supersonic flight and smaller opening when configured for subsonic flight. Also, for supersonic flight, the cross-sectional area of the air intake structure decreases in the direction of air flow. For subsonic flight, the cross-sectional area of the air intake structure is relatively constant. For supersonic flight, the exhaust structure defines a cross-section which increases in the direction of air flow.