# US 10,766,634 B1 · Ground proximity warning system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,766,634 B1 - Document ID: US10766634B1 - Status: Granted - Kind: B1 - Application number: 15/871,222 - Filed: 2018-01-15 - Granted: 2020-09-08 - Earliest claimed: 2018-01-15 - Applicants: Luther Lonidier - Inventors: Luther Lonidier - Web page: https://patentgrep.com/patent/US10766634B1 ## CPC - B64D 47/02: Arrangements or adaptations of signal or lighting devices - G08G 5/21: located onboard the aircraft - B64D 45/04: Landing aids; Safety measures to prevent collision with earth's surface - G05D 1/0676: {specially adapted for landing} - G08G 5/54: for approach or landing - G01C 5/005: {altimeters for aircraft (G01C5/02, G01C5/06 take precedence)} - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - G08G: TRAFFIC CONTROL SYSTEMS (guiding railway traffic, ensuring the safety of railway traffic B61L; arrangement of road signs or traffic signals E01F9/00; radar or analogous systems, sonar systems, lidar systems specially adapted for traffic control G01S13/91, G01S15/88, G01S17/88; {radar or analogous systems, sonar systems, lidar systems specially adapted for anti-collision purposes G01S13/93, G01S15/93, G01S17/93}) - G05D: SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES - G01C: MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY (measuring liquid level G01F; radio navigation, determining distance or velocity by use of propagation effects, e.g. Doppler effects, propagation time, of radio waves, analogous arrangements using other waves G01S) ## Abstract The ground proximity warning system is an instrument. The ground proximity warning system is configured for use with a private aviation aircraft. The private aviation aircraft further comprises landing gear and a cockpit. The ground proximity warning system measures the altitude of the private aviation aircraft from a landing strip when the private aviation aircraft is within 3 meters of the landing strip. The ground proximity warning system generates an audible series of clicks within the cockpit to indicate the altitude to a pilot. A higher click frequency indicates a lower altitude. The ground proximity warning system comprises a trigger circuit, a selection circuit, a pulse generator, a detector circuit, a dividing circuit, a buffer, and a cockpit speaker. The trigger circuit, the selection circuit, the pulse generator, the detector circuit, the dividing circuit, the buffer, and the cockpit speaker are electrically interconnected. ## Claims ### Claim 1 An instrument for measuring altitude comprising: a trigger circuit, a selection circuit, a pulse generator, a detector circuit, a dividing circuit, a buffer, and a cockpit speaker; wherein the trigger circuit, the selection circuit, the pulse generator, the detector circuit, the dividing circuit, the buffer, and the cockpit speaker are electrically interconnected; wherein the instrument for measuring altitude is configured for use with a private aviation aircraft; wherein the private aviation aircraft further comprises landing gear and a cockpit; wherein the instrument for measuring altitude measures the altitude of the private aviation aircraft from a landing strip; wherein the instrument for measuring altitude measures the altitude of the private aviation aircraft within three meters of the landing strip; wherein the instrument for measuring altitude generates an audible series of clicks within the cockpit to indicate the altitude to a pilot; wherein a higher click frequency indicates a lower altitude; wherein the instrument for measuring altitude measures the altitude of the private aviation aircraft by measuring a reflected pulse from an ultrasonic pulse directed towards the landing strip; wherein the trigger circuit is a timing circuit; wherein the trigger circuit initiates an operation of the instrument for measuring altitude after deployment. ### Claim 2 (depends on 1) The instrument for measuring altitude according to claim 1 wherein the trigger circuit further comprises an initiation signal and a trigger reset; wherein the initiation signal is an electrical signal; wherein the initiation signal is electrically connected to the selection circuit; wherein the trigger reset is an input into the trigger circuit. ### Claim 3 (depends on 2) The instrument for measuring altitude according to claim 2 wherein the initiation signal is generated at regular intervals by the trigger circuit unless the trigger reset is activated. ### Claim 4 (depends on 3) The instrument for measuring altitude according to claim 3 wherein the selection circuit is an ‘or’ gate; wherein the selection circuit further comprises a first input, a second input, and a first output; wherein the first input is electrically connected to the initiation signal of the trigger circuit; wherein the second input is electrically connected to the detector circuit; wherein the first output is electrically connected to the pulse generator. ### Claim 5 (depends on 4) The instrument for measuring altitude according to claim 4 wherein when the selection circuit detects a signal selected from the group consisting of the initiation signal and the detector circuit, the selection circuit activates the first output of the selection circuit. ### Claim 6 (depends on 5) The instrument for measuring altitude according to claim 5 wherein the pulse generator is an electric circuit; wherein the pulse generator is attached to the landing gear. ### Claim 7 (depends on 6) The instrument for measuring altitude according to claim 6 wherein the pulse generator further comprises a trigger input, a pulse generating transducer, and the ultrasonic pulse; wherein the first output is electrically connected to the trigger input of the pulse generator; wherein the first output activates the trigger input such that the pulse generator generates and transmits the ultrasonic pulse in the direction of the landing strip; wherein the pulse generating transducer creates the ultrasonic pulse; wherein the ultrasonic pulse generated by the pulse generator is directed towards the landing strip; wherein the ultrasonic pulse is transmitted as a wave through the atmosphere; wherein the pulse generating transducer generates the ultrasonic pulse at ultrasonic frequencies. ### Claim 8 (depends on 7) The instrument for measuring altitude according to claim 7 wherein the pulse generating transducer generates each ultrasonic pulse over a previously specified duration. ### Claim 9 (depends on 8) The instrument for measuring altitude according to claim 8 wherein the detector circuit is an electric circuit; wherein the detector circuit is attached to the landing gear; wherein the detector circuit is a device that detects the reflected pulse from the ultrasonic pulse off the landing strip; wherein the detector circuit generates a detection signal indicating that the reflected pulse has been received. ### Claim 10 (depends on 9) The instrument for measuring altitude according to claim 9 wherein the field of view of the detector circuit is selected such that the private aviation aircraft can move up to five feet during the pulse and detection process. ### Claim 11 (depends on 10) The instrument for measuring altitude according to claim 10 wherein the detector circuit further comprises the detection signal, a pulse detection transducer, and the reflected pulse; wherein the detection signal is an electrical voltage that is generated by the detector circuit; wherein the pulse detection transducer is an electrical circuit; wherein the pulse detection transducer detects the energy generated by the reflected pulse; wherein the reflected pulse refers to a portion of the energy contained in the ultrasonic pulse that is reflected from the landing strip back to the pulse detection transducer; wherein the detection of the reflected pulse causes the pulse detection transducer to generate the detection signal. ### Claim 12 (depends on 11) The instrument for measuring altitude according to claim 11 wherein the detection signal electrically connects to the second input of the pulse generator, the trigger reset of the trigger circuit, and the dividing circuit. ### Claim 13 (depends on 12) The instrument for measuring altitude according to claim 12 wherein the dividing circuit is an electric circuit; wherein the dividing circuit is a counting circuit that generates a cockpit indication signal; wherein the dividing circuit generates the cockpit indication signal after a previously determined number of detection signals have been received. ### Claim 14 (depends on 13) The instrument for measuring altitude according to claim 13 wherein the buffer is an amplifier; wherein the cockpit indication signal is amplified by the buffer. ### Claim 15 (depends on 14) The instrument for measuring altitude according to claim 14 wherein the cockpit speaker is a transducer that is mounted in the cockpit; wherein the cockpit speaker generates an audible sound that is heard in the cockpit; wherein the amplified cockpit indication signal from the buffer produces a clicking sound through the cockpit speaker. ### Claim 16 (depends on 15) The instrument for measuring altitude according to claim 15 wherein as the private aviation aircraft moves closer to the landing strip, the frequency of the generation of the detection signal increases; wherein as the private aviation aircraft moves closer to the landing strip, the frequency of the clicks generated by the cockpit speaker increases. ### Claim 17 (depends on 16) The instrument for measuring altitude according to claim 16 wherein the pulse generator generates ultrasonic pulses within a frequency range of 40 khz to 60 khz.