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Test and Analysis of an Advanced Technology Landing Gear

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A retractable, crashworthy main landing gear for a utility helicopter was designed, fabricated and tested to the crashworthiness requirements of a vertical velocity of 42 fps, at ± 10° roll and −5°/+ 15° pitch. The landing gear is very compact and highly maintainable, and automatically extends in less than two seconds in an emergency. Through energy absorbing trade‐off studies and crashworthiness analyses, the gear was optimized to absorb 60 percent of the energy from a level impact at 42 fps; the remaining energy was absorbed by the fuselage and the stroking seat. The landing gear was evaluated through single‐gear platform and iron‐bird drop tests. Analytical models were also used to predict the performance of the landing gear design. The analysis results compared very well with the test results. The test and analysis results identified differences in the behavior of the gear in the two types of tests.

Document Type: Research Article


Affiliations: McDonnell Douglas Helicopter Company, Mesa, Az.

Publication date: July 1, 1992

More about this publication?
  • The Journal of the American Helicopter Society is the world's only scientific journal dedicated to vertical flight technology. It is a peer-reviewed technical journal published quarterly by AHS International and presents innovative papers covering the state-of-the-art in all disciplines of rotorcraft design, research and development. (Please note that AHS members receive significant discounts on articles and subscriptions.)

    Journal subscribers who are AHS members log in here if you are not already logged in.

    Authors can find submission guidelines and related information on the AHS website.

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