Flight-loads effects on horizontal tail free-play-induced limit cycle oscillation

被引：0

作者：

Chen, P.C. ^{[1
,1
]}

Lee, D.H. ^{[1
,1
,2
]}

机构：

[1] ZONA Technology, Inc., Scottsdale, AZ 85258, United States

[2] AIAA

来源：

Journal of Aircraft | 1600年 / 45卷 / 02期

关键词：

The purpose of this paper is to study the impact of the flight-loads effects on the free-play-induced limit cycle oscillation using a direct simulation approach. This is achieved by computing the transient responses of an F-16 aeroelastic model with various free-play angles in its horizontal tails under various trim conditions; while subjected to external excitations due to gust or pilot input command. It is found that for the restrained structures; limit cycle oscillation always occurs; even with a very small free-play limit; as long as the horizontal tail is unloaded. However; once the horizontal tail is loaded at a trim condition; limit cycle oscillation disappears; even with a large free-play limit up to ±0.2 degrees. In contrast; for the unrestrained structures; even with large free-play limits up to ±0.1 degrees; limit cycle oscillation occurs only within a short period of time when the horizontal tail is unloaded. This is because for a free-free aircraft; when the horizontal tail is unloaded; the aircraft is untrimmed and then a transient maneuver will be developed and; consequently; the horizontal tall is rapidly loaded. In addition; it is unlikely that the F-16 can maintain an unloaded horizontal tail for a sufficiently long time until the limit cycle oscillation is fully developed. This suggests that the military specification for control surface free-play limit (±0.017 degrees) is probably too stringent for the F-16 and can be relaxed to reduce the manufacturing and maintenance costs;

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摘要：

Conference article (CA)

引用

页码：478 / 485