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Dynamic Stability Analysis of a Hovering Helicopter with a Sling Load

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Equations of motion are derived for a hovering single‐rotor helicopter with zero‐offset flapping hinges, attitude stabilization and a sling load, being an aerodynamically unloaded compound pendulum, suspended from a fixed hook. The motion is restricted to a vertical plane and has in total 3 degrees of freedom. The stability is discussed in general terms. A numerical example for the lateral stability of a large helicopter with a sling load is included. The agreement with experimental results is good.
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Document Type: Research Article

Affiliations: Nationaal Lucht- en Ruimtevaartlaboratorium, Sloterweg 145 Amsterdam-W, The Netherlands

Publication date: 1965-04-01

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  • 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.)

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