Abstract
The integrated design problem posed by the need for oblique wing aircraft aeroelastic roll trim at subsonic airspeeds is examined. It is shown that the need for roll trim is reduced when structural tailoring with advanced composite materials is used, but there is a maximum oblique wing sweep angle above which tailoring is ineffective. A formula for this sweep angle is developed. The need for a combination of asymmetrical aileron input and aeroelastic tailoring of a laminated wing structure is also examined. The design tradeoff between structural tailoring, to reduce the need for ailerons for roll trim, and aileron control surface effectiveness to provide roll trim is illustrated using an example configuration. Tailoring the aileron size so that the aileron reversal dynamic pressure and the static aeroelastic divergence dynamic pressure of the restrained oblique wing are identical is also discussed.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
