IN2013CH02074A - - Google Patents

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Publication number
IN2013CH02074A
IN2013CH02074A IN2074CH2013A IN2013CH02074A IN 2013CH02074 A IN2013CH02074 A IN 2013CH02074A IN 2074CH2013 A IN2074CH2013 A IN 2074CH2013A IN 2013CH02074 A IN2013CH02074 A IN 2013CH02074A
Authority
IN
India
Prior art keywords
landing
aircraft
hard
identify
subjected
Prior art date
Application number
Inventor
Prabakaran A
Sreenivasa S
Original Assignee
Hindustan Aeronautics Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hindustan Aeronautics Ltd filed Critical Hindustan Aeronautics Ltd
Priority to IN2074CH2013 priority Critical patent/IN2013CH02074A/en
Publication of IN2013CH02074A publication Critical patent/IN2013CH02074A/en

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  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

This invention relates to aircraft landing phenomenon. The devise which is installed on the aircraft shock absorber, helps in detecting "hard Landing". Landing gear shock absorbers are designed to absorb the aircraft vertical kinetic energies with controlled landing reactions at the time of landing. Landing gear & attachment brackets are subjected to this landing reaction which is to be contained within design limits. If however, due to some unforeseen circumstances, if the landing gears are subjected to higher reactions, it is mandatory to ground the aircraft for detailed inspection to identify the extent of damage & repairs required before clearing for flight. Hence detecting the aircraft Hard landing is crucial to decide on the criticality of the aircraft inspection requirements. Presently, the method followed to identify the aircraft hard landing is based on feed back from flight crew & pilot"s feel which is highly subjective. This invention enables clear identification of whether an aircraft did hard landing or not based on the shock absorber oil pressure which is a true representative of the landing reaction.
IN2074CH2013 2013-05-10 2013-05-10 IN2013CH02074A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
IN2074CH2013 IN2013CH02074A (en) 2013-05-10 2013-05-10

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
IN2074CH2013 IN2013CH02074A (en) 2013-05-10 2013-05-10

Publications (1)

Publication Number Publication Date
IN2013CH02074A true IN2013CH02074A (en) 2015-09-18

Family

ID=54396372

Family Applications (1)

Application Number Title Priority Date Filing Date
IN2074CH2013 IN2013CH02074A (en) 2013-05-10 2013-05-10

Country Status (1)

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IN (1) IN2013CH02074A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10112702B2 (en) 2017-02-08 2018-10-30 Goodrich Corporation Hard-landing detection system
FR3147262A1 (en) 2023-03-31 2024-10-04 Airbus Helicopters Method and system for detecting a hard landing

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10112702B2 (en) 2017-02-08 2018-10-30 Goodrich Corporation Hard-landing detection system
FR3147262A1 (en) 2023-03-31 2024-10-04 Airbus Helicopters Method and system for detecting a hard landing

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