Accession Number:

ADA025712

Title:

Structural Studies of Oblique Folding Wings.

Descriptive Note:

Technical memo.,

Corporate Author:

JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB

Personal Author(s):

Report Date:

1976-04-01

Pagination or Media Count:

65.0

Abstract:

Design studies on an oblique folding wing for a 34-in.-diameter, subsonic, cruise-type missile are described. Aeroelastic divergence and load amplification are investigated. It is found that divergence is not a problem, but load buildup on the forward-swept wing and load reduction on the aft-swept wing result in large rolling moments. Design studies of the wing pivot indicate that a Conrad four-point bearing and a torsion-spring actuator should result in a lightweight, reliable, and inexpensive fold mechanism. Weights and volumes of the oblique wing design are computed and compared with results of previous studies of swing-wing and wraparound-wing configurations. The wraparound wing is found to be the lightest and provides the greatest fuel volume. Author

Subject Categories:

  • Aircraft
  • Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE