Abstract
The paper presents a real-time technique for determining the minimum number of panel-to-panel support brackets in an unpressurised spacecraft body and their installation positions employing topology optimisation in order to satisfy the dynamic compatibility requirements between the spacecraft and its launch vehicle. These support brackets connect honeycomb panels of the spacecraft body, which form the foundation of its structural design. The technique should be used at early design stages (such as pilot project and draft design) to generate structural design options in real time. We provide a general approach to using the technique as well as its detailed description based on a test problem example utilising the MSC. Patran/Nastran software package. We stated the optimisation problem mathematically and described its parameter selection. We list primary advantages and disadvantages of this technique as compared to the classical use of topology optimisation. Results obtained via the technique proposed may be used as guidelines for design engineers developing design documentation. The paper also outlines potential further development of the technique.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
More From: Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering
Disclaimer: 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.