Patents by Inventor Jaibir Singh
Jaibir Singh has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11822352Abstract: A system and method onboard an aircraft generates pilot awareness of obstacle clearance during an engine out (EO) go around (GA) situation. The system herein receives inputs from either a pilot selection or aircraft state change indicating a GA below a published missed approach altitude and also receives an input from an engine status monitor indicating an EO situation. As a GA below the published missed approach altitude does not ensure obstacle clearance with an EO, the systems herein generate a pseudo engine out go around procedure (PEOGAP) which calculates a minimum climb gradient maintaining a minimum separation from all obstacles within an area bound by the published missed approach. Once generated, the systems herein display the PEOGAP to the pilot for adequate obstacle separation and pilot awareness.Type: GrantFiled: May 11, 2021Date of Patent: November 21, 2023Assignee: Rockwell Collins, Inc.Inventors: Jaibir Singh, Shankar Ganesh Narayanasamy Sadasivam, Harish H S
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Patent number: 11817000Abstract: A system and method to assist piloting an aircraft in landing phase is disclosed. The system includes a pseudo glide path calculation module that includes a processor and a memory communicatively coupled to the one processor and having instructions stored upon. The instructions, when executed by the processor, cause the one or more processors to receive coordinates for a runway, receive exit path coordinates for a runway, receive aircraft configuration data, receive aircraft status data, receive runway environmental data, calculate a relative position of the aircraft in reference to the exit path coordinates and the runway environmental data, generate a pseudo displaced threshold for the runway, and generate a pseudo approach glide path profile based on the pseudo displaced threshold. The pseudo displaced threshold and the pseudo approach glide path profile may be depicted on a display. A runway occupation time may also be calculated.Type: GrantFiled: March 30, 2021Date of Patent: November 14, 2023Assignee: Rockwell Collins, Inc.Inventor: Jaibir Singh
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Publication number: 20220189324Abstract: A system and method to assist piloting an aircraft in landing phase is disclosed. The system includes a pseudo glide path calculation module that includes a processor and a memory communicatively coupled to the one processor and having instructions stored upon. The instructions, when executed by the processor, cause the one or more processors to receive coordinates for a runway, receive exit path coordinates for a runway, receive aircraft configuration data, receive aircraft status data, receive runway environmental data, calculate a relative position of the aircraft in reference to the exit path coordinates and the runway environmental data, generate a pseudo displaced threshold for the runway, and generate a pseudo approach glide path profile based on the pseudo displaced threshold. The pseudo displaced threshold and the pseudo approach glide path profile may be depicted on a display. A runway occupation time may also be calculated.Type: ApplicationFiled: March 30, 2021Publication date: June 16, 2022Inventor: Jaibir Singh
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Publication number: 20220129016Abstract: A system and method onboard an aircraft generates pilot awareness of obstacle clearance during an engine out (EO) go around (GA) situation. The system herein receives inputs from either a pilot selection or aircraft state change indicating a GA below a published missed approach altitude and also receives an input from an engine status monitor indicating an EO situation. As a GA below the published missed approach altitude does not ensure obstacle clearance with an EO, the systems herein generate a pseudo engine out go around procedure (PEOGAP) which calculates a minimum climb gradient maintaining a minimum separation from all obstacles within an area bound by the published missed approach. Once generated, the systems herein display the PEOGAP to the pilot for adequate obstacle separation and pilot awareness.Type: ApplicationFiled: May 11, 2021Publication date: April 28, 2022Inventors: Jaibir Singh, Shankar Ganesh Narayanasamy Sadasivam, Harish HS
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Patent number: 10755583Abstract: A method is provided for monitoring compliance with air traffic control (ATC) instructions by an air crew of an aircraft. First, voice and text ATC commands are received by an ATC instruction moderator support system (AIMSS) located on board the aircraft. The voice and text ATC commands are converted into a data format by the AIMSS. The ATC commands are used to determine an expected aircraft state while a current aircraft state is determined by the aircraft sensors. The current aircraft state is compared with the expected state and determined if it is in compliance. If the current state is in non-compliance, it is determined if the non-compliance is allowable and it is then classified as either no action or incorrect action by the aircrew. Finally, an alert of the noncompliance is generated with the AIMSS.Type: GrantFiled: October 23, 2017Date of Patent: August 25, 2020Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Abneesh Singla, Sreenivasan Govindillam K, Srinivas D. Gonabal, Pradeep Huncha, Vedavyas Rallabandi, Jaibir Singh, Sunil Kumar KS
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Publication number: 20190122564Abstract: A method is provided for monitoring compliance with air traffic control (ATC) instructions by an air crew of an aircraft. First, voice and text ATC commands are received by an ATC instruction moderator support system (AIMSS) located on board the aircraft. The voice and text ATC commands are converted into a data format by the AIMSS. The ATC commands are used to determine an expected aircraft state while a current aircraft state is determined by the aircraft sensors. The current aircraft state is compared with the expected state and determined if it is in compliance. If the current state is in non-compliance, it is determined if the non-compliance is allowable and it is then classified as either no action or incorrect action by the aircrew. Finally, an alert of the noncompliance is generated with the AIMSS.Type: ApplicationFiled: October 23, 2017Publication date: April 25, 2019Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Abneesh Singla, Sreenivasan Govindillam K, Srinivas D. Gonabal, Pradeep Huncha, Vedavyas Rallabandi, Jaibir Singh, Sunil Kumar KS
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Patent number: 10247574Abstract: A system and method for determining and displaying a minimum maneuverable altitude for an aircraft to turn back includes automatically processing aircraft characteristic data, aircraft flight trajectory data, and environmental/airport services data, in a processing system, to determine a rate of change of aircraft maneuverable altitude with respect to change in aircraft heading. At least the determined rate of change of aircraft altitude with respect to change in aircraft heading is processed, in the processing system, to determine the minimum maneuverable altitude at least engine out conditions. Terrain data is processed, in the processing system, to determine a terrain clearance height above which the minimum maneuverable altitude may be implemented. The minimum maneuverable altitude is rendered, on a display device, on the altitude tape, and a pseudo gate is rendered on the display device that represents a height above the terrain that corresponds to the minimum maneuverable altitude.Type: GrantFiled: May 18, 2017Date of Patent: April 2, 2019Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Jaibir Singh, Sreenivasan Govindillam K., Raghu Shamasundar, Abneesh Singla
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Publication number: 20180335315Abstract: A system and method for determining and displaying a minimum maneuverable altitude for an aircraft to turn back includes automatically processing aircraft characteristic data, aircraft flight trajectory data, and environmental/airport services data, in a processing system, to determine a rate of change of aircraft maneuverable altitude with respect to change in aircraft heading. At least the determined rate of change of aircraft altitude with respect to change in aircraft heading is processed, in the processing system, to determine the minimum maneuverable altitude at least engine out conditions. Terrain data is processed, in the processing system, to determine a terrain clearance height above which the minimum maneuverable altitude may be implemented. The minimum maneuverable altitude is rendered, on a display device, on the altitude tape, and a pseudo gate is rendered on the display device that represents a height above the terrain that corresponds to the minimum maneuverable altitude.Type: ApplicationFiled: May 18, 2017Publication date: November 22, 2018Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jaibir Singh, Sreenivasan Govindillam K., Raghu Shamasundar, Abneesh Singla