Patents Assigned to Safe Flight Instrument Corporation
  • Patent number: 10336467
    Abstract: A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.
    Type: Grant
    Filed: July 11, 2017
    Date of Patent: July 2, 2019
    Assignee: Safe Flight Instrument Corporation
    Inventors: Randall A. Greene, Shawn P. Beyer, Robert D. Teter
  • Publication number: 20190176997
    Abstract: An electronic aircraft control system and an electronic aircraft control method are provided. In some embodiments, the aircraft control system includes a motor including a rotating shaft, a lever including an axis of rotation, the lever connected to the rotating shaft, wherein the position of the lever is not maintained by a mechanical clutch during normal operations. In some embodiments, the aircraft control system includes a fail-safe system for maintaining mechanical friction of the lever in an event of a failure, a sensor identifying a position of the lever, and a transmitter transmitting the lever position to a controller, the controller adjusting an aircraft performance device based on the received lever position. In some embodiments, the motor provides a torque on the lever. In some embodiments, the fail-safe system includes shear pins configured to break when a sufficient amount of manual torque is applied to the lever.
    Type: Application
    Filed: December 13, 2018
    Publication date: June 13, 2019
    Applicant: Safe Flight Instrument Corporation
    Inventors: Michael J. LAMBTON, Louis C. SIMONS, Randall A. GREENE
  • Patent number: 10269252
    Abstract: A collision warning method includes receiving a collision risk indication from a traffic collision avoidance system of an aircraft, receiving a preset altitude, comparing the preset altitude and an altitude associated with the collision risk indication, and providing a warning in the aircraft when the preset altitude and the altitude associated with the collision risk are within a threshold.
    Type: Grant
    Filed: October 12, 2015
    Date of Patent: April 23, 2019
    Assignee: Safe Flight Instrument Corporation
    Inventor: Randall A. Greene
  • Patent number: 9828113
    Abstract: An aircraft tailstrike warning method includes identifying a first value representing an aircraft angle of attack, identifying a second value representing a maximum aircraft angle of attack, identifying a difference between the first value and the second value, and providing a tailstrike warning when the difference between the first value and the second value is less than a threshold amount.
    Type: Grant
    Filed: November 5, 2013
    Date of Patent: November 28, 2017
    Assignee: SAFE FLIGHT INSTRUMENT CORPORATION
    Inventors: Randall A. Greene, Shawn Beyer
  • Publication number: 20170305573
    Abstract: A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.
    Type: Application
    Filed: July 11, 2017
    Publication date: October 26, 2017
    Applicant: Safe Flight Instrument Corporation
    Inventors: Randall A. GREENE, Shawn P. BEYER, Robert D. TETER
  • Patent number: 9701422
    Abstract: A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.
    Type: Grant
    Filed: April 29, 2016
    Date of Patent: July 11, 2017
    Assignee: Safe Flight Instrument Corporation
    Inventors: Randall A. Greene, Shawn P. Beyer, Robert D. Teter
  • Patent number: 9637243
    Abstract: An aircraft lift transducer may include a vane, actuator, an LC circuit, and a processor. The vane may be positioned on the leading edge of a wing of the aircraft, where the angle defined by the chord of the wing and the vane changes when the aircraft angle of attack changes. The actuator may be associated with the vane and change position when the angle defined by the vane and the chord changes. The LC circuit may include an induction coil spaced from the actuator and an oscillator. The oscillation frequency of the LC circuit may change when the position of the actuator changes. The processor may receive the change in the oscillation frequency and may determine a corresponding change in an available lift of the aircraft.
    Type: Grant
    Filed: December 23, 2013
    Date of Patent: May 2, 2017
    Assignee: Safe Flight Instrument Corporation
    Inventors: Joseph S. Tiseo, Randall A. Greene
  • Patent number: 9580186
    Abstract: A helicopter stall warning method includes receiving an airspeed of the helicopter, determining a stall airspeed based on multiple factors associated with the helicopter, the multiple factors comprising ambient temperature near the helicopter, the helicopter's altitude, and the helicopter's gross weight, determining a stall warning threshold derived from the stall airspeed, and providing a tactile warning through a collective helicopter control when the helicopter's airspeed meets or exceeds the stall warning threshold.
    Type: Grant
    Filed: January 25, 2016
    Date of Patent: February 28, 2017
    Assignee: SAFE FLIGHT INSTRUMENT CORPORATION
    Inventor: Randall A. Greene
  • Patent number: 9546003
    Abstract: A pitch command display method includes identifying touchdown of an aircraft, identifying a first value representing an actual pitch reduction rate of the aircraft, identifying a second value representing a target pitch reduction rate of the aircraft, determining a difference between the first value and the second value, and displaying a pitch command when the difference between the first value and second value is greater than a threshold amount and the aircraft has touched down.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: January 17, 2017
    Assignee: SAFE FLIGHT INSTRUMENT CORPORATION
    Inventors: Randall A. Greene, Shawn P. Beyer
  • Publication number: 20170008639
    Abstract: A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.
    Type: Application
    Filed: February 29, 2016
    Publication date: January 12, 2017
    Applicant: Safe Flight Instrument Corporation
    Inventors: Randall A. GREENE, Shawn P. BEYER, Robert D. TETER
  • Publication number: 20170008642
    Abstract: A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.
    Type: Application
    Filed: April 29, 2016
    Publication date: January 12, 2017
    Applicant: Safe Flight Instrument Corporation
    Inventors: Randall A. GREENE, Shawn P. BEYER, Robert D. TETER
  • Patent number: 9409649
    Abstract: A controller for determining when icing conditions are present on an outside surface of an aircraft may include a first input receiving a moisture condition on a windshield of the aircraft, a second input receiving an outside temperature, and an output that provides an icing condition determined as a function of the first input and the second input. The moisture condition can be provided by a moisture sensor positioned on an interior surface of the windshield and the windshield may include a heating system.
    Type: Grant
    Filed: December 14, 2012
    Date of Patent: August 9, 2016
    Assignee: SAFE FLIGHT INSTRUMENT CORPORATION
    Inventors: Randall A. Greene, Peter R. Cordes, Robert D. Teter
  • Publication number: 20160159494
    Abstract: A pitch command display method includes identifying touchdown of an aircraft, identifying a first value representing an actual pitch reduction rate of the aircraft, identifying a second value representing a target pitch reduction rate of the aircraft, determining a difference between the first value and the second value, and displaying a pitch command when the difference between the first value and second value is greater than a threshold amount and the aircraft has touched down.
    Type: Application
    Filed: March 14, 2014
    Publication date: June 9, 2016
    Applicant: SAFE FLIGHT INSTRUMENT CORPORATION
    Inventors: Randall A. GREENE, Shawn P. BEYER
  • Patent number: 9346552
    Abstract: An autothrottle retard initiation method includes receiving an aircraft's ground speed, receiving the aircraft's vertical speed, determining autothrottle retard initiation height based on the aircraft's ground speed, the aircraft's vertical speed, and an aircraft vertical landing speed factor, receiving the aircraft's height above ground, and initiating autothrottle retard when the aircraft's height above ground and the autothrottle retard initiation height are equal.
    Type: Grant
    Filed: April 11, 2014
    Date of Patent: May 24, 2016
    Assignee: Safe Flight Instrument Corporation
    Inventors: Randall A. Greene, Shawn P. Beyer
  • Patent number: 9193473
    Abstract: An aircraft safety system includes a Stall/Spin Warning & Recovery Computer, an angle of attack sensor, a side slip sensor and an angle of attack display. The Stall/Spin Warning and Recovery Computer detects whether the aircraft is in a safe condition or an unsafe condition. The angle of attack display includes a first configuration that displays information indicative of safe aircraft condition when the orientation detector detects a safe condition and a second configuration that displays information indicative of unsafe aircraft condition when the computer detects an unsafe condition. The display may transition from the first configuration to the second configuration when the orientation detector detects an unsafe condition and then to a third configuration, which may include visual control-input instructions that enable recovery to a safe condition.
    Type: Grant
    Filed: September 20, 2013
    Date of Patent: November 24, 2015
    Assignee: SAFE FLIGHT INSTRUMENT CORPORATION
    Inventors: Arthur C. Barth, Randall A. Greene, Louis Simons, Darren Taillie
  • Publication number: 20150291287
    Abstract: An autothrottle retard initiation method includes receiving an aircraft's ground speed, receiving the aircraft's vertical speed, determining autothrottle retard initiation height based on the aircraft's ground speed, the aircraft's vertical speed, and an aircraft vertical landing speed factor, receiving the aircraft's height above ground, and initiating autothrottle retard when the aircraft's height above ground and the autothrottle retard initiation height are equal.
    Type: Application
    Filed: April 11, 2014
    Publication date: October 15, 2015
    Applicant: SAFE FLIGHT INSTRUMENT CORPORATION
    Inventors: Randall A. GREENE, Shawn P. BEYER
  • Patent number: 9151335
    Abstract: A clutch includes an input, an output, first and second control disks, and a control. The output and the input may be releasably coupled. The first control disk may be positioned between the input and the output. The first control disk and second control disk may be coupled and the output may be moveable between the control disks. The control may apply a torque to the second control disk, establishing a relative rotation between the output and the first control disk and decoupling the output and input.
    Type: Grant
    Filed: February 24, 2014
    Date of Patent: October 6, 2015
    Assignee: SAFE FLIGHT INSTRUMENT CORPORATION
    Inventor: Peter R. Cordes
  • Publication number: 20150240882
    Abstract: A clutch includes an input, an output, first and second control disks, and a control. The output and the input may be releasably coupled. The first control disk may be positioned between the input and the output. The first control disk and second control disk may be coupled and the output may be moveable between the control disks. The control may apply a torque to the second control disk, establishing a relative rotation between the output and the first control disk and decoupling the output and input.
    Type: Application
    Filed: February 24, 2014
    Publication date: August 27, 2015
    Applicant: SAFE FLIGHT INSTRUMENT CORPORATION
    Inventor: Peter R. CORDES
  • Publication number: 20150175270
    Abstract: An aircraft lift transducer may include a vane, actuator, an LC circuit, and a processor. The vane may be positioned on the leading edge of a wing of the aircraft, where the angle defined by the chord of the wing and the vane changes when the aircraft angle of attack changes. The actuator may be associated with the vane and change position when the angle defined by the vane and the chord changes. The LC circuit may include an induction coil spaced from the actuator and an oscillator. The oscillation frequency of the LC circuit may change when the position of the actuator changes. The processor may receive the change in the oscillation frequency and may determine a corresponding change in an available lift of the aircraft.
    Type: Application
    Filed: December 23, 2013
    Publication date: June 25, 2015
    Applicant: Safe Flight Instrument Corporation
    Inventors: Joseph S. TISEO, Randall A. GREENE
  • Patent number: 9051061
    Abstract: A system for safely landing an aircraft including a low range radio altimeter, a barometric altimeter, and an autothrottle control. The low range radio altimeter calculates a first height of the aircraft above ground-level, the barometric altimeter calculates a second height of the aircraft above ground-level, and the autothrottle control determines if the first height and the second height do not correlate. If the first and second heights are determined to lack correlation, then automatic thrust-control of the aircraft is stopped. In some embodiments, the second height is partially calculated by accessing a ground elevation database to obtain an elevation of the ground above sea level and determining a difference between the elevation of the ground above sea level and an elevation of the aircraft above sea level.
    Type: Grant
    Filed: December 14, 2012
    Date of Patent: June 9, 2015
    Assignee: Safe Flight Instrument Corporation
    Inventor: Randall A. Greene