Abstract
Continuing Chapter V, internal stress resultants are established for the open rings in (he fuselage due to the various statically equivalent and self‐equilibrating load systems. The determination of the frame redundancies leads immediately to the corresponding results for the closed rings. The procedure is developed for both single‐ and double‐cell cross‐sections with cither singly‐or doubly‐connected rings. A brief account is also given of the flexibility of a diaphragm or bulkhead, describing how cither the force or displacement method may be used. The analysis of the fuselage basic system concludes with an investigation of thermal stresses in the closed frames.
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.
