Abstract
Design And Aerodynamic Analysis Of Compliant Mechanism Based Morphing Wings
Highlights
Wing warping worked by twisting the wing so that the angle of attack would vary across the span of the wing, with one side experiencing an increase, while the other experienced a decrease
For the 00 tests, the morphing wing had up to almost 29% higher drag at high speeds
At the time of writing, most advanced applications of compliant mechanisms, such as the 2-DOF gas thruster mount designed by Brighman Young University in partnership with NASA is designed to be 3-D printed out of titanium
Summary
As long as man has been able to achieve flight, they have been pushing the boundary of what is possible in both air and space. The method of high lift generation and orientation of the aircraft has become widely accepted to be controlled through discrete elements such as flaps, ailerons, rudders, etc. The Wright brothers, who achieved the first-ever successful powered flight, did not use the aforementioned discrete control surfaces Instead they implemented something that was called wing warping. Wing warping worked by twisting the wing so that the angle of attack would vary across the span of the wing, with one side experiencing an increase, while the other experienced a decrease This change in angle of attack allowed for control over the lift generated on each side and allowed for control over the lateral stability of the airplane [1]
Sign-in/Register to view highlights & summary 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.
