Structural Studies of Oblique Folding Wings.
JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB
Pagination or Media Count:
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
- Guided Missiles