Leonard S Greene Deceased347 Varick St, Jersey City, NJ 07302

6454724, Sep 24, 2002

Oct 25, 2000

09/695313

Leonard M. Greene - White Plains NY

Safe Flight Instrument Corporation - White Plains NY

A61B 500

600534

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.

6575410, Jun 10, 2003

Apr 25, 2001

09/841062

Leonard M. Greene - White Plains NY

Safe Flight Instrument Corporation - White Plains NY

G05D 112

244186, 244180, 244184, 244187

An airborne glide slope tracking system includes a radio altimeter for producing a signal indicative of the instantaneous altitude of the aircraft and a glide slope error indicator for producing a signal indicative of the angular deviation from glide slope. The two signals are multiplied to produce a glide slope error signal in feet and fed to a summing device directly and through a lead filter to generate a signal for a throttle servo to increase or decrease the thrust of the aircraft. A longitudinal accelerometer signal is then added to a signal indicative of a difference between an aircrafts reference angle of attack and actual angle of attack to produce a signal to a pitch command to provide an angle which will be sustained by the power of the aircraft.

6611748, Aug 26, 2003

Jan 8, 2001

09/755044

Leonard M. Greene - White Plains NY

Safe Flight Instrument Corporation - White Plains NY

G06F 1548

701100, 701 99, 416 35, 700304

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. The servo driven throttle control also includes a pair of sprag clutches with one of the clutches disposed between each of the shafts and a manual throttle control.

6666623, Dec 23, 2003

Jun 13, 2002

10/167585

Leonard M. Greene - White Plains NY

Safe Flight Instrument Corporation - White Plains NY

B63C 1102

405186, 405185, 441 88, 441 96

A buoyancy control device includes a buoyancy compensator to be worn by a scuba diver, a compressed air tank, a depth or pressure gauge and a valve connecting the buoyancy compensator and compressed air tank for releasing air into and out of the buoyancy compensator. A microprocessor is connected to the depth gauge and the valve for controlling the amount of air in the buoyancy compensator in response to the depth of the diver. In addition, the microprocessor is programed for automatically controlling the rate of ascent of a diver under normal conditions and for a faster rate of ascent under emergency conditions. The device also includes an override function which allows a second diver to override the normal rate of ascent and to initiate the faster rate of ascent in an emergency.

6676088, Jan 13, 2004

Oct 7, 2002

10/265366

Leonard M. Greene - White Plains NY

Safe Flight Instrument Corporation - White Plains NY

G05D 112

244187

An aircraft flare control system for semi-automatically controlling the pitch and thrust of an aircraft during landing is disclosed. The system includes a flight director and indication of the pitch angle of an aircraft during a landing maneuver and a flare computer. The flare computer includes a control law defining a predetermined pitch angle of the aircraft as a function of height above ground level. The system also includes a radio altimeter connected to the flare computer for producing a signal indicative of the height of the aircraft, a signal of pitch deviation from the control law is generated to allow a pilot or auto-control to adjust the pitch to comply with the control law. A thrust control for retarding the throttle as a function of altitude above ground level is also provided.

7082769, Aug 1, 2006

Feb 7, 2005

11/050668

Leonard M. Greene - White Plains NY, US

Safe Flight Instrument Corporation - White Plains NY

F02C 7/26

60778

A helicopter having a helicopter turbine engine disposed therein includes an over-stress protection system. The over-stress protection system includes a computer for storing data and an input such as a keyboard for inputting a safe temperature profile for starting the turbine engine. A temperature sensor is provided for measuring the actual turbine outlet temperature during the start up of the helicopter turbine engine. The actual engine temperature is then compared with the safe engine temperature profile and water and/or alcohol is injected into the engine when an actual temperature exceeds the safe temperature. The use of a ground based tank for use during start up and an airborne tank for in flight use are also disclosed.

7337045, Feb 26, 2008

Apr 22, 2005

11/111919

Leonard M. Greene - Mamaroneck NY, US

G05D 1/00

701 9, 701 6, 701 7, 701 14

An airborne windshear detection and warning system includes a pitot tube for detecting the airspeed of an aircraft and an angle of attack vane for detecting an aircraft's angle of attack. Signals are generated and fed to a signal processor for determining a relationship between the airspeed and the aircraft's angle of attack. A signal indicative of the aircraft's normal relationship plus or minus a preselected value is also input into the signal processor. Then when the actual relationship exceeds the normal value plus or minus the preselected value for a preselected period of time, a signal is generated by the signal processor and is an indication of a hazardous windshear. A warning is then given to the pilot to take immediate corrective action.

7367531, May 6, 2008

Aug 9, 2005

11/199266

Leonard M. Greene - Mamaroneck NY, US

G05D 1/00

244195, 244 1713, 89 111

A method and system in an airborne aircraft to evade a heat seeking missile includes the steps of detecting the launch or “lock on” of a heat seeking missile and reducing the radiation from the aircraft's engine by reducing the engine speed to idle. The method may also include the steps of shutting down and restarting an engine and taking countermeasures to distract the missile or distorting its tracking system. In addition, a method and system for automatically shutting down an engine and/or injecting cooling water into the engine's exhaust port are disclosed.